ES2610393T3 - Sistema de peso ajustable de borde de fuga para palas de rotor principal de helicóptero - Google Patents

Sistema de peso ajustable de borde de fuga para palas de rotor principal de helicóptero Download PDF

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Publication number
ES2610393T3
ES2610393T3 ES05076137.8T ES05076137T ES2610393T3 ES 2610393 T3 ES2610393 T3 ES 2610393T3 ES 05076137 T ES05076137 T ES 05076137T ES 2610393 T3 ES2610393 T3 ES 2610393T3
Authority
ES
Spain
Prior art keywords
rotor blade
trailing edge
recess
rotor blades
main 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.)
Expired - Lifetime
Application number
ES05076137.8T
Other languages
English (en)
Inventor
Robert T. Loftus
Michael J. Mcnulty
Kevin Henthorn
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.)
Boeing Co
Original Assignee
Boeing Co
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 Boeing Co filed Critical Boeing Co
Application granted granted Critical
Publication of ES2610393T3 publication Critical patent/ES2610393T3/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
    • B64C27/008—Rotors tracking or balancing devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/001—Vibration damping devices
    • B64C2027/005—Vibration damping devices using suspended masses
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Un rotor de aeronave que comprende: una pala (42) de rotor que tiene una longitud longitudinal con extremos opuestos proximal (44) y distal (46), y una anchura lateral entre los bordes opuestos de ataque (48) y de fuga (52), y un rebaje (74) formado en la pala (42) de rotor adyacente al borde de fuga (52) de la pala de rotor; y un peso (92, 92') de equilibrado conectado a la pala (42) de rotor en una posición que es intermedia a los extremos proximal y distal de la pala de rotor y que es adyacente al borde de fuga (52) de la pala de rotor, el peso (92, 92') de equilibrado estando conectado a la pala de rotor en el rebaje (74), caracterizado por que: el rebaje (74) de la pala de rotor tiene una forma aerodinámica siendo el rebaje (74) longitudinalmente estrecho hacia el borde de ataque (48) de la pala de rotor y siendo el rebaje (74) más amplio hacia el borde de fuga (52) de la pala de rotor.

Description

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Claims (1)

  1. imagen1
    imagen2
ES05076137.8T 2004-05-17 2005-05-17 Sistema de peso ajustable de borde de fuga para palas de rotor principal de helicóptero Expired - Lifetime ES2610393T3 (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US847006 2004-05-17
US10/847,006 US7118343B2 (en) 2004-05-17 2004-05-17 Trailing edge adjustable weight system for helicopter main rotor blades

Publications (1)

Publication Number Publication Date
ES2610393T3 true ES2610393T3 (es) 2017-04-27

Family

ID=34938276

Family Applications (1)

Application Number Title Priority Date Filing Date
ES05076137.8T Expired - Lifetime ES2610393T3 (es) 2004-05-17 2005-05-17 Sistema de peso ajustable de borde de fuga para palas de rotor principal de helicóptero

Country Status (3)

Country Link
US (1) US7118343B2 (es)
EP (1) EP1598269B1 (es)
ES (1) ES2610393T3 (es)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8029240B2 (en) * 2007-11-08 2011-10-04 The Boeing Company Rotor blade adjustable weight retention system
EP2123556B1 (en) * 2008-05-22 2010-12-08 Agusta S.p.A. Helicopter antitorque tail rotor blade
US8192162B2 (en) * 2008-07-29 2012-06-05 Loftus Robert T Field installable and removable helicopter rotor blade vibration and blade tracking device
US8668285B2 (en) * 2008-08-13 2014-03-11 Becklin Holdings, Inc. Systems and method for securing electronics equipment
US9403594B2 (en) * 2012-09-25 2016-08-02 The Boeing Company Adjustable payload enclosure for wing
US9914533B2 (en) * 2013-12-05 2018-03-13 Sikorsky Aircraft Corporation In-wing device retention
EP3233630B1 (en) * 2014-12-19 2019-09-18 Sikorsky Aircraft Corporation Aircraft rotor blade with reduced stress
WO2017048683A1 (en) * 2015-09-17 2017-03-23 Sikorsky Aircraft Corporation Stress reducing holes
US10239604B2 (en) * 2016-05-21 2019-03-26 Bell Helicopter Textron Inc. Structurally biased proprotor blade assembly
US10981647B2 (en) * 2017-08-02 2021-04-20 Bell Helicopter Textron Inc. Rotor span-balance pocket
US11254424B2 (en) * 2019-09-30 2022-02-22 Textron Innovations Inc. Balance weight assemblies for rotor blades
CH717385A1 (de) * 2020-05-06 2021-11-15 Kopter Group Ag Heckrotorkopf eines ummantelten Heckrotors eines Drehflügelflugzeugs und Blatthalterung.
US12006026B2 (en) 2020-07-10 2024-06-11 Haymatt, L.L.C. Sound-reducing rotor blade tracking wedge profile
US12589863B1 (en) 2021-07-07 2026-03-31 Haymatt, L.L.C. Sound-reducing rotor blade tracking wedge profile
US12214872B2 (en) 2023-04-07 2025-02-04 Lockheed Martin Corporation Tip end joint arrangement for a rotor blade with reconfigurable attributes for structural and aerodynamic tuning
US12497166B2 (en) 2023-04-07 2025-12-16 Lockheed Martin Corporation Tip end joint arrangement for a rotor blade with reconfigurable attributes for structural and aerodynamic tuning
US12491986B2 (en) * 2023-12-19 2025-12-09 Textron Innovations Inc. Inertial weight system for main rotor blades

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3999888A (en) * 1975-06-25 1976-12-28 United Technologies Corporation Composite tip weight attachment
US4601639A (en) * 1984-03-19 1986-07-22 Bell Helicopter Textron Inc. Nodalized rotor
GB2327926B (en) * 1987-06-26 1999-06-02 Aerospatiale Blade with a weak radar signature
US6139271A (en) * 1998-03-17 2000-10-31 Chadwick-Helmuth Company, Inc. Helicopter rotor blade weighting
FR2784351B1 (fr) * 1998-10-12 2000-12-08 Eurocopter France Dispositif et procede pour reduire les vibrations engendrees sur la structure d'un aeronef a voilure tournante, notamment un helicoptere
EP1412245B1 (en) * 2001-08-02 2011-03-02 Bell Helicopter Textron Inc. Helicopter main rotor blade balance weight retention assembly

Also Published As

Publication number Publication date
EP1598269A2 (en) 2005-11-23
EP1598269B1 (en) 2016-12-28
US20050254947A1 (en) 2005-11-17
EP1598269A3 (en) 2015-03-04
US7118343B2 (en) 2006-10-10

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