Trajectory Planning And Guidance Of Boost Glider

Boost glider is launched to a certain height by boost rocket.Depending on its large lift drag ratio shape,it glides in the upper atmosphere at hypersonic speed for a long time and a long distance.It has the respective advantages of ballistic missile and cruise missile,and has the characteristics of high speed,high altitude,long range and strong maneuverability.In the hope of achieving long-range rapid and accurate strike and power delivery,its application prospect is very broad.In this paper,taking attacking time sensitive targets in the air as the background,based on the analysis of the trajectory characteristics and mission of each flight phase,the trajectory planning and terminal guidance of ascent phase and reentry phase are studied.Firstly,according to the different flight characteristics of boost phase,reentry phase and terminal guidance phase,the motion mathematical model of active phase,reentry phase and relative motion equation of terminal guidance are established respectively,and the atmospheric model and the relevant supplementary equations for solving the motion parameters of aircraft are given,which provide reference for the following active phase trajectory design,reentry phase and terminal guidance phase It lays a foundation for reentry trajectory planning and terminal guidance research.Secondly,the trajectory design task of the active phase is analyzed.It is pointed out that the active phase is mainly divided into vertical rising phase,turning phase and constant phase.The design parameters of the active ph ase are extracted,that is,the constant change rate of the maximum turning angle of attack and pitch angle program is taken as the design variables,and the terminal longitude and latitude and trajectory inclination angle of the active phase are set as th e terminal constraints for trajectory design;For the case that the design quantity is more than the constraint quantity,an improved Newton iterative method is proposed,which can be applied to the case that the iterative control quantity is more than the terminal constraint quantity;In order to limit the control quantity to a reasonable range,a trigonometric function control quantity conversion met hod of iterative maximum and minimum control quantity is proposed.The trajectory design process of active phase is introduced in detail,and the trajectory design simulation of active phase is carried out.Then,according to the requirement of hitting time sensitive target,a time constrained reentry trajectory design method is proposed.The roll angle profile is designed as a quadratic function,so that both range and time can be constrained at the same time;For trajectory design of reentry phase,a trajectory design method based on reverse calculation is proposed.This method considers trajectory design of reentry phase and active phase at the same time.Firstly,a preset reentry point is obtained by reverse integration,and then the active phase is verified by trajectory iteration of active phase,so as to obtain feasible trajectory of active phase and reentry phase,and complete the task of trajectory planning.Finally,in order to achieve accurate attack and effective damage to the target,the problem of terminal guidance is studied.Firstly,the proportional guidance method is proposed to solve the guidance problem of attacking the ai r target in the down phase.Considering the better damage to the target,the trajectory shaping guidance law is proposed.The two guidance laws are verified by simulation.In a word,this paper puts forward the methods of trajectory design in active phase and trajectory planning in reentry phase,and studies the re lated technologies of terminal guidance.