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.
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