[특허]Method for using a steerable tall fin to reduce the vibration generated on the fuselage of a helicopter

[미국특허] Method for using a steerable tall fin to reduce the vibration generated on the fuselage of a helicopter 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00 B64C-013/00 B64C-011/00 B64C-027/78 B64C-027/00
출원번호	US-0019633 (2004-12-23)
등록번호	US-7461819 (2008-12-09)
우선권정보	FR-03 15299(2003-12-23)
발명자 / 주소	Eglin,Paul
출원인 / 주소	Eurocopter
대리인 / 주소	Young & Thompson
인용정보	피인용 횟수 : 7 인용 특허 : 18

초록 ▼

A method and a device reduces the vibration generated on the structure 17 of a helicopter 2 by the flow of air through the main rotor 5 and by the flow of air along the fuselage 3. The device 1 includes: at least one sensor 18, 19, 20 measuring the vibration generated on the structure 17; and computer element 30 responsive to the vibration measurements to determine variation in the angle of incidence of a tail fin 9 of the helicopter 2 suitable for generating an opposing force {right arrow over (T1)}, {right arrow over (T2)} for opposing the vibration, and transmitting the variation in angle of incidence as determined in this way to a control system 10 for controlling the angle of incidence of the tail fin 9.

대표청구항 ▼

What is claimed is: 1. A method of reducing vibration in a structure of a helicopter having a main rotor and a tail boom with a steerable tail fin and a tail rotor, comprising the steps of: exciting a lateral vibration in the tail boom of the helicopter with a downward flow of air from the main rotor onto the structure of the helicopter, the downward flow of air having a diameter substantially equal to a diameter of the main rotor and having varying pressure and speed; measuring the lateral vibration on at least one location of the helicopter; determining a variation of an angle of incidence of a movable control surface of the tail fin that generates a force opposing the measured lateral vibration; and varying the angle of incidence of the movable control surface of the tail fin the determined variation to generate the force opposing the measured lateral vibration without applying alternating variation to a pitch of blades of the tail rotor. 2. The method of claim 1, wherein the generated lateral vibration is a first lateral bending mode of the tail boom. 3. The method of claim 1, wherein the generated lateral vibration has a frequency of 5 to 6 Hz. 4. The method of claim 1, wherein the method is inoperable when the helicopter is on the ground and in particular flight conditions. 5. The method of claim 1, wherein the at least one location where the lateral vibration is measured is on the tail fin. 6. The method of claim 1, further comprising the steps of exciting a vertical vibration in the structure of the helicopter, measuring the vertical vibration on at least one location of the helicopter, determining a variation of an angle of incidence of a part of a substantially horizontal control surface that generates a force opposing the measured vertical vibration, and varying the angle of incidence of the part of the substantially horizontal control surface the determined variation to generate the force opposing the measured vertical vibration. 7. The method of claim 1, further comprising the step of filtering the measured lateral vibration. 8. The method of claim 1, further comprising the step of limiting an amplitude of the force opposing the measured lateral vibration. 9. The method of claim 1, wherein the tail fin is parallel to a plane of symmetry of the helicopter. 10. The method of claim 1, wherein the tail fin is inclined relative to a plane of symmetry of the helicopter. 11. The method of claim 1, wherein the movable control surface of the tail fin is a trailing edge flap that is hinged to a stationary upstream part of the tail fin.

이 특허에 인용된 특허 (18) 인용/피인용 타임라인 분석

Tulinius Jan (Huntington Beach CA), Active flexible wing aircraft control system.
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Hill,Wayne; Tsimring,Lev S., Active vibration control system.
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Chakravarty Abhijit J. M. (Renton WA) Cooper Steven R. (Seattle WA) Ho John K. H. (Renton WA) Tran Chuong B. (Everett WA), Aircraft modal suppression system.
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Najmabadi, Kioumars; Tran, Chuong B.; Ho, John Koon-Hung, Aircraft multi-axis modal suppression system.
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Bleeg Robert J. (Mercer Island WA), Apparatus and method for reducing aircraft loads resulting from atmospheric turbulence and gusts.
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Middleton Robin (Bellevue WA), Apparatus and method for warning of a high yaw condition in an aircraft.
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Tefft Franklin A. (Killingworth CT) Perez Ricardo L. (Plantsville CT) Barnum Ronald E. (Trumbull CT), Helicopter hover stability and cruise gust effect alleviation.
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Kubica,Francois, Inertial reference system for an aircraft.
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Garza Roberto M. (P.O. Box 7036 San Antonio TX 78207), Means for controlling lateral movement of a helicopter.
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Bryant William F. (Bellevue WA) Nadkarni Arun A. (Kirkland WA) Salo Paul (Seattle WA), Method and apparatus for reducing unwanted sideways motion in the aft cabin and roll-yaw upsets of an airplane due to at.
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Girard Laurent (Marseille FRX) Krysinski Tomasz (Marseille FRX) Michel Pierre (Aix-en-Provence FRX), Method and device for filtering the vibratory excitations transmitted between two parts especially between the rotor and.
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Krysinski Thomasz,FRX ; Beroul Frederic Andre Henri,FRX, Method and device for reducing the effect of the vibration generated by the driveline of a helicopter.
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Krysinsky Tomasz,FRX, Method and device for reducing the vibration generated on the structure of a helicopter.
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Jordan Heinz (Wlfnitz bei Klagenfurt ATX), Rotary wing flying craft.
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Weiner Steven D. (Orange CT) Moffitt Robert C. (Seymour CT), Shroud-fin integration shelf for a helicopter empennage structure.
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Rollet Philippe A. (Velaux FRX) Eglin Paul G. (Aix en Provence FRX), Single-rotor helicopter having a compound anti-torque system, and a method of countering the torque induced by said sing.
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Juergen Becker DE, System and method for compensating structural vibrations of an aircraft caused by outside disturbances.
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Lacabanne Michel (Saint-Orens FRX), System enabling the flutter behavior of an aircraft to be improved.
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이 특허를 인용한 특허 (7) 인용/피인용 타임라인 분석

Weiner, Steven D.; Eadie, William J., Main rotor rotational speed control for rotorcraft.
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Kelaidis, Manousos, Method for controlling rotorcraft airfoil to minimize auxiliary rotor noise and enhance rotorcraft performance.
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Eglin, Paul; Queiras, Nicolas; Barraco, André; Malburet, Francois, Method of controlling and regulating the deflection angle of a tailplane in a hybrid helicopter.
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Marze, Henri-James, Method of optimizing a ducted anti-torque rotor of a rotorcraft, in particular a helicopter, to minimize acoustic annoyance, and a ducted anti-torque rotor obtained thereby.
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McCollough, James M.; Wood, Tommie L., Rotorcraft anti-torque rotor and rudder system.
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Groen, David L., Use of auxiliary rudders for yaw control at low speed.
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Groen, David L., Use of auxiliary rudders for yaw control at low speed.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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연합인증

[미국특허] Method for using a steerable tall fin to reduce the vibration generated on the fuselage of a helicopter 원문보기

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이 특허에 인용된 특허 (18) 인용/피인용 타임라인 분석

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[미국특허] Method for using a steerable tall fin to reduce the vibration generated on the fuselage of a helicopter 원문보기

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연구과제 타임라인

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이 특허에 인용된 특허 (18) 인용/피인용 타임라인 분석

이 특허를 인용한 특허 (7) 인용/피인용 타임라인 분석

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