具有约束的双机空战机动控制设计方法研究  

Study on maneuver control design method of dual aircraft air combat with constraints

作　　者：明瑞晨 刘小雄[1,2] 李煜 章卫国 MING Ruichen;LIU Xiaoxiong;LI Yu;ZHANG Weiguo(School of Automation, Northwestern Polytechnical University, Xi′an 710129, China;Shaanxi Province Key Laboratory of Flight Control and Simulation Technology, Xi′an 710129, China)

机构地区：[1]西北工业大学自动化学院,陕西西安710129 [2]陕西省飞行控制与仿真技术重点实验室,陕西西安710129

出　　处：《西北工业大学学报》2021年第6期1368-1376,共9页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(62073266);航空科学基金(201905053003);陕西省自然科学基金(2019JM-163)资助。

摘　　要：针对空战轨迹控制中遇到的态势约束问题,提出了一种约束反步法飞行控制律。该方法在考虑传统飞行过程中状态量幅值和带宽约束的同时,将双机空战中的角度态势信息引入到控制律中,在控制律设计中定义跟踪误差的修正量,并使用角度态势信息对修正量进行自适应更新。当角度态势为优势时,认为系统可正常执行机动任务,修正量快速收敛为0;当角度态势为劣势时,则修正量变大,并影响机动使角度态势朝优势变化。仿真结果表明,机动飞行时该方法能快速调整轨迹,使得己机的角度态势朝有利方向变化。Aiming at the situation constraint problem in air combat trajectory control,a constrained backstepping flight control law is proposed.This method considers the constraints of the amplitude and bandwidth of the state variables in the traditional flight process.At the same time,it also introduces the situation information of the two aircraft air combat into the control law.The correction error is defined in the control law error,and the angle situation information is used to update the correction error.When the situation is dominant,the system can perform the maneuver task normally,and the correction error converges to 0 quickly When it is a disadvantage,the correction error becomes larger,and affects the maneuver,so that the situation changes to the advantage.The simulation results show that the method can effectively make the situation change in a favorable direction during maneuvering flight.

关 键 词：飞行控制律 反步法 角度态势信息 修正量 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]