GB578680A - Improvements in or relating to helicopter blades - Google Patents

Improvements in or relating to helicopter blades

Info

Publication number
GB578680A
GB578680A GB6355/44A GB635544A GB578680A GB 578680 A GB578680 A GB 578680A GB 6355/44 A GB6355/44 A GB 6355/44A GB 635544 A GB635544 A GB 635544A GB 578680 A GB578680 A GB 578680A
Authority
GB
United Kingdom
Prior art keywords
laminations
spar
blade
helicopter rotor
relating
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
GB6355/44A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB578680A publication Critical patent/GB578680A/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
    • B64C27/46—Blades
    • B64C27/473—Constructional features

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)

Abstract

578,680. Helicopter rotor blades. UNITED AIRCRAFT CORPORATION. April 5, 1944, No. 6355. Convention date, Feb. 27, 1943. [Class 4] A helicopter rotor blade comprises a spar 12 at the leading edge, incorporating central metal laminations 22, 24, and at the sides thereof glue-impregnated rubber or canvas laminations 30, 38, and 32, 40, respectively, the laminations being adhesively secured to wood plies 20, 28, 36, 44, 26, 34 and 42, and the assembly held together by bolts 46. The metal laminations serve to resist centrifugal forces, the other laminations damping blade vibrations, while in addition the blade is flexible in the direction of its rotation. Ribs 14 are attached to the spar 12, for example in the manner described in Specification 578,681.
GB6355/44A 1943-02-27 1944-04-05 Improvements in or relating to helicopter blades Expired GB578680A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US578680XA 1943-02-27 1943-02-27

Publications (1)

Publication Number Publication Date
GB578680A true GB578680A (en) 1946-07-08

Family

ID=22013213

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6355/44A Expired GB578680A (en) 1943-02-27 1944-04-05 Improvements in or relating to helicopter blades

Country Status (1)

Country Link
GB (1) GB578680A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995020104A1 (en) * 1994-01-20 1995-07-27 Torres Martinez, Manuel Fabrication of aerodynamic profiles
ES2089965A2 (en) * 1994-01-20 1996-10-01 Torres Martinez M Process for manufacturing aerodynamic profiles for wind- powered generator, aerodyne and similar blades

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995020104A1 (en) * 1994-01-20 1995-07-27 Torres Martinez, Manuel Fabrication of aerodynamic profiles
ES2089965A2 (en) * 1994-01-20 1996-10-01 Torres Martinez M Process for manufacturing aerodynamic profiles for wind- powered generator, aerodyne and similar blades

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