Li Shang-wen , Zhao Feng-qi , Liu Suo-en , Liang Yu-min , Lü Jin-hai
Abstract:The effect of several combustion catalysts,such as energetic lead salt B,aromatic acid lead salt C,aromatic acid copper salt B,carbon black CB1 or CB4,on the combustion behavior of screw-compressed Al-RDX-CMDB propellants was investigated when they were used alone or as a combination of two or three of them. The experimental results show that both energetic lead salt B and nonenergetic aromatic acid lead salt C are able to increase the burning rate and decrease pressure exponent of the propellants when they are respectively used together with copper salt and carbon black.The catalytic activity of energetic lead B is higher than that of aromatic acid lead salt C.The reason is that the thermal decomposition product PbO of energetic lead salt B has a higher catalytic activity than the later's.
Shan Wen-gang , Liu Xiao-gang , Yu Hong-jan , Chen Xue-li , Lei Liang-fang
Abstract:It was studied the influence of kneading time, curing time, curing temperature and cessation angles on the burning rate, pressure exponent and mechanical properties of solid propellants consisting of NC granules, oxidizer and combustion stabilizer etc. The results show that the interface properties of mixed solid materials affect the infusion of NG into NC granules,which controls the burning rate and pressure exponent of propellants. The kneading time of RDX CMDB slurry affects the combustion and mechanical properties.The combustion and mechanical properties are improved by the increase of curing time at 70℃.
Chen Rong-sheng , Zheng Jian , Xiong Zhong-nian
Abstract:The formation process and characteristics of the networks of complicate chemical crosslinked PU elastomers were analyzed and discussed. A simplified model of the complicate network structure and the theoretical calculation method of Mc were proposed.
Song Hong-chang , Yang Dong , Chen Shu-lin , Li Shang-wen
Abstract:Based on the theory of solid propellant burning rate, a formula of burning rate pressure index is deduced and its chemical essence is emphatically analyzed and discussed from the points of the chemical structure of propellants and the featured reaction in combustion process, and the optimization principle of pressure index is given therefore.
Chen Shi-wu , Xu Zhi-hong , Li Kai-ba , Gu Qi-wei
Abstract:The properties of a new type of energetic polyether with side chains containing octa-fluoro pentyl groups are studied. The fluoro-carbonic polyethers are hydroxy-terminated poly (1,1,5-trihydrooctafluoropentylglycidyl ether) (FCPE-1) and its copolyether with tetrahydrofuran (FCPE-2) . The experimental results show that they have higher thermal stability and chemical stability than conventional hydrocarbonic polyethers (HCPE). Moreover, FCPE-1 has better stability property than FCPE-2. The cured polyurathane rubber and the high energy-density propellant of FCPE-2 possess both good mechanical property and excellent stability.
Liu Guo-quan , Zhao Zhen-di , Wang Tian-you , Peng Jin-feng
Abstract:A series of liquid propellant formulations containing different percentage of hydroxyammonium nitrate (HAN), triethanolamine nitrate (TEAN) and water were designed to determine their viscosity at different temperature. The variation rule of viscosity respect to the content of ingredients and temperature are obtained by means of regression and fitting the experimental viscosity with temperature for different formulations.
Zhao Feng-qi , Wang Xin-hua , Bao Guan-ling , Zhang Yan
Abstract:The effect of silica aerogel (SiO2) on the mechanical and bonding strength and ablativity of room temperature vulcanized (RTV) silicone rubber used for inhibiting of solid rocket propellants were investigated. The results show that SiO2 is an effective reinforce filler. With the increase of SiO2 content, the tensile strength of silicone rubber and the bonding strength of silicone rubber coated HMX-CMDB propellant or Al-RDX-CMDB propellant increase, but the ablation resistance of silicone rubber becreases.
Jiang Hui-ping , Shuai Hong-hai
Abstract:Based on analyzing the origin of infra red signature of solid propellant plume, the technical approaches to reduce the infra red signature are systematically reviewed,and some side effects on propellant properties resulted from these approaches are discussed.
Abstract:Different ways were tried to enhance the energy of double base propellant made by using screw extrusion,and the effect of engine structure and loading condition on specific impulse was studied as well.The experimental results show that the specific impulse can exceed 2354N·s/kg under the reasonal combination of some important factors such as proper propellant formulation,the engine stucture and loading condition.
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Editorial Board of Chinese Journal of Energetic Materials
Vol. , No.,
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