Research On HTV Trajectory And Ascent Guidance Algorithm Simulation

HTV missile has been a heated research topic recently,for it combines the strengths of ballistic missile and winged missile.Briefly,HTV missile is composed of two parts,booster and glide warhead.The first part pushes the missile up to several kilometers,and then making use of its strong lift-drag ratio,the second part takes down the target,either by jumping towards higher sky or swoop directly downwards.In this paper,an innovative HTV missile is considered: It is shut down entirely in aerosphere and is forced to fly in lower trajectory flying mode,later in its ascent,guidance is achieved by designing its trajectory.This paper studies the history and the ad-hoc of research on abroad HTV missile,particularly the ascent trajectory design and guide methods.Several such methods,along with their underlying ideas are summarized;in terms of both is strengths and weakness.The research trend in the field is also analyzed.Coordinate system definition and transformation between coordinate systems are introduced;HTV missile's centroid kinetic model are built,and conducted a dimensionless,for the sake of simplifying the optimization algorithm.Based on literature review and analysis,“direct shooting method + sequential quadratic programming” is chosen as the trajectory optimization method.Specifically,gradient calculation,matrix updates,penalty function and one-dimensional search are used and slightly revised to solve parameter optimization problem,which serves as the theoretical foundation for boost-glide missile ascent trajectory design.Based on optimization theory and iteration theory separately,two new trajectory design method are proposed,which also take into account engineering reality.In the one that's based on optimization theory,mode of program angles and process constrain are introduced,and from two independent simulation,attack angle and attitude angle are changing steadily,and final height,speed,trajectory angle meet the constrain.In the one that's based on iteration theory,a model is described,three parameters are tuned,and the simulation shows that trajectory configuration in reason,the final status all meet the constrain.Finally,a close-loop guidance is proposed based on the assumption that solid-powered HTV missile without burn control.Specifically,the first flight segment and glide segment uses tracking guidance,while the sec ond segment uses approach optimal guidance.A Monte-Carlo simulation,which takes into account external disturbance and system error shows that placement of the entire shooting range is not extensive,and is relevantly uniformly distributed.The proposed method performs well.