高超声速滑翔飞行器约束预测校正再入制导

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。

Constrained predictor-corrector reentry guidance for hypersonic glide vehicle

For the reentry guidance law design problem of high lift-to-drag ratio hypersonic glide vehicle,reentry trajectory was divided into initial descent phase,transition phase and quasi-equilibrium glide phase.At the initial descent phase,constant bank angle was employed.At the transition phase,maximum bank angle was employed.At the quasi-equilibrium glide phase,a on-line guidance law designed based on numeric predictor-corrector method and quasi-equilibrium glide conditions was presented.The guidance law can generate reasonable bank angle profile which can satisfy the path constraints and terminal constraints.The results of standard initial condition simulation and error initial condition simulation show that the predictor-corrector can not only acquire higher accuracy,but has strong robustness to the initial errors at all constraints to be satisfied,even at the uncertain conditions.