基于改进割线法的高超声速飞行器再入预测制导  

Improved Secant Method-based Predictive Reentry Guidance for Hypersonic Vehicle

作　　者：张晓峰[1,2] 张惠平[3,4] 杨业[4] 王宏伦[1,2] 邵星灵[1,2] 

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191 [3]北京理工大学自动化学院,北京100081 [4]北京航天自动控制研究所,北京100854

出　　处：《战术导弹技术》2016年第1期56-63,共8页Tactical Missile Technology

基　　金：国家自然科学基金资助项目(61175084)

摘　　要：针对基于割线法的预测校正算法对高超声速飞行器再入制导中初值敏感度较高及时效性和制导精度较低的问题,提出了一种基于改进割线法的再入预测校正制导方法。将改进割线法应用在纵向制导计算倾侧角数值大小,横侧向制导设计了横程走廊边界控制倾侧角的反转策略以保证制导精度。仿真结果表明,该算法易于实现,对初值不敏感,有较快的制导指令解算时间,制导精度较高,且对扰动偏差不敏感的优点。An improved secant method-based predictor-corrector guidance law combined with optimization theory is developed for the limitation of initial values, timeliness and guidance-precision of the hypersonic vehicles reentry secant method-based predictor-corrector guidance law. And the improved secant method is used for calculating the bank angle for longitudinal guidance, a lateral reversal logic based on the approximate linearity between cross range and velocity is designed for lateral guidance. Simulation results show that, the guidance law has the advantages of easy to implement, less calculation time and high guidance precision, and is not sensitive to the initial iterative value and disturbances.

关 键 词：再入制导 改进割线法 预测校正 倾侧角 高超声速飞行器 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]