CN103879555A - Electrically driven helicopter tail rotor transmission system - Google Patents
Electrically driven helicopter tail rotor transmission system Download PDFInfo
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- CN103879555A CN103879555A CN201210563828.9A CN201210563828A CN103879555A CN 103879555 A CN103879555 A CN 103879555A CN 201210563828 A CN201210563828 A CN 201210563828A CN 103879555 A CN103879555 A CN 103879555A
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- 230000005540 biological transmission Effects 0.000 title abstract description 10
- 230000017105 transposition Effects 0.000 claims description 4
- 230000009347 mechanical transmission Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 12
- 230000005284 excitation Effects 0.000 description 7
- 230000009466 transformation Effects 0.000 description 4
- 239000003638 chemical reducing agent Substances 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
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- 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
- Y02T50/40—Weight reduction
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Abstract
The invention belongs to the field of aircraft design, and relates to an electrically driven helicopter tail rotor transmission system in aircraft design. The system comprises a motor, a motor power source, and a control system; the motor at the tail of a helicopter is connected with a helicopter tail rotor; the motor is the power source of the helicopter tail rotor; the control system controls the rotating speed of the helicopter tail rotor. The electrically driven helicopter tail rotor transmission system of the invention substitutes electrically driven transmission for mechanical transmission, substitutes for a traditional tail rotor pitch link mechanism by changing the tail rotor rotating speed, reduces the structure weight, improves the energy utilization rate of the motor, improves the assembly maintainability of the tail rotor transmission system, reduces the noise and vibration level of the whole helicopter, and has great practical application value.
Description
Technical field
The invention belongs to Aircraft Design field, driven type helicopter tail rotor driving system while relating to a kind of Aircraft Design.
Background technology
The driving system of existing helicopter tail rotor is generally made up of parts such as intermediate gearbox, tail transmission shaft, tail reducer, tail-rotor pitch-change-links, wherein, the energy at main reduction gear place is delivered to tail-rotor by intermediate gearbox, tail transmission shaft, tail reducer, drives tail-rotor to rotate; Pilot guidance pedal drives tail-rotor pitch-change-link by linkage, thereby changes the angle of attack of tail-rotor leaf, thereby changes the big or small object that realizes helicopter balance or direction change of tail blade thrust.
The driving system of existing helicopter tail rotor is mechanical type, has the inherent characteristicses such as structural weight is large, degradation of energy is large, vibration noise is large, control leverage possibility jam, assembling maintenance difficult.
Summary of the invention
The object of the invention is: a kind of driven type helicopter tail rotor driving system, change the transmission of existing tail-rotor energy and mode, by electric drive mode with control the mode of tail-rotor thrust with power (tail-rotor rotating speed), replace the structures such as existing tail transmission shaft, tail reducer, tail-rotor linkage, tail-rotor pitch-change-link, improve capacity usage ratio, reduce structural weight, reduce helicopter body vibration and noise, maintenance assembling is easy.
Technical scheme of the present invention is:
A kind of driven type helicopter tail rotor driving system, native system comprises electrical motor, motor power source and control system; Wherein, the electrical motor that is positioned at helicopter afterbody is connected with helicopter tail rotor, the propulsion source that electrical motor is helicopter tail rotor, the rotating speed of control system control helicopter tail rotor.
Described a kind of driven type helicopter tail rotor driving system, is characterized in that, described motor power source comprises electrical generator and electrical generator propulsion source.Further, described a kind of driven type helicopter tail rotor driving system, is characterized in that, described electrical generator propulsion source is driving engine, APU, main reduction gear or rotor shaft.
Described a kind of driven type helicopter tail rotor driving system, is characterized in that, described motor power source is accumulator jar.
Described a kind of driven type helicopter tail rotor driving system, it is characterized in that, described control system comprises pedal, angular-motion transducer and power controller, wherein, pedal is arranged in driving compartment, the angular transposition that pedal produces is converted into electric signal through angular-motion transducer, and this electric signal is by the rotating speed of power controller control helicopter tail rotor.Further, described a kind of driven type helicopter tail rotor driving system, described control system is connected with electrical motor, controls the horsepower output of electrical motor.Or, described a kind of driven type helicopter tail rotor driving system, described control system is connected with electrical generator, controls the horsepower output of electrical generator.
Described a kind of driven type helicopter tail rotor driving system, described control system also has helicopter attitude sensor, and power controller is compared to helicopter attitude sensor and pedal input, carries out closed loop control.
