适应多射程与路径约束的再入预测校正制导  

Reentry Predictor-corrector Guidance Adapting to Multi Range andPath Constraints

作　　者：郭浩辰 黄汉斌 郭涛[1] 杨业[1] GUO Haochen;HUANG Hanbin;GUO Tao;YANG Ye(Beijing Aerospace Automatic Control Institute,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《导弹与航天运载技术（中英文）》2024年第5期48-55,共8页Missiles and Space Vehicles

摘　　要：针对存在不同分布的路径约束与不同航程需求的升力式飞行器再入飞行任务,设计二次曲线形式的倾侧角剖面以增强飞行器的侧向机动能力,通过预测校正的迭代过程修正倾侧角剖面以满足航程需求,采用改进人工势场法设计侧向制导方法导引飞行器满足路径约束,最后通过粒子群算法优化制导参数以获得性能最优的轨迹。仿真结果验证了该算法能够适应多种航程需求与路径约束且以较高精度满足终端约束。To address the reentry missions with different path constraints and range requirements,a conic based bank angle is designed to enhance the lateral maneuverability,and the predictor-corrector guidance method is used to revise the bank angle profile to satisfy the range requirements.The improved artificial potential field method is used to design the lateral guidance method to satisfy the path constraints.Finally,the guidance parameters are optimized by particle swarm optimization algorithm to obtain the trajectory with the best performance.Simulation results verify that the algorithm can adapt various range requirements and path constraints,and meet the terminal constraints with high accuracy.

关 键 词：升力式飞行器 路径约束 预测校正制导 人工势场 粒子群优化 

分 类 号：V448[航空宇航科学与技术—飞行器设计]