GB1342584A – Rotors for rotary winged aircraft
– Google Patents
GB1342584A – Rotors for rotary winged aircraft
– Google Patents
Rotors for rotary winged aircraft
Info
Publication number
GB1342584A
GB1342584A
GB1791670A
GB1342584DA
GB1342584A
GB 1342584 A
GB1342584 A
GB 1342584A
GB 1791670 A
GB1791670 A
GB 1791670A
GB 1342584D A
GB1342584D A
GB 1342584DA
GB 1342584 A
GB1342584 A
GB 1342584A
Authority
GB
United Kingdom
Prior art keywords
aircraft
attack
cam
sinusoidal
blade angle
Prior art date
1970-04-15
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
GB1791670A
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.)
Robertson F H
Original Assignee
Robertson F H
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.)
1970-04-15
Filing date
1971-04-19
Publication date
1974-01-03
1971-04-19
Application filed by Robertson F H
filed
Critical
Robertson F H
1974-01-03
Publication of GB1342584A
publication
Critical
patent/GB1342584A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
Abstract
1342584 Rotary winged aircraft F H ROBERTSON 19 April 1971 [15 April 1970] 17916/70 Heading B7W Means for effecting non-sinusoidal cyclic pitch change of the blades 20 of a rotary winged aircraft rotor whilst independently allowing a sinusoidal cyclic pitch control to be superimposed thereon comprises spindles 22 which are bolted to the wing roots and are in threaded engagement with spirally-splined plunges 28 bearing on a cam 36 whose surface is designed to cause the blade angle of attack to be varied in azimuth to suit the speed of the aircraft. Sinusoidal pitch variation is achieved by means of a tiltable spider 10 connected to levers 13 which are straight splined to the plungers 28 to permit indpendence of operation. Cam 36 can rise and fall on fixed splines 37; its upper end is circular to correspond to hovering or vertical descent of the aircraft, and its lower end is shaped to set the correct blade angle of attack at all points around the rotor tip path at maximum forward speed. As this speed is approached, cam 36 is moved up the splines 37 by an automatic or manually controlled actuator 40, thus causing plungers 28 to rotate spindles 22 and vary the blade angle of attack in azimuth in such a way that the blade lift is kept constant. Collective pitch change may be incorporated by arranging for the entire cyclic picht control assembly (including spider 10) to be adjustable in a vertical direction.
GB1791670A
1970-04-15
1971-04-19
Rotors for rotary winged aircraft
Expired
GB1342584A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB1791670
1970-04-15
Publications (1)
Publication Number
Publication Date
GB1342584A
true
GB1342584A
(en)
1974-01-03
Family
ID=10103504
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB1791670A
Expired
GB1342584A
(en)
1970-04-15
1971-04-19
Rotors for rotary winged aircraft
Country Status (2)
Country
Link
US
(1)
US3756743A
(en)
GB
(1)
GB1342584A
(en)
Families Citing this family (9)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
IT1164936B
(en)
*
1979-02-27
1987-04-15
Giovanni Agusta Costruzioni Ae
INTERNAL CONTROL ROTOR SHAFT FOR HELICOPTERS
US4650400A
(en)
*
1984-03-26
1987-03-17
David Constant V
Helicopter blade pitch adjusting system
US4697986A
(en)
*
1984-03-26
1987-10-06
David Constant V
Helicopter blade cyclic pitch control system
US4778340A
(en)
*
1985-11-25
1988-10-18
Costruzioni Aeronautiche Giovanni Augusta S.P.A.
