Modelling and Guidance of a Small Conventional Launcher
نویسندگان
چکیده
This paper illustrates the main results achieved in the context of a project, financed by the Italian Space Agency, concerning the modelling and control of next generation small conventional space launchers. The first part of the paper describes the mathematical translational model of the launcher. Then the derivation of the optimal trajectory to be tracked by the launcher will be illustrated. Such trajectory has been obtained via a direct optimisation approach, which allows reformulating the original continuous optimal control problem as a non-linear programming problem, i.e. as a finite dimensional optimisation problem. Finally the angular motion model is detailed.
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