升力式再入飞行器全程三维自主制导方法  

Three dimensional autonomous guidance method for whole flight of lift reentry vehicle

作　　者：傅瑜 陈阳 李延军 许江涛[2] 

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]哈尔滨工程大学航天工程系,哈尔滨15001

出　　处：《哈尔滨工业大学学报》2016年第4期97-103,共7页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金面上项目(11372080)

摘　　要：为增强升力式再入飞行器任务的灵活性,减少射前准备,实现快速发射和精确打击,研究一种升力式再入飞行器全程三维自主制导方法.首先,再入段制导提出通过再入走廊上下边界内插得到阻力加速度剖面,倾侧角采用两次反转的设计方法,通过调节阻力加速度剖面的内插值系数和倾侧角的反转点来满足约束和精度的要求;然后,下压段仅依靠飞行器当前信息和目标点位置采用比例导引的形式来设计导引律,并通过对导引系数的实时更新实现以一定的弹道倾角对目标的精度打击;最后通过对再入段和下压段衔接点处控制指令的平滑过渡,得到全程三维自主制导方法.蒙特卡洛打靶仿真结果表明,该制导方法能够导引飞行器在满足再入约束的情况下以规定的弹道倾角对目标实施精确打击,其中打击偏差小于10 m,弹道倾角偏差小于1.3°.In order to enhance mission flexibility, reduce launch preparation, and achieve quick launch and precision strike, a three dimensional autonomous guidance method for lift reentry vehicle＇s whole flight is studied in this paper. Firstly, a method is proposed for reentry phase, whose drag acceleration profile is obtained by interpolation between upper and lower boundary of entry corridor and two reversals of bank angle. The reentry process constraints and precision can be met by adjusting interpolation factor of the drag acceleration profile and reversal point of the bank angle. Then, the hit phase guidance law is designed in the form of proportional navigation guidance law based on vehicle and target position. The vehicle can strike target exactly with certain precision by updating the guidance coefficient in real time. Lastly, the whole flight guidance method is obtained using smooth transition at the joint point control commands of entry phase and hit phase. Monte Carlo simulation results show that the guidance method can guide the vehicle to strike target exactly with certain precision and meet process constraints, and the hit deviation is less than 10 m, the angle deviation is less than 1.3°.

关 键 词：再入飞行器 全程制导 再入走廊 在线规划 精确打击 

分 类 号：V448[航空宇航科学与技术—飞行器设计]