宇航学报 ›› 2022, Vol. 43 ›› Issue (4): 465-475.doi: 10.3873/j.issn.1000-1328.2022.04.008

• 制导、导航、控制与电子 • 上一篇    下一篇

飞行器制导控制一体化编队控制器设计

陈昶荣,许鑫   

  1. 北京机电工程研究所,北京 100074
  • 收稿日期:2021-04-12 修回日期:2021-10-11 出版日期:2022-04-15 发布日期:2022-04-15

Controller Design of Aircraft Formation Based on Integrated Guidance and Control

CHEN Chang rong, XU Xin   

  1. Beijing Electro Mechanical Engineering Institute, Beijing 100074, China
  • Received:2021-04-12 Revised:2021-10-11 Online:2022-04-15 Published:2022-04-15

摘要: 针对主从式结构飞行器协同编队控制问题,以侧滑转弯飞行器为研究对象,采用制导控制一体化(Integrated guidance and control, IGC)方法设计编队控制器。首先在惯性坐标系中定义相对运动坐标系,建立相对运动模型,结合飞行器动力学模型,得到全状态制导控制一体化模型;然后采用反演方法,结合滑模变结构与神经网络自适应理论设计了编队控制器,并证明了控制系统稳定性;最后在高速情况下进行了六自由度数值仿真,对比了IGC设计方法与分离设计方法的控制性能。仿真结果表明所设计的IGC控制器能够快速精确地对期望编队队形进行构建与保持,并且较分离设计方法具有优越性。

关键词: 飞行器, 制导控制一体化(IGC), 反演方法, 滑模变结构, 神经网络

Abstract: Aiming at the control problem of aircraft cooperative formation based on leader follower structure, taking side slip turning aircraft as the research object, the integrated guidance and control (IGC) method is used to design the controller. Firstly, the relative motion coordinate system is defined in the inertial space, and the relative motion model is established. Combined with the dynamic model, the IGC model is obtained. Secondly, the formation controller is designed based on the sliding mode variable structure and neural network theory by using the backstepping method, and the stability of the control system is proved. Finally, the six degree of freedom numerical simulation is carried out under high speed condition, and the control performance of the IGC method is compared with that of the separate design method. The simulation results show that the IGC controller can construct and maintain the desired formation quickly and accurately, and it is superior to the separate design method.

Key words: Aircraft, Integrated guidance and control(IGC), Backstepping method, Sliding mode variable structure, Neural network

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