Center for Energetic Concepts Development, Department of Mechanical Engineering, University of Maryland

References for Chapter 5 "Combustion"

1. Relation between Plasma Ignition Energy and Some Chemical Characteristics of Primary Explosives, Ding Wei-xing, [Engineering Institute of Engineer Corps, PL University of Science and Technology, Nanjing 210007, China], Zhang Ning, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2010, 33 (1):87-90, 1, 189

Abstract: The relation between semiconductor bridge (SCB) plasma ignition energy and some chemical characteristics of primary explosives including lead azide (LA), lead styphnate (LTNR), nickel hydrazine azide (NHA), nickel hydrazine nitrate (NHN), tetrazene (Tz) and lead picrate (LP) are investigated. The result indicates that there is no direct relation between plasma ignition energy and activation energy of explosives. It shows that correlation coefficient is 81% between plasma energy and the temperature of LTNR, NHA, Tz and LP when the reaction conversion degree is 5%. However, the correlation is deteriorated as all the six explosives are considered. As for the relation between plasma energy and critical temperature of those six compounds, the correlation is better when the heat reaction is modified and the coefficient is 0.82, illuminating that there exist connection among plasma ignition energy and explosive characteristics, especial critical temperature.

2. Combustion Characteristics of Multilayer Gun Propellant, Wei Lun, Wang Qiong-lin, Liu Shao-wu, Zhu Yang-chun, Guo Feng, Zheng Shuang, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants. 2010, 33 (1):75-78.

Abstract: The influence of the structures on the progressive burning of multilayer gun propellant disk was discussed and the theoretical Γ-Ψ curves were obtained by an established combustion model of the multilayer gun propellant disk, and the static burning behaviors of the multilayer propellant with different structures were studied by the closed bomb test. The results show that the trends of multilayer gun propellant experimental curves are similar to the trends of multilayer gun propellant theoretical curves while propellant burned mass was in 0.2 – 0.8; too large (or too small) K and X has a negative impact on progressive burning of the multilayer propellant, and only within reasonable choice, will the progressive burning of the multilayer propellant get better; The characteristic of constant surface burning is present and progressive burning of the multilayer propellant becomes better with the width to its initial thickness W rising

3. Experimental Study on the Dynamic Response of Booster Explosive JH-14C under Impact Load, Zhang Zi-min, Xu Bi-ying, Zhong Kai, Yuan Baohui, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants. 2010. 33 (1):57-59, 63.

Abstract: The dynamic response performance of booster explosive JH-14C under different strain-rate (from 1400s-1 to 4000s-1) impact over-loading is studied by using the split Hopkinson pressure bar technique. The macro failure-forms of booster explosive JH-14C and failure-modes of the recovery specimen are observed and analyzed by SEM and corresponding stress-strain curves are obtained. Results indicate that the stress-strain curves of booster explosive JH-14C exhibit distinct strain-rate effect and failure-stress increase as the increase of strain-rate, but failure-strain keep invariant

4. Effect of Sealing Conditions on Fast Cook-off Response Properties of Passive RDX, Zhi Xiao-qi, Hu Shuang-qi, Xu Shuang-pei, Li Juan-juan; [School of Mechanical Engineering, North University of China, Taiyuan 030051, China], Xiao Zhi-hua; [Shanxi Jiangyang Chemical Co., Ltd, Taiyuan 030041, China], Chinese Journal of Explosives & Propellants, 2010, 33 (1): 31-33, 37

Abstract: In order to assess vulnerability of booster explosive.Seven sealing types of cook-off bomb are designed.The cook-off tests of passive RDX cylinder with shells are used to study the response characters of passive RDX in different sealing conditions and to analyze principal factors affecting the characters.The result indicated that seal structure of shell is a vital effect factor to the cook-off response of passive RDX.In same conditions,along with sealing degree getting from strong to weak,the response of passive RDX increases,considering that the sealing condition affects vulnerability of booster explosive and reducing vulnerability of booster explosive to made a leak for the shells is an important method

5. Study on Preparation Process of ε-HNIW Booster Explosive by Water Slurry Method, Chen Jian, Wang Jing-yu, Wang Bao-guo, Huang Hao; [School of Chemical Engineering and Environment, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2009 32 (2): 28-31

Abstract: In order to obtain high-performance,low-sensitivity booster explosive,HNIW was used as the base explosive to make ε-HNIW booster explosive by water slurry method.The orthogonal experiment for optimizing process was designed,and main factors affecting the coating effect were investigated through single factor tests.FT-IR,SEM and impact sensitivity testing methods were used to characterize the coated samples.The result indicated that the order of influencing factors for coating effect was as follows: temperature,agitating rate,the adding rate,the degree of vacuum.The optimized technical condition was experiment temperature 70℃,the degree of vacuum 0.05 MPa,agitating rate 700 r • min-1,the adding rate 0.725 ml • s-1.The structure of crystal didn′t change in the coating process and the value of characteristic height H50 of coated samples was higher than that of ε-CL-20 by 27 cm

6. Detonation Wave Characteristics of Dual Explosive under Asymmetrical Initiation, Ding Gang, Yuan Bao-hui; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (1): 79-82

Abstract: The characteristics of detonation wave in dual explosive under asymmetrical initiation was studied.The shape of the detonation front,the t vs.d coordinate and the shape distribution of the detonation wave was gained by the slit scan technique of rotating mirror camera. The velocity distribution,the formed reason of the concave detonation front and the spread rule of the detonation convergence wave were analyzed.The detonation front is convergent shape of bow wave and it can accelerate the detonation velocity of the inner explosive

7. Preparation and Properties of LLM-105/EPDM Molding Powders, Dong Jun, Wang Jing-yu, Liang Lei, Li Dan, An Chong-wei; [Chemical and Environment Institute of North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2009, 32 (5):14-17.

Abstract: Selecting EPDM(ethylene propylene diene monomer)as binder and 2,6-diamino-3,5-dinitropyrazine(LLM-105)as main explosive,the molding powders composed of EPDM and LLM-105 were prepared by solution-water suspension method and pressed into booster charges.SEM was employed to characterize the raw and coated sample,and the mechanical sensitivities,thermal decomposition characteristics,thermal stability and detonation velocity were measured and analyzed.The results show that compared with that of raw LLM-105 and traditional booster explosive,the mechanical sensitivities of molding powders are decreased to certain extent,and their thermal stability is improved significantly.The detonation velocity of booster charge with density of 1.518g•cm-3 reach 7915m/s

8. Deflagration to Detonation Transition Process in Aluminum Dust-Air Mixture, Li Xiao-dong, Wang Jing-yu, [College of Chemical Engineering and Environment, North University of China, Taiyuan 030051, China], Liu Qing-ming, Bai Chun-hua; (State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants. 2009, 32 (6):58-61

Abstract: Ignition,flame acceleration and deflagration to detonation transition in fine flake aluminum dust-air mixture under weak ignition of 40J was studied in a horizontal tube with an inner diameter of 199mm and length of 29.6m and equiped with 40 sets of special dust dispersion system.The influences of aluminum dust concentration and ignition delay time on the deflagration to detonation transition(DDT) process of aluminum dust-air mixture were discussed.The experimental results show that the whole DDT process of aluminum dust-air mixture can be divided into slow reaction compression stage and fast reaction shock stage.With the ignition delay time of 370ms and aluminum dust concentration of 300g•m3,the dimensionless transition distance from ignition point to the detonation wave formed in aluminum dust-air mixture is 83 times L/D ratio,and detonation occurs with a peak overpressure of 9.8MPa and velocity of 1670m•s-1.Self-sustained detonation wave of aluminum dust-air mixture is characterized by the existence of spin detonation structure.The front wave velocity and overpressure of self-sustained aluminum dust-air mixture oscillate with the propagation distance

9. Constant Volume Combustion Properties of Combustible Cartridge Case, Li Yu, Zhao Cheng-wen, Guo De-hui, Zhou Wei-liang; [School of Chemistry and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Xu Fu-ming; [Xi'an North Huian Chemical Co., Ltd, Xi'an 710302, China], Chinese Journal of Explosives & Propellants, 2009, 32 (4):75-79

Abstract: The effect of different charge density, different ignition pressure and different moisture on the combustion properties and energy release properties of combustible cartridge case was studied through closed-bomb test.The results show that as the charge density and the ignition pressure increase,the cartridges burning rate and the maximum pressure increase,the combustion stability is improved and energy of cartridges releases more sufficient.The effect of charge density on energy release decreases with increasing the ignition pressure.Strong hygroscopicity of combustible cartridges is verified through absorption experiment of moisture. When samples contain moisture,the burning rate and the combustion stability of low charge density decrease significantly,and the combustion duration extends, however,the influence on impetus is weak

10. Uniformity and Stability of Combustion Heat and Its Uncertainty Analyses for Mg/Al Fuel-rich Propellant, Pang Wei-qiang, Fan Xue-zhong, Sun Zhi-hua, Xu Hui-xiang, Zhang Xiao-hong; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (4):64-67

Abstract: Mg/Al fuel-rich propellants were prepared by means of improving the craftwork based on the experimental formulation of Mg/Al fuel-rich solid propellants.The combustion heat of Mg/Al fuel-rich propellant,which was in system sampling,was determined by means of constant temperature oxygenic bomb calorimeter.The uniformity and stability of the results were studied by variance and student′s T-test method,and the uncertainties of the test were analyzed.The results show that the combustion heat of this sort of Mg/Al fuel-rich propellants prepared had better uniformity and stability.Its extended uncertainty is less than 3.0 in case of k=2

11. Experimental Study on Deflagration-to-Detonation Transition in Pressed High-Density Explosives, Wang Jian, Wen Shang-gang, He Zhi, Wang Jun; [Laboratory for Shock Wave and Detonation Physics Research Institute of Fluid Physics, CAEP, Mianyang, Sichuan 621900, China], Chinese Journal of Explosives & Propellants, 2009, 23 (6):27-30

Abstract: To study the effect of ACP,a fast burning energy material,on the deflagration-to-detonation transition(DDT) in the modified double-base propellant,the experimental study of DDT process of propellant under the condition of porous charge is carried out with the testing system established by the DDT tube.The positon-time relationship and the stress wave shape for the front of deflagration and detonation are recorded using the ionization probes and piezoelectric stress sensors.The experimental results of the propagation velocity of wave front,the location of the detonation transition point and the pressure in different positions of the charge bed are calculated and compared.The results show that the fast burning material ACP can increase the transition tendency of the modified double base propellant to DDT.When the percentage of ACP variates from 5% to 7%,the tendency of the transition from deflagration to detonation in charges increases obviously

12. Determination of the HMX Content in Booster JO-9CI, Wang Jin-ying, Jiang Xia-bing, Zhang Jing-lin; [School of Chemical Engineering and Environment, North University of China, Taiyuan, 030051, China], Chinese Journal of Explosives & Propellants, 2009, 32 (4):88-90.

Abstract: An optimizing chemical analysis method was used to analyze the component of a certain batch of booster JO-9Cl. The experiment results indicate that: the consumption of acetic ester, the mass fraction of sodium hydroxide (NaOH) solution and alkali hydrolyses time have some effect on analytical results. When the mass ratio of acetic ester/booster JO-9Cl is 5 – 5.5, the mass ratio of alkali solution (definite concentration) /booster JO0Cl keep at 90 – 100, and hydrolyses time is shortened to 4h, the parallel misalignment of the results is smaller, and the continuous stability of experiment data are better than that of ultraviolet/visible spectrophotometry. The content of HMX in booster JO-9Cl is determined more accurately by optimizing analytical method

13. Preparation and Characterization of Membranous RDX/SiO2 Booster, Wang Jin-ying, Jiang Xia-bing, Zhang Jing-lin; [Institute of Chemical Engineering and Environment, North University of China, Taiyuan 030051, China], Chen Jian-shen; [Jiang-yang Chemical Industry Limited Company of Shanxi Province, Taiyuan 030041, China], Chinese Journal of Explosives & Propellants, 2009, 32 (5): 29-32

Abstract: The white sub-transparent membranous RDX/SiO2 booster was prepared with pulley and manual spin coating methods by adding sequentially the definite solution of N, N-dimethylformamide (DMF) dissolving RDX and that of water dissolving polyvinyl alcohol (PVA) in the process of the silica SiO2) sol transformation into the gel. The SEM results indicate that the spherical, block like and strip RDX crystals with three-dimensional sizes in the range of 0.3-1.0μm are dispersed within the frames of nano-silica. Compared with the mixture of RDX doped SiO2 (RDX-SiO2) at same conditions, the impact and friction sensitivities of the membranous RDX/SiO2 composite both decrease obviously. The detonation velocity of the membranous composite shows that the performance of booster mainly affected by the thickness and particle size of the composite; especially at low charge density

14. Conception and Principle of Controlled Burning Gun Propellant, Wang Qiong-lin, Liu Shao-wu, Zhang Yuan-bo, Yu Hui-fang, YaoYue-juan, Wang Feng, Zhu Yang-chun, GUO Feng, Wei Lun; [Xi’an Modern Chemistry Research Institute, Xi’an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (5):71-74

Abstract: From the point of view of enhancing the burning progressivity and total energy of gun propellant, a new conception gun propellant and charge i.e. controlled burning gun propellant (CBGP) and charge have been put forward. With the help of the data obtained by closed bomb test and interior ballistic test, three important formulae are obtained. The formulae show that the gun propellant with high muzzle velocity should satisfy the requirement of high energy and high burning progressivity at the same time and the correctness of CBGP conception was verified

15. A Quantitative Assessment Method of Gun Propellant Combustion Progressivity Based on Closed Bomb Test, Wang Qiong-lin, Liu Shao-wu, Zhang Yuan-bo, Yu Hui-fang, Yao Yue-juan, Zhu Yang-chun, Wei Lun; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Zhao Xiao-feng; [Military Representative Office of Missile Device, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (3): 71-74

Abstract: Through comparing the combustion process of gun propellant by dynamic interior ballistic cycle with static closed-bomb test,an ideal gun propellant with special progressivity distribution is found.Based on the difference of progressivity distribution between an ideal and a real gun propellant,a quantitative assessment method of gun propellant progressivity based on closed-bomb test has been proposed.The testing results show that the assessment results well accord with the data of interior ballistic cycle

16. A Quantitative Assessment Method of Gun Propellant Combustion Progressivity Based on Closed Bomb Test, Wang Qiong-lin, Liu Shao-wu, Zhang Yuan-bo, Yu Hui-fang, Yao Yue-juan, Zhu Yang-chun, Wei Lun; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Zhao Xiao-feng; [Military Representative Office of Missile Device, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (3): 71-74

17. Application of High Energy Density Compounds CL-20,DNTF and ADN in High Energy Propellant, Wei Lun, Wang Qiong-lin, Liu Shao-wu, Zhu Yang-chun, Guo Feng, Zhang Yuan-bo; [Xi'an Modern Chemistry Research Institute, Xi'an 710065,China], Chinese Journal of Explosives & Propellants, 2009, 32( 1): 17-20

Abstract: To apply the high energy density compounds(HEDCs) in high energy and high burning rate propellant widely,the influence of CL-20,DNTF and ADN on the compatibility,energy and burning behavior of nitramine propellant RGD7A was studied by closed bomb test and VST.The results show thatthe compatibility of CL-20 and DNTF with RGD7A is excellent.CL-20 and DNTF make the energy and density of nitramine propellant increase.In comparison with RGD7A propellant,the burning rate and pressure exponent of nitramine propellant containing CL-20 DNTF increased under the champer pressure 40-240MPa

18. Experimental Study on Continuous Detonation Velocity of Modified ANFO, Xu Sen, Tang Shuang-ling, Liu Da-bin; [Chemical School of Nanjing University of Science and Technology, Nanjing 210094,China/ National Quality Supervision Testing Center for Industrial Explosive Materials, Nanjing 210094, China], Wang Jian-ling; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (3): 25-28

Abstract: The continuous velocity probe was chosen to study the continuous detonation velocity and detonation development of modified ANFO under different ignition conditions.The experimental results show that, for modified ANFO with the different conditions of priming,which were: detonator/160g booster charge,detonator/160 g booster charge/PMMA spacer and only detonator itself,the stationary detonation velocities are 4569,4496,4559 m/s,respectively,and the run distance to detonation under such ignition conditions are 3.5,7.3 and 20 cm,respectively,the corresponding time of detonation development are 0.01,0.025 and 0.06 ms.The energy of priming explosive is larger,the time of detonation development and run distance to detonation of modified ANFO are shortened,namely,the modified ANFO is easier to become steady detonation

19. Analysis of Abnormal Interior Ballistic Performance of an Equilibrium Launcher at High and Low Temperature, Yun Lai-feng; [Military Representative Bureau in Nanjing of General Armament Department of PLA, Nanjing 210024, China], Rui Xiao-ting; [School of Power Engineering, Nanjing University of Science & Technology, Nanjing 210094, China], Feng Ke-hua; [Jiangsu Yongfeng Machinery Co. Ltd, XuYi Jiangsu 211722, China], Chinese Journal of Explosives & Propellants, 2009, 32 (2): 68-71