Described control system comprises pedal, linkage and tail-rotor pitch-change-link, and pedal is by linkage control tail-rotor pitch-change-link.
Technique effect of the present invention is:
Driven type helicopter tail rotor driving system of the present invention is replaced mechanical drive, is replaced traditional tail-rotor apart from drag link mechanism by changing tail-rotor rotating speed by driven type transmission, can reduce structural weight, improve the capacity usage ratio of driving engine, the assembling maintainability of raising tail-rotor driving system, the noise and vibration level of reduction helicopter entirety, there is larger actual application value.
Accompanying drawing explanation
Fig. 1 is the embodiment of the present invention 1 system principle diagram;
Wherein, 1-electrical generator, 2-pedal, 3-angular-motion transducer, 4-power controller, 5-electrical motor.
Fig. 2 is pedal motion schematic diagram
Fig. 3 is the schematic diagram of Helicopter Main oar hand of rotation and tail-rotor direction of pull
Fig. 4 is the embodiment of the present invention 2 system principle diagram;
Wherein, 1-electrical generator, 2-pedal, 3-angular-motion transducer, 4-power controller, 5-electrical motor.
Fig. 5 is the embodiment of the present invention 3 system principle diagram;
Wherein, 2-pedal, 3-angular-motion transducer, 4-power controller, 5-electrical motor.
Fig. 6 is the embodiment of the present invention 4 system principle diagram;
Wherein, 1-electrical generator, 2-pedal, 3-angular-motion transducer, 4-power controller, 5-electrical motor.
Fig. 7 is the embodiment of the present invention 5 system principle diagram; Wherein, 1-electrical generator, 5-electrical motor.
The specific embodiment
Below by specific embodiment, the present invention is described in further details.
Embodiment 1:
Refer to Fig. 1, it is driven type helicopter tail rotor driving system schematic diagram of the present invention.Driven type helicopter tail rotor driving system of the present invention comprises electrical generator 1, pedal 2, angular-motion transducer 3, power controller 4, electrical motor 5.
Wherein, described electrical generator 1 is arranged on external engine, be electric energy by the part kinetic transformation of driving engine, pedal 2 is arranged in driving compartment, and angular-motion transducer 3, power controller 4 are arranged on aircraft inside, and electrical motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor driving system is made up of electrical generator 1, electric wire, electrical motor 5, electrical generator 1 is by driven by engine, by electric wire to electrical motor 5 horsepower outputs, thereby drive tail-rotor to rotate; Control system is made up of pedal 2, angular-motion transducer 3, power controller 4, angular-motion transducer 3 is arranged on pedal rotating shaft place, the deflection angle theta (consulting Fig. 2) of trampling pedal 2 is converted into electric signal and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular-motion transducer and pedal maximum deflection angle θ
maxratio, in conjunction with the deflecting direction of pedal, change the electric current in electrical motor 5 excitation coils, change excitation coil magnetic field, control horsepower output W, thereby control tail-rotor rotating speed and control the size of tail-rotor power, reach balance or change the object of helicopter direction.
In above-mentioned formula, the horsepower output that W is electrical motor, W
maxfor electrical generator 1 is exported to the max power constraint of the maximum power of electrical motor 5 or electrical motor 5 self,
the tail-rotor power while keeping helicopter steady, W
minfor variable; θ is pedal angle of inclination, and direction is determined according to main oar hand of rotation, θ
maxfor the maximum deflection angle of pedal.
Specific embodiment is as follows: suppose that Helicopter Main blade is with left-hand revolution, tail-rotor need to produce the pulling force (consulting Fig. 3) that makes helicopter rotate counterclockwise trend, definition left foot is pedaled and is produced when downward angular transposition θ for just, and when right pedal produces downward angular transposition, θ is for bearing.When trampling left foot and pedaling, the power of the W of output during than the normal position of pedal
greatly, it is large that tail-rotor pulling force becomes, and helicopter afterbody left-hand revolution causes Nose Left driftage, in like manner tramples right pedal and cause Airplane Nose Right driftage.
Embodiment 2:
Refer to Fig. 4, it is driven type helicopter tail rotor driving system schematic diagram of the present invention.Driven type helicopter tail rotor driving system of the present invention comprises electrical generator 1, pedal 2, angular-motion transducer 3, power controller 4, electrical motor 5.
