Abstract: To maximize the total impulse of aerospike nozzle engine, numerical computation method was adopted on the full travel contour optimization of aerospike nozzle The process of building optimization model including the assumptions and the steps of the contour optimization was presented in detail The typical results of contour optimum, which can be used for contour design of aerospike nozzle,were also shown

Key words: Rocket engine;Plug nozzle;Numerical calculation;Structure optimization

摘要： 为了使塞式喷管发动机的总冲最大 ,利用数值计算方法对塞式喷管型面进行了全飞行过程的优化。详细介绍了优化模型的建立过程及优化的假设与步骤 ,最后给出了典型优化的结果 ,其结果对塞式喷管的型面设计有很大的参考价值。

关键词: 火箭发动机;塞式喷管;数值计算;型面优化