Abstract: The reasons of abnormal interior ballistic performance of an equilibrium launcher at high and low temperature are analyzed.Interior ballistic equations of an equilibrium launcher are established,its interior ballistic performance is computed at normal,high and low temperature respectively.By analyzing the computation and test results and test phenomenon,pointing out that abnormal performance at low temperature is caused by the severe fracture of propellant produced in ignition process and the brittleness of propellant at low temperature.The abnormal performance at high temperature is caused by the decrease of initial burning area because of propellant softening at high temperature and felting of propellant patches.The two phenomena and their randomicity affect the probable error of muzzle velocity,especially the propellant fracture at low temperature may be the hidden trouble to launch safety,considering that the propellant of the weapon system should be replaced by another material with good temperature performance

20. Interior Ballistic Performance of the Sheet Multilayer Propelling Charge, Zhang Jiang-bo, Zhang Yu-cheng, Wang Qiong-lin, Jiang Shu-jun, Zhao Xiao-mei, Yan Wen-rong, Li Qiang; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (2):64-67

Abstract: The sheet multilayer propelling charge was made.The inner of the charge was made of high energy propellant with higher burning rate and the outer one was made of low burning rate propellant containing macromolecular deterrent material.The sheet multilayer charge with different content of deterrent material and different layer constructions was investigated by closed bomb test and 30 mm simulation gun shootong.The experimental results show that MD1 and MD2 multilayer charge containing different contents of deterrent both have good progressive combustion performance and MD2 is better than MD1,the muzzle velocity of MD1 with outer-to-inner layer thickness ratio of 1 ∶ 10 increases 77.4 m • s-1 than that of 5/7 single base propellant,the muzzle velocity of MD2 with thickness ratio of 1 ∶ 5 increases 108.7 m • s-1 than that of 5/7 single base propellant while keeping max pressure almost constant.The results also show that by changing deterrent content in the outer layer and the ratio of the outer-to-inner layer thickness of the sheet multilayer propellant,the effect of increasing the total charge mass and so as to raise the muzzle velocity without maximum pressure increment could be expected

21. Interrupted Combustion Experiment of SF-3 Propellant with Plasma Ignition, Zhang Yu-cheng, Li Qiang, Zhang Jiang-bo, Jiang Shu-jun, Yan Wen-rong, Zhao Xiao-mei, Wang Gu-tai; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (3):75-78

Abstract: Two comparative tests related to combustion performance and interruption combustion were carried out with a vented chamber under the conditions of plasma ignition and regular ignition. The changes of burned surface were examined with SEM. The results indicated that there were a lot of micro holes on the burned surface after the propellant had been ignited by a bottom jet plasma generator. The existed micro holes increased burning area on the surface of propellant, and led to a deviation of the SF-3 propellant burning with plasma ignition from the geometric burning rule to a certain extent. The unitized contents of Cu, C, O elements on the interrupted combustion surface of SF-3 propellant are different under two ignition conditions. The unitized contents of the three kinds of elements were 0.7%, 30.0% and 69.3% respectively under the regular ignition condition, however 3.0%, 35.5% and 61.5% respectively under the plasma ignition condition. This difference showed that the combustion performance of SF-3 propellant could be affected evidently by the high temperature particles of C and Cu which were produced by the plasma generator.

22. Combustion Characteristics of ETPE Propellant with Plasma Ignition, Zhao Xiao-mei, Yu Bin, Zhang Yu-cheng, Yan Wen-rong, [Xi’an Modern Research Institute, Xi’an 710065, China], Chinese Journal of Explosives & Propellants, 2009, 32 (5): 75-78

Abstract: In order to solve the problem of the long delay time of ignition and the difficulty in ignition of ETPE propellant, the ETPE propellant was ignited by the electrical arc plasma which was generated by plasma producer via high power pulse electrical power. The ignition and combustion characteristics of ETPE propellant was studied under the effect of plasma. The results indicated that in comparison with general way of ignition, the plasma effect made the burning rate of the ETPE propellant enhance evidently, and the delay time of ignition shorten, and the consistency of ignition improved, considering that the shortening of the delay time of ignition and enhancing of the initial burning rate are caused by the strong effect of plasma flow with high-temperature and high-speed. This effect causes RDX grain leaping over the process of heat-absorbing and liquating and entering into the process of decomposing and heat-release rapidly.

23. Hot-Spot Effect of Local Defects in Shocked Sapphire Crystal, Zheng Xian-xu, Wang Rong-bo, Tan Duo-wang, Zhao Jun, He Zhi, He Li-hua, Liu Cang-li; [Laboratory for Shock Wave and Detonation Physics Research Institute of Fluid Physics, CAEP, Mianyang, Sichuan 621900, China], Chinese Journal of Explosives & Propellants, 2009, 32 (3): 12-15

Abstract: Explosive materials are replaced by sapphire crystal and a defect induced hot-spot is fabricated in the sapphire crystal by femtosecond laser ablation. The optical radiation and temperature of hot-spot are measured by pyrometer, and this measurement results can be used to analyze the formation and propagation of hot-spot. The results demonstrate that the more intense optical radiation and higher temperature will be emitted from the hot-spot in shocked heterogeneous sapphire than that in the shocked homogeneous sapphire. The growth and decay of the hot-spot is very fast and the total duration of the hot-spot is about 200 nano-seconds. A novel experimental method for further studying the formation and propagation of hot-spot in explosive materials is established.

24. Combustion Physical Model of Potassium Perchlorate Composite Powder, Chen Xiao-ming, Zheng Lin, Zhang Kuo, Yan Wen-rong; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chen Zhi-hui; [Military Representative Office of NO.845 PLA, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (5): 84-86

Abstract: The combustion characteristics of potassium per chlorate composite powder were studied by DSC, electron microscope scan and burning test in closed-bomb. The results show that the burning rate pressure exponent of the powder decreases obviously when the pressure increases. The burning rate will be unchanged when the pressure comes to a constant value. It shows a burning rate-pressure (u-p) platform phenomenon obviously. The pressure exponent is bigger at -400C, and the (u-p) platform phenomenon does not appear. The burning process was analyzed thoroughly based on the physical configuration and combustion characteristics of this kind of powder. The combustion physical model of potassium per chlorate composite powder was presented, and the combustion mechanism was explained. Based on the combustion mechanism the u-p characteristics and the different combustion characteristics between high and low temperature of the powder were expounded.

25. Design of the Transient Ignition Installation and Its Testing System, Duan Yun, Zhang Qi; [State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2008, 31 (5): 43-45

Abstract: To study the ignition sensitivity of explosive under the outside effect and evaluate the security of use. Transient ignition devices based on high-voltagean discharge and an ignition energy test system based oscillography DPO5054 is designed. Through igniting the fuel air explosive (FAE], the ignition energy of 2.443J of fifty percent is obtained. This offered a new method for exactly testing the ignition energy of the sample.

26. Effect of Organic Lead Salts on Combustion Characteristics and Thermal Decomposition of High Energy Modified Double Base Propellants, Fu Xiao-long, Fan Xue-zhong, Li Ji-zhen, Liu Xiao-gang, Zhang La-ying; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (2): 49-52

Abstract: The effect of three organic lead salts, including lead 3-nitro-1, 2, 4-triazol-5-onate, lead sallcylate and lead stearate, on combustion characteristics and thermal decomposition of high energy modified double-base (HEMDB) propellant were studied at various pressures. The results show that the effect of organic lead salts on the combustion characteristics and DSC characteristics values of HEMDB is obvious. Lead 3-nitro-1, 2, 4-triazol-5-onate, lead sallcylate and lead stearate can accelerate the thermal decomposition of RDX in HEMDB propellant. The burning rate and DSC characteristics values of the HEMDB propellant increase as pressure increases. The burning rate of HEMDB propellant was found to be related to the DSC characteristics values of HEMDB propellant in the pressure range from 1MPa to 10MPa

27. Power of Aluminized Explosives with Different Diameters, Han Yong, Huang Hui, Huang Yi-min, Lu Xiao-jun, Guan Li-feng, Jiang Zhi-hai, Gao Da-yuan; [Institute of Chemical Materials, CAEP, Mianyang, Sichuan 621900, China], Chinese Journal of Explosives & Propellants, 2008, 31 (6): 5-7

Abstract: In order to study the deviation extent from the similarity law about the energy released process of aluminized explosives with different diameters, the cylinder tests of two aluminized explosives with diameters of 50mm and 100mm were performed by a slit scanning photography technique with a high speed rotating camera. The slit was located at 200mm for explosive with Ф50mm and 300mm for explosive with Ф100mm apart from the rear end of cylinder. The experiment result shows that the expansion velocity of Ф100mm cylinder is five percent higher than that of Ф50mm cylinder, the ratio energy of Ф100mm cylinder is eleven percent higher than that of Ф50mm cylinder at the similar expansion position. It reveals that the similarity law of the cylinder expansion velocity does not recur for the two aluminized explosives, which is true for ideal explosives. The power of large size aluminized explosives would be underestimated by the small size cylinder test.

28. Damage Characteristics of Propellant Charge of Composite Perforating Device, Jing Zhen-yu; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (2): 5-8

Abstract: The HTPB/AP composite propellant loaded in the composite perforating device was taken as a chief object. By the simulated tests acted under different loads, the damages of the propellant charge samples were simulated. With the measuring technique for the density of propellant grain and closed bomb test, the damage level of the samples was analyzed and the combustion characteristics of the damaged propellant charge were studied. The results show that under different loads acted on the HTPB/AP composite propellant, a microcosmic change and damage occurs in its internal structure. Its damage level is successively in high velocity impact, low velocity impact, quasi-static compression and high temperature impact. The more serious the damage level, the greater the change of the combustion characteristics. Under the high velocity impact and low velocity impact, the combustion characteristics of the composite propellant become convective combustion or compressive combustion. Under the condition of a certain environmental restriction, it is possible that the deflagration to detonation transition may occur.

29. Influence of Ammonium Perchlorate and Aluminum Powder on the Combustion Characteristics of AP-CMDB Propellant, Li Ji-zhen, Fan Xue-zhong, Liu Xiao-gang; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (4): 61-63, 90

Abstract: The influences of particle size and content of ammonium per chlorate (AP) and aluminum powder (Al) on the combustion characteristics of AP-CMDB propellant are experimentally studied by determining the burning rates and pressure exponents of the propellant at different pressures. The results show that the smaller granule AP and the larger granule Al powder make the burning rates of AP-CMDB propellant increase effectively, and the smaller granule AP and Al make the pressure exponents in the pressure range of 10-20MPa increase. When the mass fraction of Al powder is lower than 14%, the combustion characteristics of AP-CMDB propellant are not obviously affected by the contents of AP and Al. When the mass fraction of Al powder is higher than 14%, the burning rates of AP-CMDB propellant are decreased because of the incomplete combustion of Al.

30. Influence of Metal Salicylates on the Combustion Characteristics and Thermal Behavior of AP-CMDB Propellant, Li Ji-zhen, Fan Xue-zhong, Zheng Xiao-dong, Liu Xiao-gang, Zhang La-ying; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (2): 43-45,60

Abstract: The influence of lead(II) salicylate (PbSa], copper(II) salicylate (CuSa], bismuth(II) salicylate (BiSa], lead(II) methylene-bissalicylate (Pb2Sa2], copper(II) methylene-bissalicylate (Cu2Sa2) and lead(II) copper(II) methylene-bissalicylate (PbCuSa2) on the combustion characteristics and thermal behaviors of the AP-CMDB propellants were experimentally studied. The results showed that the pressure exponents of the AP-CMDB propellants decreased in a certain extent with the increase in burning rates of the propellants at low pressures and the decrease in burning rates at high pressures. The peak temperature of thermal decompositions of binary system NC/NG in the AP-CMDB propellants were affected obviously by all the metal salicylates, and the peak temperature of thermal decompositions of AP at high temperature were brought forward obviously by CuSa and Cu2Sa2. It was also found that the pressure exponents of the AP-CMDB propellants in the wide pressure range of 1 – 20MPa can be decreased efficiently by the copper (II) salts of salicyle (CuSa, Cu2Sa2 and PbCuSa2).

31. Establishment of Semiconductor Bridge Ignition Model and Its Numerical Simulation, Liu Ming-fang, Zhang Xiao-bing; [School of Power and Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2008, 31 (5): 87-90

Abstract: Through analysis of input energy of the semiconductor bridge ignition circuit, considering that when the input energy is bigger than critical energy E, the ignition of the semiconductor bridge is the plasma ignition based on the physics of semiconductor and the non-Fourier heat conduction theory. The mathematic-physical model was established and analyzed using the numerical analysis method. The distribution curves affecting the ignition delay time by the input energy, pellet radius, plasma temperature are obtained. The curves show the feasibility and the rationality of the established model.

32. Correlation between PDSC Characteristic Value and Burning Rate for the Solid Propellants, Liu Zi-ru, Zhao Feng-qi, Zhang La-ying, Yin Cui-mei; [Xi’an Modem Chemistry Research Institute, Xi’an 710065, China], Liu Yan; [Beijing Chemical Defense Research Institute, Beijing 102205, China], Chinese Journal of Explosives & Propellants, 2008, 31 (2): 9-17

Abstract: The characteristic values of PDSC (high pressure differential scanning calorimetric) for 32 propellants, including DB, CMDB, XLDB and NEPE, were correlated with burning rates by an empiric formula u =ku1/2.For the formula, p is pressure, Sd = Hd / (Te – To], Hd is decomposition heat, To and Te are onset and end temperatures of heat release on DSC curve, respectively. The results show that the good fittings of the formulas for all tested propellants appear in pressure range (≤7MPa) of PDSC so far. It is found that ku, correlation factor of burning rate with PDSC characteristic value, can be used to study the effect of burning catalysts and the influence of component on burning rate for the propellants.

33. The Energy Release Law of Propellant Based on Relative Pressure Impulse, Lü Bing-feng, Xiao Zhong-liang, Zhang Li-hua, Liu You-ping; [School of Chemical Engineering and Environment, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2008, 31 (4], 57-60

Abstract: The correctional model of relative pressure impulse format is established by analyzing and correcting the geometric combustion law for studying propellant actual energy release law. Theoretical and experimental analysis under the conditions of various loading density, propellant, constant volume and variation volume are made. The results show that the actual energy release law is embodied in correctional model. The theory and scheme established by correctional model is reasonable.

34. Research on Multilayer Disc Nitramine Gun Propellant, Wang Qiong-lin, Liu Shao-wu, ZhuYang-chun, Guo Feng, Zhang Yuan-bo, Wei Lun; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China],Chinese Journal of Explosives & Propellants, 2008, 31 (2): 64-67

Abstract: A new multilayer disc nitramine gun propellant was developed and prepared. The effect of slow burning materials on the burning rate of high energy nitramine gun propellant was studied by the constant-pressure burning rate test and closed bomb test. Combustion stability of multilayer disc nitramine gun propellant was studied by rupture combustion tests. The results show that slow burning materials can decrease the burning rate of propellant and enhance its progressive combustion performance effectively. The 30mm interior ballistic test showed that compared to reference nitramine mutiperforated propellant, multilayer disc nitramine gun propellant can increase muzzle kinetic energy of 15%.

35. Detonation Transfer Reliability Test Method for Interlayer Initiation Train, Wen Shang-gang; [Laboratory for Shock Wave and Detonation Physics Research, Institute of Fluid Physics, CAEP, Mianyang, Sichuan 621900, China], Chinese Journal of Explosives & Propellants, 2008, 31 (6): 8-11

Abstract: Various probable factors affecting the detonation transfer performances of interlayer initiation train were analyzed. Combing with the characteristics of two interlayer initiation trains with different shape, a test method of evaluating the detonation transfer reliability was presented. By means of this method, the reliability of one interlayer initiation train initiating main charge was evaluated, and the satisfactory results were obtained. The analysis results obtained from reliability test methods are useful to design interlayer initiation train or to evaluate the reliability of this train.

36. Experiment and Photo acoustic Simulation of Secondary Combustion Phenomenon of B/KNO3 Mixture Ignited by Laser, Ye Ying-hua, Shen Rui-qi, Hu Yan; [School of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2008, 31 (6): 60-64

Abstract: A secondary combustion phenomenon during the ignition process of 40/60-B/KNO3 mixture excited by Nd:YAG pulse laser, was observed and attested by high-speed camera at 2000fps and by photo-detector. The reactive photo acoustic model also confirmed the secondary combustion phenomenon, which was established to simulate the laser ignition process, involving the contribution of chemical reaction different from the famous G-R model. The first combustion is supported by laser energy while the secondary combustion is determined by the balance of the competition between the heat generation and dissipation processes. With increasing the laser energy, the heat accumulating process shortens and the combustion interval decreases.

37. Design and Application of Flyer Velocity Model Accelerated by Electric Exploding Foil, Zeng Qing-xuan, Zhao Yan, Liang Qi; [School of Aerospace Science and Engineering, Beijing Institute of Technology], Yuan Shi-wei; [National Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2008, 31 (6): 50-53

Abstract: Based on the non-linear resistance model of foils in the process of explosion, a theoretical model for the electric-power of exploding foils was given. According to some of LLNL experimental velocities of flyers, the ratio of energy for accelerating flyers to that absorbed by foils was estimated, i.e. pre-burst β1≈9.9×10-3,and post-burst β2≈8.6×10-3.The model of electric-power with energy conversion coefficient was applied to the one-dimension hydrodynamic code. And the position and velocity histories of flyers driven by exploding foils were simulated by this code. The calculated deviations of the flyer velocity lie in ±8% for LLNL experimental data. The simulated curves of flyer velocity history coincide well with those of VISAR measurement.

