考虑攻角约束的导弹制导控制一体化设计  

Integrated Missile Guidance and Control Design with Angle of Attack Constraint

作　　者：吴笛 王心明 何金刚[2] 张金鹏[2] 李世华[1] Wu Di;Wang Xinming;He Jingang;Zhang Jinpeng;Li Shihua(School of Automation,Southeast University,Nanjing 210096,China;China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]东南大学自动化学院,南京210096 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2022年第3期14-20,共7页Aero Weaponry

基　　金：航空科学基金项目(20180112006)。

摘　　要：针对制导与控制一体化系统,考虑目标机动、导弹参数摄动和导弹攻角约束等问题,提出了一种具有攻角约束的复合制导方法。首先,针对二维制导问题建立制导与控制一体化系统,将目标机动和导弹中存在的参数摄动作为集总扰动,利用广义比例积分观测器对相应的扰动信息进行观测估计。然后,利用惩罚机制和分块反步法的设计思想,将扰动的观测信息进一步融入到控制器的设计过程中进行前馈补偿,最终实现了攻角约束下的精确制导。最后,进行数值仿真,验证了所提出的控制方案的有效性。This paper proposes a composite guidance method with angle of attack constraint for the integrated guidance and control system with the problems of target maneuver,missile parameter perturbation and missile angle of attack constraint.Firstly,an integrated guidance and control system is established for the two-dimensional guidance problem.The target maneuvering and parameter perturbations about the missile are regarded as lumped disturbances,and the corresponding disturbance information is observed and estimated by using the generalized proportional integral observers.Then,using the penalty mechanism and the design idea of block backstepping,the disturbance observation information is further integrated into the design process of the controller as feedforward compensation to realize the accurate guidance under the angle of attack constraint.Finally,numerical simulation results are given to verify the effectiveness of the proposed control scheme.

关 键 词：制导控制 一体化 攻角约束 惩罚机制 分块反步法 复合控制 广义比例积分观测器 导弹 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] V249.1[航空宇航科学与技术—飞行器设计]