GB2090214A - Controlling Helicopter Rotors - Google Patents
Controlling Helicopter Rotors Download PDFInfo
- Publication number
- GB2090214A GB2090214A GB8026309A GB8026309A GB2090214A GB 2090214 A GB2090214 A GB 2090214A GB 8026309 A GB8026309 A GB 8026309A GB 8026309 A GB8026309 A GB 8026309A GB 2090214 A GB2090214 A GB 2090214A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- blades
- hub
- controlled
- control
- 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.)
- Granted
Links
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
- B64C27/72—Means acting on blades
-
- 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
-
- 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
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
- B64C27/615—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including flaps mounted on blades
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
Helicopter rotor hub 10 with the blades as an assembly, the blades can be integral or separate, and controlled without any mechanical control linkage attached to the airframe. Electrical signals and/or optical signals passed through a transmitter unit 16 to the rotor hub position the rotor blades by driving a positioning motor 18 attached to each blade, the motor acting on the blade root, via gearing, or on an aileron on the blade. Electrical power fed to rotors via slip ring 8. An alternative semi- hydraulic control system is described (Fig. 7 not shown). <IMAGE>
Description
SPECIFICATION
Laser Electronically Controlled Helicopter Main
Rotor Hub and Aileron Controlled Rotor Blades (Rotating Wing Aircraft)
My invention will almost completely eliminate rotor induced vibration from helicopters by removing the present accepted method of controlling rotor blades through pitch change control rods to the blades.
Existing systems of changing/controlling pitch all rely on a mechanical linkage, this means that the force required to twist a rotor bide must use the chassis or airframe as the basis for the initial thrust to the rotor blades. This must and in fact does, create a mechanical reaction between airframe (helicopter) and rotor blade directly proportional to the force applied combined with the setting of the blades. For example if the blades are set in collective pitch (hovering flight) vibration will be less for any given revolution per minute, than for the equivalent R.P.M. in cyclic pitch (moving flight).
To take these facts a stage further, it is known fact that more rotor blades equal more vibration.
The proof of this can be seen by the success of existing 2 rotor designs, which are both cheaper to make and maintain and produce less vibration as well.
With my rotor head there will be less vibration than the 2 blade type whilst using any combination of blades a particular design would require. Less complexity will help reduce maintenance times and because of reduced vibration, airframe life will increase as will servicing intervals. Further advantages will acrue from less complexity because of an overall reduction in weight, this will improve payload/range and speed performance figures.
Another benefit, though less important will come from less aerodynamic drag to a much cleaner rotor hub design externally and mechanically because the rotor power unit(s) would only have to rotate the hub and not overcome the mechanical drag associated with conventional pitch change mechanisms.
Another invention is shown incorporated on the drawings enclosed (sheet 3) that is the control of the rotor blade(s) by aileron, exploiting the phenomena known as aileron reversal (on fixed wing aircraft) with the rotor blade rigidly connected to the hub (rigid rotor) or by electrical drive from the hub see sheet 4.
Although partly mechanical the last system will still achieve the sought after reduced vibration levels because the source of pitch change is connected to the rotor hub and will therefore riot transmit mechanically induced vibration through the airframe.
* The use of the LASER in this invention does not preclude the use of alternative electronics to achieve the same control functions and as such must not invalidate my rights to invention and
PATENT.
Reference numbers in the drawings (Figs. 19).
1 Blade control cilerons
3 Control unit in cockpit (bias unit incorporated
to achieve full cyclic/collective control
electronically)
6 Signal wires and power carrying lines
7 Control pulses/signals to aileron position
motor
8 Slip rings (in top of rotor hub to transfer
electrical power)
9 Control unit (triggerhead)
10 Rotor hub (forged as one piece unit; or
moulded/laminated in plastic, e.g. GRP,
carbon fibre; blades could be made
detachable.