38. Effects of Aluminum Powder Content on Exhaust Signature of CMDB Propellant, Zhang Xiao-hong, Tan Hui-min; [School of Material Science and Engineering, Beijing Institute of Technology, Beijing 100081, China, Zhao Feng-qi; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2008, 31 (2): 21-24

Abstract: The effects of aluminum powder content on exhaust signature of CMDB propellant, such as visible, infrared and laser transmission, infrared radiant temperature and radiance, were studied by using transmitter, thermal-image instrument, FTIR spectrum device and high-speed camera etc. The results show that the visible, infrared and laser transmission of exhaust plume of CMDB propellant are greatly decreased, while the infrared radiant temperature, radiance and dimension of flames are obviously increased as the content of aluminum powder increases in the formulation of CMDB propellant. It was also observed that the content of aluminum powder has slight influences on the types of final combustion products of CMDB propellant

39. Effect of Components on Combustion and Mechanical Properties of HTPB Propellant with High Energy, Chen Sheng, Liu Yun-fei, Yao Wei-shang; [School of Materials Science and Engineering, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2007, 30 (5)

Abstract: The combustion properties and mechanical properties of HTPB propellant with 90% solid mass fraction were studied by changing the content and particle size of oxidizer AP, bonding agent and the value of R. The results show that the energy of HTPB propellant increases with the increase of the solid content, and the combustion properties and mechanical properties also keep in a good state. Under the condition of high solid mass fraction, the combustion and mechanical properties of HTPB propellant display some distinct rules as the change of the directions for producing chemicals. The propellants combust steadily and the burning rate and pressure exponent can be controlled. Its burning rate-pressure exponent is between 0.30 and 0.40.The mechanical properties are tested at three different temperatures: 600C, 250C and -400C, revealing that the maximum tensile strength of the propellant at the three temperatures is larger than 1.0 MPa and the maximum elongation of HTPB propellant at -400C can reach 74.7%.

40. Progress of Study on Method of Diagnosing the Combustion Mechanism of Solid Propellant, Ding Li, Zhao Feng-qi, Xu Si-yu; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2007, 30 (6): 75-78

Abstract: The progresses in the method, equipment and investigation results of diagnosing the thermal decomposition of energetic material and combustion wave structure of propellant were introduced. Are reviewed with 16 references .Meanwhile, the results in this field by these means were reported. The development direction of research on combustion mechanism was discussed. With the development of new and sophisticated method and techniques, the diagnosis techniques and application in this field should be improved for obtaining the effective message to understand the combustion mechanism exactly.

41. Influence of Different Catalyzes on Decreasing Burning Rate Pressure Exponent of Double-Base Propellant, Liao Xin, Ma Fang-shen, Du Ping, Wang Ze-shan; [Department of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2007, 30 (4):25-28

Abstract: In order to discuss technical approach of decreasing burning-rate pressure-exponent of propellant, a method of decreasing burning-rate pressure-exponent of double-base propellant by additive catalyze has been studied. Nine catalyzes are selected. The burning-rate pressure-exponent of double-base propellant containing catalyzes is measured and disposed in terms of segment. The law of depressing burning-rate pressure-exponent of double-base propellant with different catalyzes at different pressure interval is discussed. The results show that different catalyzes at different pressure interval have different effects in decreasing burning-rate pressure exponent of double-base propellant, the general trend is that in low pressure interval it has more obvious effects. Of nine catalyzes studied, nano-mCuO and Pb3O4 catalyzes can decrease burning-rate pressure-exponent of double-base propellant obviously.

42. The Combustion Properties of HTPB Propellants under High Pressures, Song Ji-ge, Zhang Zhan-quan, Liu Bing; [Inner Mongolia Synthetic Chemical Engineering Institute, Huhehaote 010010, China], Chinese Journal of Explosives & Propellants, 2007, 30 (3): 55-58

Abstract: In order to improve the combustion properties of HTPB propellants, the effect of carbonate composites, ferrocene derivative G, high-nitrogen energetic material M, nanometer metal oxide particles and nano-aluminum on combustion characteristics of HTPB propellants was studied. The results show that carbonate composites decreased the burning rate and pressure exponent of HTPB propellants. The ferrocene derivative G decreased the pressure exponent of HTPB propellants to 0.27 in the pressure range of 8.60 - 17.12MPa, and increased their burning rate. High-nitrogen energetic material M decreased both the burning rate and the pressure exponent of HTPB propellants. Modifier M and G decreased the pressure exponent of HTPB propellants to 0.24 in the pressure range of 8.63 - 16.48MPa.Nano aluminum and nano-metal oxide obviously decreased the pressure exponent of HTPB propellants.

43. Factors Influencing Pressure Exponent of Boron-Based Fuel-Rich Propellant, Wu Wan-e; [The Second Artillery Engineering Institute, Xi'an 710025, China], Mao Gen-wang, Hu Song-qi, Wang Ying-hong; [College of Astronautics, Northwestern Poly-technical University, Xi'an 710072, China], Chinese Journal of Explosives & Propellants, 2007, 30 (3): 62-64, 68

Abstract: In order to obtain the main factors affecting the pressure exponent of boron-based fuel-rich propellant, propellant samples were prepared via mix of the compositions in mixing machine, pouring in vacuum and curing at constant temperature. The burning rate of propellants was determined by strand target method, and the pressure exponent was obtained from u=apn. The experimental results indicate that the pressure exponent is affected by HTPB content, AP content and gradation and catalyst content to a certain extent. The pressure exponent will increase as HTPB content and AP weight mean diameter decrease, while AP content and catalyst content increase.

44. A New Correcting Method for Pressure Curve in the Whole Burning Process of Propellants in Closed Bomb Test, Ying San-jiu, Xiao Zheng-gang, Xu Fu-ming; [Department of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2007, 30 (4): 62-64, 69

Abstract: Two factors resulting in pressure loss in closed bomb test were discussed. A new correcting method for pressure loss was established in light of theoretical equation used for pressure loss correcting and the pressure-time curves measured in closed bomb tests, and the temperature-time curve of vessel wall is unnecessary. Established method can interpret the effects of gas thermo-dynamical parameters and co-volume on pressure loss in closed bomb. Compared with the conventional correcting methods for pressure loss, the new method can obtain not only the propellant force and co-volume, but also the pressure curves and burning rate curves in the whole burning process of propellants. Results of closed bomb tests show that the new established method is simple and practical.

45. Effect of Combustion Catalysts on the Combustion Properties of TEGDN Gun Propellant, Zhao Feng-qi, Xu Si-yu, Zheng Lin, Yi Jian-hua, Gao Hong-xu, Chen Xiao-ming, Hao Hai-xia, Li Shang-wen; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2007, 30 (4): 38-42

Abstract: Some catalysts are putting into TEGDN gun propellants and the effect of these catalysts on combustion properties of TEGDN gun propellant is studied through closed bomb test. The result shows that, certain combustion catalyst can decrease the pressure exponent of part of combustion pressure region of TEGDN gun propellant, the pressure region decreased is related to the kind of catalysts. Lead phthalic acid can shorten combustion time, improve burning rate and increase combustion gas generation brisance of TEGDN gun propellant. Copper salt can depress the combustion gas generation brisance of TEGDN gun propellant

46. Effect of the Reliability of Coating Layer on the Measurement of Burning Rate of High Buring Rate Propellant and Improved Methods, Zheng Lin, Zhao Hong-li, Chen Xiao-ming, Zhao Feng-qi; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2007, 30 (3): 59-61

Abstract: The burning rates of the propellants grain coated by silicon rubber at the pressure range from 30 to 80 MPa were measured by the Crawford test. The results indicated that the burning rates of the propellants were increased significantly during the combustion process. The abnormal increasing of the burning rates at high-pressure range was caused by the de-bonding between the propellant and the inhibitor at high-pressure and the erosive burning of the propellant grain. It was found that the modified propellant grain inhibited with inorganic inhibiting layer by applying improved inhibiting technology, appears reliable inhibiting and steady combustion at high pressure. It was pointed out that the application of the inhibiting materials with low thermal conductivity coefficient and reliable bonding effect is the key technique for ensuring the measurement accuracy of burning rates of the propellant in high pressure range.

47. Effect of Extrusion and Fracture of Gun Propellant Charge on Combustion Behavior. Xu Jin-xing; [Beijing University of Science and Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 1007, 30 (3): 69-71

Abstract: In order to determine the relations between combustion behavior of propellant charges and its extrusion process, a dynamic simulating device is adopted to prepare samples of propellant charges which have been pressed with different dynamic high pressure and fractured subsequently. The combustion behaviors of samples have been tested in closed bomb and the burning law was studied. It is found that the initial phase of combustion for fractured samples has been boosted up, and the latter phase of combustion corresponding to high pressure region has been weakened reversely. The fracture of propellant charge owe to high pressure enduring has bad effect on launch-safety.

48. Effects of NGu on the Combustion Performance of Nitramine Propellants Containing RDX, Zhang Zou-zou, Jiang Shu-jun, Zhang Yu-cheng, Yang Yan; [Xi’an Modern Chemistry Research Institute, Xi’an 710065, China], Chinese Journal of Explosives & Propellants, 2007, 30 (3): 72-74

Abstract: To investigate from micro angles the effects of NGu on the pressure exponent change of burning rate of nitramine propellant containing RDX, the quenched experiments of gun propellants with RDX and NGu were carried out by rapid chamber depressurization in an ignition-and-combustion simulator under the pressure about 35 MPa. The burned surfaces of the quenched propellant samples were observed by SEM. The results show that the balance state between deflagration of RDX and melted layer of the propellants has an influence on the change of burning rate pressure exponent. The melted layer formed on the surface of the nitramine propellants containing NGu can restrain the deflagration of RDX. When the mass ratio of RDX and NGu is less than 1.0, the burning rate pressure exponent of the propellants will reduce obviously. There is an acerous crystal on the combustion-ending surface when the propellants have ingredients of RDX and NGu.

49. Effect of Novel Energetic Composite Catalysts on Combustion Properties of Minimum Smoke Propellant, Zhao Feng-qi, Gao Hong-xu, Luo Yang, Wang Bai-cheng, Gao Yin, Li Shang-wen; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2007, 30 (2): 1-4,16

Abstract: In order to investigate the effect of novel energetic catalysts on the combustion properties of minimum smoke propellant, the RDX-CMDB propellant samples containing various energetic composite catalysts were prepared through a non-solvent extrusion technique. The propellant burning rates at different pressures were measured by a strand burner and the experimental data were treated and analyzed with a linear regression method. The results show that in the energetic catalysts studied, lead salt of 2-hydroxy-3, 5-dinitropyridine (2HDNPPb)/copper salt of 2-hydroxy-3, 5-dinitropyridine [2HDNPCu) and lead salt of 4-hydroxy-3, 5-dinitropyridine (4HDNPPb)/2HDNPCu composite catalysts possess better catalytic effect and ability to reduce pressure exponent for the propellant. In comparison with single energetic lead salt or copper salt, the mixtures of lead and copper salts of hydroxypyridines have higher catalytic efficiency when the total content of catalyst added is constant.

50. Effects of Physical Dimension on Combustion Performance of Tubular Variable-burning-rate Gun Propellant, Zhang Li-hua, Ma Zhong-liang, Liu You-ping, He Zeng-di, Lü Bing-feng, Xiao Zhong-liang; [School of Chemical Engineering and Environment, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2007, 30(2):13-16

Abstract: The effects of physical dimension (inner diameter and length-to-diameter ratio) on the combustion performance of a tubular variable-burning-rate gun propellant were investigated by closed bomb test. The difference between theoretical and experimental Γ-Ψ curves was compared and analyzed. The experimental results show that this gun propellant would not present good progressive combustion performance when its inner diameter is too large or too small. When the length-to-diameter ratio is less than 2, it has an obvious adverse effect on progressive combustion, and the suitable value of length-to-diameter ratio is 2.5 as considering the comprehensive effects of combustion property and packing density. The main reason for the difference between theoretical and experimental Γ-Ψ curves was that some postulated conditions assumed in the derivation process of theoretical equations cannot be met in experimental test.

51. The Experimental Study on Deflagration-to-Detonation Transition in Modified Double-base Propellant with ACP, Dong Shu-nan, Wang Shi-ying, Yao Bao-xue; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Zhu Jin-Sheng; [Air Force Military Representative Office in Shijiazhuang Region, Handan Hebei 056028, China], Chinese Journal of Explosives & Propellants, 2007, 30 (2): 17-20

Abstract: To study the effect of ACP, a fast burning energy material, on the deflagration-to-detonation transition (DDT) in the modified double-base propellant, the experimental study of DDT process of propellant under the condition of porous charge is carried out with the testing system established by the DDT tube. The position-time relationship and the stress wave shape for the front of deflagration and detonation are recorded using the ionization probes and piezoelectric stress sensors. The experimental results of the propagation velocity of wave front, the location of the detonation transition point and the pressure in different positions of the charge bed are calculated and compared. The results show that the fast burning material ACP can increase the transition tendency of the modified double base propellant to DDT. When the percentage of ACP increases from 5% to 7%, the charges from deflagration to detonation increases a lot.

52. Experimental Studies on Velocity Measurement of Mylar Flyer Driven by Exploding Metal Foils with VISAR, Deng Xiang-yang, Peng Qi-xian, Zhao Jian-heng, Wang Gui-ji, Liu Jun, Tan Fu-li, Tang Xiao-song; [Institute of Fluid Physics, CAEP, Mianyang, Sichuan 621900, China], Chinese Journal of Explosives & Propellants. 2007, 30 (2): 45-48

Abstract: In order to improve the design of exploding foil initiation systems, the velocity of Mylar flyer driven by the exploding foil was measured by VISAR. The principle of VISAR and the experimental setup and the measuring method of determining the velocity of Mylar flyer were introduced. The velocity history of Mylar flyer was given at different charging voltages and various exploding bridge sizes. The discharge circuit parameter, electromagnetic interference, emitting light from shock and reflectivity affecting velocity measurement were discussed. The velocity measurement precision influenced by the deformation of Mylar flyer was estimated. Some problems that affect velocity measurement were solved and some important techniques for velocity measurement of Mylar flyer were obtained. Velocity measurement of Mylar flyer by VISAR was successfully obtained.

53. Deflagration to Detonation Transition Characteristics of NEPE Propellant, Zhao Xiao-bin, Pu Yuan-yuan, Chen Jiao-guo, Wang Chen-xue, Guan Hong-bo; [Safety and Storage Evaluating Center, Hubei Institute of Aerospace Chemo technology, Xiangfan Hubei 441003, China], Chinese Journal of Explosives & Propellants, 2007, 30 (1): 4-8

Abstract: The study ways, characterization parameters and influence factors of deflagration to detonation transition are introduced.DDT tube; photoelectric cell, strain gauge and witness board are used to study the transition characteristics of the deflagration to detonation of NEPE propellant slurry in the mixing process. The relation curve between the pre-detonation column length of NEPE propellant slurry and the loading density in DDT tube exhibits a typical U shape. The deflagration to detonation transition cannot occur for NEPE propellant slurry in the experimental condition, when the loading density of the propellant slurry is more than 95% of theoretical loading density. There is a better correlation between the fragmentation extent of DDT tube and the pre-detonation column length. The smaller the pre-detonation column length is, the severer the fragmentation extent of DDT tube. NEPE propellant slurry has the possibility of deflagration to detonation transition, because the vertical mixer is hermetic and the propellant slurry is inhomogeneous in the mixing process.

54. Study of Low Temperature Coefficient Mechanism of Polymer Deterred Propellants, He Wei-dong; [School of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Dong Chao-yang; [Luzhou North Chemical Industrial Co.LTD, Luzhou Sichuan 646003, China], Chinese Journal of Explosives & Propellants, 2007, 30 (1): 9-12

Abstract: In order to analyze the low temperature coefficient mechanism of single-base propellant deterred by poly(ethylene glycol dimethacrylate) (D1], the physicochemical properties, liner expansion coefficient and mechanical performance, of polymer D1 and single-base propellant at different temperatures are studied by dynamic mechanical analyzer and material tester. Combustion performances of deterred multi-perforation single-base propellants are studied by closed bomb test and interrupted-burning test. Results show that the linear expansion coefficients of D1 have large difference with that of single-base propellant. The exposed-perforation ratio of deterred single-base propellants at low temperature is larger than that at normal temperature. The low temperature coefficient effect of single-base propellant deterred by polymer D1 is the comprehensive results of two factors: (1) the differences of coefficient of expansion between the propellants and polymer D1 lead to some spaces between polymer D1 and propellants surface and increase burning surface area at low temperature, [2) the increase of burst ratio of deterred multi-perforation propellants at low temperature also reduces the temperature coefficient.

