GB1118117A - Helicopter with tail-mounted rotor system for propulsion and yawing control - Google Patents
Helicopter with tail-mounted rotor system for propulsion and yawing controlInfo
- Publication number
- GB1118117A GB1118117A GB1770666A GB1770666A GB1118117A GB 1118117 A GB1118117 A GB 1118117A GB 1770666 A GB1770666 A GB 1770666A GB 1770666 A GB1770666 A GB 1770666A GB 1118117 A GB1118117 A GB 1118117A
- Authority
- GB
- United Kingdom
- Prior art keywords
- control
- propeller
- rudder
- tail
- main rotor
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/8272—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising fins, or movable rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
1,118,117. Controlling helicopters. DORNIER-WERKE G.m.b.H. 22 April, 1966 [22 April, 1965], No. 17706/66. Headings B7G and B7W. A helicopter has a tail mounted screw propeller rotatable about a longitudinal axis to produce forward thrust and provided with cyclic pitch control for yaw control. The propeller blades 12 are pivotally mounted, preferably by the hub which forms part of a constant velocity joint (Fig. 4, not shown) and is tilted by movement of a swashplate 13. The cyclic pitch variations thus change the plane of rotation of the blades, and the thrust direction (Figs. 3a, 3b, not shown). The pilot's rudder bar 16 operates the cyclic control and a rudder 22 immediately upstream of the propeller through a mixing unit 20 which varies the control movements applied to the rudder and swashplate in accordance with ram air pressure (i.e. forward speed), so that at cruising speed only the rudder is operated, but when hovering, both rudder and swashplate are operated. The mixing unit may additionally be controlled manually. The main rotor and tail propeller are driven by a gas turbine engine (2, Fig. 1, not shown), through a gear-box (3) with separate output shafts. Collective pitch control of the main rotor and the tail propeller are effected together by a pilot's control lever 23 and in the same sense. The collective pitch of the tail propeller may be increased automatically as the cyclic pitch increases to provide a sufficient range of yawing moment, and may also be varied independently by an electric motor 28 operated by a button 30 on the control column 29, to preserve an efficient balance between the forward thrusts produced by the main rotor and tail propeller. An instrument 31 indicates when a certain forward position of the column 29 has been reached. Control surfaces, wings.-A tailplane (8, Fig. 1, not shown) is located in the downwash of the main rotor; this is stated to prevent a sudden trim change as the helicopter accelerates from hovering flight. The helicopter is also supported during forward flight on wings (7), the lift of which can be varied by spoilers or flaps or by varying their incidence, e.g. so that sufficient body incidence can be attained to cause autorotation of the main rotor in the event of engine failure.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DED47084A DE1272729B (en) | 1965-04-22 | 1965-04-22 | Combination aircraft with a rotor arranged at the tail |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1118117A true GB1118117A (en) | 1968-06-26 |
Family
ID=7050180
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1770666A Expired GB1118117A (en) | 1965-04-22 | 1965-04-22 | Helicopter with tail-mounted rotor system for propulsion and yawing control |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE1272729B (en) |
FR (1) | FR1484732A (en) |
GB (1) | GB1118117A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2197276A (en) * | 1986-09-26 | 1988-05-18 | Airship Ind | Improvements in airships |
US9041519B2 (en) | 2009-02-04 | 2015-05-26 | Mikado Model Helicopters GmbH | Model helicopter attitude control and receiving device with reduced size and self-learning features |
