### 涡轮基组合动力与火箭的耦合特性分析及匹配优化设计

1. 厦门大学 航空航天学院, 厦门 361005
• 收稿日期:2020-09-16 修回日期:2020-11-03 发布日期:2021-01-08
• 通讯作者: 朱剑锋 E-mail:zhjf@xmu.edu.cn
• 基金资助:
航空动力基金（6141B090325）

### Performance coupling analysis and optimal design of rocket-assisted turbine-based combined cycle engines

GUO Feng, ZHU Jianfeng, YOU Yancheng, XING Fei

1. School of Aerospace Engineering, Xiamen University, Xiamen 361005, China
• Received:2020-09-16 Revised:2020-11-03 Published:2021-01-08
• Supported by:
Aeronautics Power Foundation of China (6141B090325)

Abstract: For the rocket-assisted turbine-based combined cycle engine, an analysis method for matching the vehicle and the propulsion system is proposed based on the trajectory optimization method of the Gauss pseudospectral. For the longest cruise range of the hypersonic aircraft with horizontal ground take-off and Mach number 5 cruise, the coupling characteristics between the Turbine-Based Combined Cycle engine (TBCC) and rocket are analyzed and optimization designs for the rocket-augmented TBCC engine are presented. Results show that for the feasible TBCC scheme (take-off thrust-to-weight ratio of 1.0), introducing a rocket with an appropriate thrust can increase the total efficiency and reduce the total mass consumption during the climb phase, and improve the cruise range slightly (assisted by a rocket of the 4% take-off weight thrust can increase the range by 0.97%).When the TBCC scheme is infeasible (take-off thrust-to-weight ratio of 0.8), introducing a rocket can help the TBCC engine to accelerate the vehicle to the cruise phase, and the cruise range can be increased by 7.9% compared with the feasible TBCC scheme. Considering the negative impact of both the inert weight and the low unit-frontal-area thrust on cruise performance, it is recommended that the cruise vehicle with 25% structural mass ratio adopts a propulsion system of "TBCC (take-off thrust-to-weight ratio of 0.7) assisted by a rocket of the 13% take-off weight thrust". For the accelerating vehicle with a 55% structural mass ratio, it is recommended to adopt a propulsion system of "TBCC (take-off thrust-to-weight ratio of 0.98) assisted by a rocket of the 5% take-off weight thrust".