55. Kinetics of Lead Carbohydrazide Perchlorate by Flash Pyrolysis, Hu Xiao-chun; [The 3rd Department, Institute of Chemical Defense, Beijing 102205, China], Zhang Tong-lai, Zhang Jian-guo, Qiao Xiao-jing, Yang Li, Sun Yuan-hua; [State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2006, 29 (6): 33-37

Abstract: The exothermic decomposition reaction kinetics of lead carbohydrazide per chlorate (PbCP) was determined by T-jump/FTIR spectroscopy at high temperatures following very rapid heating process. The time-to-exotherm (tx) values evolved from the control voltage traces of the Pt filament during the flash pyrolysis yielded the kinetic parameters in the 300 – 3400C range at 0.1MPa Ar atmosphere: Ea =70.68kJ•mol-1, lnA =16.30. The activation energy determined was much smaller than that given previously by Kissinger and Ozawa-Doyle method, which also occurred with other energetic materials making these values qualitatively consistent. In addition, the decomposition kinetics of evolution of the major four individual gas products was resolved by the increase in specific absorbances, which might be essential for detailed combustion modeling of solid energetic materials.

56. The Factors Affecting Monoxide (CO) Concentration in Propellant Combustion Gas of a Gun-propelled Laser-Guided Missile Propelling Charge, Wang Qiong-lin, Jiang Shu-jun, Yu Bin, Liu Shao-wu, Wang Feng, Chen Zhi-qun; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (6): 61-64

Abstract: Some factors affecting CO concentration in combustion gas of a gun-propelled laser-guided missile propelling charge are investigated by means of closed-bomb-IR test used in lab scale investigation and on-line IR used in tank gun operation. Tests show that CO concentration is strongly related to the propellant and less strongly related to combustion pressure. Decreasing missile preserving temperature, adding small amount of oxidant into propellant, using oxidant bag in propelling charge all can decrease CO peak concentration in tank cabin effectively during firing. Turning on tank engine can speed up CO exhausting process greatly, but has no effect on CO peak concentration. Increasing cartridge ignitibility also can reduce breech flame phenomena. All these can be well explained by water gas reaction mechanism, oxygen balance and interior ballistic theory.

57. Gas Generation Rule about Tubular Gun Propellant with Two Different Burning Rate Layers, Zhang Li-hua, He Zeng-di, Xiao Zhong-liang; [Institute of Chemical Engineering & Environment, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2006, 29 (6): 65-68

Abstract: To establish the Γ vs. Ψ expression, the gas generation rule about tubular gun propellant with two different burning rate layers was theoretically analyzed. Under the precondition of following the geometric combustion law, the equations describing Γ vs. Ψ relation of this kind of variable burning rate gun propellant were derived by using its initial geometric size, burning-rate ratio and density ratio of internal and external layer as the basic variables. The critical length-to-diameter ratio needed for elaborating the characteristics of progressive combustion of this gun propellant was obtained. The influences of inner diameter, length-to-diameter ratio and burning-rate ratio of this gun propellant on its gas generation rule were discussed through calculated Γ-Ψ curve examples. The calculated results showed that this tubular gun propellants with two layers can present progressive combustion in early stage while a step of Γ in intermediate or late stage when the initial geometric size and burning-rate ratio have proper values.

58. The Effect of Density in Composition B on Deflagration-Detonation-Transition Behavior, Wen Shang-gang, Huang Wen-bin, Zhao Feng; [Institute of Fluid Physics, CAEP, Mianyang, Sichuan 621900, China], Wang Sheng-qiang, Wang Shi-ying, Yao Bao-xue; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5): 5-8

Abstract: The composition B applied widely in conventional weapons was chosen as the object of this research. By means of electrical pin and pressure gauge techniques, an experimental study was made to explore the different mechanisms at work in the deflagration-detonation-transition (DDT) of three kinds of 40/60-TNT/RDX-composition B with different density in the range of 1.597 to 1.681g/cm3.The experimental results showed that there was a critical density for transition to detonation at certain confinement condition. Different densities resulted in different results, transition to detonation was more easier for low density explosive. Under strong confinement condition (steel tube with an inner diameter of 20mm and an outer diameter of 64mm and length 500mm], a DDT was obtained for the composition B with density of 1.597g/cm3,and the inducement distance was 295 to 310mm.

59. Primary Study on Phenomena of Firelight Radiating from Explosion of Condensed Explosives, Yi Jian-kun, Yang Zhi-xu, Wu Teng-fang, Zhai Guo-feng, [Engineering Institute of Engineer Corps, PLA University of Science & Technology, Nanjing 210007, China], He Wu-yi; [Guilin Institute of Air Force PLA, Guilin Guangxi 541003, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5): 12-16

Abstract: In order to understand the mechanism and factors of firelight radiating from explosion of condensed explosive, theoretical analyses on mechanism of radiation in each phase of explosion of condensed explosive were proceeded. The factors affecting the intensity of radiation based on analyses on experimental results in literature were studied. The phenomenon of firelight from explosion of sixteen kinds of condensed explosives was investigated with high speed photography. The results show that the process of radiation of firelight from explosion consists of two phases: detonation and afterburning. The detonation pressure, detonation temperature, detonation velocity and oxygen balance of condensed explosive have effect on the maximal intensity of radiation during explosion. The duration of firelight from explosion of condensed explosives is influenced by the oxygen balance and the mass of condensed explosive.

60. Preliminary Analysis on Cone Burning of Solid Propellant in End-Burning Rocket Motors, Xu Peng, Liang Jing-yuan, Liang Guo-zhu; [School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China], SUN Zai-yong; [The 41st Research Institute, The Sixth Academy of CASC, Huhehot 010010, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5): 32-24, 64

Abstract: Main factors that cause the cone burning of solid propellant were emphatically analyzed and compared, such as the concentration of fine oxidizer particle and the migration of plasticizer and curing agent at the interface near the wall. The most basic reason of causing the cone burning was that the concentration and particle size of oxidizer at the interface were different from that near the center line. To prove the analysis in theory, the burning rate of a certain AP propellant was calculated with various particle size and concentration of the oxidizer using the burning rate formula based on the granular diffusion flame (GDF) combustion model, showing a change trend in burning rate, proving a current analysis and giving a reference for avoiding the cone burning in engineering.

61. Application of Fast-Burning Energetic Compound ACP in HTPB Composite Propellants, Ran Xiu-lun, Yang Rong-jie; [College of Materials Science and Engineering, Beijing Institute of Technology, Beijing 100081, China], Wang Guo-qiang; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5): 42-45

Abstract: The effects of fast-burning energetic compound ACP with various contents in propellants on the combustion properties of low-burning rate, medium-burning rate, high-burning rate HTPB propellants were investigated by Crawford test and firing test of neutral burning Ф64mm motor. The results showed that the ACP made the burning rate of above-mentioned three kinds of HTPB/AP/Al propellants, and the pressure exponents of the propellants in the pressure range of 6.86-15MPa increase obviously. For instances, 5% ACP in propellant samples made the burning rate of above three propellants at 15MPa enhance by 11.3%, 82.9%, (67.8%], respectively. The firing tests of neutral burning Ф64mm motors loaded with HTPB/AP/Al propellant grain containing ACP showed stable chamber pressure-time histories. The primary evidence of non-parallel layer combustion in the motors by the fast-burning energetic compound ACP was obtained.

62. Test Method of Combustion Remains of Gun Propellant, Wang Qiong-lin, Liu Shao-wu, Zhang Yuan-bo, Zheng Shuang; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5), 57-59

Abstract: Characteristics of gun propellant combustion remains and their negative effects on interior and exterior ballistics have been studied, suggesting that gun propellant combustion remains can be sorted into three categories, one adhesive remains, one floating remains and another sinkable remains, and the front two remains are mostly harmful. Nitrogen-bomb test, a new method, is used to determine the amount of adhesive remains and evaluate the feasibility of the method. Fume-box tests, nitrogen-bomb tests and TG tests of some different gun propellants are conducted and results obtained show that nitrogen-bomb test can clearly show the difference of adhesive remains of different gun propellants. Floating remains are measured by Fume-box test. Tests reveal that different gun propellant has dramatically different adhesive remains, more adhesive remains usually accompany with more floating remains.

63. Combustion Properties of a Glued Consolidation Gun Propellant, Ma Zhong-liang, Xia Ping, He Zeng-di, Xiao Zhong-liang; [Department of Chemistry and Environment, North China Institute of Technology, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2006, 29 (5): 60-62

Abstract: The variable-burning rate gun propellant with glue and consolidation was manufactured with the grains of the variable-burning rate gun propellant as the base propellant and slightly managed with energetic glue to surface and firmly pressed. This charge has resolved the problem of progressive combustion of consolidation charge. The law of burning gas release of high charge density gun propellant was effectively controlled by combining the high charge density and progressive combustion performance of the variable-burning rate gun propellant. The combustion performance of base propellant and the variable-burning rate gun propellant with glue and consolidation were analyzed comparatively by the p-t and L-B curves from traditional closed bomb test. The results indicate that the variable-burning rate gun propellants with glue and consolidation kept high progressive burning of the variable-burning rate gun propellant and have high charge density and burning reappearance.

64. Function of Carbon Materials Used in Solid Propellants and Their Action Mechanism, Wang Han, Zhao Feng-qi, Li Shang-wen, Gao Hong-xu; [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (4): 32-35

Abstract: The function in catalyzing combustion, action mechanism and action rules of carbon black, C(60], fullerene soot, carbon fiber and carbon nano-tube in solid propellants are summarized. It is found that the carbon black and C(60) in double base (DB) or composite modified double base (CMDB) propellant can enrich catalyst, prevent catalysts from conglomerating and make double base systematic propellant produce plateau or mesa effect, the pressure exponent of double base systematic propellant reduce and the burning rate at low pressure of double base systematic propellant enhance evidently. The carbon fiber improves the conduction of heat exchange, increases intensity of propellant, enhances the burning rate of propellant and prevents propellant from cracking. The carbon fiber and carbon nano-tube in propellant promote the decomposition of energetic material and enhance the burning rate of composite propellant. The development direction of the carbon materials used in solid propellants is prospected.

65. Study of UP Coating Double base Propellants with DNT, Cao Ji-ping, Li Dong-lin, Wang Ji-gui, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29 (4): 41-43, 46

Abstract: The curing mechanism of unsaturated polyester resin (UPR) and the inhibition mechanism of DNT to UPR were studied. A coating method was designed. Two composite primers DT-1 and DT-2 were developed and used to double base propellant containing DNT. The results show that the obstruction property of DT-1 is better than that of DT-2, but its adhesiveness with UPR was poor. The DT-2 has good adhesiveness with propellant but its obstruction property is not good. Under the conditions of using the DT-1/DT-2 mixture, and taking the exposure time of 180min and jelling time of up 110 min, the adherence of UP to some propellant containing DNT is very good. The adhesion strength of the sample obtained by the ring shearing test is 6.83MPa and the breaking point is not on interface, showing that the coating method can meet the requirement of adhesive the propellant charge.

66. A Non-lead Catalyzed Nitramine Modified Double Base Propellant with Low Burning Rate and Low Flame Temperature, Wang Feng, Sun Zhi-gang, [Military Office, Xi'an North Huian Chemical Industry Lt. Co., Xi'an 710302, China],Qin Neng, He Hai-min, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China],Chinese Journal of Explosives & Propellants, 2006, 29 (4): 49-53

Abstract: To decrease the burning rate and flame temperature of low flame temperature and low burning rate double base propellant, an energetic additive (PQ, a nitramine product) was added to a CMDB propellant containing HMX. The effect of the substitution of composite energetic additives composed of PQ and HMX for NC and NG partly on the burning rate and flame temperature of the propellant was studied, and the combustion performance of the propellant was adjusted using general Pb-Cu catalysts and non-lead salt catalysts. The results revealed that the PQ-HMX composite energetic additives are able to efficiently decrease the theoretical flame temperature to lower than 1200K and the burning rate was lower than 2.5mm/s at 10MPa and 200C. Comparing with the use of general Pb-Cu catalysts, non-lead salt catalysts had higher catalyzing efficiency. The propellant containing non-lead salt catalysts showed better combustion performance, the pressure exponent reached as low as 0.16 in the range of 3-7MPa and appeared a plateau combustion phenomenon. The decrease of the burning rate and flame temperature by adding energetic additive PQ is due to the reduction of energy level of the propellant and the decrease of the chemical reaction rate by the endothermic melting of PQ.

67. The Influence of Agglomerated Boron on Burning Rate of Fuel-Rich Solid Propellant, Pang Wei-qiang, Zhang Jiao-qiang, Hu Song-qi, Dang Jian-bo, Guo Ji-ying, [Northwestern Polytechnic University, Xi'an 710072, China], Chinese Journal of Explosives & Propellants, 2006, 29 (3): 20-22

Abstract: The agglomerated boron, which has good roundness and particle size of 0.105 – 0.19mm, has been prepared through a dry process, and the fuel-rich propellant sample which contains 32% of agglomerated boron and with the heat value 32MJ/kg has been successfully prepared. The burning rate and pressure index of propellant samples, with different AP gradation and Mg/Al (particle size) combination and agglomerated boron with different particle size, has been determined by strand burner method. It is found that the processing of fuel-rich solid propellant become less difficult when the agglomerated boron is introduced for replacing ordinary boron powder. That would make it realized to increase the content of boron, fine AP and other solid ingredients in composition so as to improve the heat value and combustion characteristics of propellant mentioned above. Especially, increasing the content of fine AP in composition has led to the significant enhancement of burning rate and pressure index of propellant samples, but the effects of particle size of Mg/Al and agglomerated boron are rather minor.

68. The Development of Two-Directional Energy-Focusing Cutter and Its Application for Fore-Splitting Blasting, Zhou Yao, [Nanjing University of Science & Technology, Nanjing 210094, China / China North Industries Group Corporation, Beijing 100821, China], Li Xiao-lin, Tong Yan-jun, Wang Ze-shan, [Beijing Norcin-tech Corporation, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2006, 29(3):70-72

Abstract: The ordinary linear energy-focusing cutters, which contain dynamite as detonator, cannot meet the requirements for fore-splitting and smoothing blasting in demolishes engineering. So a tow-directional energy-focusing cutter, in which an industry dynamite with low-cost and low detonation velocity has been adopted to form main detonator, and two high explosive strips are adopted to form supporting detonator to boost up main detonator to produce strong focusing gas and metal shoot, has been designed and fabricated. This two-directional cutter has been actually used in demolish engineering for fore-splitting and smoothing blasting. The results have indicated that this new type of cutter has high performance and is convenient for using in demolishes engineering.

69. Design and Experiments of Aft-Ignition for Small Solid Rocket Motor, Zhang Qiu-fang, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Wang Ning-fei, [Beijing Institute of Technology, Beijing 100081, China], Tian Wei-ping, [The 41st Institute of the Fourth Academy of China Aerospace Science & Technology Corporation, Xi'an 710025, China, Chinese Journal of Explosives & Propellants, 2006, 29 (2): 51-54

Abstract: According to the igniter design of similar solid rocket motors, celluloid was adopted as the igniter case and black powder as the amorce. Ignition pressure was chosen as a criterion of igniting the propellant. Based on the experimental formula of fore-ignition design, the initial amorce mass of a small solid rocket motor with end-and-lateral burning grain and aft-ignition manner was estimated firstly. A simulation combustion container was made to obtain the ignition characteristics of the igniter, such as the ignition peak, the delay time, and the opening manner of the nozzle closure. The ignition tests of the primers ignition manner and electric-squib ignition manner at different conditions were studied respectively. The results indicated that, though the amorce mass was the same, the ignition pressure, the ignition delay and opened manner of the nozzle closure were different .Finally, the electric-squib ignition manner was regarded as the suitable choice due to the thought of reliability and maintainability for the solid rocket motor and checked in a lot of motor ignition successfully.

70. Catalysis of Bismuth 2, 4-Dihydroxylbenzoate in Combustion of Double-base Propellant, Song Xiu-duo, ZhaoFeng-qi, Xu Si-yu, Gao Hong-xu, Gao Yin, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2006, 29(1): 36-39

Abstract: In order to evaluate the efficiency of bismuth 2, 4-dihydroxylbenzoate (β-Bi) on catalyzing burning of propellant and search for its effect mechanism, the sample of propellant containing β-Bi is prepared by extrusion technology, and the catalytic performance of β-Bi in the combustion of double-base propellant was investigated. The results show that β-Bi possesses good catalytic effect on combustion of double-base propellant and an excellent ability to enhance burning rate and reduce pressure exponent. When β-Bi together with a little carbon black (CB) and copper salt is used, the catalytic effect is better. The thermal decomposition mechanism of β-Bi was investigated by the simultaneous device of the solid reaction cell in situ/ RSFT-Re discovering that the active component in the catalytic combustion process of propellant was Bi2O3.

71. Improvement of Burning Rate for Solid Propellants by ACP, Wang Feng, [Military Office, Xi'an North Huian Chemical Industrial Lt. Co., Xi'an 710302, China], Wang Guo-qiang, Teng Xue-feng, Zhong Lei, Liao Lin-quan, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Ran Xiu-lun, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2006, 29 (1): 44-47

Abstract: Extraordinary and outstanding effect of improving the burning rate of modified double-base propellant, AP based composite propellant and N-15D propellant was achieved with fast-burning energetic material ACP. The burning rates of propellants were all substantially improved but the pressure exponent was not changed basically by incorporating ACP with different particle size and content into HMX-and RDX-based modified double-base propellants. The burning rate was greatly increased by incorporating ACP into AP based composite propellant and the pressure exponent was superior to 0.45 at 7 – 15MPa. It was successfully tested on the Φ64mm motor and p-t curve was obtained. The burning rate of base formulation was quite low when incorporating ACP into N-15D propellant, but the burning rate was still improved and the pressure exponent was increased slightly. The increments of the burning rate were 40.62% for HMX-based modified double propellant, 38.00% for RDX-based modified double propellant, 37.35% for AP based composite propellant and 9.90% for N-15D propellant.

