吸气式组合动力高超声速飞行器上升段制导方法研究

针对涡轮/冲压/火箭三组合动力水平起降高超声速飞行器爬升段飞行轨迹设计和制导律设计问题，首先考虑宽速域组合动力发动机多模态特性和高低速气动特性差异，分别开展了涡轮段、引射段、纯冲压段及冲压火箭段的飞行策略研究，提出了不同阶段的飞行攻角剖面构型和火箭流量剖面构型，将无穷维轨迹优化问题转化为有限维参数规划问题，进而完成了组合动力上升段飞行轨迹的优化设计；在此基础上，结合轨迹线性化控制方法，开展了组合动力上升段轨迹跟踪制导律设计研究，给出了保证闭环稳定性和控制品质的制导律参数设计准则，最后通过开展仿真分析说明了提出轨迹设计及制导方法的有效性。

Investigation on Ascent Guidance Law for Air Breathing Combined Cycle Hypersonic Vehicle

The ascent trajectory design problem of air-breathing combined-cycle hypersonic vehicle is studied in this paper. By considering the different characteristics of the combined-cycle engine and aerodynamics within the flight envelope, the flight strategy for turbo mode, ejecting mode, scram mode and scram-rocket mode is proposed respectively. Then, by constructing the proper attack angle profile and rocket flow profile, the infinity dimension optimization problem is simplified as the finite dimension parameters optimization problem, which can be solved effectively via the sequence quadratic program algorithm. Moreover, by using the trajectory linearization control approach, the tracking guidance law for the combined-cycle ascent phase is designed, and the principle for choosing the controller parameters to guarantee the stability and performance is also provided. In the end, the simulation is carried out and the results demonstrate the efficacy of the proposed design approach.