Improvement of Combustion Heat Testing Equipment of Fuel-Rich Propellant Based on Boron
Referring to the combustion heat testing method of GJB 770A— 97, adopting oxygen bomb calorimeter models GR 3500, the problems in the combustion heat test of fuel-rich propellant based on boron were investigated. The temperature distributing trend was given by the method of numerical simulation. The results show that the combustion ablation of oxygen bomb parts and the sample’s un-fully combustion must be resolved in the combustion heat testing of fuel-rich propellant based on boron. Feasible experimental method was put forward in the paper, the results show: the oxygen bomb parts were not ablated by combusting and the ingredient in the propellant can be combusted completely in the improved oxygen bomb. The parallel error of the testing results is 1.992%.
combustion heat fuel-rich propellant ozygen bomb calorimeter
WANG Yinghong ZHANG Fangli SUN Zhihua CHEN Chao
College of Astronautics, Northwestern Polytechnic University, Xian 710072, Shaanxi, China Xian Modern Chemistry Research Institute, Xian 710065, Shaanxi, China
国际会议
2009 International Autumn Seminar on Propellants,Ezplosives and Pyrotechnics(2009国际推进剂、炸药、烟火技术秋季研讨会)
昆明
英文
1-4
2009-09-22（万方平台首次上网日期，不代表论文的发表时间）