72. Low Temperature Sensitivity of Variable-Burning Rate Gun Propellant, He Zeng-di, Liu You-ping, Ma Zhong-liang, Lü Bing-feng, Xiao Zhong-liang, [Department of Chemical Engineering, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2006, 29 (1): 65-67

Abstract: By changing thickness of the crazes with temperature, the burning area of the propellant is changed. A compensating system is founded in two-layered variable-burning rate propellant and low temperature coefficient of the propellant is realized. The craze and thickness of craze changing with temperature were observed by means of SEM; the combustion character of two layered variable-burning rate propellant at high, low and normal temperature was obtained by the closed bomb test. The interior ballistic performance on 30mm gun to observe temperature coefficient was analyzed. The results indicate that using the thickness of craze changing with temperature to change the burning area of the propellant can change the rate of gas production of propelling charge. The closed bomb test shows that the combustion performance is about the same at different temperatures. The interior ballistics performance shows that the variable-burning rate propellant has low temperature coefficient.

73. Formulation Design of a New Ignition Composition and Its Performances, Tian Chun-lei, Gao Jun-guo, Du Shi-guo, Han Qi-wen, [Ordnance Engineering College, Shijiazhuang 050003, China], Chinese Journal of Explosives & Propellants, 2006, 29 (1): 12-16

Abstract: In order to find out a new civil ignition powder, the Al, Mg, KNO3 and S used as major elements to form a new type of ignition composition. The orthogonal design method was used to optimize the formulations. In this way, 16 different ignition composition prescriptions were produced. Used Real software to simulate the burning process with computer, the energy parameters of all ignition compositions was calculated. According to the real temperature of five different prescriptions formed in selected range, the best formulation was optimized. The igniting efficiency of the selected optimal powder was tested in Bruceton's way. And the same parameter of black powder was tested under the same condition. The results show that the ignition distance of new composition is 7.916 cm while the black powder is 2.942 cm, indicating that the ignition performance of new ignition powder is better than that of black powder. The new ignition powder can ignite the thermite reliably.

74. Combustion Property of High Energy and High Strength Propellant, Huang Zhen-ya, Wang Ze-shan, He Wei-dong, Xu Wan-yu, [School of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2005, 28 (4): 61-63

Abstract: In order to search the combustion performance of a new propellant with polyether polyurethane binder plastized by mixed nitrate ester, the combustion characteristic of the JMZ propellant in the range of different pressure was researched by closed bomb normal test and high pressure test. The test results showed that burning rate pressure exponent values of the JMZ propellant are large at low pressure, as those of RDX nitramine propellants, but the burning rate pressure exponent values gradually diminish along with increase of pressure and are equivalent to those of conventional propellants at high pressure. There are no obvious turning phenomena in course of the change of burning rate pressure exponent values. In addition, according to the test results, the JMZ propellant revealed a good burning progressive in initial stage which should be beneficial for barrel weapon.

75. Combustion Property of Oblate Propellant with Micropores in Air, Lin Xiang-yang, Cheng Xiang-qian, Pan Ren-ming, Yin Ji-gang, [School of Chemical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2005, 28 (4): 68-71

Abstract: In order to study the combustion property of oblate propellant with micro pores prepared by chemical foamed process, the apparent mass burning rate of the propellant is measured by strand burner method in air at normal pressure. Experimental results show that the bulk density, grain size, test temperature and the loading condition have obvious effects on the mass burning rate of the oblate propellant with micro pores. The mass burning rate of single base micro pores propellant increases with decreases of the bulk density. It also increases with the rise of load diameter and the particle size. Comparing with normal propellant, test temperature has more effects on the mass burning rate of single base oblate propellant with micro pores. When test temperature increases from 288K to 332K, the mass burning rate of single base oblate propellant with micro pores increases over 4.5 times. The materials of tube for loading particles and the load height have less effect on the apparent mass burning rate.

76. The Combustion Characteristics of RDX Modified Double Base Spherical Small Size Propellants, Cai Sheng, Wang Ze-shan, [Chemical Engineering School, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2005, 28 (2): 26-28, 82

Abstract: The grain distribution and thermal decomposition characteristic of RDX in RDX modified double base spherical small size propellants are discussed. The combustion mechanism of RDX modified double base spherical small size propellants is presented. The combustion properties of the RDX modified small size propellants are determined by a closed vessel and analyzed theoretically. The results show that the decompositions of RDX and double-base groups in modified double base spherical small size propellants are carrying through independently. With the improvement of the pressure, the burning rate of the modified double base spherical small size propellants will be higher than that of remodeled double base spherical small size propellants.

77. Mechanical Sensitivity and Combustion Properties of CMDB Propellant Containing PSAN, Dang Yong-zhan, Zhao Feng-qi, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2005, 28 (2): 13-15

Abstract: The mechanical sensitivity and combustion properties of CMDB propellant using phase stabilized ammonium nitrate (PSAN) as oxidizer were investigated through the burning rate, impact sensitivity and friction sensitivity measurements. The experimental results show that PSAN is effective for improving the sensitivity of CMDB propellant, the burning rate of CMDB propellant with PSAN is lower than that of CMDB propellant with RDX, and the pressure exponent of CMDB propellant with PSAN is higher than that of CMDB propellant with RDX. With increasing the PSAN content in CMDB propellant, the burning rate decreases, and the pressure exponent increases in the pressure range of 1 to 5 MPa.

78. Effects of Types of Lead Compounds on the Combustion Characteristics of Smokeless NEPE Propellants, Fan Xue-zhong, Zhang Wei, Li Ji-zhen, Sun Yu-kun, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1): 9-11, 24

Abstract: The effects of three kinds of lead compounds on the combustion characteristics of smokeless NEPE propellant were investigated by Crawford bomb test and elemental analyses of quenched surface of propellant samples. The used lead compounds were LF (an energetic lead compound], LP (an organic lead compound) and LC (an inorganic lead compound], respectively. The propellant samples, containing LF, LP and LC, were prepared by slurry casting process. It was found that those lead compounds all could decrease the pressure exponents of the propellant to 0.33 – 0.48 in the pressure range of 3 – 5Mpa and to 0.18 – 0.58 in the pressure range of 5 – 12MPa, respectively. LP, which also had no side effect on the curing process of the propellant, can obviously improve the combustion characteristics of smokeless NEPE propellant in the pressure range of 3 – 12MPa. The results of elemental analyses indicated that the content of lead on the combustion surface of propellant containing LF or LP is more enriched than that of the propellant containing LC.

79. Experimental Study on the Electric Performance of Detonator Components Used in a Nuclear Warhead, Fei Ji-you, Li Ya-rong, [College of Mechanical Engineer, Dalian Jiaotong University, Dalian 116028, China], Zhu Man-lin, [The Second Artillery Engineering College, Xi'an 710025, China], Chinese Journal of Explosives & Propellants, 2005, 28 (3): 73-75

Abstract: To examine the electric performance of detonator components used in a nuclear warhead stored for several decades, the research on the electric performance experiment was carried out by using the same term storing detonator unit. The experiment adopted a GSJ high speed video camera and same spark detonator synchronous explosive device. The results show that the stored detonators still have good performance of fire abilities, high degree of security capability, and synchronous dispensability that is little than 0.4μs, and the performance can satisfy the demand of blasting normal.

80. Detonation Performance of TATB, TCTNB and TCDNB, Gao Da-yuan, Xu Rong, Dong Hai-shan, Li Bo-tao, [Institute of Chemical Materials, CAEP, Mianyiang, 621900, China], Lü Chun-xu, [School of Chemical Engineering, NUST, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2005, 28 (2): 68-71

Abstract: The detonation velocity and pressure of Ф20mm cylinder TATB, TCTNB/Wax (97%/3%) and TCDNB/Wax (97%/3%) have been measured by ionization probes and manganin gauge, and their detonation parameters and the equilibrium composition of detonation products at C-J state have been computed by means of the VLWR code. The testing results show that the detonation velocity and pressure are 7.452 mm•μs-1 and 24.40 GPa for TATB, (6.890) mm•μs-1 and 20.28 GPa for TCTNB and 5.973 mm•μs-1 and 15.30 GPa for TCDNB respectively. The calculated results were close to experimental values, showing that the calculated results are satisfactory.

81. Research of HTPB/AP Composite Propellant Shock Wave Ignition, Lei Wei-guo, Wu Quan-dao, Wei Guo-ping, Yuan Tie-gang, Huo Hong-xing, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2005, 28 (3): 34-36,51

Abstract: The influence of shock wave on the detonation performance of HTPB/AP composite propellant used in plus penetrator is studied by means of clapboard experiments. The results show that the HTPB/AP composite propellant can be detonated reliably by means of reasonably controlling the shock wave intensity. A new method is provided for the initiation of other propellants.

82. Temperature Response of Aluminum Particle Heated by Thermal Effects of Explosive Detonation, Luo Ai-min, Zhang Qi, Bai Chun-hua, Li Jian-ping, [Disasters, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1], 35-38

Abstract: An analyzing system of high speed movement is used to record detonation products expansion process of Nitromethane (NM).The temperature response of aluminum particles is calculated by using thermal penetration theory under thermal effects of NM detonation. The results show that the thermal effect of NM detonation on aluminum particles is more intensive in expansion phase than that in region of NM detonation, whereas this effect on aluminum particles in detonation zone is neglected. Smaller aluminum particle in NM detonation region can be heated to its ignition temperature promptly, implying that aluminum oxidation reaction becomes possible in region of NM detonation.

83. The Catalytic Combustion of DB Propellant with Low Burning Rate and Low Flame Temperature, Qin Neng, Wang Liang, [College of Astronautics, Northwestern Polytechnic University, Xi'an 710072, China], Xie Bo, Tian Chang-hua, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2005, 28 (2): 6-9

Abstract: The combustion performance, thermal decomposition, and quenched surface appearance and element distribution of double-base (DB) propellant containing general lead and copper salt catalysts with low burning rate and low flame temperature were investigated. The following experimental phenomena were observed: (1) the elements distribution of quenched samples surface were not uniform, and element C and catalysts existed accumulation to some degree, [2) the quenched surfaces of samples containing catalysts appeared different balls, and different catalysts formed the balls with different diameter distribution, the main compositions of the balls were Pb elements, and the others were small amount of other elements and these balls connected to form long chain and short branch one another, [3) the un-combustion surfaces of samples with or without catalysts had no balls. The results indicated that general lead and copper salt catalysts used in common DB propellants also had catalytic effect on DB propellant with low burning rate and low flame temperature, and also have great effects on thermal decomposition.

84. Properties of the Supplying Power System for the Flyer-Initiating Device, Tan Ying-xin, Zhang Jing-lin, Tan Ru-mei, [Environment and Safety Engineering Department, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1), 22-24

Abstract: The function of the supplying power system for the flyer-initiating device is studied. The working principle of the supplying power system is analyzed in theory. By using the Rogowski coil, the electrical parameters of the power system are tested. The curves of the short circuit discharge and resistant circuit discharge are recorded by oscillograph. The circuit parameters of the system obtained is T2.0μs, L≤82nH and R≤47mΩ. The working time of explosion foil is 1.8μs. These data indicate that this system can be used as a supply power device for the flyer-initiating device.

85. The Thermal Decomposition and Combustion of a New Type High Energy Polymer GAP, Wang Tian-fang, Li Shu-fen, [Department of Chemical Physics, University of Science and Technology of China, Hefei 230026, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1): 5-8

Abstract: The research process and the status of the applications of GAP are summarized. The experimental studies of the thermal decomposition and the combustion of GAP are introduced, and the calculation studies of the combustion products of GAP are also mentioned. The results are compared and discussed in a certain extent. Some new effective investigating methods, such as GCMS,pyrolytic MS,MBMS,IR/UV/CO_2 laser-induced decomposition, laser-supported decomposition, etc, are presented.

86. Principle and Realizable Approach of Variable Burning Rate Propellant, Xiao Zhong-liang, He Zeng-di, Liü You-ping, Ma Zhong-liang, Lu Bing-feng, [Department of Chemical Engineering, North University of China, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1): 25-27

Abstract: According to the interior ballistic performance of guns, a concept of variable-burning rate propellant was put forward, the fundamental principle of this propellant was discussed and the technologic way to realize the principle was explained.In order to realize the variable-burning rate ,the propellant has two layers ,inner layer's burning rate is higher than the outer layer's. The results show that two-layered variable-burning rate propellant has wishful discharge rule and good properties of progressive combustion.The propellant has the advantages of high energy,universal applicability and high security.

87. Measurement of the Signal Transmittance of Solid Propellant Plume with Smoke-Box Method, Zhang Jin-min, Yuan Hua, He Tie-shan, Liu Jun-feng, [The 42nd Institute of the Fourth Academy of CASC, Xiangfan 441003, China], Chinese Journal of Explosives & Propellants, 2005, 28 (1], 12-14, 21

Abstract: A signal (including visible light, near-mid-far infrared radiation) transmittance measuring system and a smoke-box were studied and established to evaluate the signature of solid propellant formulation base on the framework of SCF (Signature Characterization Facility). In order to validate this system, a number of tests performed by adopting different propellant formulations under different experimental conditions. The result shows that the testing accuracy of the system is less than 3%. Based on the experimental data, a standard to characterize the signals transmittance of primary and secondary smoke has been established. The results indicate that the signal transmittance decreases with increasing the content of Al powder for primary smoke and closely relates to the content of AP in propellant formulation for secondary smoke, and the occurrence of secondary smoke is related to the temperature and humidity in the smoke -box.

88. Effect of Copper Compounds and Carbon Black on the Combustion Characteristics of Smokeless NEPE Propellants, Zhang Wei, Li Ji-zhen, Sun Yu-kun, Fan Xue-zhong, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2005, 28(3): 27-29, 33

Abstract: The effect on two copper compounds (AD and BC) and three carbon blacks of their combustion characteristics on the non-smoke NEPE propellant are studied by determining the combustion characteristics of propellant at different pressures and analyzing the composition of elements on quick quenched surface. The results show that the suitable amount of AD (an organic copper compound) can improve the combustion characteristics of the propellant and reduce the pressure exponents of the propellant to less than 0.45 in the pressure range of 3 – 20MPa. The catalysis of AD is weaker than that of the same quantity of BC (an organic copper compound) in the pressure range of 12 – 18MPa; the reason might be thatthe content of copper from AD on the combustion surface is lower than that from BC on the combustion surface. Three carbon materials can change the burning rate of the propellant in the pressure range of 3 – 18MPa. Increasing added quantity of ethyne carbon in the propellants can enhance the burning rate and lower the pressure exponent of the propellant in the pressure range of 3 – 20MPa.

89. Current Progress of Flame Retarded Polyurethane Materials Containing Phosphorus and Halogen Flame Retardants, Chang Hai, [Northwest Polytechnic University, Xi'an710072, China], Wang Ji-gui, Gan Xiao-xian, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (2): 56-59

Abstract: This paper introduces the current progress of flame retarded polyurethane materials containing phosphorus and halogen flame retardants .The main works are now developing new additive flame retardants, reactive flame retardants of organic phosphate and flame retarded binders for flame retarded polyurethane materials. This paper also suggests that the future works should focus on improving comprehensive properties of flame retarded polyurethane materials and going deep into study flame retarded mechanism.

90. Investigation of Solid Explosives Initiation under Shock Waves, Chen Lang, Wu Jun-ying, Fang Qing, Ke Jia-shan, Feng G Chang-gen, [Lab for Prevention and Control of Explosion Disasters, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2004, 27 (1): 1-4

Abstract: For investigating the characteristics of solid explosives initiated by shock waves, the Card Gap Test of JO-9195 explosive was carried out and recorded with high speed camera. The critical thickness of Plexiglas clapboard to initiate the explosive was predicted. The shock initiation model of explosives was given. The numerical simulations of explosive initiation were conducted. The pressure histories inside explosives under shock waves loading were calculated. The threshold pressure to initiate the explosive and the run distance of detonation were discussed.

91. Several Problems Inquired on CARS Thermometry in Propellant Combustion, Hao Hai-xia, Li Chun-xi, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (1): 45-48

Abstract: A discussion is given that soot, C2 radical and laser intensity have an influence on CARS (Coherent anti-Stokes Raman Scattering) applied to propellant combustion and temporal and spatial resolution is inquired into CARS thermometry precision in propellant flame. The discussion demonstrates that it is necessary to research that the propellant flame soot has an effect on CARS temperature and that the importance of realizing high temporal and spatial resolution are realized in propellant combustion.

