GB630396A - Improvements in sustaining rotor for aircraft - Google Patents

Improvements in sustaining rotor for aircraft

Info

Publication number
GB630396A
GB630396A GB21895/47A GB2189547A GB630396A GB 630396 A GB630396 A GB 630396A GB 21895/47 A GB21895/47 A GB 21895/47A GB 2189547 A GB2189547 A GB 2189547A GB 630396 A GB630396 A GB 630396A
Authority
GB
United Kingdom
Prior art keywords
blade
sealed
trailing edge
air
spar
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
GB21895/47A
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.)
Autogiro Company of America
Original Assignee
Autogiro Company of America
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 Autogiro Company of America filed Critical Autogiro Company of America
Publication of GB630396A publication Critical patent/GB630396A/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

Abstract

630,396. Helicopter rotors. AUTOGIRO CO. of AMERICA. Aug. 8, 1947, No. 21895. Convention date, Feb. 9, 1940. [Class 4] A hollow blade for an aircraft sustaining rotor is substantially sealed at its inboard end against ingress of air and is apertured adjacent its outboard end to provide for egress of air from within the blade to prevent a centrifugal increase of internal pressure distorting the blade profile. The blade comprises a tubular spar to which are attached apertured ribs 7 connected by a trailing edge member (not shown) and partially covered by plywood 9 and wholly covered by fabric 10. An end rib 15 is sealed around the spar 4, which is internally sealed by a plug (not shown). A reinforced aperture 12 is provided at the lower trailing edge surface of the blade tip.
GB21895/47A 1940-02-09 1947-08-08 Improvements in sustaining rotor for aircraft Expired GB630396A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US630396XA 1940-02-09 1940-02-09

Publications (1)

Publication Number Publication Date
GB630396A true GB630396A (en) 1949-10-12

Family

ID=22046520

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21895/47A Expired GB630396A (en) 1940-02-09 1947-08-08 Improvements in sustaining rotor for aircraft

Country Status (1)

Country Link
GB (1) GB630396A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3096053A (en) * 1960-11-17 1963-07-02 Gen Grid Corp Low density construction material
WO2004045948A1 (en) * 2002-11-20 2004-06-03 Rotary Wing Innovations Limited Rotary blade

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3096053A (en) * 1960-11-17 1963-07-02 Gen Grid Corp Low density construction material
WO2004045948A1 (en) * 2002-11-20 2004-06-03 Rotary Wing Innovations Limited Rotary blade
GB2411634A (en) * 2002-11-20 2005-09-07 Rotary Wing Innovations Ltd Rotary blade
GB2411634B (en) * 2002-11-20 2006-05-24 Rotary Wing Innovations Ltd Rotary blade

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