Trajectory Planning And Reentry Guidance For Boost-glide Vehicle

This paper focuses on the near space vehicle represented by HTV-2,and studies its dynamics modeling,trajectory planning,and strike phase guidance and control.The paper is mainly divided into the following contents:Firstly,the dynamic models of this paper are established,including the detailed models of the earth and the atmosphere.The detailed and brief dynamic models of the propellant stage and the glide body are given in detail,which lays a foundation for the trajectory optimization of quasi-balanced glide and sequential convex optimization in the following paper.Furthermore,the altitudinal velocity at different constant angles of attack is analyzed,which provides a basis for the design of various index parameters of the glider.Secondly,the trajectory planning method based on the quasi-balanced glide was studied.After studying the angle-velocity profile,altitude-velocity profile and heeling angle-velocity profile of the aircraft,the longitudinal and lateral flight corridors of the aircraft were given,and the trajectory of the aircraft was preliminarily designed.Then,this paper analyzes the flight capability,and analyzes the range of its flight reachable area according to the residual range theory.Then,dynamic pressure and other spacecraft reentry trajectory constraints planning,through the dimensionless,expansion system dimensions,dynamics equation discrete parameterization,liberalization of constraint equations are linearized,time,finally,it is concluded that sequence convex optimization algorithm with penalty function.In addition,in order to introduce the relaxation factor into the loose constraint,this paper uses the method of introducing the relaxation factor into the optimization index for trajectory optimization.According to the sequential convex optimization algorithm,this paper simulates the different stages of the trajectory of the aircraft by changing the constraint conditions successively,and gives the trajectory of the whole segment of the aircraft.Finally,the guidance method of the strike section is studied.In this paper,the proportional guidance method is used to strike the target,and the capability range of the proportional guidance method is analyzed.Finally,combining attitude dynamics and attitude control,a six-DOF dynamics model is established for simulation,which verifies the correctness of the guidance method and capability range analysis.