塞式喷管多参数性能优化计算  

Optimized performance calculation in multi-parameter for aerospike nozzle

作　　者：覃粒子[1] 刘宇[1] 王一白[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2002年第2期28-33,共6页Journal of Astronautics

基　　金：国家 8 63计划 ( 863-2 -3-4 -10 );高等学校骨干教师资助计划资助

摘　　要：从影响塞式喷管推力性能的因素中总结出内喷管倾角、内膨胀比、总膨胀比、燃气总压和飞行高度这五个主要因素 ,并以推力最大为目标函数运用枚举和逐层优化的方法对上述五个参数的取值进行优化计算 ,提出了对这五个参数进行优化取值的方法并得到了相关结论。其结论可为实际的塞式喷管发动机设计研制提供部分的理论依据 。Five most important parameters,that is the obliquity of internal nozzle,the expansion ratio of internal nozzle,the engine expansion ratio,the stagnation pressure of the gas and the flight altitude,are selected from all the factors that influence the thrust performance of the aerospike nozzle.In order to gain the maximal thrust,the values of the above five parameters are optimized by enumeration stage by stage.Their relations and effect on the thrust are analyzed too.At the same time,the method of the optimization and the conclusions drawn by adopting it are presented.And the conclusions can direct the development of the actual aerospike nozzle.

关 键 词：火箭发动机 推力性能 能数优化 塞式喷管发动机 计算 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]