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针对大升阻比高超声速滑翔飞行器的再入制导问题,将再入轨迹划分为初始下降段、过渡段和准平衡滑翔段。初始下降段采用定倾侧角飞行,过渡段在最大倾侧角附近飞行,准平衡滑翔段利用数值预测校正方法和准平衡滑翔条件在线设计同时满足过程约束和终端约束的倾侧角制导律。通过标准条件和扰动条件下的仿真结果表明,这种制导律在满足各种约束的条件下,不仅能够达到较高的精度,而且对初始误差具有良好的鲁棒性,能够应付再入时各种不确定性因素的影响。
Aiming at the reentry guidance problem of the high-lift-drag hypersonic gliding aircraft, the reentry trajectory is divided into the initial descending section, the transition section and the quasi-balanced gliding section. The initial descent stage adopts the fixed-tilting angle flight, the transitional section flies near the maximum tilting angle, and the quasi-balanced gliding section uses the numerical predictive correction method and the quasi-equilibrium gliding conditions to design the roll angle guidance law satisfying both the process constraints and the terminal constraints. The simulation results under standard and perturbed conditions show that the proposed guidance law not only achieves high precision but also has good robustness to initial errors under various constraints, The impact of uncertainties.