关键词: 液体推进剂火箭发动机;多级火箭;方案论证

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.

Key words: Liquid rocket engines. Concept research;Multistage rocket