固体火箭发动机设计是一项复杂的系统工程。
Solid rocket motor design is a complicated systems engineering.
此项设计技术对带反向喷管的固体火箭发动机设计具有参考作用。
This technique is available for the design of SRM with reverse nozzle.
以某大型固体火箭发动机设计为例，说明其在固体火箭发动机优化设计和参数敏感性分析中的应用。
Taking design of a large-size SRM for example, the application of this method in design optimization and parameter sensibility analysis was introduced.
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。
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。
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.
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