Integrated guidance and control design of missile with terminal impact angle constraint

Author(s):  
Ke Zhang ◽  
Peng Li ◽  
Ming Lv ◽  
Xiaoma Liu
Author(s):  
Xiang Liu ◽  
Xiaogeng Liang

To solve the multi-interceptor coordination problem and to intercept the target with impact angle constraint, a novel distributed cooperative control algorithm with impact angle constraint based on integrated guidance and control is proposed. First, the mathematic model of integrated guidance and control is established by combining the interceptor-target relative motion model with the dynamic equation of the interceptor on pitch plane. The time varying gain extended state observer is developed to estimate and compensate the unknown disturbance. Based on the estimated value and fast nonsingular dynamic surface sliding control method, the IGC algorithm of leader is given; Then, based on distributed cooperative "leader-follower" model, the cooperative control strategy of multi-interceptor is designed, and gives out speeds in two directions on pitch plane, which are transformed to the command of total velocity and trajectory angle based on kinematic relations. Finally, to control the follower, the time varying gain extended state observer and the dynamic surface sliding control method are adopted. The simulation results demonstrate the effectiveness of the distributed cooperative control algorithm.


Author(s):  
Guanjie Hu ◽  
Jianguo Guo ◽  
Jun Zhou

An integrated guidance and control method is investigated for interceptors with impact angle constraint against a high-speed maneuvering target. Firstly, a new control-oriented model with impact angle constraint of the integrated guidance and control system is built in the pitch plane by combining the engagement kinematics and missile dynamics model between the interceptor and target. Secondly, the flight path angle of the target is estimated by extended Kalman filter in order to transform the terminal impact angle constraint into the terminal line-of-sight angle constraint. Thirdly, a nonlinear adaptive sliding mode control law of the integrated guidance and control system is designed in order to directly obtain the rudder deflection command, which eliminates time delay caused by the traditional backstepping control method. Then the Lyapunov stability theory is used to prove the stability of the whole closed-loop integrated guidance and control system. Finally, the simulation results confirm that the integrated guidance and control method proposed in this paper can effectively improve the interception performance of the interceptor to a high-speed maneuvering target.


2020 ◽  
Vol 2020 ◽  
pp. 1-19
Author(s):  
Zhenhua Fu ◽  
Kuanqiao Zhang ◽  
Qintao Gan ◽  
Suochang Yang

Aiming at the problem of impact angle constraint and input saturation, an integrated guidance and control (IGC) algorithm with impact angle constraint and input saturation is proposed. A three-channel independent design model of missile IGC with impact angle constraint is established, and an extended state observer with fast finite-time convergence is designed to estimate and compensate model errors and coupling relationship between channels. Based on the nonsingular terminal sliding mode control and backstepping control, the IGC three-channel independent design is completed. Nussbaum function and an auxiliary system are introduced to deal with the input saturation. The Lyapunov function is constructed to prove the finite-time convergence of the IGC algorithm. The missile six-degree-of-freedom simulation results show the effectiveness and superiority of the IGC algorithm.


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