propellant effect

Thermal Decomposition Mechanism, Non-isothermal Reaction Kinetics of Bismuth Citrate and Its Catalytic Effect on Combustion of Double-base Propellant

柠檬酸铋的热分解机理、非等温反应动力学及其对双基推进剂燃烧的催化作用

Effect of Nitramine on Energy and Burning Rate of Low Burning Rate HTPB Propellant

硝胺对低燃速丁羟推进剂能量与燃速的影响

In order to study the effect of damage on the dangerous properties in the NEPE propellant, a series of experiments, including the damage production and observation and measurement, closed bomb test, have been performed.

为研究高能固体推进剂NEPE损伤对其燃烧性能的影响，建立了以大型落锤为加载手段，扫描显微镜、声速和密度测量为损伤观察和检测手段，密闭爆发器为研究推进剂燃烧规律的实验系统。

Energic level of NEPE solid propellant was analyzed, the effect regularity of ingredients different ratio and content on the propellant formulas standard theoretical specific impulse ( ISS) was studied.

借助电子计算机计算与分析了NEPE固体推进剂的能量水平，研究和比较了组分的含量与不同配比对推进剂配方标准理论比冲I（ss）~°值的规律性影响。

The effect of initial propellant temperature on rocket engine combustion stability for hypergolic propellant ( MMH/ NTO) is studied. A physics model for initial propellant temperature effecting evaporation rate has been developed in this paper.

对自燃推进剂（MMH/NTO）初始温度对火箭发动机燃烧稳定性的影响进行了研究，从推进剂初始温度对蒸发速率的影响规律出发，发展了初始温度大小影响蒸发速率的物理模型。

The helpful effect on propellant slosh effects was a secondary consideration.

推进剂晃动的有利性影响是一个次要的考虑因素.