The Research Of Gliding Phase Guidance For Hypersonic Glider Missile

For the guidance of hypersonic glider missile during the gliding phase,considering the high lift-drag ratio and hypersonic speed of this kind of reentryvehicle, the reentry corridor is discussed, a method of trajectory planning andcontrol is proposed as well. The content of this paper mainly includes as following:The three dimensional kinematics model of the reentry glider missile isestablished, while the constraints including heat flux density, dynamic pressure,overload, equilibrium gliding condition are discussed. Based on these constraints,the reentry corridor in velocity-height section is described, which limits the range ofreentry flight parameters.The longitudinal trajectory of the glide missile’s reentry is planned by thestandard trajectory method. With the curve of attack angle referred to the reentry ofshuttle, this paper mainly designed the curve of heeling angle to make sure thelongitudinal trajectory fulfill the reentry corridor and the range of the missile to bemaximum.Based on the planned trajectory, a tracking control method is proposed in thispaper to follow the glider missile’s reentry trajectory. A slide mode controller isdesigned for the longitudinal guidance while a heel angle inversion strategy isproposed for the lateral guidance. The simulation results show the effectiveness ofthe proposed guidance strategy.