Research On Multi-missile Cooperative Guidance And Control Technology

With the improvement of the networking and integrated missile defense system,it becomes more and more difficult for a single missile to penetrate the defense and attack the target successfully.Multi-missile cooperative operation can effectively improve the penetration ability of missile by utilizing group advantage and penetration tactics,which has become a key research topic in the department of weapon equipment development and use.This paper mainly focus on the modeling,design,and simulation for some critical problem of missile guidance and control system in the missile cooperative engagement.Assuming the multi-missile in horizontal plane under the fixed communication topology network adopt the "leader-follower" method,the paper selects the position coordinate as the coordination variable,and proposes a distributed coordination based on classical consensus algorithm.We can get the analytical solution form of expected speed and expected acceleration of each missile according to the modern control theory.Considering the matching problem between the formation coordination strategy and the missile’s own performance constraintslike speed and acceleration.The paper raises the concept of convergence cycle and uses the traversal method to solve the weight matrix of the formation coordination strategy so that it can meet the requirements of the missile’s own performance constraints and give the full play to the maneuverability of the missiles.Assuming the multi-missile under distributed communication topology network adopt the "leader-follower" method to attacking the target and the leader missile uses the proportional-guidance method to attack the target,the paper selects the range-to-goas the coordination variable and proposes a coordinationstrategy based on the improved consensus algorithm which can make the range-to-go of the follower missilesconverge to the range-to-go of the leader missile.Then we can get the desired velocity lead angle according to the feedback linearization theory so that the tracking problem of the range-to-go is transformed into the tracking problem of the velocity lead angle.The integrated guidance and control model is established by considering the cooperative strategy and the dynamic characteristics of the missile using the sliding mode control theory.Finally we analyze the influence of the topology switch on the convergence of the coordination strategy and give a simulation verification on it.A cooperative guidance and control law that is adaptable for multiple hypersonic reentry missiles with variable velocities to fly cooperatively in three-dimensional space is presented.During the process of reentry,assuming the back-to-turn reentry missile flies according to designated command of attack angle in pitching,maintains the yaw stability and realizes cooperation through rolling lateral maneuver,then we propose a cooperative strategy which is based on the information of every missile’s range-to-go and its derivate.In the case of variable missile velocity,a velocity lead angle command is obtained.So we can get the desired slope angle of velocity based on the dynamic inverse theory.Due to the inherent property of time-scale separation between the translationaland rotational dynamics of the missile,a partial integrated guidance and control method with a two-loop controller structure is designed,considering the modeling error of missile,the perturbation of aerodynamic coefficients,external disturbance and the nonlinear saturation of missile control input which is solved by using tangent hyperbolic functions and Nussbaum functions.Then the controller is designed based on dynamic surface theory and extended state observer technology.Finally,the controller can control the missile track the specified attack angle,slide angle and the desired slope angle of velocity.