[특허]Vertical gust suppression system for transport aircraft

The Boeing Company

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Vertical gust suppression system for transport aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00
미국특허분류(USC)	701/010; 244/076C; 701/004; 701/008; 701/011
출원번호	US-0958248 (2007-12-17)
등록번호	US-8774987 (2014-07-08)
발명자 / 주소	Walton, Vincent M. Borland, Christopher J. Siu, Tze L. Najmabadi, Kioumars Coleman, Edward E. Marquis, David P. McMullin, Dianne L. Milligan, Kevin H.
출원인 / 주소	The Boeing Company
대리인 / 주소	The Small Patent Law Group
인용정보	피인용 횟수 : 4 인용 특허 : 10

초록
▼

A method for vertical gust suppression due to turbulence for an aircraft having at least one of direct lift control surfaces or pitch control surfaces. The method includes sensing atmospheric turbulence, measuring the sensed atmospheric turbulence to generate turbulence data, generating a command based on the turbulence data, and applying the command to aircraft controls to actuate the direct lift control surfaces or the pitch control surfaces based on the turbulence data. Therefore, an aircraft response to the actuation of the direct lift control surfaces or the pitch control surfaces reduces a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude or a structural load of the aircraft due to the turbulence. Thus, the method reduces the effects of vertical gusts of wind on the aircraft, improves the comfort level for aircraft passengers and crew, and reduces diversions the aircraft may take to avoid the turbulence.

