Research On Energy Management Method Of High Performance UAV Unpowered Return To Landing

Based on the development history and research status of advanced unmanned aerial vehicles at home and abroad,combined with the research trend of hypersonic unmanned aerial vehicle(UAV)in China,this paper studies the energy management related issues in the unpowered return process of high-altitude and high-Mach UAV.First of all,the aircraft ontology is modeled and analyzed.In the initial design,the aircraft body was modeled in the MATLAB/SIMULINK simulation environment,and the static stability,maneuverability and other related qualities of the UAV were analyzed according to the aerodynamic characteristics of the aircraft.According to the preset flight path,the guidance and control law module of the UAV is designed,including the following modules: pitch guidance command,roll guidance command,yaw guidance command;The stability augmentation control law module includes: pitch control augmentation control law,roll control augmentation control law,yaw control augmentation control law.When the controller is designed,it is planned longitudinally and lateral-directionally respectively.In the longitudinal guidance control,the longitudinal control logic is designed by tracking the track inclination,expected glide slope and sink rate.In the lateral-directional guidance and control,the lateral-directional control logic is designed by following roll Angle,track Angle and lateral-directional cross-line flight.Through the linearization analysis of the model small disturbance,the control quality of the UVA is observed in time domain and frequency domain respectively so that to design a robust controller and ensure that the UVA has the ability to return safely in accordance with the set glide slope.The unmanned aerial vehicle researched in this subject has entered the low-altitude area and prepared to arrive at the ground after flying at supersonic speed,transonic speed and subsonic speed from the high-altitude and high-Mach state.The entire unmanned aerial vehicle landing process is unpowered,so it is very important to control the energy of the UVA within a reasonable range.Aiming at the characteristics of wide range of airspace and many flying missions of the UAV return process,the UAV return process is divided into four major stages,including the entry section,energy management section,approach landing section,and exponential pull-up section.When the UAV enters the approach landing stage,the total energy should be within a reasonable range to ensure that the speed brake can be used to control the speed of the aircraft in low altitude.Therefore,in the energy management stage,this paper combines the characteristics of the drone to plan out the energy consumption scheme of turning to S in detail,and verifies the reliability of the entire S turning.In the actual flight process of the UAV,there must be deviation between the actual aerodynamic data of the aircraft and the relevant data of the wind tunnel test used in this paper.Therefore,it is necessary to ensure that the UAV controller still has good robustness in the case of deviation in the initial conditions,block structure,aerodynamic data and atmospheric environment,and the energy management scheme plays an important role in regulating energy to ensure the UVA can land safely.In order to evaluate the control characteristics and energy management ability of UAV,pull deviation analysis is carried out under various reasonable combinations with practical significance.In the environment of MATLAB/Simulink,the aircraft model is built,and the control law with good stability is designed.The simulation analysis of large resistance,nominal resistance and small resistance is carried out for the energy management scheme proposed in this paper under reasonable assumptions.At the same time,wind speed interference and structural error analysis are added to verify the safe and reliable return ability of the aircraft in the energy corridor.