In this article, an integrated guidance and control design method for general nonlinear flexible hypersonic flight vehicles in the presence of dynamic uncertainties based on the ${\mathcal{L}}_1$ adaptive state feedback control approach is presented. Initially, the 6-degree-of-freedom integrated guidance and autopilot dynamic model is organized using the combination of flexible uncertain hypersonic flight vehicle dynamic model and hypersonic flight vehicle-target relative motion model whereas aerodynamic and model uncertainties, cross-coupling effects, and disturbances are considered. The proposed integrated guidance and control method based on ${\mathcal{L}}_1$ adaptive control scheme afterward is designed to realize control objectives including closed-loop stability, high-performance target interception, state regulation, uncertainties compensation, and reduction of the adverse flexibility effects on the overall performance. The whole Targets are proven thereupon based on the Lyapunov theory. Finally, the three-dimensional simulation results confirm the effectiveness of suggested integrated guidance and control law not only in closed-loop stability but also in high-performance target interception using the smooth control input.

本文提出了一种基于动力学的不确定性的通用非线性柔性高超音速飞行器综合制导与控制设计方法。 ${\mathcal{大号}}_{\mathrm{1个}}$提出了自适应状态反馈控制方法。最初，结合柔性不确定性高超音速飞行器动力学模型和高音速飞行器-目标相对运动模型，组织了六自由度综合制导和自动驾驶动力学模型，而空气动力学和模型不确定性，交叉耦合效应和考虑干扰。提出的基于控制的综合制导控制方法${\mathcal{大号}}_{\mathrm{1个}}$之后的自适应控制方案旨在实现控制目标，包括闭环稳定性，高性能目标拦截，状态调节，不确定性补偿以及减少对整体性能的不利灵活性影响。随即基于李雅普诺夫理论证明了整个目标。最后，三维仿真结果证实了所建议的综合制导和控制律不仅在闭环稳定性方面而且在使用平滑控制输入的高性能目标拦截中均有效。