ES2060576T1 - Sistema para controlar las vibraciones armonicas superiores en paletas de rotor de helicoptero. - Google Patents

Sistema para controlar las vibraciones armonicas superiores en paletas de rotor de helicoptero.

Info

Publication number
ES2060576T1
ES2060576T1 ES93119661T ES93119661T ES2060576T1 ES 2060576 T1 ES2060576 T1 ES 2060576T1 ES 93119661 T ES93119661 T ES 93119661T ES 93119661 T ES93119661 T ES 93119661T ES 2060576 T1 ES2060576 T1 ES 2060576T1
Authority
ES
Spain
Prior art keywords
cylinder
hhc
rotor blade
force
helicopter rotor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
ES93119661T
Other languages
English (en)
Other versions
ES2060576T3 (es
Inventor
Wilmer H Reed Iii
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dynamic Engineering Inc
Original Assignee
Dynamic Engineering Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dynamic Engineering Inc filed Critical Dynamic Engineering Inc
Publication of ES2060576T1 publication Critical patent/ES2060576T1/es
Application granted granted Critical
Publication of ES2060576T3 publication Critical patent/ES2060576T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B64C27/57—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/72—Means acting on blades
    • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
    • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
    • B64C2027/7294—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps actuated mechanically, e.g. by means of linkages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)
  • Vibration Prevention Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Apparatuses For Generation Of Mechanical Vibrations (AREA)
  • Wind Motors (AREA)

Abstract

EL CONTROL DE LAS ARMONICAS SUPERIORES (DE AQUI EN ADELANTE HHC) DE LAS VIBRACIONES DE LAS PALAS DEL ROTOR DE UN HELICOPTERO SE CONSIGUE MEDIANTE UN CILINDRO RANURADO, ROTATIVO, ACTIVAMENTE CONTROLADO (11) QUE SE ENCUENTRA MONTADO EN UNA SECCION EXTERIOR DE CADA PALA (12). LA ROTACION CONTINUA DE CADA CILINDRO (11) ALREDEDOR DE SU EJE LONGITUDINAL PRODUCE UNA FUERZA AERODINAMICA PERIODICA EN LA PALA (12) A UNA FRECUENCIA DOS VECES MAYOR QUE LA FRECUENCIA DE ROTACION DEL CILINDRO. LA INTENSIDAD DE LA FUERZA QUEDA CONTROLADA POR EL TAMAÑO DE UNA ABERTURA RANURADA (110,111,112,133) QUE HAY FORMADA EN EL CILINDRO MIENTRAS QUE LA VELOCIDAD DE ROTACION DEL CILINDRO SE SINCRONIZA PARA QUE CORRA A UN MULTIPLO DE LA VELOCIDAD DEL EJE ACCIONADOR DE LA PALA DEL ROTOR. LA INTENSIDAD Y LA FASE DE LA FUERZA DE HHC SE REGULAN, BIEN MANUALMENTE O BIEN MEDIANTE UN CONTROL DE REALIMENTACION ACTIVO, PARA MINIMIZAR CUALQUIER CARGA VIBRATORIA TRANSMITIDA AL FUSELAJE A TRAVES DEL EJE ACCIONADOR DE LA PALA DEL ROTOR. UNA VENTAJA SIGNIFICATIVA OFRECIDA POR ESTE CONCEPTO, RELATIVA A OTROS METODO DE HHC, ES SU BAJO REQUISITO DE POTENCIA.
ES93119661T 1992-12-11 1993-12-07 Sistema para controlar las vibraciones armonicas mas altas en palas de rotor de helicoptero. Expired - Lifetime ES2060576T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/989,583 US5314308A (en) 1992-12-11 1992-12-11 System for controlling higher harmonic vibrations in helicopter rotor blades

Publications (2)

Publication Number Publication Date
ES2060576T1 true ES2060576T1 (es) 1994-12-01
ES2060576T3 ES2060576T3 (es) 1997-06-16

Family

ID=25535244

Family Applications (1)

Application Number Title Priority Date Filing Date
ES93119661T Expired - Lifetime ES2060576T3 (es) 1992-12-11 1993-12-07 Sistema para controlar las vibraciones armonicas mas altas en palas de rotor de helicoptero.

Country Status (11)

Country Link
US (1) US5314308A (es)
EP (1) EP0601527B1 (es)
JP (1) JPH072187A (es)
KR (1) KR940014085A (es)
CN (1) CN1092727A (es)
AT (1) ATE152062T1 (es)
DE (2) DE69310111T2 (es)
DK (1) DK0601527T3 (es)
ES (1) ES2060576T3 (es)
GR (2) GR940300078T1 (es)
TW (1) TW239107B (es)

