关键词: 火箭发动机;塞式喷管;数值计算;型面优化

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