Abstract: A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.

Abstract: A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.

Abstract: A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.

Abstract: A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.