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DE19528155C1 (de) * 1995-08-02 1996-06-27 Deutsche Forsch Luft Raumfahrt Verdrehbares Rotorblatt aus faserverstärktem Kunstharz
WO1999012809A1 (en) * 1996-03-11 1999-03-18 Advanced Technology Institute Of Commuter-Helicopter, Ltd. Rotor control system
US5973440A (en) 1997-07-07 1999-10-26 Nitzsche; Fred Structural component having means for actively varying its stiffness to control vibrations
FR2770826B1 (fr) * 1997-11-07 2000-01-07 Eurocopter France Pale de rotor a volet orientable
JP2907335B1 (ja) 1998-03-24 1999-06-21 株式会社コミュータヘリコプタ先進技術研究所 ロータブレードのフラップ駆動装置
DE10035333B4 (de) * 2000-07-20 2008-08-14 Eads Deutschland Gmbh Rotorblatt mit Steuerklappen
DE10052757A1 (de) * 2000-10-25 2002-05-08 Zf Luftfahrttechnik Gmbh Rotorblatt-Steuerungsvorrichtung
US6493689B2 (en) 2000-12-29 2002-12-10 General Dynamics Advanced Technology Systems, Inc. Neural net controller for noise and vibration reduction
US6671590B1 (en) 2001-04-30 2003-12-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method and system for active noise control of tiltrotor aircraft
EP1412245B1 (en) * 2001-08-02 2011-03-02 Bell Helicopter Textron Inc. Helicopter main rotor blade balance weight retention assembly
FR2871435B1 (fr) * 2004-06-10 2006-08-18 Eurocopter France Dispositif d'indication d'un niveau de battement
US8435002B2 (en) 2004-08-30 2013-05-07 Lord Corporation Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations
CN101022994B (zh) 2004-08-30 2012-07-04 洛德公司 直升飞机振动控制系统和消除振动的旋转力发生器
US7722322B2 (en) 2004-08-30 2010-05-25 Lord Corporation Computer system and program product for controlling vibrations
US8162606B2 (en) 2004-08-30 2012-04-24 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
US8267652B2 (en) 2004-08-30 2012-09-18 Lord Corporation Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
DE102005007129B4 (de) * 2005-02-17 2008-07-10 Zf Friedrichshafen Ag Einrichtung zur Steuerung von Rotorblättern eines Hubschraubers
US7648338B1 (en) 2006-09-14 2010-01-19 Sikorsky Aircraft Corporation Dual higher harmonic control (HHC) for a counter-rotating, coaxial rotor system
WO2009055007A2 (en) 2007-10-25 2009-04-30 Lord Corporation Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations
FR2929253B1 (fr) 2008-03-28 2013-09-13 Sartorius Stedim Biotech Sa Cadre rigide pour conteneur 3d a contenant au moins partiellement deformable
US8985068B2 (en) 2010-07-22 2015-03-24 Robert Bosch Gmbh Systems and methods for avoiding resonances excited by rotating components
EP2670661B1 (en) 2011-02-04 2015-01-14 Lord Corporation Rotary wing aircraft vibration control system with resonant inertial actuators
US10607424B2 (en) 2012-02-10 2020-03-31 Appareo Systems, Llc Frequency-adaptable structural health and usage monitoring system (HUMS) and method with smart sensors
WO2013120103A1 (en) 2012-02-10 2013-08-15 Appareo Systems, Llc Frequency-adaptable structural health and usage monitoring system
US9816529B2 (en) 2013-03-15 2017-11-14 Kcf Technologies, Inc. Propeller sound field modification systems and methods
US9394045B2 (en) 2013-03-15 2016-07-19 Kcf Technologies, Inc. Propeller sound field modification systems and methods
JP6469389B2 (ja) * 2014-08-29 2019-02-13 三菱航空機株式会社 航空機の加振システム、及び、航空機
CN104670492B (zh) * 2015-01-23 2016-11-16 南京航空航天大学 一种直升机桨叶嵌入式径向运动摆振阻尼器
IL240316B (en) 2015-08-03 2018-10-31 Technion Res & Dev Foundation Method and system for parametric amplification
EP3168145B1 (en) * 2015-11-10 2020-01-29 Sikorsky Aircraft Corporation Reduced power individual blade control system on a rotorcraft
DE102016213720A1 (de) 2016-07-26 2018-02-01 Zf Friedrichshafen Ag System zur Datenübermittlung und -verarbeitung zur Regelung eines Rotorblattaktuators
US11299263B2 (en) 2016-12-07 2022-04-12 Textron Innovations Inc. Automatic, active blade tracking and balance system
CN108639335B (zh) * 2018-04-04 2020-06-02 北京航空航天大学 一种面向振动与噪声控制的直升机旋翼副翼的柔性变形系统
CN113955142B (zh) * 2021-10-09 2023-09-05 中国直升机设计研究所 一种旋翼1ω谐波振动实时调整控制方法
CN115056979B (zh) * 2022-07-01 2023-05-23 南京航空航天大学 基于旋翼摆振方向周期型运动的振动主动控制方法及系统

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Also Published As

Publication number Publication date
KR940014085A (ko) 1994-07-16
ATE152062T1 (de) 1997-05-15
EP0601527B1 (en) 1997-04-23
DE69310111D1 (de) 1997-05-28
DE601527T1 (de) 1995-04-06
ES2060576T3 (es) 1997-06-16
DE69310111T2 (de) 1997-08-07
TW239107B (es) 1995-01-21
EP0601527A1 (en) 1994-06-15
CN1092727A (zh) 1994-09-28
JPH072187A (ja) 1995-01-06
GR3023986T3 (en) 1997-10-31
US5314308A (en) 1994-05-24
GR940300078T1 (en) 1994-11-30
DK0601527T3 (da) 1997-10-27

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