Research On Optimization Of Flight Strategy Of Loitering Munition Based On Wing Bump Technology

In recent years,the development of loitering munitions has attracted more and more attention from all countries.The research on loitering munitions have made rapid progress,which puts forward higher requirements for the tactical indicators of loitering munitions,especially the requirements for good aerodynamic characteristics.The aerodynamic parameters of the wings of loitering munitions can be improved by adding the wing bumps,so that the maneuverability and endurance can be improved to a certain extent.In this thesis,four phases of loitering munition flight are divided according to different mission and flight attitude: climb flight phase,stable flight phase,loiter flight phase and guidance attack phase;a kind of basic parameters and mission of loitering munition is given by referring to a foreign research plan of loitering munition;a basic flight scheme is proposed by combining flight phase and mission.It can realize a series of tactical requirements,such as crossing the enemy defense,reconnoitering the target area and attacking the predetermined target.According to the proposed flight plan,a control system integrating program angle control,overload control,altitude control,tilt turn control,roll stability control and other control methods is designed to ensure that the loitering munition can stably fly according to the preset flight plan The flight process of the loitering munition under the designed control system is analyzed,and the feasibility of the system is verified.The feasibility of optimizing the flight strategy by improving the aerodynamic parameters is discussed.It is considered that the wing bump is conducive to improving the available overload of the missile body,saving the engine thrust,thus improving the range and extending the endurance time.Nonlinear robust control is adopted to improve flight stability;mathematical software MATLAB is used for simulation analysis.