高超声速飞行器复杂约束多任务制导控制降阶一体化设计方法研究

Aiming at the problem of guidance and control design for diving hypersonic vehicles, the reduced-order integrated guidance and control (ROIGC) design approaches for hypersonic vehicles with complicated constraints and multiple missions are studied. The current literatures focused on integrated guidance and control (IGC) researches are mostly based on the full states high-order IGC design framework. There are relatively few studies on IGC model improvement and IGC design considering maneuver, terminal state control with complicated constraints and multiple missions. For reducing the system order and promoting IGC design approach, the reduced-order integrated guidance and control design approaches with complicated constraints and multiple missions are proposed in this project. The integrated guidance and control for diving hypersonic vehicles is conducted, and the control constraints, terminal state constraints, diving maneuver, flight stability, and impact accuracy are all considered in the process of IGC and ROIGC design. The design approaches with respect to the full state high-order IGC design considering impact angle constraints and diving maneuver, the adaptive disturbance rejection ROIGC design based on analytical model of commanded body rates, and the fully ROIGC design for diving and maneuver hypersonic vehicles will be studied and implemented. This research will promote the development of guidance and control theory and IGC design of hypersonic vehicles. The system order and design parameters of guidance and control system can be both reduced. The newly proposed method can also improve the utilization of velocity measurements in the body coordinate frame. This research may have certain theoretical value and engineering application value.

针对高超声速飞行器俯冲制导控制问题，研究提出复杂约束多任务集成制导控制降阶一体化（Reduced-order integrated guidance and control，ROIGC）设计方法。现有制导控制一体化（Integrated guidance and control，IGC）研究主要是基于高阶IGC框架，考虑机动、终端控制的IGC设计和IGC模型创新研究相对较少。本项目将以丰富IGC设计思路和降低模型阶数为基本目标，研究提出过程约束、控制约束条件下面向落角控制、俯冲机动、飞行稳定和命中目标多任务需求的全耦合IGC和ROIGC设计方法。研究解决带落角约束的俯冲机动全状态耦合IGC设计、基于角速率指令解析模型的自适应抗扰ROIGC设计和基于速度矢量分量的全集成ROIGC设计等关键问题。所提方法可简化IGC设计流程，减少设计参数，提高速度分量利用率，具有一定的理论价值和工程应用价值。

针对快时变、强耦合、非线性、含未知干扰的高超声速飞行器在复杂约束条件下的俯冲机动制导控制一体化设计（Integrated guidance and control，IGC）问题，本项目研究提出了考虑过程约束、控制约束、终端约束等条件下实现机动突防、飞行稳定、终端落角和命中目标的多任务制导控制降阶一体化（Reduced-order integrated guidance and control，ROIGC）设计方法。建立了适于制导控制系统（Guidance and control，G&C）设计的过载、动压、终端落角和控制约束的表征模型，将落角约束转化为视线角终端控制问题，将俯冲机动转化为期望视线角设计与跟踪问题；建立包含质心和绕质心状态变量的严格反馈型全状态耦合IGC模型，利用块动态面方法完成了带落角约束的俯冲机动IGC设计；通过数值仿真验证了所提方法的有效性，结果表明当机动范围有限且机动时长较短时效果较好，机动幅度过大会造成终端命中精度下降。建立了基于体坐标系内加速度分量的三通道角速率指令解析计算模型，推导了以视线角二阶导数为状态变量以舵偏角为控制输入的ROIGC设计模型，设计自适应估计律对模型中不确定项进行估计完成了俯冲机动自适应ROIGC设计；将G&C系统阶数降低为4阶，省略了姿态角跟踪控制环路，减少了系统设计参数。建立了以速度、速度倾角和航向角的一阶导数为状态变量，以舵偏角为控制输入的全集成ROIGC模型，设计纵向S型俯冲机动弹道验证了新模型的有效性，完成了俯冲机动全集成ROIGC设计；将姿态角和角速率跟踪控制转化为解析计算过程，省略气流角反插值计算过程，高效利用了加速度的高阶导数信息，G&C系统阶数和复杂度均有所降低。项目所提方法将有效拓展IGC设计的研究思路、数学模型和方法技巧，丰富和发展了制导控制一体化设计理论，具有一定的理论价值和工程应用价值。