气动塞式喷管实验与数值模拟研究  

Experimental and Numerical Studies on Aerospike Nozzles

作　　者：刘宇[1] 张正科[1] 程显辰[1] 张振鹏[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《北京航空航天大学学报》1999年第6期676-679,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：863 高技术计划;国家自然科学基金

摘　　要：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．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.

关 键 词：实验 流场模拟 特征线法 塞式喷管 固体火箭 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] V435