92. Combustion Property Character of Variable-Burning Rate Gun Propellant, He Zeng-di, Liu You-ping, Ma Zhong-liang, Lü Bing-feng, Xiao Zhong-liang, [Dept. of Chemical Engineering, North China Institute of Technology, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2004, 27 (3): 10-1

Abstract: The principle and realizable approach of variable-burning rate propellant, the burning rate of inner layer is higher than that of the outer layer are introduced. The combustion character of two layered variable-burning rate propellant in closed bomb test is analyzed and the interior ballistic performance on 30mm gun is construed. Contrast with single base gun propellant with polymer coating layer, the two-layered variable-burning rate propellant has good properties of progressive combustion and low temperature coefficient

93. Application of Multi-Point Synchronous Explosive Logic Circuit of the Ring Propagating Charge, Hu Shuang-qi, Tai Ling, Cao Xiong, [North China University of Science and Technology, Taiyuan030051, China], Chinese Journal of Explosives & Propellants, 2004, 27 (3): 62-65

Abstract: To improve the initiating capacity of the booster pellet, the multi-point synchronous explosive circuit was applied to initiate the booster ring."One in four out" and "one in eight out" synchronous explosive circuit was designed. The synchronous time was analyzed. And the experimental program was designed to test the initiating capacity. The experimental results stated that the initiating capacity of booster pellet ring was obviously improved by applying the multi-point synchronous explosive circuit.

94. The Soft-Sensing Megtlier of the Inwall Temperature of Closed-Bomb, Huang Feng-liang, [Dept of Control Science and Engineering, Nanjing Normal University, Nanjing210042, China], Yu Yong-gang, [College of Power Engineering, Nanjing University of Science and Technology, Nanjing210042, China], Chinese Journal of Explosives & Propellants, 2004, 27(1): 59-62

Abstract: Based on a soft-sensing model and its corresponding solution, and combined with an example, the in-wall temperature of closed bomb has been studied with the soft-sensing method. The results show the in-wall temperature of closed bomb can be measure with the given model and its solution. The obtained curve of the in-wall temperature vs. time before the peak value is smooth. It is very important for further study on the maximum temperature.

95. Reaction Mechanism of Metallized Explosive with Composite Metals Powder, Huang Ya-feng, Wang Xiao-feng, [Xi'an Modern Chemistry Research Institute, Xi'an710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 26-28

Abstract: The reaction mechanism of Ti-Ni metalized explosive is investigated by detonation heat comparison between calculation and experiment result and X-ray experimentation of solid reaction products. The results of X-ray experiments show that there are oxide and alloy in the detonation products. The content of titanium which is oxidized into oxide is 57.0%, which is more than that of titanium turning into alloy. So there is not only alloy reaction but also oxidization reaction in the reaction of metalized explosive containing Ti-Ni metal powder, and oxidization reaction is faster than alloy reaction, which is in line with chemistry kinetics.

96. Inhibition of Very High Burning Rate Propellant, Li Xiao-dong, Yang Rong-jie, Li Jian-min, [School of Materials Science and Engineering, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 63-65

Abstract: A novel propellant, which was of porous structure and had very high burning rate (above 1 000 mm/s], was prepared. Its inhibitor is very important in studying the application of very high burning-rate propellant. The propellant grains with size Φ 25×25 mm were inhibited using polyvinyl chloride (PVC) as inner layer and cellulose acetate added flake asbestos as outer layer. The experiment of determining the thickness of coating layer, termination burning and indirect proof was studied. Results show that the convection burning of VHBR propellant is stable, no flame-leak. Its burning rate is above 1 000 mm/s by using this way.

97. Establishment of Burning Rate Models of Smokeless Modified Double-base Propellant Containing Fast Burning Energetic Substance, Liao Lin-quan, Qin Guang-ming, Li Xiao-jiang, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China, Chinese Journal of Explosives & Propellants, 2004, 27 (3): 21-24, 28

Abstract: Four mathematical models describing the combustion of smokeless modified double-base propellant, which contain fast burning energetic substance with different shapes (cube, globular, cuboid, and slice], are established. The mathematical equations of burning rate and the available size of fast burning energetic substance substances in the direction of combustion are deduced. With the help of the established mathematical model, the burning rates of propellants containing 5% and 7% ACP are calculated under different pressures. The results show that the calculated values of burning rates are in good agreement with the experimental ones.

98. The Application of Surface Active Agent in Propellants, Liao Xin, Huang Zhen-ya, Yang Wen-bao, Wang Ze-shan, [Nanjing University of Science and Technology,Nanjing210094, China], Chinese Journal of Explosives & Propellants. 2004.27(1):63-65.

Abstract: The combustion properties of LOVA propellant were studied through closedvessel. The results show that the particle geometry and grain size of nitramine influence the combustion property greatly. The nitramine treated by chemically re-crystallization was needle-like, the propellant made by this nitramine could produce stress centralization easily, and this nitramine was not good for improving its burning property. The nitramine treated by ball grind was cobblestone-like and efficient for combustion property. The larger of the nitramine grain size, the higher of the burning rate and the exponent. The combustion property of propellant could be improved by decreasing its grain size, but its burning rate index would become high when the grain size was smaller than a value. After treating the nitramine with surface-active agent, the combustion property of the propellant could be improved greatly.

99. Burning Properties of a New Kind of High-burning Rate Propellant, Ma Yu-ying, Guo Xiao-de, Liu Yun-zhi, [Shanxi xing′an Factory of Chemical Materials, Taiyuan 030008, China], Chinese Journal of Explosives & Propellants, 2004, 27 (2): 38-40

Abstract: This article introduces the porons grain structure and combustion characteristics of a novel high burning-rate propellant. Base on motor test results, it is found that the propellant exhibit three type of combustion manners at different motor loading parameters. The combustion manners include parallel layer burning, limited convection burning and convection burning.

100. Study of the Flame Retardant Mechanisms of Phosphorated Flame Retardants in Polyurethane Elastomer, Shi Ai-juan, Wang Ji-gui, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China, Chinese Journal of Explosives & Propellants, 2004, 27 (1): 40-44

Abstract: The flame retardant mechanisms of two phosphorated flame retardants P1~# and TCP in isocyanurate-modified polyurethane elastomer (IMPUE) were studied. By limiting oxygen index (LOI], TG-DTA, FTIR and X-ray spectrum, the results show that the flame retardant mechanisms of P1 and TCP used for IMPUE are the gas phase, condensed phase and discontinuous heat exchange, of which gas phase mechanism and discontinuous heat exchange mechanism were predominant mechanism of P1~# to IMPUE. The condensed phase mechanism and discontinuous heat exchange mechanism were predominant mechanism of TCP to IMPUE.

101. Theoretical Research of Influence of Chemical Components on Combustion Property of Double Base Plateau Propellants Wang Yi, [The 705 Research Institute of China Shipbuilding Industry Corporation, Xi'an 710065, China], Song Hong-chang, Bai Hua-ping, [Nanjing University of Science and Technology, Nanjing 210094, China], Kang Jian-cheng, [The Military Affairs, Department of North Taiyuan, Xing’an Factory of Chemical Material, Taiyuan 030008, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 55-58

Abstract: The influence of main chemical components of double base plateau propellant on its combustion property was investigated by theoretical computation, which was based on one-dimensional gaseous phase reaction flow model. The computation results were not only in agreement with domestic and international practical experience, but also could explain the chemical essence of propellant burning process. So through optimizing propellant formula, the results might be used to adjust the burning rate and pressure exponent of double base plateau propellants.

102. Study on Combustion Mechanism of Fuel-Rich Propellant Holding Boron Coated with AP, Wang Ying-hong, Li Bao-xuan, Hu Song-qi, Li Jin-xian, [College of Astronautics, Northwestern Polytechnic University, Xi'an 710072, China], Chinese Journal of Explosives & Propellants, 2004, 27 (2): 44-47

Abstract: The combustion wave temperature profiles and flame structures of fuel-rich propellant containing boron are measured by using W-Re micro-thermal couple and flame photo technique. The surface appearance and element distribution of extinguished samples are analyzed by JMS-5800SEM. The heat which releases in condensed-phase is obtained by integrating the DSC curve. The difference of the combustion characteristic between two propellants whose contain boron coated with and without AP is compared by measuring the heat of explosive and burning rate of the propellants. The results show that when the formulations are invariable, which contains boron-coated with AP, the adiabatic flame temperature of explosion and the burning rate in lower pressure are increased. Meanwhile, the combustion course of the propellant was confirmed preliminary.

103. A Study of Decreasing Acid Value of Booster Pellets Used PETN, Wei Tian-yu, Wang Ji-ming, Ran Jun-peng, Zhao Rui-xian, [No.805 Factory, Military Representative Office of No.805 Factory, Baiyin730900, China], Chinese Journal of Explosives & Propellants, 2004, 27 (1): 20-22

Abstract: The process of decreasing the acid value of the booster pellets used semi-finished PETN was studied by the exploring test in lab, the mini test and the medium test on the production line. The test data show that after the digesting in de-acid agent, every specifications of the semi-finished PETN can meet the regulations of the contract. The performance of the product meets the application requirement completely. Utilizing the available equipment, the batch production can be carried out.

104. Adjustment on the Burning Behaviors of the Propellant Containing Diazidopenane, Wei Xue-tao, Qing Hui, Cui Peng-teng, Liu Yi, Yang Jian-xing, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 46-49

Abstract: Based on comparison and analysis of the adjustment technical paths of the combustion performance of propellant, the principle and method of adjusting the combustion performance of DIANP propellant with high content of plasticizer is proposed. The deterrent coated material suitable for DIANP propellant is determined, it is composed of DIANP propellant and a deterrent B. The combustion properties of deterrent coated DIANP propellant are tested with the closed bomb. The experiment results show that using deterrent coating technique could reduce the initial pressure rate of DIANP propellant, and obtain the effect of progressive combustion; the coated thickness is the most important factor of the deterrent- coated propellant for adjusting combustion performance

105. Presentational Regulations of Combustion in Propellant of Gun-Boosted Missile, Wu Xiao-qing, Xiao Zhong-liang, [Department of Chemical Engineering, North China Institute of Technology, Taiyuan030051, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 50-51, 62

Abstract: The launching characterization of gun-boosted missile was discussed, and its characterization in propellant is that the combustion pressure is between solid propellants and conventional solid propellants. The combustion properties of the propellant of gun-boosted missile in the process of launching were tested and assessed in the closed combustion bomb with the pressure range below 100 MPa. The results show that it has different characteristics compared with conventional propellants. All of these will have practical significance for the study of new type propellant of gun-boosted missile.

106. Effect of Base Explosive RDX on Pelleting Characteristics of CH-6 Compound, Yan Ji-sheng, [Gansu YinGuang Chemical Industrial Complex, Baiyin 730900, China], Chinese Journal of Explosives & Propellants, 2004, 27 (3): 53-54, 59

Abstract: The pelleting charateristics of two CH-6 composite explosives composed of pressure-cook RDX and RDX refined with actone respectively, were determined by the pelleting characteristics test and X-ray inspection method. The results indicated that the pelleting characteristics of CH-6 composite explosive containing pressure-cooks RDX were better than these of CH-6 composite explosive containing RDX refined with actone. The reason of difference in pelleting characteristics was discussed.

107. Ignition and Combustion Behavior of a Type of LOVA Solid Propellant, Yang Chun-xia, Zhao Bao-chang, Li Bao-ming, [Ballistic Lab, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 31-34

Abstract: To study the ignition and combustion behavior of a type of LOVA propellant based on RDX, the closed vessel experiments are accomplished. Then the different patterns of the obtained P-t curve and dP/dt-P/P(max) curves are given and analyzed, and the interaction mechanism plasma and LOVA propellant is discussed for the further research on the configuration of propelling charge and enhanced combustion effect in application to ETC firing.

108. Influence of the Surface Treating of Azidonitramine Propellants on Their Initial Combustion，Yang Li-xia, Jiang Shu-jun, Li Li, Yang Yan, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (1): 66-67, 73

Abstract: The characteristics of initial combustion in gun chamber concerning the surface treated azidonitramine propellants with desensitizing and coating were studied by means of experiments. The results show that the initial combustion performance of the surface treated is improved. The results also show the differences of influence between two kinds of surface treating on the initial combustion.

109. Ignition and Combustion Behaviors of LOVA Gun Propellant, Zhang Yu-cheng, Yang Li-xia, Jiang Shu-jun, [Xi'an Modern Chemistry Research Institute, Xi'an710065, China], Chinese Journal of Explosives & Propellants, 2004, 27 (2): 41-43, 80

Abstract: Two kinds of LOVA gun propellants with different binders were prepared. They are L15A (RDX76%, NC4%, DOP8%) and L13A (RDX76%, NC4%, CAB12%, ATEC8%) respectively. The ignition and combustion behaviors were investigated with a closed bomb and a simulator of ignition and combustion. The results indicate that the LOVA gun propellants are difficult to be ignited; however, its ignition behavior can be improved by adding AP into the igniter. The LOVA gun propellants have the characteristic of lower coefficient and higher exponent to its exponential formula of burning rate versus pressure. The rule of gas generation and burning behavior in the initial stage of the two LOVA samples were studied by the closed bomb tests at the same ignition condition. It is found that there is a rapid increasing of gas generation rate for the LOVA propellant with energetic binder. It shows that the LOVA propellant with energetic binder has a better ignition ability compared to the LOVA propellant with inert binder.

110. The Low Temperature-Sensitive Coefficient Charge of Flat Ball Gun Propellant, Zhao Qi-lin, Huang Shun-you, Li Chun-zhi, [Luzhou North Chemical Industries Co., Ltd, Luzhou646003, China], Chinese Journal of Explosives & Propellants, 2004, 27 (4): 42-45

Abstract: A low temperature-sensitivity charge, which was composed of loose flat-ball gun propellants and dense flat-ball gun propellants, was designed. The temperature-sensitivity of designed charge was controlled by adjusting the proportion of loose propellant. The burning properties, chamber pressure wave and physical stability of the charge at different temperatures were characterized by close bomb test and 30 mm gun shooting test. The results show that the designed charge has relatively low temperature-sensitivity, stable chamber burning properties, excellent physical stability and shooting security.

111. Safety for High Energy Nitramine Propellant Used in High Pressure Gun, Huang Zhen-ya, Liao Xin, [Nanjing University of Science and Technology, Nanjing210094, China, Chinese Journal of Explosives & Propellants, 2003, 26 (4): 8-10, 19

Abstract: The characteristics of pressure wave, adaptabilities of interior ballistic and dynamic burning alive in lower temperature of RGD7 propellant in high pressure gun have been studied and analyzed, by using the 30 mm high pressure simulated gun tests and comparing to the single base propellant. The results show that the characteristics of low burning rate in lower pressure make for improving the dynamic conditions in bore and putting up preferable adaptabilities of interior ballistic, so that RGD7 propellant has fine safe property used in gun. But its mechanics performance in lower temperature should be more improved by reason of higher dynamic burning alive in lower temperature.

112. The Influence of Different Damages of CCCF Composite Propellant Charge on the DDT Behavior, Lei Wei guo, Wu Jie ling, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2003, 26 (3): 32-34

Abstract: Damaged samples of HTPB/AP CCCF composite propellant charge was prepared by four kinds of methods which may simulate the different damage states of high energy gas fracturing application. Their influences on the combustion stability and DDT behaviors were investigated through hermetic bomb test and DDT tube test. It is concluded that DDT would not occur in these damaged charges under non-confined conditions, but might occur in the oil well.

113. CARS Diagnostics for Combustion Flame Temperature of Double-Base Propellant, Li Chunxi, Zhao Ming, Zhang Ruie, Yuan Chao, Zhao Fengqi, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2003, 26 (1], 65-67

Abstract: The combustion flame CARS spectra of the double-base propellant and its flame temperature values have been obtained. The results show that the temperature measured by CARS spectroscopy is in agreement with values calculated by thermodynamics. The temperature change observed by continuously collecting the CARS spectra indicates that CARS technology can be used for real-time diagnostics of the flame temperature during the propellant combustion.

114. Study on the Combustion Stability of Desensitized Propellants, Li Li, Zhao Bao chang, Xu Bin, [Nanjing Normal University, Nanjing 210097, China, Chinese Journal of Explosives & Propellants, 2003, 26 (1): 50-52, 64

Abstract: The combustion stability of three main types of gun propellants (single based propellant, double based propellant and nitramine propellant], which are desensitized with two different methods, is analyzed and evaluated. The effect of the two desensitized methods on combustion stability of the propellants is concluded. It is shown that the burning rate of the propellants increase through both of the two desensitized methods, but the instability of combustion and the burning rate-pressure exponent respectively increase also.

115. Theoretic Analysis on Pressure Sensitivity of Ultra-High Burning Rate Propellant, Li Xiao dong, Yang Rong-jie, Li Jian-min, [Beijing Institute of Technology, Beijing100081, China], Chinese Journal of Explosives & Propellants, 2003, 26 (3], 24-26

Abstract: Pressure sensitivity of ultra high burning rate propellant (UHBRP) was analyzed theoretically. A technological method of reducing the pressure sensitivity of UHBRP was referred. By this method, the densities of UHBRP pellets increase gradually from one end to another, then pressure sensitivity will be reduced greatly, the pressure exponent will be reduced to zero theoretically.

116. Study on Combustion Property of NEPE Propellant with Low Aluminum Content, Li Xiao meng, Liu Yun fei, Yao Wei shang, Tan Hui min, [Beijing Institute of Technology, Beijing100081, China], Chinese Journal of Explosives & Propellants, 2003, 26 (2): 50-52

Abstract: The combustion properties of NEPE propellant with 8% aluminum content were studied. It was observed that increasing the ratio of NG/DEGDN, decreasing the particle size of AP, and increasing contents of fine particle AP are effective measures to increase the burning rates of the propellant. Simultaneously, decreasing the particle size of HMX can reduce its burning rate and pressure exponent. PbCO3 synthesized by ourselves can reduce the pressure exponent more than the bought one.

