Taking system optimization design of SRM as the example, physical programming of was proven to be efficient in modelling of decision-making uncertainty during the solid rocket motor design.
以固体火箭发动机总体方案优化设计为例，证明了物理规划方法作为固体火箭发动机设计决策不确定性建模方法的有效性。
The burst pressure of filament wound pressure vessels which is applied to solid rocket motor case and gas tank in industry is an important design parameter.
用于固体火箭发动机壳体和工业贮罐的纤维缠绕压力容器，爆破压强是重要的设计参数。
Good references for solid rocket motor nozzle design and research are provided.
可为固体火箭发动机喷管的设计与研究提供有效参考。
Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis.
通过热和结构计算，对固体火箭发动机喷管缝隙设计进行了分析。
According to the thermal shielding model of solid rocket motor, an approach of ablation heat shield design of end-burning grain with embedded wire was put forward in this paper.
根据固体火箭发动机绝热防护模型，提出了一种嵌金属丝端燃装药绝热层设计方法。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
Rubber product used in solid rocket motor is an important part of missile system. The storage time for reliable work is one of important parameters in finalizing the design of solid rocket motor.
固体火箭发动机用橡胶制品是导弹系统的重要零件，其可靠工作的期限和贮存期是固体火箭发动机定型的重要依据之一。
Angular stiffness and elastomer shear strain on maximum swinging Angle are important indexes in flexible joint design of solid rocket motor.
角刚度(又称弹性比力矩)及弹性件在最大摆角下的剪切应变是固体发动机柔性接头设计的重要指标。
Angular stiffness and elastomer shear strain on maximum swinging Angle are important indexes in flexible joint design of solid rocket motor.
角刚度(又称弹性比力矩)及弹性件在最大摆角下的剪切应变是固体发动机柔性接头设计的重要指标。
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