[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
미국특허분류(USC)	701/010; 701/007; 701/011; 244/076C; 244/177; 244/194
출원번호	US-0368139 (2009-02-09)
등록번호	US-8219266 (2012-07-10)
우선권정보	FR-08 00701 (2008-02-11)
발명자 / 주소	Puig, Stephane Byzery, Romeo
출원인 / 주소	Airbus Operations SAS
대리인 / 주소	Dickinson Wright PLLC
인용정보	피인용 횟수 : 4 인용 특허 : 10

초록
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Disclosed is a method and device for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight. The lateral effects are attenuated by applying a roll control order to control a first controllable movable member that acts on aircraft roll and minimizes aircraft roll-wise disturbances due to wind, and a yaw control order that controls a second controllable movable member to act on aircraft yaw. The roll and yaw control orders are calculated based on a sideslip value of the aircraft, while the yaw control order i...

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1. A method for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight, the method comprising the steps of: a) estimating, by a roll moment estimator, a roll moment of the aircraft due to wind;b) measuring current values of first aircraft parameters;c) calculating, by a calculating unit, based on said estimated roll moment and said measured current values, the following: a roll control order to control at least one first controllable movable member to act on aircraft roll, said roll control order applied to said first movable member to minimize aircraft roll-wise disturbances due to wind; anda yaw control order to control at least one second controllable movable member to act on aircraft yaw; wherein:said roll control order is applied to said first movable member,said yaw control order is applied to said second movable member, andin step c): said roll and yaw control orders are calculated based on a sideslip value representing sideslip value of the aircraft due to the wind; andsaid yaw control order is calculated as a function of said roll control order so that said yaw control order compensates for aircraft lateral effects due to turbulence and lateral effects due to application of said roll control order to said first movable member,wherein in step a), to estimate said roll moment due to the wind:a global roll moment DCl is determined with the aid of the following expression: DCl=ΔL/(ρ·V2·S·co/2) in which:ΔL is a coefficient which is calculated on the basis of measured values of parameters of the aircraft;ρ is the density of the air;V is the air speed of the aircraft;S is the surface area of the airfoil of the aircraft; andco represents the mean aerodynamic chord of the aircraft;a roll moment ΔClδl which is engendered by the current control of movable members of the aircraft, which act on the roll, is determined; andsaid roll moment ΔClW is calculated with the aid of the following expression: ΔClw=DCl−ΔClδl. 2. The method as claimed in claim 1, wherein: in step a), the following operations are further carried out: current values of second parameters of the aircraft are measured;based on said measured current values of said second parameters, horizontal wind existing outside the aircraft at a current position of the aircraft is calculated;based on said calculated horizontal wind, a lateral component Vv1 of wind existing outside the aircraft at the current position is deduced; andsaid sideslip value representing sideslip due to the wind is calculated according to the following expression: βv1=−Vv1/V, V being a measured air speed of the aircraft, where βv1 is the sideslip value; andin step c), the sideslip value is applied to calculate said control orders. 3. The method as claimed in claim 1, wherein: in step a): a sidewind Vv2 existing in front of the aircraft is measured by a measurement unit onboard the aircraft; anda sideslip value βv2 representing sideslip due to the wind is calculated according to the following expression: βv2=−Vv2/V, V being a measured air speed of the aircraft; andin step c), the sideslip value βv2 is applied to calculate said control orders. 4. The method as claimed in claim 1, wherein: a characteristic parameter relating to the roll is determined; andthe characteristic parameter is compared with a threshold value; andsaid roll and yaw control orders are applied when said characteristic parameter is greater than said threshold value. 5. A method for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight, the method comprising the steps of: a) estimating, by a roll moment estimator, a roll moment of the aircraft due to wind;b) measuring current values of first aircraft parameters;c) calculating, by a calculating unit, based on said estimated roll moment and said measured current values, the following: a roll control order to control at least one first controllable movable member to act on aircraft roll, said roll control order applied to said first movable member to minimize aircraft roll-wise disturbances due to wind; anda yaw control order to control at least one second controllable movable member to act on aircraft yaw; wherein:said roll control order is applied to said first movable member,said yaw control order is applied to said second movable member, andin step c): said roll and yaw control orders are calculated based on a sideslip value of the aircraft; andsaid yaw control order is calculated as a function of said roll control order so that said yaw control order compensates for aircraft lateral effects due to turbulence and lateral effects due to application of said roll control order to said first movable member,wherein in step a), to estimate said roll moment due to the wind:wind at a given distance in front of the aircraft is measured with the aid of an appropriate measurement means onboard the aircraft;a profile of the wind in front of the aircraft is determined with the aid of this measurement; andsaid roll moment is calculated on the basis of this profile. 