Research On Blended Control Method For Missile With Lateral Thrust And Aerodynamic Of Orbit Control

Recently,hypersonic vehicles with high maneuverability have developed rapidly,which has brought new challenges to the original anti-aircraft missile interception system.The traditional pure gas-powered control missiles have been difficult to meet the ever-changing requirements of the battlefield,so compound control missiles with lateral direct force emerged at the historic moment.This article takes the track-controlled compound control missile as the research object,and studies the problems of the compound control missile.The main research content includes the missile's attitude control method and the track control direct force and aerodynamic command distribution method.It has certain theoretical significance and actual value.The research content includes the following aspects:Firstly,modeling is based on the dynamics and kinematics equations of the composite control missile and the relative motion equations of the missile target,and the model is simplified according to the research needs to obtain the attitude control model,which lays the foundation for the subsequent design of the attitude control law.Secondly,the auto-disturbance control method is used to design the attitude control law.In order to reduce the influence of external disturbances and model uncertainties on system stability,an auto-disturbance control method was introduced,and an expanded state observer was used to estimate and compensate the system disturbances and uncertainties,and an attitude control law was designed;further aimed at ADRC In the control method,the problem of slow ESO convergence speed is improved.The expanded state observer is a sliding mode observer with faster convergence speed.Based on this,the design of the three-channel attitude control law is completed;the simulation compares and analyzes the two attitude control methods The performance is good or bad,which verifies the superiority of this method.Third,research on the overload instruction allocation algorithm.For the orbit-controlled compound control missile,the relative distance of the projectile and the overload tracking error are used as the key parameters of the command assignment parameters.The fuzzy control theory is used to establish the fuzzy rules.The particle swarm algorithm is used to solve the combined cost of overload tracking deviation and fuel consumption.Optimal problem,complete the design of the overload instruction distribution algorithm;and take the circular maneuvering target as an example for simulation verification.Finally,the above research results are applied to the six-degree-of-freedomsimulation experiment of the orbit-controlled compound control missile.For the two common maneuvering targets,the attitude control law and overload command distribution algorithm designed in this paper are used.The six-degree-of-freedom simulation results verify The effectiveness of the design method in this paper.