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In this paper, terminal guidance problem for aerodynamic missile with side window detection is considered. Firstly, the description of side window constraint is given. In order to formulate this guidance problem as a control problem with input constraint, side window constraint is transformed into attack angle constraint. Then the terminal guidance law is designed based on predictive control. Simulation...
For a class of continuous non-smooth attitude controllers for spacecraft, input-to-state stability theory of nonlinear systems is used to conduct performance analysis, and the conditions of attenuation against exogenous disturbances and robustness against uncertainties are given for the closed-loop systems. First, sufficient conditions for the input-to-state stability are given for a class of homogeneous...
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