关键词: 再入滑翔飞行器, 速度约束制导律, 偏置比例导引, 误差动力学

Abstract: Focusing on the speed control degradation problem during the terminal guidance phase of reentry gliding vehicles due to model uncertainty, such as aerodynamic parameter perturbations, a novel robust bias proportional navigation guidance law with speed constraint is proposed. This guidance law can satisfy the accuracy requirements for target interception and terminal speed constraint of the reentry glide vehicle, and it has robustness against uncertainties such as perturbations in aerodynamic parameters. Based on the principle of additional angle of attack deceleration, the error dynamics between flight speed and an ideal speed curve is established. By introducing the theory of fixed-time convergence error dynamics and considering the model uncertainty caused by the perturbations of aerodynamic parameters during the flight, a speed constraint guidance law based on the fixed-time convergence error dynamics is derived. It is also proven that the speed error dynamic is converged under the bounded model uncertainty. Numerical simulations are conducted to validate the performance of the proposed guidance law, and its robustness against initial parameter and aerodynamic parameter perturbations is also verified through Monte Carlo tests.

Key words: reentry glide vehicle, speed constraint guidance law, bias proportional navigation guidance, error dynamic