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Terminal Guidance of an Air-to-Surface Missile Using Optimal Control and Filtering

机译:基于最优控制和滤波的空地导弹末制导

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The optimal control of an air-to-surface missile is determined for a criterion with an integral quadratic weighting of state and control plus a quadratic weighting of terminal state. The controller is then simulated with the nonlinear equations of motion. The control law is capable of correcting errors in both translational and angular position which are determined relative to a nominal path. A Kalman filter is then employed to smooth the state signals which are corrupted by white noise. Representative values of noise, which characterize a range of optical seekers, are used. Greatly improved performance is obtained. (Author)

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