Design Of Landing Guidance Law And Evaluation System For Fixed-wing UAV

The combination of long-range and high-precision fixed-wing UAVs with aircraft carriers will have a revolutionary impact on future naval warfare.Therefore,this paper mainly studies the design and research of the automatic landing guidance system and the corresponding evaluation system for fixed-wing UAV.Firstly,the approach motion model of a UAV is established.According to the U.S.military standards,the carrier-related model and the wake-related model are built.On this basis,taking the linear small disturbance mathematical model of UAV as the controlled object,and referring to the configuration of F/A-18 A full-automatic landing control loop,the UAV flight control system including autopilot and field power compensation device is constructed.Secondly,the traditional baseline evaluation method of carrier-based aircraft is briefly introduced and its shortcomings are analyzed.The partial least squares method in statistics is used for reference and applied to the landing evaluation system.A large number of flight attitude data of UAV landing in different flow fields are counted.The method of dividing training set and test set is used to validate the validity.The corresponding evaluation software is compiled for real-time evaluation.The whole process of UAV landing guidance is studied and the longitudinal guidance law is designed.Considering the inadequacy of UAV’s immunity to complex environment during landing,the feed-forward control commands of height change rate are designed for cock wake,the prediction and compensation devices for deck motion are designed,and the numerical simulation of automatic landing control system is introduced to verify the performance of the control system.Finally,according to the calculation formula of simulation landing point and the prediction of evaluation software based on partial least squares method,it is concluded that the existing automatic landing system can not guarantee the small range fluctuation of longitudinal landing point.Therefore,based on the basic principle of particle swarm optimization,the fitness function based on command response characteristics and flight attitude stability is designed,and the parameters of the whole automatic landing control system are optimized,and the rationality of the new control parameter set is verified by simulation.