11 Position motor 1 2 Receiving matrix
13 Optional servo tab operation for aileron
14 Receiver 1 5 Laser tubes (fibre optics) 1 6 Matrix of laser transmitter leads 1 8 Laser controlled electric pitch change motor 1 9 Rotor hub (modified conventional rigid hub)
20 Gear driven blade root/s
21 Mechanically controlled transmitter ring
22 Hydraulic positioning arms controlled by
unit in cockpit.
Claims
1. An electronically controlled rotor head which will dispense with all direct control linkages to the airframe. See Figs. 1,2 and 3.
2. Aileron controlled rotor blades using rotor twist or flexion to achieve pitch change/control.
See Fig. 1.
3. Rotor blade pitch controlled by electric servo motor(s) controlled from the triggerhead tube.
See Fig. 2.
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (1)
- **WARNING** start of CLMS field may overlap end of DESC **.SPECIFICATION Laser Electronically Controlled Helicopter Main Rotor Hub and Aileron Controlled Rotor Blades (Rotating Wing Aircraft) My invention will almost completely eliminate rotor induced vibration from helicopters by removing the present accepted method of controlling rotor blades through pitch change control rods to the blades.Existing systems of changing/controlling pitch all rely on a mechanical linkage, this means that the force required to twist a rotor bide must use the chassis or airframe as the basis for the initial thrust to the rotor blades. This must and in fact does, create a mechanical reaction between airframe (helicopter) and rotor blade directly proportional to the force applied combined with the setting of the blades. For example if the blades are set in collective pitch (hovering flight) vibration will be less for any given revolution per minute, than for the equivalent R.P.M. in cyclic pitch (moving flight).To take these facts a stage further, it is known fact that more rotor blades equal more vibration.The proof of this can be seen by the success of existing 2 rotor designs, which are both cheaper to make and maintain and produce less vibration as well.With my rotor head there will be less vibration than the 2 blade type whilst using any combination of blades a particular design would require. Less complexity will help reduce maintenance times and because of reduced vibration, airframe life will increase as will servicing intervals. Further advantages will acrue from less complexity because of an overall reduction in weight, this will improve payload/range and speed performance figures.Another benefit, though less important will come from less aerodynamic drag to a much cleaner rotor hub design externally and mechanically because the rotor power unit(s) would only have to rotate the hub and not overcome the mechanical drag associated with conventional pitch change mechanisms.Another invention is shown incorporated on the drawings enclosed (sheet 3) that is the control of the rotor blade(s) by aileron, exploiting the phenomena known as aileron reversal (on fixed wing aircraft) with the rotor blade rigidly connected to the hub (rigid rotor) or by electrical drive from the hub see sheet 4.Although partly mechanical the last system will still achieve the sought after reduced vibration levels because the source of pitch change is connected to the rotor hub and will therefore riot transmit mechanically induced vibration through the airframe.