On The Model Of Asymmetric Bombing Disturbance Effect And Rejecting Control Technique For Unmanned Aerial Vehicle

Today,the flight combat platform for Military Applications presents the trend of multi-task and unmanned.Unmanned Aerial Vehicles(UAVs)usually perform asymmetric attack tasks in actual combat.The disturbance force and moment produced by unilateral missile dropping of UAVs will affect the flight stability and safety of UAVs.Therefore,it is of great practical significance to study the modeling and suppression control technology of UAVs’ asymmetric missile dropping disturbance effect.In this paper,based on the research and development project of a multi-mission configuration UAV bombing process simulation system,the main tasks of UAV asymmetric bombing disturbance modeling and suppression control technology research include: based on the aerodynamic disturbance dynamics characteristics of UAV asymmetric bombing,UAV asymmetric bombing disturbance effect mathematical modeling and asymmetric bombing disturbance suppression control technology.Surgical research.The specific work is as follows:Firstly,in this thesis,the combat environment of UAV with multi-mission configuration is studied and the atmospheric environment and local laminar flow around the wing of a UAV during cruising are analyzed.This paper integrates and processes UAV data to complete UAV three-dimensional modeling based on CATIA 3D Modeling software.Meanwhile the laminar flow simulation of wing is finished in the COMSOL Multiphysics software environment.Computational Fluid Dynamics(CFD)simulation of the whole fuselage flow field of UAV in asymmetric mounted cruise flight was carried out in ANSYS Fluent.Secondly,based on the analysis results of the influence factors of aerodynamic disturbance caused by asymmetric mounting,and according to the flight dynamics principle,a mathematical model of the disturbance effect of asymmetric projectile throwing of UAV close to the physical scene is established.The model is balanced,linearized and decoupled.Finally,the mathematical models of longitudinal and lateral systems of fixed-wing aircraft are obtained.Thirdly,based on the mathematical model of UAV asymmetric bombing disturbance effect,the flight control scheme of UAV is analyzed.The relationship between UAV nonlinear system model control law and linear system model control law is discussed in detail.The UDE-based asymmetric bombing effect suppression controller and direct rudder compensation controller are designed and demonstrated.Under the environment of MATLAB Simulink,the simulation of different control schemes is completed,and the working conditions of the controllers before and after the introduction of disturbance suppression strategy are compared and analyzed.As a sub-project of a multi-mission configuration UAV simulation system,this thesis completes the cross-disciplinary research of UAV asymmetric bombing process in control science,aerodynamics and computational fluid dynamics.The core work supports the development of flight simulation software and the hardware-in-the-loop simulation of upper integrated avionics system.