GB595987A - Improvements in or relating to helicopters - Google Patents

Improvements in or relating to helicopters

Info

Publication number
GB595987A
GB595987A GB1783145A GB1783145A GB595987A GB 595987 A GB595987 A GB 595987A GB 1783145 A GB1783145 A GB 1783145A GB 1783145 A GB1783145 A GB 1783145A GB 595987 A GB595987 A GB 595987A
Authority
GB
United Kingdom
Prior art keywords
rotor
lever
link
pitch
blades
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
GB1783145A
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.)
Fairey Aviation Co Ltd
Original Assignee
Fairey Aviation Co Ltd
Filing date
Publication date
Application filed by Fairey Aviation Co Ltd filed Critical Fairey Aviation Co Ltd
Publication of GB595987A publication Critical patent/GB595987A/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
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8218—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft wherein the rotor or the jet axis is inclined with respect to the longitudinal horizontal or vertical plane of the helicopter

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

595,987. Helicopters. FAIREY AVIATION CO., Ltd., and BENNETT, J. A. J. July 12, 1945, No. 17831. [Class 4] A helicopter comprises an auxiliary lifting rotor in tandem with, and astern of, the main rotor, the tip-path plane of the auxiliary rotor being inclinable forwardly and laterally by means of cyclic pitch control of the blades thereof so that the resulting forward and lateral components of thrust may be utilized for forward propulsion and balancing the reaction torque of the main rotor. The axis of the main rotor may be inclined laterally so that the lateral component of the main rotor thrust balances the lateral component of the auxiliary rotor thrust in hovering flight. Control of rolling or pitching may be effected by cyclical adjustments of the pitch of the main rotor blades. Changes in the longitudinal position of the centre of gravity may be compensated for by a collective adjustment of the pitch of the auxiliary rotor blades. The axis of the main rotor may be displaced laterally from the centre of gravity so that a cyclical adjustment of blade pitch is required for lateral balance. As shown, the main rotor b is driven from a power unit d through a gear-box e and shaft f, and the auxiliary rotor c is driven in the opposite direction through a shaft g, gear-box h and shaft j. The blades of rotor b are mounted on a hub k without freedom to " flap " or " lag," but are arranged for collective and cyclical pitch control by means of a linkage m. The blades of rotor c are mounted on flapping pivots and blade-pitch may be adjusted collectively or cyclically by a linkage 17. The linkages m and 17 are actuated for collective pitch control by a lever n, links p and 14, bell-crank levers r and 15 and links s and 16. Lever r is also coupled by a link 30 to the engine throttle 31. Longitudinal cyclical pitch control of the blades of rotor b is effected through a link w, bellcrank lever x and link y by fore and aft movement of a lever u. Lateral movement of the lever u is transmitted through a torque tube 11 and link 13 to effect lateral control. Longitudinal cyclical control of rotor c is effected by means of a lever 18, link 20, bell-crank lever 21 and link 22, and lateral control by means of a rudder bar 23, links 25, 26 and 27, bell-crank lever 28 and link 29.
GB1783145A 1945-07-12 Improvements in or relating to helicopters Expired GB595987A (en)

Publications (1)

Publication Number Publication Date
GB595987A true GB595987A (en) 1947-12-24

Family

ID=1733450

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1783145A Expired GB595987A (en) 1945-07-12 Improvements in or relating to helicopters

Country Status (1)

Country Link
GB (1) GB595987A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2571566A (en) * 1949-01-04 1951-10-16 John A Green Control system for multiple rotor helicopters
US3081052A (en) * 1957-06-03 1963-03-12 United Aircraft Corp Variable stabilizing means
US4502840A (en) * 1982-03-19 1985-03-05 Stephan Roman Blade pitch control in rotatable bladed devices for vehicles

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2571566A (en) * 1949-01-04 1951-10-16 John A Green Control system for multiple rotor helicopters
US3081052A (en) * 1957-06-03 1963-03-12 United Aircraft Corp Variable stabilizing means
US4502840A (en) * 1982-03-19 1985-03-05 Stephan Roman Blade pitch control in rotatable bladed devices for vehicles

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