6. The method as claimed in claim 5, wherein: in step a), the following operations are further carried out: current values of second parameters of the aircraft are measured;based on said measured current values of said second parameters, horizontal wind existing outside the aircraft at a current position of the aircraft is calculated;based on said calculated horizontal wind, a lateral component Vv1 of wind existing outside the aircraft at the current position is deduced; andsaid sideslip value representing sideslip due to the wind is calculated according to the following expression: βv1=−Vv1/V, V being a measured air speed of the aircraft, where βv1 is the sideslip value; andin step c), the sideslip value is applied to calculate said control orders. 7. The method as claimed in claim 5, wherein: in step a): a sidewind Vv2 existing in front of the aircraft is measured by a measurement unit onboard the aircraft; anda sideslip value βv2 representing sideslip due to the wind is calculated according to the following expression: βv2=−Vv2/V, V being a measured air speed of the aircraft; andin step c), the sideslip value βv2 is applied to calculate said control orders. 8. The method as claimed in claim 5, wherein: a characteristic parameter relating to the roll is determined; andthe characteristic parameter is compared with a threshold value; andsaid roll and yaw control orders are applied when said characteristic parameter is greater than said threshold value. 9. A method for attenuating lateral effects on an aircraft due to turbulence encountered by the aircraft during flight, the method comprising the steps of: a) estimating, by a roll moment estimator, a roll moment of the aircraft due to wind;b) measuring current values of first aircraft parameters;c) calculating, by a calculating unit, based on said estimated roil moment and said measured current values, the following: a roll control order to control at least one first controllable movable member to act on aircraft roll, said roll control order applied to said first movable member to minimize aircraft roll-wise disturbances due to wind; anda yaw control order to control at least one second controllable movable member to act on aircraft yaw; wherein:said roll control order is applied to said first movable member,said yaw control order is applied to said second movable member, andin step c): said roll and yaw control orders are calculated based on a sideslip value of the aircraft; andsaid yaw control order is calculated as a function of said roll control order so that said yaw control order compensates for aircraft lateral effects due to turbulence and lateral effects due to application of said roll control order to said first movable member,wherein in step c), said roll control order and said yaw control order are calculated with the aid of the following expressions: δl=[−nδr(lp·pv+lβv·βv)]/(nδr·lδl−lδr·nδl)δr=−(nβv·βv+nδl·δl)/nδr in which: δl is the roll control order,δr is the yaw control order,pv is a roll rate due to the wind;βv is said sideslip value;lp, lβv, lδl, lδr are roll moment coefficients; andnβv, nδr, nδl are yaw moment coefficients. 10. The method as claimed in claim 9, wherein: in step a), the following operations are further carried out: current values of second parameters of the aircraft are measured;based on said measured current values of said second parameters, horizontal wind existing outside the aircraft at a current position of the aircraft is calculated;based on said calculated horizontal wind, a lateral component Vv1 of wind existing outside the aircraft at the current position is deduced; andsaid sideslip value representing sideslip due to the wind is calculated according to the following expression: βv1=−Vv1/V, V being a measured air speed of the aircraft, where βv1 is the sideslip value; andin step c), the sideslip value is applied to calculate said control orders. 11. The method as claimed in claim 9, wherein: in step a): a sidewind Vv2 existing in front of the aircraft is measured by a measurement unit onboard the aircraft; anda sideslip value βv2 representing sideslip due to the wind is calculated according to the following expression: βv2=−Vv2/V, V being a measured air speed of the aircraft; andin step c), the sideslip value is applied to calculate said control orders. 12. The method as claimed in claim 9, wherein: a characteristic parameter relating to the roll is determined; andthe characteristic parameter is compared with a threshold value; andsaid roll and yaw control orders are applied when said characteristic parameter is greater than said threshold value.

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

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이 특허에 인용된 특허 (10)

이 특허를 인용한 특허 피인용횟수: 4

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

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이 특허에 인용된 특허 (10)

이 특허를 인용한 특허 피인용횟수: 4

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IPC 상세정보(version : 201201)

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