117. Combustion Property of NEPE Propellant, Liu Yun-fei, Yao Wei-shang, Li Xiao-meng, Tan Hui-min, [School of Chemical Engineering & Materials Science, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2003, 26 (4], 30-32

Abstract: The effect of B12H12[N(C2H5)4]2 (YL 6) on combustion property of NEPE solid propellant was studied. The compatibility of YL 6 and nitrate ester, the effect of YL 6 on the curing reaction and on the thermal decomposition behavior of ammonium per chlorate and nitroamino compounds were studied by Differential Scanning Calorimetry (DSC). It was observed that YL 6 exhibited not so good compatibility with nitrate ester which accelerated the thermal decomposition of nitroamino compounds but had little effect on ammonium per chlorate and on the curing reaction. When YL 6 was applied to NEPE solid propellant, the burning rate of propellant increased comparing to plumbean citrate as burning rate catalyst and the pressure exponent was effectively brought down to 0.13 in high pressure which was called platform phenomenon.

118. Preparation by Explosion Method and the Interference Function of Expanded Graphite, Qiao Xiao jing, Zhang Tong lai, Ren Hui, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2003, 26 (1): 70-73

Abstract: Potassium chlorate and potassium per chlorate are selected as oxidant in pyrotechnic compounds. When the pyrotechnic compounds were ignited, the transition from combustion to explosion would occur under a suitable ignition train, and the expanded graphite was produced and dispersed in air to realize the interference function. It was effective to avoid oxidation of the expanded graphite and to increase the yield of available component for interference by adjusting oxygen balance.

119. Adjustment on the Combustion Performance of Low Flame Temperature and Low Burning Rate Double Base Propellant, Qin Neng, Wang Ningfei, [Northwestern Polytechnic University, Xi'an 710072, China], Wang Liang, [Xi'an Modern Chemical Research Institute, Xi'an 710065, China], Chinese Journal of Energetic Materials, 2010, 18 (1): 110-114

Abstract: To adjust the combustion performances of low flame temperature and low burning rate propellants, some catalysts, such as lead salts, copper salts, carbon black and assistant plasticizer were appended into four low burning rate formulations, whose theoretical flame temperature ranged from 900K to 1700 K, and the function of the catalysts and their additive amount were tested. The results show that those usual catalysts can also work upon low flame temperature and low burning rate DB propellants. The variety of catalysts has different effects on burning rate and pressure exponent, and the combined catalysts can improve the combustion performance obviously. Besides, assistant plasticizer can also affect the combustion performance

120. Study on Clear-Burning Gun Propellant, Wang Qiong-lin, Liu Shao-wu, Tang Hui-min, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2003, 26 (4): 5-7

Abstract: Deterred-propellant often results in muzzle smoke. A new kind of clear-burning double base gun propellant contain polymer deterrent and new stabilizer is introduced. The propellant has low muzzle smoke, low maximum pressure, high muzzle velocity, low temperature sensitivity and excellent safe life. This improvement in interior ballistic performance is achieved by a combination of high oxygen-containing and diffusion-stable deterrent, slightly increased energy content and very progressive burning behavior.

121. Effect of Restraint Conditions on Shock Pressure of Booster, Wang Zuo shan, Liu Yu cun, Zhang Jing lin, Zhang Bao min, [North China Institute, Taiyuan, 030051, China], Chinese Journal of Explosives & Propellants, 2003, 26 (2): 10-12

Abstract: The shock pressure of booster HMX/F2641 with smaller charge diameter was determined under three sorts of restraint conditions through manganin manometric method, and the test results were discussed according to shock kinetics. The practical density of explosive samples used in the experiment was 90% of the theory density value. The effect of restraint condition on shock pressure under smaller charge diameter tends to increase following the increasing of impedance, but with less amplitude variation for charge diameter between 3.0 mm and 5.0 mm and wider amplitude variation for 1.5 mm charge diameter.

122. Surface Treatment of PETN via Decreasing Static Electricity, Yu Xian-han, [Gansu Yinguang Chemistry Corporation, Baiyin 730900, China], Chinese Journal of Explosives & Propellants, 2003, 26 (4): 55-56

Abstract: The surface treatment method of PETN by means of a surfactant is introduced. The testing and analyzing were carried out for the surfactant decreasing static electricity of PETN. The type and concentration of the statu-proof surfactant were optimized. The results show that static electricity of PETN is greatly decreased after it was treated with this surfactant. Thus, it benefits the production process and quality of detonating cord.

123. The Design of Propellant Charge of an Ejection Cartridge, Zhang Tianfei, [Beijing Institute of Technology, Beijing 100081, China], Li Jitian, Ma Jingui, [China Aviation Life Support Research Institute, Xiangfan 441003, China], Chinese Journal of Explosives & Propellants, 2003, 26 ( 3): 5-8

Abstract: In this paper, the ultimate characteristic parameters and ballistic performance of an ejection cartridge are calculated by analyzing its action and operational requirements. The selection principle of the propellant is presented. Through ballistic calculation and analysis, the charge configuration is preliminarily fixed and verified by tests. These efforts lay a good foundation for the cartridge design and its production.

124. Combustion Characteristics of Smokeless XLDB Propellant at Low and High Pressure, Zhang Wei, Chen Jin-nan, Fan Hong-jie, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2003, 26 (4): 27-29, 50

Abstract: The combustion characteristics of smokeless XLDB propellant at different pressure were studied in detail by analysis of flame structure, combustion waves and SEM. It was showed that the model of combustion process of smokeless XLDB propellant is transferred from that of double-based propellant type to composite propellant type.

125. Energetic Lead or Copper Salts of Hydroxypyridines as Combustion Catalysts of RDX-CMDB Propellant, Zhao Feng-qi, Chen Pei, Luo Yang, Zhang Ru-ie, Li Shang-wen, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2003, 26 (3], 1-4

Abstract: The effect of six kinds of energetic lead or copper salts of hydroxypyridines on the combustion properties of RDX-CMDB propellant was investigated. It is discovered that the lead salts of hydroxypyridines containing nitro groups possess better catalytic effect and ability to reduce pressure exponent for the propellant, especially for lead salt of 2-hydroxy-3, 5-dinitropyridine, which has the highest catalytic efficiency. The catalysis of the energetic copper salts of hydroxypyridines in the propellant is not obvious. The catalysis difference between lead salt 2-hydroxy-3, 5-dinitropyridine and 4-hydroxy-3, 5-dinitropyridine is due to their different thermal decomposition mechanism and different carbon content formed in the decomposition process.

126. Formula Design of Infrared Smoke Composition Based on Uniform Design Method, Zhou Zun Ning, Pan Gong Pei, Li Yi, Guan Hu, [Nanjing University of Science & Technology, Nanjing, 210094], Chinese Journal of Explosives & Propellants, 2003, 26 (2): 76-79

Abstract: Uniform design method which can reduce experiment quantity is used in the formula design of infrared smoke composition. The attenuation rate of the optimal formula in 8 - 14μm bands is bands are 96.6%. The qualitative relationship between composition ingredients and attenuation rate is also obtained by regression of the experimental results. The uniform design method proved a fast and efficient way to investigate infrared smoke composition.

127. Effect of Particle Gradation of HMX on the Compressibility of a Typical Booster Explosive, Chai Tao, Zhang Jing Lin, [North China Institute of Technology, Taiyuan 030051, China], Chinese Journal of Explosives & Propellants, 2002, 25 (4)

Abstract: Explosive HMX of two different particle sizes of 1 - 2μm and 20 - 30μm is prepared by spraying ultrafine method. The effect of the ratio of the two samples on the compressibility of typical booster explosive is studied. The relation between the ratio and formability is analyzed in theory.

128. Critical Pressure of Smokeless Propellant, Chen Guang xing, Qiang Jie bing, Yu Hong Jian, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2002, 25 (2): 52-53

Abstract: Critical pressure concept of solid propellant was introduced. The condition of maintaining RDX CMDB propellant steady burning, studies of lowering critical pressure of RDX CMDB propellant and relative experiment was discussed.

129. Calculation of the Combustion Characteristics for MTV Pyrotechnics, Chen Ming Hua, Jiao Qing Jie, Wen Yu Quan, [Beijing institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2002, 25 (3): 75-78

Abstract: The combustion temperature and reaction heat of the MT and MTV pyrotechnics are calculated theoretically. The ratio of magnesium and Teflon is obtained when the highest temperature and reaction heat are produced. The amount of separated carbon and magnesium di-fluoride after combustion is calculated and analyzed.

130. Ignition Agents Suitable for Nitramine Propellants, Du Cheng zhong, Li Li, Li Xian, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2002, 25 (3): 69-72

Abstract: The different ignition agent formulas were composed with the usual ignition materials such as NC, NH4ClO4, BP and so on, and their ignition capabilities igniting nitramine propellants were examined. The new type of ignition agent formulas which could improve nitramine propellant ignition properties were obtained though the ignition simulated tests comparing with the single base propellants. The ignition delay time of nitramine propellants ignited by ignition agent E containing NC 23.1%, BP 38.5%, NH4ClO4 38.5% at -40 is similar to the single base propellants.

131. Deflagration to Detonation Transition Behavior of Explosive JOB-9003, Huang Yi Min, Feng Chang Gen, Long Xin Ping, [Department of Engineering Safety, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2002, 25 (1): 54-56

Abstract: The experiments of the deflagration to detonation transition of granular HMX and JOB 9003 explosives were carried out. The effects of the composition, density and confinement of explosives on the DDT process were studied. The principles of explosives DDT were analyzed. The experimental results illustrate the compositions and the charge conditions of explosives have influences on DDT behavior. The granular HMX explosives are easy to happen to DDT, but the pressed JOB 9003 explosives composed by HMX chiefly are not.

132. Progress In Investigation of condensed Explosives Initiated by Low Amplitude Shock (XDT), Ke Jia Shan, Chen Lang, Feng Chang Gen, [School of Mechanic Electronics Engineering, Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2002, 25 (2): 35-38

Abstract: This paper presents the XDT events of condensed explosive by low amplitude shock, and recommends the methods of experiments and numerical simulation for the XDT investigations .The developing trend for XDT investigation is forecasted.

133. Study on Curing Catalysis of Combustion Catalyst for EMCDB Propellant, Liu Chun, Li Xiao-jiang, Cai Bing-yuan, An Fang-ya, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2002, 25 (2): 42-44

Abstract: The experiment, applied to study the curing catalysis of combustion catalysis for polyurethane EMCDB propellant, was designed, the catalytic activity of eight Pb salts and four Cu salts was compared, the Pb salts and Cu-salts, which could be used as combustion catalyst ingredient of EMCDB propellant, were selected. Experimental results showed that some Pb salts had stronger catalytic activity to the cross linking reaction, almost all Cu salts and carbon black had no catalytic activity, only these Pb salts, which had weaker catalytic activity, could be used as the combustion catalyst ingredient of EMCDB propellant.

134. Mechanism Analysis of the Influence of Al Shape and Size on the Detonation Properties of Aluminized Explosives, Miao Qin Shu, Xu Geng Guang, Wang Ting Zeng, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2002, 25 (2): 4-5, 8

Abstract: The mechanism of the influence of the shape and particle size of aluminum on the detonation properties of aluminized explosives is explained by means of the secondary reaction theory and the heat dilution theory. It is indicated that the fundamental factor is the specific surface area changed with different shape and particle size of aluminum. It has also been pointed out that changing the particle size of aluminum is a good way to optimize the properties of aluminized explosives.

135. The Closed Vessel Study of Low Temperature Nitroamine Propellant Combustion Properties, Shi Xian-yang, Wang Ze-shan, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2002, 25 (3): 61-63

Abstract: The combustion properties of low temperature sensitivity coated (LTSC) nitroamine propellant had been studied using granule powder as concussion gas source in closed vessel. The burning properties of coated nitroamine propellant at different temperatures and with different coated layer thickness are compared. This is one of the basic tests for inspecting the LTSC effect of coated propellant.

136. Experimental Study on Ignition and Flame Spreading of Modular Charge, Yu Bin, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2002, 25 (4): 69-70

Abstract: This thesis presents experimental studies and theory analysis technology of ignition and flame spreading, as well as interior ballistic cycle in the gun with modular charges. The ignition and its flame spreading test system of the modular charges in the natural environment is built up, a number of ignition and its propagation methods are simulated, the characteristic parameters of the system in the natural environment are obtained.

137. Research in Solid Fuel-Rich Propellant, Zhang Wei, Zhu Hui, Fang Ding you, [National University of Defense Technology, Changsha 410073, China], Chinese Journal of Explosives & Propellants, 2002, 25 (1): 25-29

Abstract: It was reviewed that the development in solid fuel rich propellant abroad and mainland. The composition, combustion characteristics and its modification of the various fuel rich propellants, the hydrocarbon propellant, the magnesium propellant and the boron propellant, were demonstrated.

138. Study of Combustion Property of HNIW Monopropellant, An Hong Mei, Liu Yun fei, Li Xiao Meng, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2001, 24 (1): 32,36-37

Abstract: The combustion property of HNIW monopropellant was studied by adding some additives. The results of experiments indicate that the decomposition products of HNIW affected the burning behaviors of HNIW monopropellant. The burning rate of HNIW monopropellant is decreased through adding the products of decomposition of HNIW. The used catalysts in the experiment have catalyzed the combustion property of HNIW monopropellant.

139. Experimental Investigation of Propagation Properties of Blast Waves in Air and in Semi-rigid Polyurethane Foam, Chen Wang-hua, Feng Wei, Peng Jin-hua, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (4): 41-42, 45

Abstract: The reflected overpressure distribution of blast wave of No.8 detonator with paper shell was measured in semi-rigid polyurethane foam (SRPUF], and the incident overpressure distribution of the detonator in air was also tested in this paper. By the symposium of ideal-gas-state-equation, the reflected overpressures in air were calculated. The contrast and the analysis on the two reflected over pressure distribution were carried out. The propagation properties of the blast waves in the two media were discussed qualitatively, and the gap and cushioning property of SRPUF material was analyzed as well.

140. Study of Plasma Ignition Single Propellant, Dai Rong, Li Bao-ming, Zhang Jian-qi, [Ballistic Lab, Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (1): 60-61

Abstract: In the solid propellant electro thermal chemical (SPETC) propulsion concept, it has been proved that plasma can be successfully used to optimize and control the propellant ignition process. The ignition properties of types of single propellants in plasma source are analyzed in the paper. The characteristic of propellants ignition in deferent plasma power is obtained and the work provide experiment evident for the study of plasma interior ballistic ignition.

141. Study on Low Burning Rate NEPE Propellant, Li Xiao Meng, Liu Yun Fei, Yao Wei Shang, Tan Hui Min, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2001, 24 (3): 1-3, 9

Abstract: A low burning rate NEPE propellant were investigated by means of adding some burning rate inhibitors and adjusting its composition. The compatibility of additives with nitrite ester, combustion properties of the propellant and the standard specific pulse of Φ40 rocket motor were measured. It was observed that the burning rate of the propellant could be depressed by bigger particle diameter AP, low ratio of NG/DEGDN, less AP content and presence of burning rate inhibitors. The burning rate under 4.0MPa could be 4.7mm/s, and standard specific pulse was 2239.3N•s/kg without additives.

142. Calculation of Smoke Transmission Based on First Order Multiple Scattering Approximation, Li Yi, Pan Gong Pei, Wang Xue, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (2): 34, 39-41

Abstract: The radioactive transport equation of smoke extinction is solved by the method of first order multiple scattering approximation. The result which is more accurate than Lambert Beer law is used to simulate an infrared smoke transmission test.

143. Study on the Combustion Properties of XLDB Propellant, Lu Dian-lin, Fan Xue-zhong, Sun Yu-kun, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2001, 24 (4], 50-51

Abstract: The effects of all factors, such as different types of catalyst, RDX, NG etc., o n the combustion properties of XLDB propellant were thoroughly studied. The specific impulse of the propellant determined by Φ64mm motor is also reported. It w as found that the effects of these factors on the combustion properties of XLDB propellant is obvious.

144. Research on Lowering the Flame Temperature of Aerosol Generating Agent Using Additives, Qiao Hai-tao, Yang Rong-jie, Li Xiao-dong, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2001, 24 (2): 42-43, 47

Abstract: The influence of two kinds of additives on the flame temperature of EBM extinguishing agent has been studied. The flame temperature can be obviously lowered by the additives. It is found that the combination of two kinds of additives is more effective for lowering the flame temperature of the aerosol generating agent.

145. Study on the Design Method of Grain Binding High Burning Rate Propellant, Sha Heng, Li Feng-sheng, Song Hong-chang, Chen Su-lin, [China North Chemical Industrial Corporation, Beijing 100089, China and Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (4): 4-7

Abstract: The processing technique of grain binding high burning rate propellant (GBHRP) was introduced. The burning rates of both small grainy propellants and fast burning binders were calculated by means of the burning rate-calculated characteristic chemical group method of propellant. The burning rate-designed method of grain binding high burning rate propellant was proposed.

