CN104229123A - Device without helicopter tail rotor - Google Patents
Device without helicopter tail rotor Download PDFInfo
- Publication number
- CN104229123A CN104229123A CN201310249677.4A CN201310249677A CN104229123A CN 104229123 A CN104229123 A CN 104229123A CN 201310249677 A CN201310249677 A CN 201310249677A CN 104229123 A CN104229123 A CN 104229123A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- supporting
- moment
- movement parts
- following characteristics
- 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.)
- Pending
Links
Landscapes
- Transmission Devices (AREA)
Abstract
The invention relates to a device without a helicopter tail rotor. The invention provides a device for eliminating inversion torque influence caused by a rotor wing. By adopting the device, the power consumption is relatively low, and the influence caused by the reverse torque can be eliminated without utilizing a conventional technology of a helicopter, such as the tail rotor, an air blowing structure or a two-propeller structure. The device comprises a moving part, a bearing part, a power device, and a control device for coordinating the relations between a driver and the device and between a helicopter body and the device by virtue of driving wheels.
Description
Technical field
The present invention relates to a kind of device eliminating the impact of rotor torque reaction.
Background technology
During rotor rotational, often can produce torque reaction to the fuselage of its rotation of driving, the method for common elimination torque reaction impact has three kinds: 1. band tail boom tail prize, eliminates the impact of rotor torque reaction with the tail-rotor air blowing acquisition moment of reaction.2., with DCB Specimen, DCB Specimen direction of rotation, torque reaction is cancelled out each other.3. use tail-rotor blowing method, typical type is the MD series of the U.S..
Summary of the invention
Apparatus of the present invention comprise the movement parts 1 done relative motion with fuselage; Be fixedly linked with fuselage, be convenient to the supporting 2 of 1 motion; The engine installation 3 that actuation movement part 1 moves and drive wheel 4; Regulation device 5.
Movement parts wherein has following characteristics: by engine installation and drive wheel, the supporting on fuselage can do the motion of relative fuselage, produces the counteraction force and moment contrary with rotor torque reaction to supporting and fuselage.
Supporting has following characteristics: be fixedly linked with fuselage, movement parts can be made thereon to move or the motion of actuation movement part, accept the counteraction force and moment that movement parts produces itself and fuselage.
Engine installation can be arranged on movement parts or supporting is inner; Also can by drive the engine installation of rotor and driving device substitute, just as the actuating device of present helicopter tail rotor.
Engine installation is generally equipped with the drive wheel of actuation movement part.
The principal character of regulation device is: the needs that coordination driver and fuselage change the moment of reaction, with the relation of apparatus of the present invention, performs the order to moment of reaction change demand.
When driver and fuselage change demand to torque reaction, can by controlling the transmission of signal such as electronic circuit or mechanical device to regulation device.Regulation device can have two class formations:
One class is by pressure between controlled motion part 1 and supporting 2, simultaneously the horsepower input of motivation of adjustment device, enters the antagonistic force required for that control and moment size.
Two classes are controlled motion part 1 arm of force sizes on supporting 2, simultaneously the horsepower input of motivation of adjustment device, enter the antagonistic force moment required for that control.
Known by formula P=F.V, for less power, obtain larger antagonistic force, the relative fuselage low-speed motion of movement parts can be made.
Figure of description illustrates: Figure 1 shows that helicopter tail slurry structural representation.Fig. 2 is embodiment one structural representation.Fig. 3 is embodiment two structural representation.
Illustrate below in conjunction with example structure:
Fig. 2 is embodiment one structure: 6 is rolling discs, and 8 is that plain bearing and `7 shell form movement parts 1; Transmission shaft 11, power reverser 10, drive wheel 9, forms supporting 2; Control path 14 and controller 12, fixed type bearing 13 forms control regulation device 5.
When dynamical axis 11 transferring power is to drive wheel 9, drive wheel 9 rotates, and rotating disk 6 is rotated.When rotating disk 6 rotates, an antagonistic force can be produced to drive wheel 9, enter you and the moment of reaction is produced to supporting 2 and fuselage, offset main rotor to the torque reaction of fuselage.
When main rotor torque reaction increases, sustainer, main engine horsepower output can increase, the power being correspondingly input to apparatus of the present invention can increase, simultaneously, control path controls regulation device 5, and make pressure increase between movement parts 1 and supporting 2, antagonistic force increases thereupon, antagonistic force moment increases, and offsets the main rotor torque reaction after increasing.When main rotor converse rotating force reduces, situation is contrary with upper.
Controller 12 acts on similar power-transfer clutch, and by push-and-pull movement parts 1, control the pressure between drive wheel 9 and rolling disc 6, controller adopts linear electric motors herein, can certainly make machinery or hydraulic pressure into, electromagnetic structure.Control path is 14.
Fig. 3 is embodiment two structure: forward dish 15, shell 16, and fixed type bearing 17 forms supporting; Rotating shaft 22, engine installation 20, drive wheel 18 forms movement parts; Control path 21, control piece 19 forms regulation device.
When motoricity device 20 drives drive wheel 18 to rotate, whole movement parts can be driven to forward motion on dish 15, antagonistic force is produced to forwarding dish 15, produce the demand command routing of the moment of reaction to pod may 19, push-and-pull drive wheel, regulate and control engine installation 20 throttle, motivation of adjustment rating of set, to adjust moment of reaction size simultaneously.When power increase, and extrapolate drive wheel time, the moment of reaction increase; Otherwise the moment of reaction reduces.
Claims (5)
1. movement parts has following characteristics: by engine installation and drive wheel, fuselage supporting can do the motion of relative fuselage, produces the antagonistic force moment contrary with rotor torque reaction to supporting and fuselage.
