用运载器评价发动机方案的方法

A METHOD FOR ASSESSMENT OF ENGINE SCHEMES IN TERMS OF LAUNCH VEHICLE PERFORMANCE

关键词:  液体推进剂火箭发动机  多级火箭  方案论证

Key words:  Liquid rocket engines. Concept research  Multistage rocket

摘要:

早期在对液体推进剂火箭发动机方案进行评价与选择时,仅以发动机本身的指标(如比冲、推重比等)作为方案比较的标准。这样没有考虑发动机子系统与运载器总系统的相互联系,得不到合理的评价结果。液体推进剂火箭发动机是航天运载器的一个子系统,采用运载器的性能指标评价发动机方案才能得到比较客观的结果。 本文推导了运载器的评价指标,给出了运载器的线性化质量方程,阐述了运载器设计参数的简化确定方法,由此提出了一个采用运载器评价发动机方案的方法。最后应用提出的方法对五个发动机方案进行了评价。

Abstract:

Previously when the schemes of liquid propellant rocket engine was assessed and selected, the enpine performance (such as specific impulse, thrust-to-weight ratio, etc) were used as objective function to compare engines. The relation between the engine subsystem and vehicle system was not considered, so the reasonable assessment results cannot be obtained, considering that liquid propellant rocket engine is a subsystem of launch vehicle, it is more objective to assess liquid propellant rocket engines in terms of launch vehicle performance.In this paper, a method for assessment of engines in terms of launch vehicle performance is proposed, vehicle linear mass equations are deduced anda simplified way for determing vehicle design parameters is developed. Fin-ally five engine schemes have been assessed by applying given method.