摘要
简要叙述了液氧/煤油火箭发动机节流阀阀芯型面优化设计的方法。原有节流阀的流阻特性不满足发动机使用要求,根据系统对节流阀的参数要求,采用分段插值拟合法对节流阀阀芯型面重新进行了优化设计,优化后的节流阀液流试验合格,并通过了发动机热试车考核,其性能完全满足系统要求。
The procedure of the throttle valve core contour optimized design for LOX/kerosene rocket engine was described in this paper. The original design of the throttle valve core contour can not meet the requirement of the engine system. New methods were applied in throttle valve core contour optimization. The ground test result of the engine system proved that the newly designed valve were qualified.
出处
《火箭推进》
CAS
2009年第4期26-29,共4页
Journal of Rocket Propulsion
关键词
液氧/煤油火箭发动机
节流阀
阀芯型面
优化设计
LOX/kerosene rocket engine
throttle valve
valve core contour
design optimization
