A novel analytical model between roll, pitch rates and components of acceleration of the hypersonic vehicle is established, and a reduced-order gliding guidance and control (G&C) design approach for the hypersonic vehicle is proposed in this paper. The six-degree-of-freedom (6DOF) dynamical and kinematic equations of the hypersonic vehicle in the gliding phase are described. An analytical model suitable for the bank to turn (BTT) control strategy is derived by connecting body rates with components of acceleration in the ballistic coordinate system. A novel reduced-order guidance and control design model with respect to quasi-equilibrium gliding flight is deduced and converted into the strict feedback form. The three channel body rates are treated as pseudo-inputs for tracking errors of flight path angle and heading angle of the hypersonic vehicle. Then, the commanded control surface fin deflections of the hypersonic vehicle are obtained by controlling tracking errors of the flight path angle, heading angle, and the body rates by adopting the block dynamic surface control method. In this paper, the aerodynamic coefficient interpolation process for obtaining the commanded angle of attack and bank angle based on expectant guidance overload is avoided. Meanwhile, the control loop of tracking Euler angles for getting the desired body rates is also elided. Finally, effectiveness and robustness of the novel G&C design method are verified and investigated. Moreover, the feasibility of entering quasi-equilibrium gliding phase only depending on the aerodynamic control mechanism is discussed.

建立了高超声速飞行器侧倾，俯仰率与加速度分量之间的新型解析模型，提出了一种高超声速飞行器降阶滑行制导控制（G＆C）设计方法。描述了高超声速飞行器在滑行阶段的六自由度（6DOF）动力学和运动学方程。通过将车速与弹道坐标系中的加速度分量联系起来，得出了适用于转弯（BTT）控制策略的分析模型。推导了一种关于准平衡滑行飞行的新型降阶制导控制模型，并将其转化为严格的反馈形式。这三个通道的身体比率被视为伪输入，用于跟踪高超声速飞行器的飞行路径角和航向角的误差。然后，通过采用块动态表面控制方法来控制飞行路径角，航向角和车速的跟踪误差，从而获得高超音速飞行器的指令控制面鳍挠度。本文避免了基于预期制导过载的气动系数插值过程，以获取指令迎角和倾斜角。同时，也消除了跟踪欧拉角以获得所需体率的控制环。最后，验证并研究了新颖的G＆C设计方法的有效性和鲁棒性。此外，