高升阻比滑翔飞行器再入制导方法研究

Research on Reentry Guidance Method for High L/D Gliding Vehicles

针对高升阻比滑翔飞行器再入段制导方法的工程需求,提出了“改进的预测-校正制导+定向末制导”方法作为再入段制导方法。通过调整其横向制导的误差边界,解决了飞行器在交班点附近出现的横向误差不收敛问题,同时兼顾了较大的横向机动距离,发挥了飞行器高升阻比的特性。对预测-校正制导流程进行了改进,从而赋予了飞行器在线变更目标点的能力。在距目标一定距离时切换为末制导律,采用约束落点弹道倾角和航向角的广义比例导引法,实现对目标的定点定向打击。蒙特卡洛仿真结果表明,该制导方法对各项误差有较强的鲁棒性,具有较好的应用前景。

Aiming at the engineering requirement of the entry guidance method of the high lift-draft ratio gliding vehicle,the“improved predictor-corrector guidance+directional terminal guidance”method is proposed as the guidance method.By adjusting the error boundary of its lateral guidance law,the problem that the lateral error of the vehicle near the shift point does not converge is solved,the large cross-range and the characteristics of the high lift-draft ratio is taken into account.The author improves the predictor-corrector guidance process and gives the vehicle the ability to change target point online.When the target is close enough to the vehicle,the constrained ballistic angle and heading angle of the generalized proportional guidance method is used to achieve striking the target accurately.Monte Carlo simulation results show that the guidance method has strong robustness to each error and has good application prospect.