초록 ▼

A method and device for estimating an unwanted pitch moment of an aircraft, and applications to the pitch control of the aircraft. The device estimates an unwanted pitch moment, which can be used to form a compensation command which is added to a standard deflection command with the aim of producing

A method and device for estimating an unwanted pitch moment of an aircraft, and applications to the pitch control of the aircraft. The device estimates an unwanted pitch moment, which can be used to form a compensation command which is added to a standard deflection command with the aim of producing an automatic, active compensation, in real time, for the unwanted pitch moment of the aircraft.

대표청구항 ▼

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, andapplying to the

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, andapplying 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: Δ{circumflex over (m)}={dot over (q)}−mα*(α−αeq)−mq*q−mδq*δq 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; andmα, mq, mδq are said current coefficient values; andsending 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; andsumming said compensation command and said controlled deflection command to form said actual deflection command which is applied to the aircraft. 2. The method according to claim 1, wherein the compensation command δqcANL is calculated using the following expression: δqcANL=−(Δ{circumflex over (m)}/mδq)where:Δ{circumflex over (m)}is the unwanted pitch moment as estimated; andmδq is a coefficient of a reference model. 3. A device for automatic estimation of an unwanted pitch moment of an aircraft, that is, a pitch moment which is not produced by an action by a pilot on a control stick, which has a disruptive effect and which is not wanted, said device comprising a processor configured for: 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, andapplying to the aircraft an actual deflection command depending on said controlled deflection command, comprising the steps of:estimating an unwanted pitch moment by:determining values of the angle of attack and of the pitch rate of the aircraft, and also the angle of deflection of at least one elevator;determining current values of coefficients forming part of a reference model of a longitudinal movement of the aircraft;calculating a pitch moment using the current values thus determined, said third means being formed to calculate the pitch moment Δ{circumflex over (m)}using the following expression: Δ{circumflex over (m)}={dot over (q)}−mα*(α−αeq)−mq*q−mδq*δq where:q is the current value of the pitch rate of the aircraft (AC);{dot over (q)}is the pitch rate derivative;α is the current value of the angle of attack of the aircraft (AC);αeq is an equilibrium value of the angle of attack of the aircraft (AC);δq is the current value of the angle of deflection of the elevator (3); andmα, mq, mδq are said current coefficient values; andcalculating a compensation command, from the unwanted pitch moment thus estimated; andsumming said compensation command and said controlled deflection command to form said actual deflection command which is applied to the aircraft. 4. The device according to claim 3, wherein determining the current coefficient values comprises: determining current values of parameters related to a current flight point of the aircraft;determining said coefficients, using said current parameter values and predetermined tables. 5. A system for controlling the pitch of an aircraft including a device for estimating an unwanted pitch moment, according to claim 3, said system configured for: generating 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 means for applying to the aircraft an actual angle of deflection dependent on said controlled deflection command,calculating a compensation command based on said unwanted pitch moment, estimated using said estimating device; andadding said compensation command to said controlled deflection command to form said actual deflection command that is applied to the aircraft. 6. An aircraft comprising a device according to claim 3. 7. An aircraft comprising a system according to claim 5. 8. The method according to claim 1, wherein said current values of the angle of attack, pitch rate and angle of deflection of the elevator are measured. 9. The method according to claim 1, wherein said step of determining the current coefficient values comprises: a sub-step of determining current values of parameters related to a current flight point of the aircraft (AC); anda sub-step of determining said coefficients, using said current parameter values and predetermined tables.