基于亚燃RBCC构型的引射模态一次火箭节流策略研究

Throttling Strategy of Primary Rocket in Ejector Mode on a Ramjet-Mode-Designed RBCC Structure

关键词:  火箭基组合动力循环  亚燃构型  引射模态  性能  一次火箭  节流策略

Key words:  RBCC  Ramjet-mode-designed structure  Ejector mode  Performance  Primary rocket  Throttling strategy

摘要:

为了探究亚燃RBCC构型在引射模态下的性能表现和一次火箭节流规律，基于一设计点为亚燃模态的RBCC构型，开展了进气道/燃烧室一体化内流道的数值模拟工作，分析了一次火箭流量变化对进气量、流道压力分布、推力和比冲的影响，最终给出了引射模态下一次火箭的节流策略。结果表明：引射模态下，一次火箭流量调节对RBCC性能的影响非常复杂，且规律性和一致性较差；在亚声速引射模态，建议一次火箭以大流量工作，暂不考虑比冲性能；在超声速引射模态，建议一次火箭以小流量工作；为了提升进气道启动点附近RBCC的比冲性能，建议尝试二次燃料的喷注燃烧，但必须充分考虑对进气系统的不利影响。

Abstract:

In order to investigate the performance of RBCC engine and the throttling strategy of its primary rocket in ejector mode， numerical simulation of internel flow field of an inlet-combustor integrated RBCC configuration designed for ramjet mode was carried out. Effects of the primary rocket throttling on the intake volume， pressure distribution， thrust and specific impulse were analyzed， and the throttling strategy of the primary rocket in ejector mode was eventually proposed. It is conducted that the effect of the primary rocket throttling on the performance of the RBCC engine in ejector mode is very complex and its regularity and consistency are poor. It is recommended to adopt the strategy of the primary rocket working with relatively larger flow rate， without considering the specific impulse performance temporarily in the subsonic ejector mode. However， the primary rocket working with relatively smaller flow rate is recommended in the supersonic ejector mode. In order to improve the specific impulse performance of RBCC near the intake starting point， it is recommended to try the secondary fuel injection， but the negative effect on intake system must be fully considered.