Abstract: A terrain avoidance method and system for an aircraft includes a collision alarm device and an auto-pilot device including a first determination unit for determining a climbing order with optimal slope for the aircraft, a checking unit for checking whether a first altitude gain at the relief, by applying the optimal slope climbing order, is sufficient for clearing said relief, a finding unit for finding if at least one heading variation value exists, for which the corresponding altitude gain is sufficient to clear the relief, and a switching and calculating unit for applying to the aircraft, if the first altitude gain is sufficient, an optimal slope climbing order with an order to maintain the current heading and, if the first altitude gain is insufficient, a particular climbing order sufficient to clear the relief, with a heading order which corresponds to the selected heading variation value.

Abstract: The invention concerns a terrain avoidance method and system for an aircraft. The system comprises a collision alarm device (3) and an auto-pilot device (5) including means (7) for determining a climbing order with optimal slope for the aircraft, means (12) for checking whether a first altitude gain at the relief, by applying the optimal slope climbing order, is sufficient for clearing said relief, means (11) for finding if there exists at least one heading variation value, for which the corresponding altitude gain is sufficient to clear the relief, and means (17, 22) for applying to the aircraft, if the first altitude gain is sufficient, an optimal slope climbing order with an order to maintain the current heading and, if the first altitude gain is insufficient, a particular climbing order sufficient to clear the relief, with a heading order which corresponds to the selected heading variation value.

Abstract: The piloting system (1) for generating orders for piloting the aircraft according to at least one piloting axis, for example the pitch axis, the roll axis, the yaw axis or the engine thrust control axis, comprises at least two piloting means (2, 3), each of which is capable of calculating the derivative with respect to time of the function which represents the corresponding piloting law and which takes into account the current values of parameters of the aircraft, first means (4) for intercomparing the derivatives calculated by the piloting means (2, 3) and for selecting a derivative; and second means (10) for integrating a selected derivative in such a way as to obtain said piloting order according to said piloting axis.