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In this paper, an adaptive integrated guidance and control(IGC) law is proposed for the missile intercepting the maneuvering target with impact angle constraint. Considering the parameter uncertainties, a new IGC model is established. Subsequently, the dynamic surface control and adaptive technique are combined to design the adaptive IGC law. Finally, the simulation results are provided to verify...
This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error...
Based on backstepping control technique, a novel adaptive integrated guidance and control (IGC) law is presented for missile intercepting maneuvering target with input saturation. To deal with the uncertainties in the IGC system, adaptive control technique is utilized to estimate the upper bounds of the uncertainties. Moreover, an auxiliary system is designed to cope with the input saturation. The...
This paper deals with LPV (Linear Parameter Varying) eigenstructure assignment in BTT (bank to turn) missile attitude control using state feedback. Based on general Sylvester equations with varying coefficients, very simple parametric expressions in direct closed forms for both the closed-loop eigenvector matrix and the feedback gains are established in terms of the closed-loop eigenvalues and a group...
This paper deals with a dynamical laser antimissile problem. The laser antimissile system can destroy many targets in a short time, the attacking sequence plays an important role in practical implement. This laser antimissile problem can be seen as a dynamical traveling salesman problem. This paper introduces an enhancing algorithm to solve this problem based on three exchange strategies - the near...
The problem of integrated guidance and control for homing missiles is considered. A time-varying integrated guidance and control model of the pitch plane is formulated, and further changed into the normal form by nonlinear coordinate transformation. In order to deal with the unmatched and unknown bounded uncertainties, an adaptive auxiliary system is first constructed to approximate the normal plant,...
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