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ES488948A1 - Helicopter transmission mounting - Google Patents

Helicopter transmission mounting

Info

Publication number
ES488948A1
ES488948A1 ES488948A ES488948A ES488948A1 ES 488948 A1 ES488948 A1 ES 488948A1 ES 488948 A ES488948 A ES 488948A ES 488948 A ES488948 A ES 488948A ES 488948 A1 ES488948 A1 ES 488948A1
Authority
ES
Spain
Prior art keywords
transmission
isolators
inertial
vibrations
helicopter
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
Application number
ES488948A
Other languages
Spanish (es)
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.)
Textron Inc
Original Assignee
Textron 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 Textron Inc filed Critical Textron Inc
Publication of ES488948A1 publication Critical patent/ES488948A1/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B64C27/001—Vibration damping devices
    • B64C2027/002—Vibration damping devices mounted between the rotor drive and the fuselage

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

A helicopter transmission mounting structure (Fig. 1) in which at least three decoupled inertial isolators (26, 28, 30, 32) are connected to the transmission (12) to support the helicopter fuselage. Each of the inertial isolators (26, 28, 30, 32) is mounted in the nodal plane of the transmission (12) to absorb inplane vibrations generated by a rotor blade and transmitted through a rotor mast (10). The inertial isolators (26, 28, 30, 32) respond individually to applied vibrations which have predetermined frequencies and generate counteracting forces to reduce the amplitude of vibrations transmitted to the fuselage. In an alternative embodiment (Fig. 5) beam input links (134, 136, 138, 140) are connected from the nodal plane of the transmission to inertial isolators (142, 144, 146, 148). The beam input links are connected to transmit only those forces parallel to the rotor mast.
ES488948A 1979-02-26 1980-02-26 Helicopter transmission mounting Expired ES488948A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US1522979A 1979-02-26 1979-02-26

Publications (1)

Publication Number Publication Date
ES488948A1 true ES488948A1 (en) 1980-09-16

Family

ID=21770216

Family Applications (1)

Application Number Title Priority Date Filing Date
ES488948A Expired ES488948A1 (en) 1979-02-26 1980-02-26 Helicopter transmission mounting

Country Status (12)

Country Link
JP (1) JPS55156798A (en)
AR (1) AR226171A1 (en)
AU (1) AU534537B2 (en)
BR (1) BR8001117A (en)
CA (1) CA1142155A (en)
DE (1) DE3006762A1 (en)
ES (1) ES488948A1 (en)
FR (1) FR2449593A1 (en)
GB (1) GB2043573B (en)
IL (1) IL59458A (en)
IT (1) IT1126962B (en)
MX (1) MX6586E (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19711845C2 (en) * 1997-03-21 1999-01-14 Eurocopter Deutschland Mechanical vibration damper
US6328293B1 (en) * 1998-09-18 2001-12-11 Lord Corporation Multi-linkage suspension system including outboard isolators
CA2789340C (en) * 2010-02-16 2015-07-07 Bell Helicopter Textron Inc. Variable stiffness liquid inertia vibration eliminator

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2615657A (en) * 1946-08-28 1952-10-28 Bell Aircraft Corp Helicopter engine-rotor support
US3698663A (en) * 1970-12-07 1972-10-17 Textron Inc Rotary wing pylon mounting system
GB1380710A (en) * 1970-12-29 1975-01-15 Kawasaki Heavy Ind Ltd Rotary wing aircraft
US3845917A (en) * 1971-10-18 1974-11-05 Textron Inc Helicopter vibration isolation
US3857534A (en) * 1972-02-04 1974-12-31 Textron Inc Multi-frequency helicopter vibration isolation
FR2232481B1 (en) * 1973-06-08 1976-05-07 Aerospatiale
US3945628A (en) * 1973-12-26 1976-03-23 Textron Inc. Nodal beam inertial flexure
US3858831A (en) * 1973-12-26 1975-01-07 Textron Inc Nodal beam inertial flexure
US4088042A (en) * 1976-09-07 1978-05-09 The Boeing Company Vibration isolation system
US4111386A (en) * 1976-12-09 1978-09-05 United Technologies Corporation Helicopter rotor and transmission mounting and vibration isolation system

Also Published As

Publication number Publication date
FR2449593B1 (en) 1983-07-18
DE3006762C2 (en) 1988-10-13
AR226171A1 (en) 1982-06-15
BR8001117A (en) 1980-10-29
IL59458A (en) 1984-11-30
DE3006762A1 (en) 1980-09-11
AU5585280A (en) 1980-09-04
AU534537B2 (en) 1984-02-02
FR2449593A1 (en) 1980-09-19
MX6586E (en) 1985-07-26
GB2043573A (en) 1980-10-08
IT8047998A0 (en) 1980-02-25
JPS55156798A (en) 1980-12-06
IT1126962B (en) 1986-05-21
GB2043573B (en) 1983-03-23
JPH0214240B2 (en) 1990-04-06
CA1142155A (en) 1983-03-01

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