研究了低温推进剂液体火箭发动机供应管道系统充填过程的建模问题。
The priming process of feed lines of cryogenic propellant liquid rocket engines was studied.
以液氧加注控制系统为例，介绍液体运载火箭低温推进剂加注控制所采用的两级分布式系统。
The two level distributed control system for cryogenic propellant loading is introduced, taking the Lox loading control system for example.
AP比表面积的增大会导致推进剂初始分解温度、高低温热分解峰温和高低温下分解反应活化能的降低，但分解反应速度常数随AP比表面积的增大而增大。
The increase of AP specific surface area lead to decrease of initial decomposition temperature, decomposition peak temperature and decomposition activation energy, but reaction rate constant rise.
AP比表面积的增大会导致推进剂初始分解温度、高低温热分解峰温和高低温下分解反应活化能的降低，但分解反应速度常数随AP比表面积的增大而增大。
The increase of AP specific surface area lead to decrease of initial decomposition temperature, decomposition peak temperature and decomposition activation energy, but reaction rate constant rise.
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