GB1199595A – Trailing Rotor Convertiplane
– Google Patents
GB1199595A – Trailing Rotor Convertiplane
– Google Patents
Trailing Rotor Convertiplane
Info
Publication number
GB1199595A
GB1199595A
GB3575567A
GB3575567A
GB1199595A
GB 1199595 A
GB1199595 A
GB 1199595A
GB 3575567 A
GB3575567 A
GB 3575567A
GB 3575567 A
GB3575567 A
GB 3575567A
GB 1199595 A
GB1199595 A
GB 1199595A
Authority
GB
United Kingdom
Prior art keywords
axis
rotor
pitch
blade
blades
Prior art date
1967-08-03
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
GB3575567A
Inventor
Kenneth William Sambell
John Anthony Detore
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.)
Bell Aerospace Corp
Original Assignee
Bell Aerospace 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.)
1967-08-03
Filing date
1967-08-03
Publication date
1970-07-22
1967-08-03
Application filed by Bell Aerospace Corp
filed
Critical
Bell Aerospace Corp
1967-08-03
Priority to GB3575567A
priority
Critical
patent/GB1199595A/en
1970-07-22
Publication of GB1199595A
publication
Critical
patent/GB1199595A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
Classifications
B—PERFORMING OPERATIONS; TRANSPORTING
B64—AIRCRAFT; AVIATION; COSMONAUTICS
B64C—AEROPLANES; HELICOPTERS
B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft 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
1,199,595. Convertiplanes. BELL AERO-SPACE CORP. 3 Aug., 1967, No. 35755/67. Heading B7W. A convertiplane comprises a fuselage 10, wings 12, 14, 250 each carrying a rotor assembly 24, 26 tiltable about a transverse axis 152 between a stored position, Fig. 1, with the rotor axis of rotation lying fore-and-aft and the rotor blades 32, 34 folded parallel thereto, and an operative position as in Figs. 12, 13 for normal helicopter operation. When moving from the stored to the operative position the blades are first unfolded, and then their speed in autorotation is controlled by varying the blade pitch as the rotor assemblies are tilted about the transverse axis. When in the operative position, power from forward flight engines 18, 20, 22 is transferred to mechanically driving the rotor assemblies 24, 26. The blade pitch is controlled both cyclically and collectively not only when power driven in the operational position by the pilot, but also automatically when autorotating during both the unfolding of the blades and the rotation of the rotor assemblies about the transverse axis. The blades 264, Fig. 13, are folded about axes 272 by the extension of jack 302 acting through shaft 298 and links 294 on lever arms 292 integral with the blades. The rotor assemblies are rotated about the transverse axis by motors 334 driving worm gears engaging pinions which rotate with gear-boxes 304, there being gearing 336 and a cross-shaft to ensure that both rotor assemblies move together. Collective blade pitch control, Fig. 12. The pitch of the blade 100 is varied about the pitch axis 128 by the rotation of gear 126 by gear 124 rotating with pinion 122 driven by worm 120 which rotates about the folding axis 150. Unfolding the blade about axis 150 changes the collective pitch from – 90 to – 80 degrees, thereby starting autorotation of the rotor head. Worm 120 is rotated through gearing 118, 116, 114 moved by rack 112 linked to the rotating part of sleeve 110, the axial position of which along the axis 108 of rotor rotation is controlled by link 136 from the arms 160 pivotable about a transverse axis displaced from axis 152. The arms 160 are controlled by linkage 162, 164, 174, 172, 170. When the blades have been unfolded motor 166 acting through gearing 168 increases the collective blade pitch to about – 40 degrees, causing autorotation at about half full speed. Then as the rotor assembly is rotated about axis 152, the displacement of the axis of arms 160 causes the collective blade pitch to further increase with the speed of autorotation, so that full rotational speed occurs when the mast is erect. Then when the rotors become power driven a mechanism 178 connects up the pilot’s collective pitch control sticks 176. Cyclic blade pitch control.-The cyclic pitch of blade 100 is varied by moving the worm 120 axially along axis 150, by linkage 148, 146, 144, 142, 140 connected to the rotating part 105 of swashplate mechanism 104, whose tilt about axis 106 is controlled by a link 138 attached to a bell-crank. This engages a cam groove 158 in a cylinder 154 which automatically controls the rotor blade cyclic pitch as the rotor assembly is rotated about axis 152. Cyclic blade pitch is controlled when the rotors are powerdriven by the axial movement of the cylinder 154 along the axis 152 by a linkage 220 connected via mechanisms 216, 218 to the pilot controls 180, 182 which also control the control surfaces by suitable linkages 184, 186, 188.
GB3575567A
1967-08-03
1967-08-03
Trailing Rotor Convertiplane
Expired
GB1199595A
(en)
Priority Applications (1)
Application Number
Priority Date
Filing Date
Title
GB3575567A
GB1199595A
(en)
1967-08-03
1967-08-03
Trailing Rotor Convertiplane
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB3575567A
GB1199595A
(en)
1967-08-03
1967-08-03
Trailing Rotor Convertiplane
Publications (1)
Publication Number
Publication Date
GB1199595A
true
GB1199595A
(en)
1970-07-22
Family
ID=10381223
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB3575567A
Expired
GB1199595A
(en)
1967-08-03
1967-08-03
Trailing Rotor Convertiplane
Country Status (1)
Country
Link
GB
(1)
GB1199595A
(en)
Cited By (4)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
CN102392775A
(en)
*
2011-09-14
2012-03-28
浙江大学
Pitch varying mechanism for horizontal shaft ocean current energy generator
WO2017035677A1
(en)
*
2015-09-02
2017-03-09
Figueroa Martinez Diómedes
Machine that travels like a car, takes off like a helicopter and flies like an aeroplane
DE102012104783B4
(en)
2012-06-01
2019-12-24
Quantum-Systems Gmbh
Aircraft, preferably UAV, drone and / or UAS
US11820499B1
(en)
*
2022-10-06
2023-11-21
Archer Aviation, Inc.
Tilt rotor systems and methods for eVTOL aircraft
1967
1967-08-03
GB
GB3575567A
patent/GB1199595A/en
not_active
Expired
Cited By (4)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
CN102392775A
(en)
*
2011-09-14
2012-03-28
浙江大学
Pitch varying mechanism for horizontal shaft ocean current energy generator
DE102012104783B4
(en)
2012-06-01
2019-12-24
Quantum-Systems Gmbh
Aircraft, preferably UAV, drone and / or UAS
WO2017035677A1
(en)
*
2015-09-02
2017-03-09
Figueroa Martinez Diómedes
Machine that travels like a car, takes off like a helicopter and flies like an aeroplane
US11820499B1
(en)
*
2022-10-06
2023-11-21
Archer Aviation, Inc.
Tilt rotor systems and methods for eVTOL aircraft
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Legal Events
Date
Code
Title
Description
1970-12-02
PS
Patent sealed
1977-03-02
PLNP
Patent lapsed through nonpayment of renewal fees
