Cooperative Guidance For Hypersonic Glide Missile

The cooperative reentry guidance problem of hypersonic Gliding Missile is a new application scenario of cooperative technology.After reentry gliding,these missiles can obtain effective range that cruise missiles can not reach.They have strong strategic deterrence ability in attack and defense,which is in the long-term interests of our country.Because the targets attacked by such strategic missiles are bound to be of great strategic significance to the enemy,therefore the equipped defense facilities have a great threat to the attack of a single gliding missile.It is an effective means to increase penetration capability and attack effect to conduct multi-missile cooperative research of such missiles.Cooperative reentry guidance technology not only faces all the problems of single member’s reentry guidance,but also demands the terminal time consistency of each member.Compared with conventional missiles or UAVs,reentry flight has no power,wide range of speed and altitude changes,and faces many process constraints,so the existing cooperative guidance technology is not applicable.For unpowered aircraft,the flight time can not be adjusted actively,but can only affect the final arrival time by affecting the flight trajectory.In this paper,cooperative schemes,adjustable intervals,trajectory design and guidance methods based on maneuverability coefficients,cooperative reentry with different positions and different initial states are studied in depth,and the following work is carried out specifically:(1)Based on the analysis of the existing reentry guidance and multi-missile cooperative guidance technology,the main problems faced by underactuated systems such as hypersonic gliding missiles are extracted,and the necessity of cooperative guidance for such reentry vehicles is concluded.Since the multi-member cooperative problem has all the characteristics in the reentry process of a single aircraft,the reentry dynamics model of a single aircraft is established before the cooperative problem is studied.(2)The feasibility of cooperative reentry for hypersonic gliding missiles,the adjustable range of total flight time and the influencing factors are studied.The effects of constraints,specific initial and terminal states,angle of attack and command response speed on total flight time and adjustable interval are discussed respectively.Based on the reachable region problem,the conclusion that the trajectory length is positively correlated with flight time is preliminarily drawn.This paper analyses the principle of the existing method of adjusting reentry time based on the boundary of the heading error/heading error corridor,and draws the conclusion that the total flight time cannot be changed without changing the longitudinal dynamics.(3)A trajectory design and guidance method based on improved maneuver coefficient is proposed.Aiming at the problem of using great circle hypothesis to calculate the trajectory length in current reentry guidance,an improved concept of maneuver coefficient is proposed,which quantifies the actual trajectory length and maneuverability intuitively.The design of reference trajectory is based on the actual trajectory length,and the dynamic heading error corridor is used as the lateral guidance logic.By predicting the range deviation of the terminal,the inversion position and number of the bank angle are adjusted to guide the vehicle to the designated area.The trajectory design and tracking method based on maneuver coefficient provides a breakthrough point for the research of time-controllable reentry problem.(4)A multi-member cooperative reentry guidance method based on reference trajectory is proposed.Firstly,the relationship between trajectory length and total flight time is studied,and the conclusion that the trajectory length corresponds to total flight time one by one is drawn when the design form of reference drag acceleration profile is given.Then,a two-level collaborative framework is proposed with the common trajectory length as the coordination variable.Finally,according to the characteristics of drag acceleration tracking,the time domain information is extracted.The solution of information extraction and collaborative logic transformation will eventually achieve time-consistent reentry collaboration among members.(5)A cooperative reentry guidance method which can directly design the total flight time is proposed.The two-parameter drag acceleration profile design method is adopted,and the reference profile is updated with the idea of prediction and correction.In cooperative mission,the expected total flight time is coordinated by the total flight time information of each member.Then,each member chooses the middle maneuvering coefficient to solve the trajectory with the constraints of trajectory length and total flight time by Using Two-Parameter Newton iteration method,and gives the reentry cooperative framework of the problem.