Abstract
Knowledge of the safe maneuvering envelope is of vital importance to prevent loss of control aircraft accidents. In this paper, determination of the safe maneuvering envelope is addressed in a reachability framework. The forwards and backwards reachable sets for a set of initial trim conditions are obtained by solving a Hamilton Jacobi partial differential equation through a semi-Lagriangian method. Results obtained using this approach are presented for a nonlinear, high-fidelity, F-16 aircraft model.
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van Oort, E.R., Chu, Q.P., Mulder, J.A. (2011). Maneuver Envelope Determination through Reachability Analysis. In: Holzapfel, F., Theil, S. (eds) Advances in Aerospace Guidance, Navigation and Control. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-19817-5_8
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DOI: https://doi.org/10.1007/978-3-642-19817-5_8
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