空天飞机复合循环推进系统新概念研究——组合发动机优化

OPTIMIZATION OF A COMBINED-CYCLE PROPULSION SYSTEMFOR SPACE VEHICLE

介绍一种用于空天飞机的组合发动机各工作模式切换的优化结果。优化过程中,在给定的飞行条件和选择的设计点参数情况下,对推进系统的安装推力、空天飞机的重量和性能作了详细的估算。

This paper presents some results of optimization of operating modes transfer in a Supercharged Ejector Ramjet (SERJ) specified for first stage of a two-stage-to-orbit space vehicle. The SERJ consists of four subsystem:Fan, Ejector, Ramjet and Air liquefaction subsystem used as a heat exchanger. Three factors are considered for estimating propulsion system installed thrust; Internal and external performances of the inlet and the nozzle; power and air extractions from the engine. An objective of minimization is the minimum of the fuel consumption, which is attained by varying the transition conditions of different engine operation modes. Then the optimum transition corditions can be obtained between SERJ and fan ramjet modes, fan ramjet and ramjet modes, ramjet and ejctor ramjet modes, ejector ramjet and rocket modes.