研究结果对该类推进剂配方设计和工艺参量选择提供了必要的实验依据。
The test results provide experimental basis for formula design and technological parameter selection of NEPE propellant.
这证明固体推进剂能量特性的优化设计是成功的，为固体推进剂配方设计提供了一种有效的计算方法。
The numerical results obtained agree fairly well with the results obtained by graphical method for determining the optimum composition of solid propel…
结果表明均匀设计在推进剂配方优化中的应用是可行的。
Results indicate it is practicable to apply even design method to select optimum formula for propellant.
贫氧推进剂燃速是固体火箭冲压发动机设计和性能分析的重要参数，也是对推进剂配方进行检验验收的主要指标。
The burning rate of the fuel-rich propellants is the parameter which is important for Ducted Rocket design and performance analysis and is main inspection criterions of propellant prescriptions.
膏体推进剂火焰温度测量对推进剂配方的研制及火箭发动机的设计具有重要意义。
The pasty propellant flame temperature measurement is very important to the propellant formula development and rocket motor design.
膏体推进剂火焰温度测量对推进剂配方的研制及火箭发动机的设计具有重要意义。
The pasty propellant flame temperature measurement is very important to the propellant formula development and rocket motor design.
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