WO2016126304A1 (en) * | 2015-02-04 | 2016-08-11 | Sikorsky Aircraft Corporation | Improved directional control for coaxial rotary wing craft |
US9437101B2 (en) | 2011-04-15 | 2016-09-06 | Ulrich Röhr | System, transmitting device, receiving device, and method for the wireless control of an RC model |
WO2016200458A3 (en) * | 2015-05-20 | 2017-03-02 | Sikorsky Aircraft Corporation | Mono-cyclic swashplate |
CN112089533A (en) * | 2020-10-13 | 2020-12-18 | 航宇救生装备有限公司 | Helicopter hoisting anti-rotation stretcher |
CN113086165A (en) * | 2021-04-20 | 2021-07-09 | 中国直升机设计研究所 | Helicopter with variable distance between main rotor and tail rotor |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB8927784D0 (en) * | 1989-12-08 | 1990-05-30 | Westland Helicopters | Helicopters |
FR2962713A1 (en) | 2010-07-13 | 2012-01-20 | Eurocopter France | METHOD AND AIRCRAFT PROVIDED WITH A BACK-UP ROTOR |
FR3014838B1 (en) | 2013-12-17 | 2015-12-25 | Eurocopter France | GIRAVION EQUIPPED WITH A REVERSE ROTOR ANTI COUPLE PARTICIPATING SELECTIVELY TO THE SUSTENTATION AND PROPULSION IN TRANSLATION OF THE GIRAVION |
FR3014837B1 (en) * | 2013-12-17 | 2017-05-26 | Eurocopter France | GIRAVION EQUIPPED WITH AN ANTICOUPLE REAR ROTOR PARTICIPATING IN THE SUSTENTATION OF THE GIRAVION BY CYCLIC VARIATION OF THE PAST OF THE PALES DUDIT ROTOR REAR |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2479549A (en) * | 1943-11-10 | 1949-08-23 | Sperry Corp | Automatic pilot for helicopters |
DE1144116B (en) * | 1959-11-06 | 1963-02-21 | Boelkow Entwicklungen Kg | Rotary wing aircraft with a tail rotor and a vertical tail |
DE1136580B (en) * | 1960-10-01 | 1962-09-13 | Boelkow Entwicklungen Kg | Rotary wing aircraft |
US3138349A (en) * | 1962-01-15 | 1964-06-23 | Piasecki Aircraft Corp | Rotary wing aircraft tail assembly and controls |
-
1965
- 1965-04-22 GB GB1770666A patent/GB1118117A/en not_active Expired
- 1965-04-22 DE DED47084A patent/DE1272729B/en active Pending
-
1966
- 1966-04-22 FR FR67008584A patent/FR1484732A/en not_active Expired
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2197276A (en) * | 1986-09-26 | 1988-05-18 | Airship Ind | Improvements in airships |
GB2197276B (en) * | 1986-09-26 | 1990-04-04 | Airship Ind | Improvements in airships |
US9041519B2 (en) | 2009-02-04 | 2015-05-26 | Mikado Model Helicopters GmbH | Model helicopter attitude control and receiving device with reduced size and self-learning features |
US9056259B2 (en) | 2009-02-04 | 2015-06-16 | Mikado Model Helicopters GmbH | Model helicopter control and receiving means |
US9437101B2 (en) | 2011-04-15 | 2016-09-06 | Ulrich Röhr | System, transmitting device, receiving device, and method for the wireless control of an RC model |
WO2016126304A1 (en) * | 2015-02-04 | 2016-08-11 | Sikorsky Aircraft Corporation | Improved directional control for coaxial rotary wing craft |
US20180257771A1 (en) * | 2015-02-04 | 2018-09-13 | Sikorsky Aircraft Corporation | Improved directional control for coaxial rotary wing craft |
US10703472B2 (en) * | 2015-02-04 | 2020-07-07 | Sikorsky Aircraft Corporation | Directional control for coaxial rotary wing craft |
WO2016200458A3 (en) * | 2015-05-20 | 2017-03-02 | Sikorsky Aircraft Corporation | Mono-cyclic swashplate |
CN112089533A (en) * | 2020-10-13 | 2020-12-18 | 航宇救生装备有限公司 | Helicopter hoisting anti-rotation stretcher |
CN113086165A (en) * | 2021-04-20 | 2021-07-09 | 中国直升机设计研究所 | Helicopter with variable distance between main rotor and tail rotor |
CN113086165B (en) * | 2021-04-20 | 2022-11-04 | 中国直升机设计研究所 | Helicopter with variable distance between main rotor and tail rotor |
Also Published As
Publication number | Publication date |
---|---|
DE1272729B (en) | 1968-07-11 |
FR1484732A (en) | 1967-06-16 |
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