GB1236650A - Hinged rotor blade attachment for helicopter rotors - Google Patents

Hinged rotor blade attachment for helicopter rotors

Info

Publication number
GB1236650A
GB1236650A GB4639268A GB4639268A GB1236650A GB 1236650 A GB1236650 A GB 1236650A GB 4639268 A GB4639268 A GB 4639268A GB 4639268 A GB4639268 A GB 4639268A GB 1236650 A GB1236650 A GB 1236650A
Authority
GB
United Kingdom
Prior art keywords
hub
bolt
lag
rotor
root end
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
GB4639268A
Inventor
Christoph Fischer
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.)
Vereinigte Flugtechnische Werke Fokker GmbH
Original Assignee
Vereinigte Flugtechnische Werke Fokker GmbH
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 Vereinigte Flugtechnische Werke Fokker GmbH filed Critical Vereinigte Flugtechnische Werke Fokker GmbH
Priority to GB4639268A priority Critical patent/GB1236650A/en
Publication of GB1236650A publication Critical patent/GB1236650A/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
    • B64C27/32—Rotors
    • B64C27/37—Rotors having articulated joints
    • 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
    • B64C27/48—Root attachment to rotor head

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pivots And Pivotal Connections (AREA)

Abstract

1,236,650. Helicopter rotor blade attachment. VEREINIGTE FLUGTECHNISCHEWERKE G.m.b.H. 30 Sept., 1968, No. 46392/68. Heading B7W. A helicopter rotor assembly comprises a rotor hub 3 rigidly connected to a rotor shaft and a pair of diammetrically opposed rotor blades 1 wherein each blade has a forked root end 2 partially embracing the hub and a bladeretaining, flapping hinge bolt 8 which extends between the forks and passes through distance pieces 9 which prevent relative root end/bolt movement and a ball-and-socket joint 7, 5 comprising a ball element 7 rigidly connected to said bolt and having a part-spherical surface that mates with a socket element 5 mounted within the hub by circlips 6. The bolts carry at one end a control lever 12 connected to pitch changing apparatus and are interconnected by lag-lead movement dampers 14. Noses 10 on the hub are received into respective recesses 11 on each root end 1 to restrict blade flapping and lag-lead movement when the blades are inoperative. An embodiment is described wherein each damper is supported partly by a bolt 8 and partly by a hub mounted pin. In a further embodiment dampers are replaced by members sufficiently stiff to prevent lag-lead movement. Each bolt 8 may be rotated through 90 degrees to coincide with the lag axis.
GB4639268A 1968-09-30 1968-09-30 Hinged rotor blade attachment for helicopter rotors Expired GB1236650A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4639268A GB1236650A (en) 1968-09-30 1968-09-30 Hinged rotor blade attachment for helicopter rotors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4639268A GB1236650A (en) 1968-09-30 1968-09-30 Hinged rotor blade attachment for helicopter rotors

Publications (1)

Publication Number Publication Date
GB1236650A true GB1236650A (en) 1971-06-23

Family

ID=10441071

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4639268A Expired GB1236650A (en) 1968-09-30 1968-09-30 Hinged rotor blade attachment for helicopter rotors

Country Status (1)

Country Link
GB (1) GB1236650A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5340279A (en) * 1992-06-22 1994-08-23 United Technologies Corporation Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors
WO2007055674A1 (en) * 2005-11-08 2007-05-18 Joint Stock Company 'yuzhmash Helicopter' Helicopter rotor
CN112278319A (en) * 2020-10-21 2021-01-29 中国航空工业集团公司上海航空测控技术研究所 Multi-model helicopter rotor dynamic balance simulation platform mechanism

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5340279A (en) * 1992-06-22 1994-08-23 United Technologies Corporation Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors
WO2007055674A1 (en) * 2005-11-08 2007-05-18 Joint Stock Company 'yuzhmash Helicopter' Helicopter rotor
CN112278319A (en) * 2020-10-21 2021-01-29 中国航空工业集团公司上海航空测控技术研究所 Multi-model helicopter rotor dynamic balance simulation platform mechanism

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