基于能量和解析预测校正的滑翔制导  

Gliding guidance based on energy and analytical predictor-corrector

作　　者：曾宪法[1] 王洁瑶[2] 王小虎[1] 

机构地区：[1]北京控制与电子技术研究所,北京100038 [2]北京机电工程总体设计部,北京100854

出　　处：《系统工程与电子技术》2013年第12期2582-2588,共7页Systems Engineering and Electronics

摘　　要：针对高超声速滑翔问题,提出了一种基于能量和解析预测校正的滑翔制导方法。所提方法分纵向制导和侧向制导两部分。在纵向,利用准平衡滑翔条件建立了待飞距离与能量、倾侧角之间的解析数学关系,实现了对待飞距离的解析预测,并结合校正算法在线确定倾侧角指令大小,以满足对待飞距离和能量的要求,同时为了实现准平衡滑翔和满足终端高度、速度约束,进一步提出了基于高度的攻角指令调节方法;在侧向,提出了一种基于横程和待飞距离的侧向运动边界,以确定倾侧角符号和控制终端侧向偏差。与传统数值预测校正制导方法相比,所提方法的计算量和耗时显著减小,并且具有较好的精度和适应性。For hypersonic gliding problem, a gliding guidance approach based on energy and analytical pre-dictor corrector is proposed. In this approach, the gliding guidance is divided into two parts： longitudinal guid-ance and lateral guidance. In the longitudinal guidance, analytical mathematical formulas of range-to-go and en-ergy, bank angle are established based on quasi equilibrium gliding condition to analytically predict range-to-go, and then the bank angle magnitude is calculated online through the correct algorithm to satisfy the range-to go and energy request. An angle of attack adjustment algorithm based on altitude is proposed to achieve quasi equi- librium gliding and make sure that the terminal altitude and velocity constraints are met. In the lateral guidance, a lateral threshold based on cross range and range-to-go is proposed to determine the sign of bank angle com-mand and control terminal heading error. Compared with the traditional numerical predietor-corrector guidance method, the calculation cost of the proposed approach is significantly reduced, and the guidance precision and adaptation are good.

关 键 词：高超声速滑翔 再入制导 准平衡滑翔 解析预测校正 

分 类 号：V448[航空宇航科学与技术—飞行器设计]