Method for the steering system of an aircraft in the ground-level flight

摘要

The aircraft can be subjected to a maximum pull-up load factor (51) and a maximum pull-down load factor (52), it is determined by the flight trajectory (63), a horizontal terrain avoidance and threats evtm, corresponding to a control law in roll, then (64) a vertical trajectory of sdt, corresponding to a law (62) for controlling the vertical acceleration. One determines (50), the lateral acceleration of the aircraft on the horizontal path evtm. The portions to the vertical trajectory sdt (64) are determined by the margin of the pull-up load factor (60) is left available by the lateral acceleration on the trajectory evtm. In order to determine the trajectory evtm, a performance of the integral of an index of cost, z + k, y2, z being the height of the aircraft, the lateral deviation between its position and an itinerary and k a weighting coefficient.