摘要
为应对组合动力飞行器涡轮/冲压发动机模态转换过程中容易出现的推力陷阱问题,开展了组合动力飞行器模态转换阶段飞行/推进一体化保护控制研究。该研究利用组合动力爬升段飞行轨迹优化方法,解决模态转换过程中组合发动机总推力无法满足平飞加速需求的推力陷阱问题。结合轨迹线性化控制方法,完成了宽速域飞行器/发动机一体化轨迹跟踪控制设计,利用迎角、油门等变量的协同调节实现轨迹跟踪控制。仿真结果表明,轨迹优化策略能够在一定程度上克服模态转换过程中的推力不足问题,一体化轨迹线性化控制方法可以有效实现爬升轨迹跟踪,避免模态转换过程对组合动力飞行器飞行任务造成的不利影响。
To deal with the problem of thrust trap during the process of turbine/ramjet mode conversion of the turbine based combined cycle(TBCC),the integrated control of turbine/scramjet mode conversion has been studied.The combined power climbing flight trajectory optimization method is used to solve the thrust trap problem that the total thrust of the combined engine cannot meet the acceleration demand of horizontal flight during the modal conversion process.The control variables and state variables are discretized to complete the trajectory optimization.The integrated control strategy is designed to complete the joint adjustment of the angle of attack and the throttle during the mode conversion.The simulation results show that the trajectory optimization method can overcome the thrust trap through a special trajectory design.The integrated protection control method improves the control quality and avoids the adverse effects of the modal conversion process.
作者
刘凯
张永亮
聂聆聪
LIU Kai;ZHANG Yongiang;NIE Lingcong(College of Mechanics and Aerospace,Dalian University of Technology,Dalian 116024,China;Beijing Power Machinery Institute,Beijing 100074,China)
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2024年第3期443-451,共9页
Journal of Astronautics
关键词
宽速域飞行器
涡轮/冲压发动机
飞行/推进一体化控制
轨迹优化
轨迹跟踪控制
Wide-speed-range vehicle
Turbine engine/Ramjet
Integrated flight/propulsion control
Trajectory optimization
Trajectory tracking control
