Patent ID: 9120556
Filing Date: 2015-09-01
Classification: B64C,B64D,G05D

Abstract:
1. A method for controlling the pitch of an aircraft, comprising the steps: producing a command for controlled deflection of at least one elevator, in accordance with a standard control law, said controlled deflection command being representative of a manual actuation by a pilot, and applying to the aircraft an actual deflection command depending on said controlled deflection command, comprising the steps of: estimating an unwanted pitch moment by: determining current values of an angle of attack and of a pitch rate of the aircraft, and also an angle of deflection of at least one elevator of the aircraft; determining current values of coefficients forming part of a reference model of a longitudinal movement of the aircraft; calculating a pitch moment Δ{circumflex over (m)}using the current values thus determined, using the following expression: where: q is the current value of the pitch rate of the aircraft; {dot over (q)}is the pitch rate derivative; α is the current value of the angle of attack of the aircraft; αeq is an equilibrium value of the angle of attack of the aircraft; δq is the current value of the angle of deflection of the elevator; and mα, mq, mδq are said current coefficient values; and sending to user means the pitch moment thus calculated, which represents an estimated unwanted pitch moment; calculating a compensation command, from the unwanted pitch moment thus estimated; and summing said compensation command and said controlled deflection command to form said actual deflection command which is applied to the aircraft.