대표
청구항
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1. A method to suppress the effects of vertical gusts due to turbulence for an aircraft having at least one control surface actuated by aircraft controls, the method comprising: collecting air data and inertial data for the aircraft during flight operations;determining an inertial angle of attack for the aircraft and a total angle of attack for the aircraft;determining a gust angle of attack as a difference between the inertial angle of attack and the total angle of attack;determining a true air speed of the aircraft;estimating a level of vertical wind gust by scaling the gust angle of attack by the true airspeed of the aircraft;generating a command based on the estimated level of vertical wind gust when the estimated level of vertical wind gust exceeds a predetermined threshold level, wherein no command is generated responsive to the estimated level of vertical wind gust when the estimated level of vertical wind gust is below the predetermined threshold level; andapplying the command to the aircraft controls to actuate at least one control surface based on the estimated level of vertical wind gust,wherein an aircraft response to the actuation of at least one control surface changes at least one of a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude, or a structural load of the aircraft due to the estimated level of vertical wind gust. 2. The method of claim 1, wherein the predetermined threshold defines a minimum level of vertical wind gust corresponding to improved ride quality and decreased motion sickness. 3. The method of claim 1, further comprising adding air and inertia data to form an estimate of the estimated level of vertical wind gust. 4. The method of claim 2 wherein generating a command based on the estimated level of vertical wind gust comprises adjusting one or more control surface outputs depending on the estimated level of vertical wind gusts. 5. The method of claim 1, further comprising using an Ultraviolet Light Detection And Ranging (UV LIDAR) to measure the atmospheric motion ahead of the aircraft. 6. The method of claim 1, wherein the generating of the command comes from a set of control laws comprising at least one of a set of filters, a high pass filter, a low pass filter, or a linear phase Finite Impulse Response filter. 7. The method of claim 6, wherein the set of control laws further comprises at least one of a stability augmentation or an autopilot. 8. The method of claim 6, wherein the set of control laws are compatible with at least one of a stability augmentation or an autopilot. 9. The method of claim 6, wherein the set of control laws produce a command to negate gust effects. 10. The method of claim 1, wherein the at least one control surface comprises at least one of a flaperon or an aileron. 11. The method of claim 1, wherein the at least one control surface comprises at least one of an elevator or a canard. 12. The method of claim 1, further comprising terminating the command when a representation of at least one of least one of a sensor fails, a command fails, or an aircraft control is invalid. 13. The method of claim 1, further comprising invoking an active aircraft control to reduce the turbulence. 14. A system for Vertical Gust Suppression, the system comprising: one or more sensors to collect air data and inertial data for the aircraft during flight operations;a gust estimator operatively coupled to the one or more sensors to: determine an inertial angle of attack for the aircraft and a total angle of attack for the aircraft;determine a gust angle of attack as a difference between the inertial angle of attack and the total angle of attack;determine a true air speed of the aircraft; andestimate a level of vertical wind gust by scaling the gust angle of attack by the true airspeed of the aircraft;filters operatively coupled to the gust estimator to generate a command to aircraft flight controls based on the estimated level of vertical wind gust when the estimated level of vertical wind gust exceeds a predetermined threshold level, wherein no command is generated responsive to the estimated level of vertical wind gust when the estimated level of vertical wind gust is below the predetermined threshold level; andat least one control surface which actuates in response to the command and aircraft flight controls to change at least one of a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude, or a structural load of the aircraft due to the vertical wind gust. 15. The system of claim 14, further comprising a true air speed module to determine a true air speed of the aircraft. 16. The system of claim 14, wherein the one or more sensors comprise an Ultraviolet Light Detection And Ranging (UV LIDAR) to measure an atmospheric motion ahead of an aircraft. 17. The system of claim 16, wherein the filters comprise at least one of a set of filters, a high pass filter, a low pass filter, or a linear phase Finite Impulse Response filter. 18. The system of claim 14, further comprising a set of control laws to generate the command, wherein the control laws comprise at least one of a stability augmentation or an autopilot. 19. The system of claim 18, wherein the set of control laws are compatible with at least one of a stability augmentation or an autopilot. 20. The system of claim 18, wherein the set of control laws produce a command to negate gust effects. 21. The system of claim 14, wherein the at least one control surface comprises at least one of a flaperon or an aileron an elevator or a canard. 22. A non-transitory computer-readable storage media including computer-program instructions executable by a flight control computer, the instructions configured to cause the flight control computer to perform operations comprising: collecting air data and inertial data for the aircraft during flight operations;determining an inertial angle of attack for the aircraft and a total angle of attack for the aircraft;determining a gust angle of attack as a difference between the inertial angle of attack and the total angle of attack;determining a true air speed of the aircraft;estimating a level of vertical wind gust by scaling the gust angle of attack by the true airspeed of the aircraft;generating a command based on the estimated level of vertical wind gust when the estimated level of vertical wind gust exceeds a predetermined threshold level, wherein no command is generated responsive to the estimated level of vertical wind gust when the estimated level of vertical wind gust is below the predetermined threshold level; andwherein an aircraft response to the actuation of at least one control surface changes at least one of a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude, or a structural load of the aircraft due to the turbulence. 23. The computer-readable storage media of claim 22, wherein the predetermined threshold defines a minimum level of vertical wind gust corresponding to improved ride quality and decreased motion sickness. 24. The computer-readable storage media of claim 22, wherein generating a command based on the estimated level of vertical wind gust comprises adjusting one or more control surface outputs depending on the estimated level of vertical wind gusts. 25. The computer-readable storage media of claim 22, further comprising terminating the command when a representation occurs of at least one of a sensor fails, a command fails, or an aircraft control is invalid. 26. The method of claim 1, wherein the at least one control surface comprises a flaperon on each wing of the aircraft and an elevator, and applying the command to the aircraft controls comprises applying the command to actuate the flaperons to modify an aircraft lift and to actuate the elevator to cancel a pitching response induced by the flaperons.

이 특허에 인용된 특허 (10)

이 특허를 인용한 특허 피인용횟수: 4

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특허 상세정보

Vertical gust suppression system for transport aircraft

초록
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대표
청구항
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이 특허에 인용된 특허 (10)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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Vertical gust suppression system for transport aircraft

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이 특허에 인용된 특허 (10)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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