[특허]Method and device for reducing on an aircraft lateral effects of a turbulence

Airbus Operations (SAS)

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Method and device for reducing on an aircraft lateral effects of a turbulence

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/16 G05D-001/08 G06F-019/00
미국특허분류(USC)	701/003; 701/010; 701/011; 244/076C
출원번호	US-0847748 (2010-07-30)
등록번호	US-8340840 (2012-12-25)
우선권정보	FR-09 03820 (2009-08-03)
발명자 / 주소	Puig, Stéphane
출원인 / 주소	Airbus Operations (SAS)
대리인 / 주소	Novak Druce + Quigg LLP
인용정보	피인용 횟수 : 1 인용 특허 : 7

초록

A method and device for reducing on an aircraft lateral effects of a turbulence. The device (1) includes means (2, 3, 5, 7, A1, A2) for calculating and applying a roll control command and a yaw control command enabling the side effects generated by a turbulence event to be attenuated on the aircraft.

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1. A method for attenuating on an aircraft (A) the side effects generated by at least one turbulence event undergone by this aircraft (A) upon a flight, method according to which, upon a flight of aircraft (A), automatically and iteratively, comprising: a) estimating a roll moment of aircraft (A), which is due to wind and a yaw moment of the aircraft (A), which is also due to wind;b) measuring the current values of aircraft (A);c) using said estimated roll moment, said yaw moment and said measured current values, calculating: a roll control command for at least one first controllable movable member (20, 21) which is likely to act on the roll of aircraft (A), said roll control command being such that, as applied to said first movable member (20, 21), it enables the roll disturbances due to wind to be minimised on aircraft (A); anda yaw control command for at least one second controllable movable member (22) which is likely to act on the yaw of aircraft (A); andd) applying: said roll control command to said first movable member (20, 21); andsaid yaw control command to said second movable member (22),a method according to which, further at step c): said roll control command δl and said yaw control command δr are calculated, using the following mathematical expression: [δ⁢⁢lδ⁢⁢r]=(C⁢⁢l⁢⁢δ⁢⁢lC⁢⁢l⁢⁢δ⁢⁢rC⁢⁢n⁢⁢δ⁢⁢lC⁢⁢n⁢⁢δ⁢⁢r)-1⁡[Δ⁢⁢C⁢⁢l⁢⁢wΔ⁢⁢C⁢⁢n⁢⁢w]wherein: Clδl and Clδr are roll moment coefficients;Cnδl and Cnδr are yaw moment coefficients;ΔClw is said roll moment due to wind; andΔCnw is said yaw moment due to wind; and said yaw control command is calculated so that, when applied to said second movable member (22), said yaw control command enables both the side effects generated by the turbulence event and the side effects generated by applying said roll control command to said first movable member (20, 21) to be compensated for on aircraft (A). 2. The method according to claim 1, wherein calculating a sideslip value of the aircraft, and then using this sideslip value thus calculated, at step a), for estimating roll and yaw moments. 3. The method according to claim 2, wherein, for calculating said sideslip value β: a value βl illustrating the derivative with respect to sideslip time is calculated using the following expression: βl=Ay+rl·Δy+rl·Δx+g·cos θ·sin φ−·cos α+p·sin αwherein: Ay is the lateral acceleration;Δx is the longitudinal distance between accelerometers used for measuring the lateral acceleration and the centre of gravity of aircraft (A);r is the yaw rate and rl is the derivative with respect to time of r;φ is the roll angle;α is the incidence angle; andθ is the trim; and this value βl is integrated so as to obtain said sideslip value β. 4. The method according to claim 1, wherein at step a), for estimating said roll moment ΔClw due to wind: a global roll moment DCl is determined, using the following expression: DCl=ΔL/(ρ·V2·S·co/2)wherein: ΔL, is a coefficient which is calculated from measured values of parameters of aircraft (A);ρ is the density of air;V is the air speed of aircraft (A);S is the airfoil area of aircraft (A); andco represents the mean aerodynamic chord of aircraft (A); and said roll moment ΔClw is calculated using the following expression: ΔClw=DCl−Clδl·δl−Clδr·δr−Clβ·β−Clβ·β−CIp·p·co/V−CIr·r·co/V wherein: CIδl, Clδr, Clβ, CIp and CIr are predetermined coefficients;δl is a roll control command;δr is a yaw control command;β is a sideslip value; andp and r are roll and yaw rates. 