GB857462A - Improvements relating to rotary wing aircraft - Google Patents

Improvements relating to rotary wing aircraft

Info

Publication number
GB857462A
GB857462A GB8211/56A GB821156A GB857462A GB 857462 A GB857462 A GB 857462A GB 8211/56 A GB8211/56 A GB 8211/56A GB 821156 A GB821156 A GB 821156A GB 857462 A GB857462 A GB 857462A
Authority
GB
United Kingdom
Prior art keywords
hub
blade
axis
pivoted
pitch
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
GB8211/56A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB8211/56A priority Critical patent/GB857462A/en
Publication of GB857462A publication Critical patent/GB857462A/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
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement

Landscapes

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

Abstract

857,462. Rotary wing aircraft rotors. LOVE, J., and KAY, D. Aug. 30, 1957 [May 31, 1956 (2)] Nos. 8211/56 and 8212/56. Class 4. A rotary wing aircraft rotor comprises a plurality of blades each articulated to a hub 1 through a pair of links 7, 8 the longitudinal axes of which lie in a plane parallel to the hub axis, the links being attached at their inboard ends to the hub for pivoting about parallel axes 9, 10 offset from and lying in planes perpendicular to the hub axis, and being attached at their outboard ends to the blade rest fitting 2 for swinging about parallel axes 5, 6 on opposite sides of and lying in planes perpendicular to the spanwise axis of the blade, the links converging towards the hub, the arrangement being such that the blade flaps about a virtual axis closer to the hub axis than the axes 9, 10. Pitch control independent of flapping movement is applied by mounting the blade root 16 for pitch change movement in bearings 17, 18 in the fitting 2. A chordwise lever (not shown) extending from the root 16 is pivoted to a link 15 pivoted to an intermediate point of a beam 12. One end of beam 12 is pivoted to a link 13 also pivoted to a lug 14 on fitting 2, and the other end of beam 12 is pivoted to a rod 11 about an axis located at the same distance from the hub axis as the virtual flapping axis. In a mean pitch setting, beam 12 and root 16, and link 13 and link 15, are parallel. Axial movement of rod 11 raises ar lowers link 15, altering the pitch of the blade. Flapping movement has substantially no effect on blade pitch. For collective pitch control only, a single rod 11 is pivoted to the beam of each blade. For cyclic pitch, each beam 12 has its own rod 11, or a single rod 11 is provided with a tiltable head. Drag hinges may be incorporated in hinges 9, 10. The hub may be fixed or tilting.
GB8211/56A 1956-05-31 1956-05-31 Improvements relating to rotary wing aircraft Expired GB857462A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB8211/56A GB857462A (en) 1956-05-31 1956-05-31 Improvements relating to rotary wing aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8211/56A GB857462A (en) 1956-05-31 1956-05-31 Improvements relating to rotary wing aircraft

Publications (1)

Publication Number Publication Date
GB857462A true GB857462A (en) 1960-12-29

Family

ID=9848020

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8211/56A Expired GB857462A (en) 1956-05-31 1956-05-31 Improvements relating to rotary wing aircraft

Country Status (1)

Country Link
GB (1) GB857462A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297080A (en) * 1979-12-17 1981-10-27 United Technologies Corporation Rotor blade pitch control linkage
US4340335A (en) * 1979-12-17 1982-07-20 United Technologies Corporation Helicopter tail rotor with pitch control mechanism
US4496284A (en) * 1982-03-18 1985-01-29 Westland Plc Helicopter rotors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4297080A (en) * 1979-12-17 1981-10-27 United Technologies Corporation Rotor blade pitch control linkage
US4340335A (en) * 1979-12-17 1982-07-20 United Technologies Corporation Helicopter tail rotor with pitch control mechanism
US4496284A (en) * 1982-03-18 1985-01-29 Westland Plc Helicopter rotors

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