2. supporting has following characteristics: be connected with fuselage, and movement parts can be made thereon to move, and accepts the counteraction force and moment that movement parts produces itself and fuselage.
3. engine installation has following characteristics can be arranged on movement parts or supporting inner; Also can by the engine installation of rotor and driving device substitute.
4. drive wheel has following characteristics: be generally provided on engine installation, and actuation movement part moves.
5. regulation device has following characteristics: accept pilot (person) and fuselage to the order of moment of reaction demand, by pressure between controlled motion part and supporting or regulate and control the antagonistic force arm of force of movement parts on supporting, coordinate the watt level of motivation of adjustment device simultaneously, enter you and control moment of reaction size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310249677.4A CN104229123A (en) | 2013-06-24 | 2013-06-24 | Device without helicopter tail rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310249677.4A CN104229123A (en) | 2013-06-24 | 2013-06-24 | Device without helicopter tail rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104229123A true CN104229123A (en) | 2014-12-24 |
Family
ID=52218212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310249677.4A Pending CN104229123A (en) | 2013-06-24 | 2013-06-24 | Device without helicopter tail rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104229123A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4928907A (en) * | 1988-02-29 | 1990-05-29 | Y & B Investment Corporation | Compound helicopter with no tail rotor |
| US4948068A (en) * | 1988-05-12 | 1990-08-14 | Mcdonnell Douglas Corporation | Circulation control slots in helicopter yaw control system |
| US5232183A (en) * | 1991-03-06 | 1993-08-03 | The Boeing Company | Helicopter anti-torque control system utilizing exhaust gas |
| US5691391A (en) * | 1992-08-21 | 1997-11-25 | Mcdonnell Douglas Helicopter | Process for making an injection molded fan blade |
| US20080093500A1 (en) * | 2004-09-28 | 2008-04-24 | Smith Dudley E | Propulsive Anti-Torque System for Rotorcraft |
| US20110121128A1 (en) * | 2009-11-23 | 2011-05-26 | Balkus Jr Carl E | Helicopter Auxilary Anti-Torque System |
| CN202828092U (en) * | 2012-09-25 | 2013-03-27 | 李金玲 | Automatic-rotor wing helicopter with no tail rotor |
-
2013
- 2013-06-24 CN CN201310249677.4A patent/CN104229123A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4928907A (en) * | 1988-02-29 | 1990-05-29 | Y & B Investment Corporation | Compound helicopter with no tail rotor |
| US4948068A (en) * | 1988-05-12 | 1990-08-14 | Mcdonnell Douglas Corporation | Circulation control slots in helicopter yaw control system |
| US5232183A (en) * | 1991-03-06 | 1993-08-03 | The Boeing Company | Helicopter anti-torque control system utilizing exhaust gas |
| US5691391A (en) * | 1992-08-21 | 1997-11-25 | Mcdonnell Douglas Helicopter | Process for making an injection molded fan blade |
| US20080093500A1 (en) * | 2004-09-28 | 2008-04-24 | Smith Dudley E | Propulsive Anti-Torque System for Rotorcraft |
| US20110121128A1 (en) * | 2009-11-23 | 2011-05-26 | Balkus Jr Carl E | Helicopter Auxilary Anti-Torque System |
| CN202828092U (en) * | 2012-09-25 | 2013-03-27 | 李金玲 | Automatic-rotor wing helicopter with no tail rotor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2261115B1 (en) | System for driving a propeller pitch change mechanism | |
| EP2261114B1 (en) | Pitch change actuation system for a counter-rotating propeller | |
| EP2097316B1 (en) | Hybrid actuator for helicopter rotor blade control flaps | |
| US8672627B2 (en) | On-blade actuator for helicopter rotor blade control flaps | |
| CN203428022U (en) | Electromagnetic variable-pitch propeller of unmanned aerial vehicle | |
| US20100123039A1 (en) | Tail rotor system and method for controlling a tail rotor system | |
| US20050226727A1 (en) | Methods and systems for controlling the pitch of a propeller | |
| RU2010143010A (en) | ANTI-VIRTUAL ROTATION AIR SCREW SYSTEM WITH VOIL FLUIDING DEVICE | |
| CN203780797U (en) | Double-motor variable-pitch multi-rotor aircraft | |
| CN103107675A (en) | Speed-adjustable magnetic eddy current shaft coupling | |
| CN203497177U (en) | Five-rotor aircraft capable of changing amplitude | |
| CN104554711A (en) | Aerodynamic control servo system for controlling load tilt angle of aerial rudder of aircraft | |
| JP2018518410A (en) | Motor-type device having reciprocating motion of moving member and accompanying control method | |
| CN107399431A (en) | Applied to the motor on electric drive helicopter tail rotor and reducer integrated device and its control method | |
| US20140322017A1 (en) | Rotary mechanical system with contactless actuation | |
| CN106464115B (en) | Electromagnetic actuators | |
| CN207466966U (en) | A kind of dynamic displacement quadrotor unmanned plane of oil | |
| CN104229123A (en) | Device without helicopter tail rotor | |
| CN203251214U (en) | Single permanent magnet disc speed regulation type magnetic force coupler | |
| US11738861B2 (en) | Propelling system with variable aerodynamic controls | |
| CN203872030U (en) | Output rotating speed-adjustable mining permanent magnet transmission device | |
| CN105752322A (en) | Electrically-driven undercarriage system and aircraft comprising same | |
| CN202856593U (en) | Helical pair type permanent magnet governor | |
| CN106130314A (en) | A kind of flexible intelligent speed-regulating type magnetic bonder | |
| CN202622817U (en) | External structure for steering engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141224 |