METHOD FOR CONTROLLING AN AIRCRAFT IN FLIGHT AT VERY LOW ALTITUDE.

摘要

P As the aircraft is capable of a maximum nose-up load factor (51) and a peak load factor (52), a horizontal terrain avoidance trajectory and EVTM threats are determined in flight (63). corresponding to a rolling control law, then (64) a vertical track SDT, corresponding to a vertical acceleration control law (62). The lateral accelerations of the aircraft are determined (50) on the horizontal trajectory EVTM. The nose-up portions of the vertical trajectory SDT are determined (64) by the nose-up load factor margin (60) left available by the lateral accelerations on the EVTM trajectory. To determine the trajectory EVTM, a performance index consisting of the integral of a cost index Z + K Y2 is minimized, Z being the altitude of the aircraft, Y the lateral deviation between its position and a route of reference and K a weighting coefficient. / P