146. Parameters Design of the Barrel of a Small Flyer Initiating System, Tan Ying-xin, Zhang Jing-lin, Wang Gui-ji, Zhang Xiao-chun, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2001, 24 (3], 51-52, 55

Abstract: The barrel is an important factor affected on the flyer initiating system. The functions of a barrel of a small flyer initiating system are analyzed. The key parameters of the barrel such as the material, length and diameter are determined. The effect of small flyer initiating system can be ensured.

147. Research on Smog Test & Characterizing Technique of Inhibitor, Wang Hong, Wang Ji Gui, Wang Lin Mei, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China ], Chinese Journal of Explosives & Propellants, 2001, 24 (3): 60-61

Abstract: The text introduces the feature property of smog, discusses the theory essence of the light decrease caused by smog, and then discusses methods of test character of the inhibitor smog. Factors, which affect the smog amount, are pointed out, and the solution to the inhibitor smog is given.

148. Effect of Azide Nitrate Ester on Combustion Behavior of Nitramine Modified Double Base Propellant, Wang Jin, Li Shu Fen, [University of Science and Technology of China, Hefei 230026, China], Chinese Journal of Explosives & Propellants, 2001, 24 (2): 22-24, 31

Abstract: The influence of azide nitrate ester PDADN [1, 3 propanediol, 2, 2 bis(azidomethyl], dinitrate (ester) ] on combustion property of nitramine modified double base propellant has been studied. The results show that PDADN can increase burning rate and energy of nitramine modified double base propellant.

149. The Testing Device of Cartridge’s Primer and Testing Method, Wang Lai-fen, Wan Xue-ren, Yi Fang, [The PLA 95856th unit, Nanjing, 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (4): 52-53

Abstract: The testing device for testing the performance of cartridge's primer was designed. The performance of press-loading small primer could be measured, and the small primer's is fixed ammunition. The results of testing and analysis show that t he performance of cartridge's primer vary regularly with stored time, and the changes make an obvious effect on the interior ballistic performance. A new way is suggested for the study of reliability on the stored ammunition and the analysis of accident.

150. Experimental Study on Reducing the Pressure Wave of Gun Propelling Charge with High Loading Density, Xiao Zheng-gang, Yang Dong, Ying San-jiu, Shi Jie, Gao Yao-lin, Xu Fu-ming, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (1): 7-10

Abstract: Two ignition methods are investigated to reduce pressure wave in large caliber gun propelling charge with high loading density. The first is adding crosswise igniter and upper ignition bag on the base of standard igniter, the second is using the low velocity detonation igniter instead of the standard igniter, at the same time adding the crosswise igniter. The firing test results of propelling charge with high loading density show that both of the two methods could meet the request of ignition. Comparing with the standard igniter, the first ignition method could ignite the charge simultaneously and entirely, but the pressure wave phenomena in barrel are serious. The flame spreading velocity of the second ignition method is faster than of the first ignition method, and the ignition pressure could be established quickly, the ignition delay time of propelling charge is short. First of all, the pressure wave can be restrained. The frequency spectral analyses show that the second ignition method could weaken and restrain the high frequency vibration, improve the characteristic of vibration in high loading density charge.

151. The Experimental Studies of the Augmentation Combustion of Propellants with Plasmas, Xie Yu-shu, Yuan Ya-xiong, Zhang Xiao-bing, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (3): 10-12

Abstract: Plasmas can alter ballistics process through control and augmentation combustion of the propellants in ETC technology, To date, the mechanisms have not been certain how plasma could modify the propellant gas generation. Many scholars have tried to explain the plasma propellant interaction mechanisms by a series of test. This paper mainly introduced the experimental studies on burn rates of the propellant with plasma abroad, including experimental equipments, methods and results.

152. A New Method to Improve the Burning Performance of Oblate Spherical Propellant, Xong Li-bin, Ying San-jiu, Luo Fu-sheng, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (4): 10-11

Abstract: A method to improve the burning performances of single-base oblate spherical powder is developed. Tests show that adding fine KNO3 grains and deterrent to propellant powder can improve its inner burning area and affect its burning rate efficiently. Thus a kind of progressing burning single-base oblate spherical is available.

153. Study on the Temperature Determination Technique for Ignition and Combustion of Propellants, Yu Bin, Du Cheng-zhong, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2001, 24 (2): 28-31

Abstract: The experiments for temperature of ignition and combustion of two propellants were done by six channel instantaneous optical pyrometer, the temperatures of ignition and combustion of two propellants were determined at different pressure and the results of experiments were analyzed, which may be used to the further studies for temperature of ignition and combustion of propellants.

154. Experimental Research on the Ignition Process of Energetic Droplet, Yu Yong-gang, Jin Zhi-ming, Liu Feng, Wu Dong-lou, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2001, 24 (2): 35-36

Abstract: Optical computerized tomography and multimedia technique of computer were used to visualize and analyze the ignition process of energetic droplet LP1846 under atmospheric pressure. Time series interference graphs of the droplet from heat decomposition to combustion were showed dynamically. The ignition temperature of the droplet was also calculated. Experimental results show that the ignition and combustion properties of the energetic droplet can be studied with optical computerized tomography.

155. Research of Laser Ignited Device in Solid Rocket Motor, Zhang Qiu-fang, Huang Qiang, Liang Yue-mei, [The 41st Institute of the Fourth Academy of CASC, Xi'an 710025, China], Chinese Journal of Explosives & Propellants, 2001, 24 (1): 13-16

Abstract: The components, working principle and test results of the laser ignited device are stated, its main properties are also discussed.

156. Study on Catalytic Combustion of HNIW Monopropellant by Metal Oxide, An Hong-mei, Liu Yun-fei, Li Yu-ping, Yang Rong-jie, Tan Hui-min, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2000, 23 (4): 1-2

Abstract: The catalytic combustion of Hexanitrohexazaisowurtzitane was studied in this paper. The result of experiments indicates that the burning rate of HNIW monopropellant is about two times of that of HMX monopropellant. The burning rate of HNIW monopropellant increases with pressure increasing. The pressure exponent of burning rate is 0.846. The burning rate of HNIW monopropellant can be changed through adding metal oxide but the pressure exponent of burning rate is not changed by metal oxide.

157. Experimental Studies on Ignition of Black Powder and Single Base Powder by an Electrically Heated Wire, Du Zhi-ming, Feng Chang-gen, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2000, 23 (2): 8-10

Abstract: Thermal ignition of black powder and single base powder by an electrically heated wire was experimentally studied. Critical ignition current through the wire and time-to-ignition was measured. Temperatures of the wire when ignition of powders occurred were calculated.

158. The Advancement and Development of Self-Sensitization Theory for Expanded Ammonium Nitrate, Lu Chun xu, Liu Zu laing, Hui Jun min, [Nanjing University of Science and Technology, Nanjing 210094, China], Chinese Journal of Explosives & Propellants, 2000, 23 (4): 2-5

Abstract: The surfactant (expanding agent) plays a decisive part in compulsory crystallization for saturated solution of Ammonium Nitrate (AN). It is the guarantee of expanding technology and basis of self sensitization theory. Expanded A possesses cap sensitivity in definite conditions which is macroscopic behavior for success of self sensitization.

159. Study on AP/DHG/CTPB Gas Generating Propellant, Liu Yun-fei, Liu Ji-hua, Luo Bing-he, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 2000, 23 (3): 12-14

Abstract: The formula and properties of composite gas generating propellant AP/DHG/CTPB were investigated. The burning property of the composite gas generating propellant was determined. The mechanism of the burning rate reduction of dihydroxyglyoxime (DHG) was analyzed.

160. Study on Combustion Mechanism of NEPE Propellant, Wang Ying, Sun Zhi Hua, Zhao Feng Qi, Li Shang Wen, Yuan Chao, [Xi’an Modem Chemistry Research Institute, Xi’an 710065, China], Chinese Journal of Explosives & Propellants, 2000, 23 (4): 22-24

Abstract: The combustion wave temperature profiles and the flame structures of NEPE propellant samples are measured by using W Re micro thermal couple and flame photo technique. The influence of major component of propellant (such as HMX, AP, Al) on the combustion properties is researched; meanwhile the surface appearance and element distribution of extinguished samples are analyzed by JMS 5800 SEM. The combustion process of NEPE propellant is suggested by synthetic analysis.

161. Study on Suppression of Flame and Temperature of Aerosol Generating Agent by Potassium Organo-Carboxylate, Yang Rong-jie, Qiao Hai-tao, [School of Chemical Engineering and Materials Science, Beijing Institute of Technology, 100081, China], Chinese Journal of Explosives & Propellants, 2000, 23 (3): 43-45
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Abstract: Effects of suppressing flame and temperature of a kind of pyrotechnic aerosol generating agent EBM extinguishing by potassium organo carboxylate have been studied. Results of modification by different additive agents at different contents are compared and analyzed.

162. Experimental Study on Ignition Property of Solid Energetic Material by Laser, Zhang Xiao-bin, Yuan Ya-xiong, Yu Bin, Weng Chun-sheng, [Nanjing University of Science and Technology, Nanjing, 210094, China], Chinese Journal of Explosives & Propellants, 2000, 23 (2): 35-37

Abstract: The experiment about ignition property of solid energetic materials was done by laser which was generated by big powerful laser instrument -ND: YAG. The influence on the ignition property, such as, difference energy, pulse width, different frequency of laser instrument, and different webs of the propellant was studied and analyzed which may be used to do further researches for ignition.

163. Study on Burning Rate Regulating by Combustion Stabilizer, Zhang Xiao-hong, Zhang Rei-er, Wang Bai-cheng, [Xi'an Modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 2000, 23 (3): 26-28

Abstract: On the basis of the research of different combustion stabilizers and common stabilizer Al2O3 on the burning rate, further research has been carried out on the possibility using different size of those stabilizers to regulate the burning rate of the propellant.

164. Combustion Properties of Insensitive Nitrocellulose Based Propellant Containing Potassium Compounds as Flash Suppressors, Zhao Feng-qi, Chen Pei, Yang Dong, Li Shang-wen, [Xi’an Modern Chemistry Research Institute, Xi’an 710065, China], Chinese Journal of Explosives & Propellants, 2000, 23 (1): 10-13

Abstract: The combustion properties of insensitive nitrocellulose based propellant containing potassium compounds as flash suppressors investigated in this paper. The results indicate that the addition of K3AlF6 badly destroys the plateau burning effect of insensitive propellant, while flash suppressor KD almost do not destroys the platonisation. The burning rates and the plateau range of the propellant containing KD can be adjusted by means of the change of composite catalysts. After 1, 2, 4 butanetriol trinitrate (BTTN) is substituted for trimethylolethane trinitrate (TMETN], the burning rates of the propellant increases apparently and the plateau effect is maintained. Nitroguanidine (NGu) enables the propellant to appear burning rate jump between 8 and 9 MPa and to produce plateau burning effect under higher pressure.

165. Study on the Traveling Charge Technique with Steady Deflagration, Tan Hui-min, Luo Yun-jun, Duo Ying-quan, [Beijing Institute of Technology, Beijing 100081, China], Chinese Journal of Explosives & Propellants, 1999, 22 (4): 30-38

Abstract: In this paper, the steady deflagration process was dealt with; the new concept which uses the steady deflagration as propelling energy source of traveling charge was presented. The classical inter ballistics model of steady deflagration traveling charge was established and solvated by the corresponding program made in this paper. The calculated results showed that the deflagration traveling charge could increase the initial velocity of projectile remarkably. It's a great future gun propulsion technique.

166. Detonation Wave Emissivity and Detonation Temperature Measurements by Imaginary Auxiliary Source Reflection Method, Yuan Bao-hui, Yuan Tian-you, Zhu Ming-wu, [Xi'an Modern Chemistry Research Institute, Xi'an 710065,China], Chinese Journal of Explosives & Propellants, 1999,18 (2): 28-31

Abstract: Based on optic principle, the method of detonation wave emissivity and detonation temperature measurement by imaginary auxiliary source reflection is described. The method overcomes the difficult that the above two parameters can′t be simultaneously measured by single or two color optic pyrometers. By this method, the detonation wave emissivity and detonation temperature of liquid explosive NM are measured, and the results are in agreement with the reference reports

167. Assignable the Regulation for the Use of Firing Energy for Combustibility Primer and Application in the Countersunk Case-less Cartridge, Zhang Yi le, [Xi'an modern Chemistry Research Institute, Xi'an 710065, China], Chinese Journal of Explosives & Propellants, 1999, 22 (3): 32-35

Abstract: In the countersunk case-less cartridge, the burning at ignition allied to the matching of charge configuration. By studying, gross firing energy of combustibility primer has an assignable the regularity was sought. According to this assignable regulation for the use of firing energy, the internal ballistic performance of case-less cartridge can be improved by adjusting weight of combustibility primer or addition ignition composition.

168. Study on Effect of Different Processing Conditions on Combustion Performance of Casting-CMDB Propellants, Chen Xue-li, Liu Xiao-gang, Yu Hong-jian, [Xi’an Modern Chemistry Research Institute, Xi’an 710065], Chinese Journal of Explosives & Propellants, 1999, 3 (1)

Abstract: Effects of different processing conditions on the combustion characteristics of casting CMDB propellants were studied in this paper. Such processing conditions include ways of treating and adding of the catalyst, the pre-dry and kneading time, the curing time and temperature etc. The results show that processing conditions have great effects on the burning rate and pressure exponent of casting CMDB propellants.

169. Review and Prediction of Improving the Ignition and Combustion Performances of Boron Particulates, Guan Dalin Wang Ningfei, [Xi’an Modern Chemistry Research Institute, Xi’an 710065], Chinese Journal of Explosives & Propellants, 1998, 16 (2)

Abstract: The generalization, summation, comparison and analysis were made about the study to improve the ignition and combustion performances of boron. The prediction and suggestion about this field were present in this paper.

170. The Effect of Size Grading of NC Powder on the Combustion Characteristics of RDX CMDB Propellant, Guan Da-lin, Liu Xiao-gang, Chen Xue-li, Zhang Shuang-jian, [Xi'an Modern Chemistry Research Institute, Xi'an 710065], Chinese Journal of Explosives & Propellants, 1998 (4)

Abstract: Using size grading of NC powder, the burning rate at the pressure range of 7 – 15MPa can be raised; therefore it is useful to lower the pressure exponent of burning rate of RDX CMDB propellant.

171. An Investigation of High Speed Ignition under the Pressure Gradient of Steepest Descent, Hao Jian-chun, [Nanjing University of Science and Technology, Nanjing 210094], Chinese Journal of Explosives & Propellants, 1998, 5 (1)

Abstract: In this paper, the pyrothechnic composition Mg•Al Ba(x)n 308A is proposed as a ignition charge of composition base bleed agent. Test results indicate that goal of high speed ignition can be attained under the pressure gradient of steepest descent.

172. Testing Study in Effect of ESD to Fire Time Reliability of 105 Electric Fire Cap, Xu Yi-gen, Liu Shang-he, Wei Guang-hui, [Hefei Military Deputy Department, Hefei 230041, China], Chinese Journal of Explosives & Propellants. 1997 (2)

Abstract: Fire time of all random sample 105 electric fire caps respectively stimulated or non stimulated by ESD and stored or non stored is tested, and all contents fire technical requirement. Normality tests show that fire time of 105 Electric fire caps is distributed log normally; its fire time reliabilities are respectively computed.

173. Study on Combustion Characteristics of Magnesium/Aluminum Fuel-Rich Propellants, Zhang Wei, Zhu Hui, Fang Ding-you, Zhang Wei-hua, Wan Zhang-ji, [National University of Defense Technology, Changsha 410073], Chinese Journal of Explosives & Propellants, 2002, 8 (1)

Abstract: It was studied systematically in this paper that the combustion characteristics of magnesium/aluminum fuel rich propellant. Then the fuel rich propellant composition was optimized. The experimental results showed that the contents of the AP and the magnesium in the metal additives have the most effective action on the combustion characteristics of the propellants. The greater the contents of AP and magnesium are the higher burning rates of the propellant and the broader flammability limit. On the other hand the flammability limit of the propellant can be modified by means of increasing its burning rate, adding super fine metal of burning rate modifier.

174. Application Study on Surface Active Agent in Determination of Azide Ion in Wastewater by UV Spectrophotometric Method, Chen Jie, Song Qize, [Nanjing University of Science and Technology, 210094, China], Chinese Journal of Explosives & Propellants, 1997, 13 (1)

Abstract: This paper presents the application in surface active agent in determination of azide ion in wastewater from sodium azide workshop of primary explosive plant by UV spectrophotometric method. The reactant CS2N3 from N3 with CS2 is measured to get a good absorption peak, on which the molar absorptive ε max at the maximum absorption wave length is 10 3 order of magnitude only. To increase determinative sensibility, the surface active agent cetyl pyridinium chloride (CPC) is chosen as hyperchromic agent through experiments. The analytic results show that the ε max value is about four times bigger than that of the original one and the determinative wave length shifts about 10nm to long wave direction as CPC is put into determined system. Additionally, the anti interference ability of the system goes up too.

175. A Study on Prevention of Accidental Explosion for Industrial Electric Detonator, Hao Jian-chun, [Nanjing University of Science and Technology 210094, China], Chinese Journal of Explosives & Propellants, 1997 (1)

Abstract: There may exist accidental firing or explosion of industrial electric detonator during manufacture, storage or transportation and in the use. In order to prevent the accident and avoid the accompanying damage and losses, the various causes of the accident are analyzed and the corresponding preventive measures are suggested.