* The use of the LASER in this invention does not preclude the use of alternative electronics to achieve the same control functions and as such must not invalidate my rights to invention and PATENT.Reference numbers in the drawings (Figs. 19).1 Blade control cilerons3 Control unit in cockpit (bias unit incorporated to achieve full cyclic/collective control electronically)6 Signal wires and power carrying lines7 Control pulses/signals to aileron position motor8 Slip rings (in top of rotor hub to transfer electrical power)9 Control unit (triggerhead)10 Rotor hub (forged as one piece unit; or moulded/laminated in plastic, e.g. GRP, carbon fibre; blades could be made detachable.11 Position motor 1 2 Receiving matrix13 Optional servo tab operation for aileron14 Receiver 1 5 Laser tubes (fibre optics) 1 6 Matrix of laser transmitter leads 1 8 Laser controlled electric pitch change motor 1 9 Rotor hub (modified conventional rigid hub)20 Gear driven blade root/s21 Mechanically controlled transmitter ring22 Hydraulic positioning arms controlled by unit in cockpit.Claims1. An electronically controlled rotor head which will dispense with all direct control linkages to the airframe. See Figs. 1,2 and 3.2. Aileron controlled rotor blades using rotor twist or flexion to achieve pitch change/control.See Fig. 1.3. Rotor blade pitch controlled by electric servo motor(s) controlled from the triggerhead tube.See Fig. 2.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8026309A GB2090214B (en) | 1980-08-13 | 1980-08-13 | Controlling helicopter rotors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8026309A GB2090214B (en) | 1980-08-13 | 1980-08-13 | Controlling helicopter rotors |
Publications (2)
Publication Number | Publication Date |
---|---|
GB2090214A true GB2090214A (en) | 1982-07-07 |
GB2090214B GB2090214B (en) | 1984-09-12 |
Family
ID=10515419
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8026309A Expired GB2090214B (en) | 1980-08-13 | 1980-08-13 | Controlling helicopter rotors |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2090214B (en) |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4655685A (en) * | 1985-12-16 | 1987-04-07 | United Technologies Corporation | Helicopter main rotor blade having a short span slot near the tip end |
DE3614371A1 (en) * | 1986-04-28 | 1987-10-29 | Henschel Flugzeug Werke Gmbh | Device for controlling rotor blades |
US4720059A (en) * | 1986-12-31 | 1988-01-19 | Stearns Jr Hoyt A | High speed helicopter |
US4808072A (en) * | 1987-09-17 | 1989-02-28 | United Technologies Corporation | Electrical grounding connector for a helicoptor rotor |
US4946354A (en) * | 1987-12-15 | 1990-08-07 | Aerospatiale Societe Nationale Industrielle | Hydraulic device for individual control of pitch of a rotor blade |
GB2280412A (en) * | 1993-07-15 | 1995-02-01 | Nigel Howard Mckrill | Helicopter rotor controlled by light signals. |
WO1996001503A1 (en) * | 1994-07-06 | 1996-01-18 | Mcdonnell Douglas Helicopter Company | Piezoelectric actuator |
GB2298624A (en) * | 1995-03-04 | 1996-09-11 | Nigel Howard Mckrill | Light controlled helicopter rotor blade |
GB2299562A (en) * | 1995-04-01 | 1996-10-09 | Nigel Howard Mckrill | Actuator for helicopter rotor blade aileron |
WO2005100154A1 (en) * | 2004-04-13 | 2005-10-27 | Wavefront Technology Pty Ltd | System for rotor head and rotor blade |
EP1630097A1 (en) * | 2004-08-31 | 2006-03-01 | The Boeing Company | Rotor blade with structurally-integrated conduit assembly and method for its use |
DE102005007129A1 (en) * | 2005-02-17 | 2006-08-24 | Zf Friedrichshafen Ag | Arrangement for controlling of rotor blades of helicopter has controlled actuator, for collective and cyclic adjustment of blade setting angle of rotor blades, which are mechanically forcibly coupled among themselves |
CN102811905A (en) * | 2010-03-23 | 2012-12-05 | 贝尔直升机泰克斯特龙公司 | Swashplate-mounted permanent magnet alternator |
EP2829471A1 (en) * | 2013-07-23 | 2015-01-28 | Sikorsky Aircraft Corporation | Swashplateless coaxial rotary wing aircraft |
DE102015225098A1 (en) * | 2015-12-14 | 2017-06-14 | Zf Friedrichshafen Ag | Rotor head cover with integrated electronics for a helicopter |
CN113928540A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter inertia variable-pitch rotor wing |
