The landing of a helicopter in autorotation is formulated as a nonlinear optimal control problem. A unique feature in the present formulation is the addition of path inequality constraints on both the control and the state vectors. The control variable inequality constraint is a reflection of the limitation on the rotor thrust coefficient. The state-variable inequality constraint is an upper bound on the vertical sink-rate of the helicopter during descent. Optimal trajectories are calculated for entry conditions well within the height-velocity (H-V) restriction curve, with the helicopter initially in hover or in forward flight. The optimal solutions exhibited control techniques similar to those used by helicopter pilots in actual autorotational landings. The study indicates that, subject to pilot acceptability, a substantial reduction could be made in the H-V restriction zone using optimal control techniques.
Optimal landing of a helicopter in autorotation
1986-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Optimal landing of a helicopter in autorotation
NTRS | 1988
|Optimal landing of a helicopter in autorotation
NTRS | 1985
|Optimal Landing of a Helicopter in Autorotation
NTIS | 1985
|Optimal landing of a helicopter in autorotation
AIAA | 1988
|Optimal landing of a helicopter in autorotation
AIAA | 1986
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