Research On Guidance And Control Technology Of High Speed Gliding Aircraft

The high-speed glide vehicle is propelled to a glide point by a rocket or a launcher,and the engine is started or aerodynamically pulled up and climbed at an appropriate altitude,thereby achieving hypersonic flight across the atmosphere.Because of its high flight speed and long range and strong penetration ability,the high-speed gliding aircraft has important strategic significance for its research.Compared with other near-space vehicles,in order to improve the lift-drag ratio to meet the requirements of long-distance flight,the high-speed gliding aircraft usually adopts a plane-symmetric aerodynamic layout.This structure and poor flight conditions make the mathematical model of the aircraft show the characteristics of strong nonlinearity,strong coupling,and uncertainty,which bring new challenges to the design of guidance and control systems.The research content and results of this article are as follows:1)A six-degree-of-freedom mathematical model for the guidance and control system of high-speed gliders is established,including dynamic models,kinematic models,and parameter uncertain models.For the cruise phase attitude control system,the dynamic equations around the center of mass are decomposed separately,and then the sliding mode variable structure control method is designed based on the decomposed equations,which provides the premise for the design and analysis of the high-speed gliding vehicle guidance control system.2)Based on the sliding mode control theory,the cruise control system of the cruise stage was designed respectively.First,the feedback linearization expression around the centroid dynamics equation is obtained according to the solution step of the dynamic inverse;then the sliding mode surface containing attitude angle and attitude angle change rate information is designed,and the control torque and rudder are obtained by combining the feedback linearization expression The expression of declination.Finally,based on the six-degree-offreedom simulation model of the high-speed gliding vehicle,the rationality of the designed cruise control system is verified3)Aiming at the high-speed and high-angle flight characteristics of the final guidance section of the high-speed gliding aircraft,an optimal guidance law with end angle constraints is derived to meet the mission requirements of high hit accuracy and strict end angle constraints.The end line-of-sight angle indirectly controls the final pitch angle of the aircraft.4)In order to improve the maneuverability of the course of the high-speed gliding aircraft from the cruise section to the descent attack section,in order to improve its heading maneuverability,the BTT-90 turn guidance rate was designed.The strategy is converted into the roll angle command of the projectile to realize the coordinated turning maneuver of the high-speed gliding aircraft.5)Based on the six-degree-of-freedom simulation model of the high-speed glider,the designed guidance and control system was simulated and verified.The simulation results show that the cruise segment flight control system can complete the stable tracking of commands,and the terminal guidance system can meet the requirements of hit accuracy and end angle constraints at the same time,verifying the correctness of the design method.