Research On Maneuver Strategy And Guidance Algorithm For Hypersonic Glide Vehicles

Hypersonic glide vehicle which has many advantages such as high speed,strong penetration ability,wide attack range and good attack effect has become the focus of current research by the world’s military power.Because of the complicated and variable flight environment,hypersonic glide vehicle is affected by multiple path constraints and unknown disturbance in different flight phase.It is also needed to avoid no-fly zones,maneuver and fly to object with different directions.To solve the problems,related research is carried out in this dissertation.First of all,based on the characteristics of hypersonic glide vehicle,dynamics and motion model are presented.At the same time,path constraints in glide phase are analyzed.The mathematical model of no-fly zone and maneuver zone are given.These models lay a foundation for further research.Secondly,sliding mode active disturbance rejection gliding guidance law is proposed for the purpose of improving the guidance system robustness and satisfying varieties of path constraints and terminal constraints.Aiming at the problem of gliding guidance with no-fly zones,a novel gliding online no-fly zone avoidance strategy is proposed.To make maneuver more effective,different maneuver approaches are given.Effectiveness of maneuver is analyzed by the simulation way.And then,aiming at the problems of guidance law and maneuver strategy in dive phase,the guidance strategy is proposed by taking advantage of symmetry principle to avoid waste of energy.By analyzing path constraints and point’s constraints in dive phase,it is found that the maximum heat flux has to be taken into account as a path constraint in dive phase.Difference between need speed and terminal velocity obtained by numerical prediction,multiplied by proportion coefficient,can be used as amplitude of maneuver overload.In this way,maneuver and speed control can be completed.At the same time,maximum heat flux constraint can be satisfied.Finally,to solve the problems of handover between glide phase and dive phase,the effect of two factors handover height and speed on the dive phase is analyzed.And a method to analytical estimate handover speed is presented.Compared with simulation result,the accuracy of the estimation is checked.Considering with the handover,simulation results of glide phase together with dive phase demonstrate the effectiveness of the proposed method sufficiently.In general,the dissertation expands the guidance theory for hypersonic glide vehicles.The proposed algorithms are usable in practice,and can provide some reference for the entry guidance of a hypersonic glide vehicle.