升力式再入飞行器全程三维自主制导方法

发布时间：2019-01-27 13:52

【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°.
[Abstract]:In order to enhance the flexibility of lifting reentry vehicle mission, reduce pre-launch preparation, and achieve rapid launch and accurate strike, a three-dimensional autonomous guidance method for lift reentry vehicle is studied. First of all, in the guidance of the reentry section, the resistance acceleration profile is interpolated through the upper and lower boundary of the corridor, and the slope angle is designed with two reversals. By adjusting the internal interpolation coefficient of the resistance acceleration profile and the inversion point of the inclination angle to meet the requirements of constraint and accuracy; Then, the guidance law is designed in the form of proportional guidance only depending on the current information of the vehicle and the position of the target, and the precision of the target is hit with a certain ballistic inclination angle by updating the guidance coefficient in real time. Finally, through the smooth transition of the control command at the junction point between the reentry section and the lower pressure section, the full-range three-dimensional autonomous guidance method is obtained. The simulation results of Monte Carlo target shooting show that the guidance method can accurately strike the target with the specified trajectory inclination angle under the condition of reentry constraint, in which the striking deviation is less than 10 m and the trajectory inclination angle deviation is less than 1.3 掳.
【作者单位】：北京宇航系统工程研究所;哈尔滨工程大学航天工程系;
【基金】：国家自然科学基金面上项目(11372080)
【分类号】：V448.2

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