Main helicopter rotor
US5163815A
(en)
*
1991-07-29
1992-11-17
Fetters Dennis L
Rotor blade control mechanism
DE19910448C1
(en)
*
1999-03-10
2000-05-18
Zf Luftfahrttechnik Gmbh
Rotor head for helicopter has rotary shaft formed as funnel shaped enclosure for drive
DE10052757A1
(en)
*
2000-10-25
2002-05-08
Zf Luftfahrttechnik Gmbh
Rotor blade control device
EP4086171B1
(en)
*
2021-05-05
2023-11-22
AIRBUS HELICOPTERS DEUTSCHLAND GmbH
A cyclic pitch angle adjustment apparatus
CN115180141A
(en)
*
2022-08-19
2022-10-14
南京航空航天大学
Movable paddle rotor system and rotor craft
Family Cites Families (10)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US1403624A
(en)
*
1919-11-14
1922-01-17
Pescara Raul Pateras
System of propellers of variable incidence and differential motion for helicopteral machines
US1454944A
(en)
*
1920-07-15
1923-05-15
Pescara Raul Pateras
System of helicopter screws
US2663374A
(en)
*
1949-03-22
1953-12-22
Ryan Aeronautical Co
Helicopter rotor control mechanism
GB791474A
(en)
*
1955-01-11
1958-03-05
Hunting Percival Aircraft Ltd
Improvements relating to helicopter rotors
US3031017A
(en)
*
1959-09-30
1962-04-24
United Aircraft Corp
Cyclic pitch control
US3080002A
(en)
*
1961-06-29
1963-03-05
Doman Helicopters Inc
Rotor with fixed pylon
US3102597A
(en)
*
1961-08-14
1963-09-03
Bell Aerospace
Method of second harmonic control
US3144908A
(en)
*
1962-12-28
1964-08-18
Bell Aerospace
Selective second harmonic control
US3554662A
(en)
*
1968-01-25
1971-01-12
Fairchild Hiller Corp
Reverse velocity rotor and rotorcraft
US3525576A
(en)
*
1969-03-10
1970-08-25
Pierre Rene Leon Bernard Doran
Jet flap control
1971
1971-04-15
US
US00134369A
patent/US3756743A/en
not_active
Expired – Lifetime
1971-04-19
GB
GB1791670A
patent/GB1342584A/en
not_active
Expired
Also Published As
Publication number
Publication date
US3756743A
(en)
1973-09-04
Similar Documents
Publication
Publication Date
Title
GB1322169A
(en)
1973-07-04
Convertiplanes
ES413589A1
(en)
1976-08-01
Aircraft transporter
GB1116164A
(en)
1968-06-06
Control system for helicopters
US2507657A
(en)
1950-05-16
Aircraft with mixed type propulsion and sustaining means
GB1342584A
(en)
1974-01-03
Rotors for rotary winged aircraft
US2601090A
(en)
1952-06-17
Helicopter control
GB1322373A
(en)
1973-07-04
Aricraft having two lift producing devices and methods of operating such aircraft
GB1260384A
(en)
1972-01-19
Rotor system for high speed helicopters and a method of controlling the pitch of a helicopter rotor
GB1110062A
(en)
1968-04-18
Convertible aircraft
US2593910A
(en)
1952-04-22
Variable pitch reversible propeller
US2600017A
(en)
1952-06-10
Variable pitch reversible propeller
US2669308A
(en)
1954-02-16
Control system for coaxial helicopter blades
GB1065582A
(en)
1967-04-19
Variable-pitch propellers
US2680579A
(en)
1954-06-08
Rotor speed control for rotorfixed wing aircraft
GB652817A
(en)
1951-05-02
Improvements in means for controlling the pitch of rotor blades of helicopters
GB936789A
(en)
1963-09-11
Blade pitch control mechanism for a helicopter
GB800890A
(en)
1958-09-03
Directional control system for rotary wing aircraft
US2499161A
(en)
1950-02-28
Rotative winged aircraft control
FR2338845A1
(en)
1977-08-19
Helicopter rotor blade feathering mechanism – has fixed pitch helical drive and swinging control blade arrangement
US2889887A
(en)
1959-06-09
Method of operating rotary wing aircraft including jet-driven rotors
FR2309401A1
(en)
1976-11-26
Rotary wing producing lift and thrust – has horizontal blades with pitch control, rotating about horizontal shaft
GB631165A
(en)
1949-10-28
Improvements in or relating to aircraft and propulsion means therefor
GB1175066A
(en)
1969-12-23
Improvements in or relating to Vertical Take-Off and Landing Aircraft
GB1175073A
(en)
1969-12-23
Improvements in or relating to Vertical Take-off and Landing Aircraft
GB601952A
(en)
1948-05-14
Improvements in aircraft with sustaining airscrews
Legal Events
Date
Code
Title
Description
1974-05-15
PS
Patent sealed [section 19, patents act 1949]
1976-04-22
435
Patent endorsed ‘licences of right’ on the date specified (sect. 35/1949)
1978-11-22
PCNP
Patent ceased through non-payment of renewal fee
