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提出了塞锥型面设计的特征线法及示例结果,得出了侧喷管粘性跨音速和超音速内流场数值计算结果,及塞锥外流和尾流的Euler方程解,总结了塞式喷管工作特性的固体推进剂燃气模拟实验系统、实验结果及主要结论.塞式喷管火箭发动机是一个复杂而有挑战性的研究方向,对于发展新一代先进天地往返运输系统有重要作用.

Experimental and Numerical Studies on Aerospike Nozzles

This paper presents the designing procedures of the wall contour of aerospike nozzle using characteristic method and a sample result; obtains the numerical results of viscous side nozzle internal flow field from transonic to supersonic flow,the Euler solution of the flow field along the plug wall and after the plug bottom,and summarizes the solid propellant test system simulating the working property of aerospike nozzles, experimental results and the main conclusions. Rocket engine with aerospike nozzle is a complex and challenging research direction. It will play important role in the development of a new generation reusable launch vehicle.