Research On Reconfigurable Control System Design Of Heavy Launch Vehicle

Boost-glide missile has been a heated research topic recently, for it combinesthe strengths of ballistic missile and winged missile. Briefly, boost-glide missile iscomposed of two parts, booster and glide warhead. The first part pushes the missileup to several kilometers, and then making use of its strong lift-drag ratio, thesecond part takes down the target, either by jumping towards higher sky or swoopdirectly downwards. In this paper, an innovative boost-glide missile is considered:It is shut down entirely in aerosphere and is forced to fly in lower trajectory flyingmode, later in its ascent, guidance is achieved by designing its trajectory.This paper studies the history and the ad-hoc of research on abroad boost-glidemissile, particularly the ascent trajectory design and guide metho ds. Several suchmethods, along with their underlying ideas are summarized; in terms of both isstrengths and weakness. The research trend in the field is also analyzed.Coordinate system definition and transformation between coordinate systemsare introduced; Boost-glide missile’s centroid kinetic model are built, andconducted a dimensionless, for the sake of simplifying the optimization algorithm.Based on literature review and analysis,"direct shooting method+sequentialquadratic programming" is chosen as the trajectory optimization method.Specifically, gradient calculation, matrix updates, penalty function andone-dimensional search are used and slightly revised to solve parameteroptimization problem, which serves as the theoretical foundation for boost-glidemissile ascent trajectory design.Based on optimization theory and iteration theory separately, two newtrajectory design method are proposed, which also take into account engineeringreality. In the one that’s based on optimization theory, mode of program angles andprocess constrain are introduced, and from two independent simulation, attack angleand attitude angle are changing steadily, and final height, speed, trajectory anglemeet 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 configurationin reason，the final status all meet the constrain.Finally, a close-loop guidance is proposed based on the assumption that solid-powered boost-glide missile without burn control. Specifically, the first flightsegment and glide segment uses tracking guidance, while the second segment usesapproach optimal guidance. A Monte-Carlo simulation, which takes into accountexternal disturbance and system error shows that placement of the entire shootingrange is not extensive, and is relevantly uniformly distributed. The proposedmethod performs well.