CN116424552A (en) * | 2023-05-26 | 2023-07-14 | 北京航空航天大学 | Active torsion blade vibration control method, system, equipment and medium |
-
1980
- 1980-08-13 GB GB8026309A patent/GB2090214B/en not_active Expired
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4655685A (en) * | 1985-12-16 | 1987-04-07 | United Technologies Corporation | Helicopter main rotor blade having a short span slot near the tip end |
DE3614371A1 (en) * | 1986-04-28 | 1987-10-29 | Henschel Flugzeug Werke Gmbh | Device for controlling rotor blades |
US4720059A (en) * | 1986-12-31 | 1988-01-19 | Stearns Jr Hoyt A | High speed helicopter |
US4808072A (en) * | 1987-09-17 | 1989-02-28 | United Technologies Corporation | Electrical grounding connector for a helicoptor rotor |
US4946354A (en) * | 1987-12-15 | 1990-08-07 | Aerospatiale Societe Nationale Industrielle | Hydraulic device for individual control of pitch of a rotor blade |
GB2280412A (en) * | 1993-07-15 | 1995-02-01 | Nigel Howard Mckrill | Helicopter rotor controlled by light signals. |
WO1996001503A1 (en) * | 1994-07-06 | 1996-01-18 | Mcdonnell Douglas Helicopter Company | Piezoelectric actuator |
US5626312A (en) * | 1994-07-06 | 1997-05-06 | Mcdonnell Douglas Corporation | Piezoelectric actuator |
GB2298624A (en) * | 1995-03-04 | 1996-09-11 | Nigel Howard Mckrill | Light controlled helicopter rotor blade |
GB2299562A (en) * | 1995-04-01 | 1996-10-09 | Nigel Howard Mckrill | Actuator for helicopter rotor blade aileron |
WO2005100154A1 (en) * | 2004-04-13 | 2005-10-27 | Wavefront Technology Pty Ltd | System for rotor head and rotor blade |
JP2006069535A (en) * | 2004-08-31 | 2006-03-16 | Boeing Co:The | Longitudinal rotor blade, aircraft, and method for operating rotor-driven aircraft |
EP1630097A1 (en) * | 2004-08-31 | 2006-03-01 | The Boeing Company | Rotor blade with structurally-integrated conduit assembly and method for its use |
DE102005007129A1 (en) * | 2005-02-17 | 2006-08-24 | Zf Friedrichshafen Ag | Arrangement for controlling of rotor blades of helicopter has controlled actuator, for collective and cyclic adjustment of blade setting angle of rotor blades, which are mechanically forcibly coupled among themselves |
DE102005007129B4 (en) * | 2005-02-17 | 2008-07-10 | Zf Friedrichshafen Ag | Device for controlling rotor blades of a helicopter |
CN102811905B (en) * | 2010-03-23 | 2015-12-02 | 贝尔直升机泰克斯特龙公司 | A kind of tilting frame system and adopt the method for this tilting frame system generation current |
CN102811905A (en) * | 2010-03-23 | 2012-12-05 | 贝尔直升机泰克斯特龙公司 | Swashplate-mounted permanent magnet alternator |
US9248909B2 (en) | 2013-07-23 | 2016-02-02 | Sikorsky Aircraft Corporation | Swashplateless coaxial rotary wing aircraft |
EP2829471A1 (en) * | 2013-07-23 | 2015-01-28 | Sikorsky Aircraft Corporation | Swashplateless coaxial rotary wing aircraft |
DE102015225098A1 (en) * | 2015-12-14 | 2017-06-14 | Zf Friedrichshafen Ag | Rotor head cover with integrated electronics for a helicopter |
US10351228B2 (en) | 2015-12-14 | 2019-07-16 | Zf Friedrichshafen Ag | Rotor head with integrated electronics for a helicopter |
DE102015225098B4 (en) | 2015-12-14 | 2021-08-05 | Zf Friedrichshafen Ag | Rotor head cover with integrated electronics for a helicopter |
CN113928540A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter inertia variable-pitch rotor wing |
CN113928540B (en) * | 2021-11-19 | 2023-10-27 | 中国直升机设计研究所 | Helicopter inertia displacement rotor wing |
CN116424552A (en) * | 2023-05-26 | 2023-07-14 | 北京航空航天大学 | Active torsion blade vibration control method, system, equipment and medium |
CN116424552B (en) * | 2023-05-26 | 2023-08-11 | 北京航空航天大学 | Active torsion blade vibration control method, system, equipment and medium |
Also Published As
Publication number | Publication date |
---|---|
GB2090214B (en) | 1984-09-12 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19970813 |