The Study On Trajectory Optimization,Guidance And Control For Space Vehicle

With the complication of international relations,all the military powers are seeking more advanced space technology to serve their own interests.As the most important part of space technology applications,space vehicles attracted widespread attention.Space vehicles is a kind of vehicles which delivery the payload from the ground to into the space orbit or from one position of space to another position of space or to the ground,including widely used disposable launch vehicle,partially reusable launch vehicles and completely reusable vehicles.As the most important part of the flight vehicle overall design,trajectory optimization is an essential part of the predemonstration program design phase.In general,spacecraft optimization problem is a very complex nonlinear problems with constraints of various conditions.Optimal control theory provides spacecraft trajectory optimization an effective way to analyze and solve the problem.From the Pontryagin maximum principle to the current intelligent control optimization,trajectory optimization method has been further developed with the improvement of computer technology.This paper studies the application of Gauss pseudospectral method in the space vehicles trajectory optimization and receding horizon control method.The space vehicles studied in this paper involve hypersonic glide vehicle,multi-stage rocket and small spacecraft(as small sapce vehicle).Firstly the reentry trajectory optimization of hypersonic glide vehicle is studied,in which the accuracy of Gauss pseudospectral method for solving optimal control problem is analyzed.And the simulation results show that Gauss pseudospectral method has a good application for solving such trajectory optimization problems,and simultaneously fast convergence.Secondly through the study of multi-stage rocket rising trajectory optimization,Gauss pseudospectral method in solving discrete optimal control problems is analyzed.Finally,the aeroassisted orbit transfer optimization and guidance and control of small spacecraft are studied,including analyzing the influence of the transfer orbit perigee height and lift-drag ratio on the aeroassisted orbit transfer,and comparing the fuel mass between aeroassisted orbit transfer and Hohmann transfer under the fixed orbit change inclination situation.In addition,based on the optimal flight trajectory,receding horizon control is studied.