亚轨道飞行器返回侧向制导规划方法  

Lateral entry guidance for suborbital launch vehicle

作　　者：闫晓东[1] 唐硕[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2010年第5期71-74,共4页Flight Dynamics

摘　　要：侧向制导方法是亚轨道飞行器返回制导方法中重要的一方面。由于亚轨道飞行器返回飞行过程短,因此采用侧向走廊的方法进行倾斜角的反向控制,末端制导精度差。为此,利用归一化能态方程的积分端点固定、积分过程快的特点,提出了一种快速收敛的迭代倾斜角反向时机规划方法。算例结果表明,采用该方法可以实现反向点的在线规划,从而有效提高了侧向制导精度。Lateral guidance method is an important part for suborbital launch vehicle（SLV） entry guidance.Due to the short range of the SLV entry,it has the shortcoming of poor terminal guidance precision,which changes the crossrange corridor based on pre-specified threshold values in the heading error of the vehicle with respect to the landing site.Applying translational dynamics with the normalized energy as an independent variable,the paper proposed a fast convergence iterative method for planning the bank angle reversal time,which can realize bank angle reversal planning onboard,thus effectively improving the lateral guidance precision.

关 键 词：亚轨道飞行器 返回制导 侧向制导 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]