降低硝酸铵的热分解温度，促进AN的热分解是解决硝酸铵推进剂点火和燃烧困难的途径之一。
One way to resolve ignition and combustion difficulties for AN-based propellant is to lower AN decomposition temperature, and to accelerate the thermal decomposition of AN.
在第一，我是持怀疑态度的想法无效点火的推进剂。
At first, I was skeptical of the idea of ineffective ignition of the propellant.
推进剂的燃烧特性及喷管堵盖打开压强对点火升压过程有较大影响。
Propellant property and nozzle closure opening pressure have an important effect on the ignition transient.
膏体推进剂的点火和燃烧特性是发动机设计的重要参数。
The ignition and combustion characteristics of pasty propellant are important parameters for the motor design.
计算结果比较理想，全部推进剂都被点燃，并且点火延迟时间减小了。
The results are better, which show that all portions of propellant are ignited, and the ignition delay is shortened.
建立了微型脉冲推力器点火启动模型，模型中考虑了两相流动和颗粒对推进剂表面的冲击传热。
Ignition start-up model of impulse micro-thruster is established, considering two phase flow and impact heat transfer of particle on the surface of propellant.
点火器生成的高温燃气通过对流方式向推进剂传热。
The hot gas produced by the igniter transfers heat to the propellant by convection.
假设点火器的产物只有高温燃气，并且高温燃气通过对流方式向推进剂传热。
It is supposed that the igniter produces hot gas only, and the hot gas transfers heat to the propellant by convection.
介绍了一种装有高能推进剂的发动机点火器的设计和试验，高能推进剂选用HTPB、HMX混合药剂。
This paper introduces the design and tests of a motor ignitor loaded with high energy propellant which is a mixture of HTPB and HMX.
理论分析着重研究了点火燃气与推进剂表面传热及推进剂内瞬态热传导规律。
Theoretical analysis emphasizes on heat transfer both inside propellant and between igniter exhaust and internal grain surface.
通过分析研究点火瞬态过程中推进剂内部急速热传导存在的非傅立叶效应，推导得到具有双曲性质的固体推进剂瞬态热传导方程。
After affirming the existence of non-Fourier effect, the hyperbolic equation suited for describing rapidity heat transfer process inside propellant is obtained.
通过分析研究点火瞬态过程中推进剂内部急速热传导存在的非傅立叶效应，推导得到具有双曲性质的固体推进剂瞬态热传导方程。
After affirming the existence of non-Fourier effect, the hyperbolic equation suited for describing rapidity heat transfer process inside propellant is obtained.
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