摘要
当前新研制的液体火箭发动机特别强调高可靠性和低成本,以往追求高性能和低质量为主的设计目标现已降为次要地位。新研制的发动机都要求进行可靠性设计。在发动机可靠性设计中,为消除故障隐患,提高产品可靠性,采用了行之有效的故障树分析(FTA)及故障模式、后果及严重度分析(FMECA)。美国先进运载系统(ALS)航天运输主发动机(STME)的设计工作采用了这种可靠性设计法,以确保发动机达到设计要求的可靠性指标(0.999)。本文不打算全面介绍液体火箭发动机可靠性设计方法和过程,只对其中采用的故障模式、后果及严重度分析以及故障树分析作简单介绍。
At present, high reliability and low cost are especially emphasized in new engine design, while high performance and low weight are considered secondary. In development of a new engine, reliability design must be carried out. The effective measures of failure mode analysis, effect analysis and criticality analysis, and fault tree analysis are adopted in new rocket engine design in order to increase reliability. This reliability design method is adopted in the Space Transportation Main Engine(STME) design of the Advanced Launch System(ALS), in order to achieve a reliability requirement of R(Eng)=0.999.This paper presents briefly the failure mode, effect analysis and criticality analysis and fault tree analysis in liquid rocket engine design.
出处
《导弹与航天运载技术》
1993年第5期27-37,共11页
Missiles and Space Vehicles
关键词
液体推进剂
火箭发动机
可靠性设计
Liquid propellant rocket engine
Reliability design
Fault analysis
