GB1308023A - Bladed rotors - Google Patents

Bladed rotors

Info

Publication number
GB1308023A
GB1308023A GB2403870A GB2403870A GB1308023A GB 1308023 A GB1308023 A GB 1308023A GB 2403870 A GB2403870 A GB 2403870A GB 2403870 A GB2403870 A GB 2403870A GB 1308023 A GB1308023 A GB 1308023A
Authority
GB
United Kingdom
Prior art keywords
hub
stiffness
hinge
spring stack
cuff
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
GB2403870A
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
Priority to US84248769A priority Critical
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1308023A publication Critical patent/GB1308023A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • B64C27/37Rotors having articulated joints
    • B64C27/39Rotors having articulated joints with individually articulated blades, i.e. with flapping or drag hinges
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • B64C27/327Retention means relieving the stress from the arm, e.g. tie-bars
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C29/00Aircraft capable of landing or taking-off vertically
    • B64C29/0008Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded
    • B64C29/0016Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage

Abstract

1308023 Helicoptor rotors UNITED AIRCRAFT CORP 19 May 1970 [17 July 1969] 24038/70 Heading B7W [Also in Divisions E2 F1 and F2] A helicopter rotor has blades 28 attached to a hub 50 by a flapping hinge 61 or a flexible section 150, Fig. 15, for movement relative to the hub, with a spring stack 104, the stiffness of which may be varied in a given plane, fixed across the hinge 61 or flexible section 150. Each blade 28 is mounted in a cuff 70 through bearings 57 to allow pitch changes controlled by horn 98. Cuff 70 is connected to hub 50 through hinge 61 and transmits centrifugal forces between the blade and hub. Spring stack 104 is rotatably mounted in the cuff 70 and in a mount 118 in hub 50 with an arm 140 or 160, Fig. 15, to rotate it to vary its stiffness. The spring stack comprises a stack of metal laminates separated by layers of Teflon (Registered Trade Mark), fastened together by a bolt 112 and mounted at each end in members 120, 130 which allow longitudinal movement of the laminates relative to one another while preventing lateral movement. The cross-section of the spring stack may be square, rectangular, circular, oval or polygonal. In the position shown in Fig. 3, the spring stack has maximum stiffness to flexing about hinge 61 and on rotation through 90 degrees so that the hinge axis 82 is parallel to the planes of the laminates it has minimum stiffness with intermediate stiffness between these positions. The spring stacks in all the blade hub connections may be operated simultanously through a star member (146), Fig. 9 (not shown). Two rotors are mounted at the wing tips of a convertiplane for rotation about the wing spanwise axis so as to operate as an articulated or semi-rigid helicopter rotor or a rigid propellor.
GB2403870A 1969-07-17 1970-05-19 Bladed rotors Expired GB1308023A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US84248769A true 1969-07-17 1969-07-17

Publications (1)

Publication Number Publication Date
GB1308023A true GB1308023A (en) 1973-02-21

Family

ID=25287432

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2403870A Expired GB1308023A (en) 1969-07-17 1970-05-19 Bladed rotors

Country Status (4)

Country Link
US (1) US3589835A (en)
DE (1) DE2032259A1 (en)
FR (1) FR2051824B1 (en)
GB (1) GB1308023A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2214989A (en) * 1988-02-11 1989-09-13 Albert Denis Laurence Mounting blades on rotors

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1302768A (en) * 1970-02-27 1973-01-10
DE3104261C2 (en) * 1981-02-07 1985-05-30 Fag Kugelfischer Georg Schaefer Kgaa, 8720 Schweinfurt, De
DE3929886A1 (en) * 1989-09-08 1991-03-28 Dornier Conrado Airplane with engine gondolas tiltable above a cross axle
US5035576A (en) * 1989-10-11 1991-07-30 United Technologies Corporation Propeller blade pin attachment
US5118256A (en) * 1991-04-29 1992-06-02 United Technologies Corporation Blade retention apparatus with elastomeric preload
WO1994015113A1 (en) * 1992-12-23 1994-07-07 United Technologies Corporation Tubular elastomer damper
US5913659A (en) * 1993-11-22 1999-06-22 United Technologies Corporation Apparatus and method for adjusting rotor blade tracking
DE4443731A1 (en) * 1994-12-08 1996-06-13 Conrado Dornier Twin fuselage V/STOL aircraft
US20100270435A1 (en) * 2005-08-15 2010-10-28 Abe Karem Wing efficiency for tilt-rotor aircraft
EP1900634A1 (en) * 2006-09-15 2008-03-19 Yellowfin Limited Marine propulsion and constructional details thereof
EP1900636A1 (en) * 2006-09-15 2008-03-19 Yellowfin Limited Marine propulsion and constructional details thereof
US8267650B2 (en) * 2007-10-30 2012-09-18 Honeywell International Inc. Sequential stiffness support for bearing assemblies and method of fabrication
US9796469B2 (en) * 2014-04-04 2017-10-24 The Boeing Company Modular rotor craft rotor hub system
EP3232008A1 (en) * 2016-04-13 2017-10-18 Rolls-Royce plc Aerofoil body

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2553193A (en) * 1946-08-12 1951-05-15 Fairey Aviat Co Ltd Rotor blade for rotary wing aircraft
US3228481A (en) * 1964-04-24 1966-01-11 Bendix Corp Tie bar bushing
DE1456107A1 (en) * 1964-07-04 1968-12-19 Westland Aircraft Ltd Drehfluegelflugzeug
US3280918A (en) * 1965-04-26 1966-10-25 Bell Aerospace Corp Rotor construction
US3504989A (en) * 1967-12-28 1970-04-07 Boeing Co Rotor system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2214989A (en) * 1988-02-11 1989-09-13 Albert Denis Laurence Mounting blades on rotors

Also Published As

Publication number Publication date
FR2051824B1 (en) 1974-09-06
DE2032259A1 (en) 1972-01-13
FR2051824A1 (en) 1971-04-09
US3589835A (en) 1971-06-29

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee