Abstract: In view of the technical requirements of the power system for reusable launch vehicle， the power system of the new generation launch vehicle which is the LOX/kerosene high pressure staged combustion rocket engine was taken as the object of study. A multi parameters， nonlinear and strong coupling engine system simulation platform was established. Based on the analysis of the technical characteristics of variable thrust liquid propellant rocket engines at home and abroad， the simulation results of single thrust regulation of LOX/kerosene engine are presented. The combined depth thrust regulation scheme for gas generator fuel flow regulator adjustment， inlet gas of main turbine diversion and oxidizer main path throttling was firstly proposed.The combined depth thrust adjustment scheme is assisted by gas blowing to improve the pressure drop of the injector.The simulation results show that the thrust regulation capability of the engine is up to 10:1. Moreover， multiple ignitions starting can be realized.It has the advantages of high performance and large adjustment range.

Key words: Reusable launch vehicle；Variable thrust engine；LOX/kerosene staged combustion engine；System simulation；Thrust regulation

摘要： 鉴于重复使用运载器对动力系统的技术需求，以我国新一代运载火箭主动力液氧煤油高压补燃循环发动机为研究对象，建立了多参数、非线性以及强耦合的发动机系统仿真平台。在分析国内外变推力液体火箭发动机技术特点的基础上，根据液氧煤油发动机单路推力调节的仿真结果，首次提出了发生器燃料路流量调节器调节、主涡轮前燃气分流以及氧化剂主路节流等相结合，并辅助以气体乳化提高喷注器压降的组合深度推力调节方案。仿真结果表明:发动机推力调节能力可达10:1，且能实现多次点火起动，具有性能高、调节范围大的优点。

关键词: 重复使用运载器；变推力发动机；液氧煤油补燃发动机；系统仿真；推力调节