5. The method according to claim 1, wherein at step a), for estimating said yaw moment ΔCnw due to wind: a global yaw moment DCn is determined using the following expression: DCn=ΔN/(ρ·V2·S·co/2)wherein: ΔN is a coefficient which is calculated from measured values of parameters of aircraft (A);ρ is the density of air;V is the air speed of aircraft (A);S is the airfoil area of aircraft (A); andco represents the mean aerodynamic chord of aircraft (A); andsaid roll moment ΔCnw is calculated using the following expression: ΔCnw=DCn−Cnδr·δr−Cnβ·β−Cnr·r·co/V wherein: Cnδr, Cnβ and Cnr are predetermined coefficients;δr is a yaw control command;β is a sideslip value; andr is the yaw rate. 6. The method according to claim 1, wherein: at a step prior to step d):at least one characteristic parameter relative to the roll and/or yaw is determined; andthis characteristic parameter is compared to a threshold value; andat step d), said roll and yaw control commands are applied, only if said characteristic parameter is higher than said threshold value. 7. A device for attenuating on an aircraft (A) the side effects generated by at least one turbulence event undergone by this aircraft (A) upon a flight, said device (1) comprising: means (3) for estimating a roll moment of aircraft, which is due to wind, as well as a yaw moment of the aircraft, which is also due to wind;means (2) for measuring the current values of parameters of aircraft (A);means (7) for calculating, using said estimated roll and yaw moments and said measured current values:a roll control command for at least one first controllable movable member (20, 21) which is likely to act on the roll of aircraft (A), said roll control command being such that, when applied to said first movable member (20, 21), it enables the roll disturbances due to wind to be minimised on aircraft (A); anda yaw control command for at least one second controllable movable member (22) which is likely to act on the yaw of aircraft (A); andmeans (A1, A2) for applying:said roll control command to said first movable member (20, 21); andsaid yaw control command to said second movable member (22),said means (7) for calculating the roll and yaw control commands being formed so as to:calculate said roll control command 81 and said yaw control command δr, using the following mathematical expression: [δ⁢⁢lδ⁢⁢r]=(C⁢⁢l⁢⁢δ⁢⁢lC⁢⁢l⁢⁢δ⁢⁢rC⁢⁢n⁢⁢δ⁢⁢lC⁢⁢n⁢⁢δ⁢⁢r)-1⁡[Δ⁢⁢C⁢⁢l⁢⁢wΔ⁢⁢C⁢⁢n⁢⁢w]wherein:Clδl and Cnδr are roll moment coefficients;Cnδl and Cnδr are yaw moment coefficients;ΔClw is said roll moment due to wind; andΔCnw is said yaw moment due to wind; andcalculate said yaw control command such that, when applied to said second movable member (22), said yaw control command enables both the side effects generated by the turbulence event and side effects generated by applying said roll control command to said first movable member (20, 21) to be compensated for on aircraft (A). 8. An aircraft system, wherein: at least one first controllable movable member (20, 21) which is likely to act on the roll of aircraft (A);at least one second controllable movable member (22) which is likely to act on the yaw of aircraft (A); anda device (1) such as that specified in claim 7, for attenuating on aircraft (A) the side effects generated by at least one turbulence event undergone by this aircraft (A) upon a flight, by determining control commands and applying them to said first and second movable members (20, 21, 22). 9. An aircraft, comprising a device (1) such as the one specified in claim 7.

이 특허에 인용된 특허 (7)

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De Magalhães Gomes, Ierko. Asymmetry-proof multi-engine aircraft. USP20190310227138.

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Method and device for reducing on an aircraft lateral effects of a turbulence

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Method and device for reducing on an aircraft lateral effects of a turbulence

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