The propulsion source of described electrical generator 1 also can be the turning units such as APU, main reduction gear or rotor shaft, drives electrical generator rotation (consulting Fig. 4) by gear/axle, thereby produces electric energy.Described electrical generator 1 is arranged on APU/ main reduction gear/rotor shaft outside, be electric energy by part kinetic transformation, pedal 2 is arranged in driving compartment, angular-motion transducer 3, power controller 4 are arranged on aircraft inside, electrical motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor driving system is made up of APU/ main reduction gear/rotor shaft, electric wire, electrical motor 5, electrical generator 1 is driven by APU/ main reduction gear/rotor shaft, by electric wire to electrical motor 5 horsepower outputs, thereby drive tail-rotor rotate; Control system is made up of pedal 2, angular-motion transducer 3, power controller 4, angular-motion transducer 3 is arranged on pedal rotating shaft place, the deflection angle theta (consulting Fig. 2) of trampling pedal 2 is converted into electric signal and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular-motion transducer and pedal maximum deflection angle θ
maxratio, in conjunction with the deflecting direction of pedal, change the electric current in electrical motor 5 excitation coils, change excitation coil magnetic field, control horsepower output W, thereby control tail-rotor rotating speed and control the size of tail-rotor power, reach balance or change the object of helicopter direction.
Embodiment 3:
Refer to Fig. 5, it is driven type helicopter tail rotor driving system schematic diagram of the present invention.Driven type helicopter tail rotor driving system of the present invention comprises accumulator jar, pedal 2, angular-motion transducer 3, power controller 4, electrical motor 5.
The propulsion source of described electrical motor 5, except electrical generator, also can be accumulator jar (consulting Fig. 5), and accumulator jar provides direct supply for electrical motor, thereby drives tail-rotor to rotate.Described accumulator jar is arranged on helicopter inside, pedal 2 is arranged in driving compartment, angular-motion transducer 3, power controller 4 are arranged on aircraft inside, electrical motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor driving system is made up of accumulator jar, electric wire, electrical motor 5, accumulator jar by electric wire to electrical motor 5 horsepower outputs, thereby drive tail-rotor rotate; Control system is made up of pedal 2, angular-motion transducer 3, power controller 4, angular-motion transducer 3 is arranged on pedal rotating shaft place, the deflection angle theta (consulting Fig. 2) of trampling pedal 2 is converted into electric signal and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular-motion transducer and pedal maximum deflection angle θ
maxratio, in conjunction with the deflecting direction of pedal, change the electric current in electrical motor 5 excitation coils, change excitation coil magnetic field, control horsepower output W, thereby control tail-rotor rotating speed and control the size of tail-rotor power, reach balance or change the object of helicopter direction.
Embodiment 4:
Refer to Fig. 6, it is driven type helicopter tail rotor driving system schematic diagram of the present invention.Driven type helicopter tail rotor driving system of the present invention comprises electrical generator 1, pedal 2, angular-motion transducer 3, power controller 4, electrical motor 5.
Described power controller 2 also can be connected with electrical generator, controls generator power, thereby controls motor power (output) and tail-rotor rotating speed.Described electrical generator [1] is arranged on external engine, be electric energy by the part kinetic transformation of driving engine, pedal [2] is arranged in driving compartment, angular-motion transducer [3], power controller [4] are arranged on aircraft inside, electrical motor [5] is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor driving system is made up of electrical generator [1], electric wire, electrical motor [5], and electrical generator [1] is by driven by engine, by electric wire to electrical motor [5] horsepower output, thereby drive tail-rotor rotate; Control system is made up of pedal [2], angular-motion transducer [3], power controller [4], angular-motion transducer [3] is arranged on pedal rotating shaft place, the deflection angle theta of trampling pedal [2] is converted into electric signal and sends power controller [4] to, the pedal deflection angle theta that power controller [4] records according to angular-motion transducer and pedal maximum deflection angle θ
maxratio, in conjunction with the deflecting direction of pedal, change the electric current in dynamo field coil, change excitation coil magnetic field, control horsepower output W, thereby change the size of electrical motor [5] power, control tail-rotor rotating speed and control the size of tail-rotor power, reach the object of balance or change helicopter direction.
Embodiment 5:
Refer to Fig. 7, it is driven type helicopter tail rotor driving system schematic diagram of the present invention.Driven type helicopter tail rotor driving system of the present invention comprises electrical generator 1, electrical motor 5.
Wherein, described electrical generator 1 is arranged on driving engine/APU/ main reduction gear/rotor shaft outside, be electric energy by part kinetic transformation, electrical motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor driving system is made up of electrical generator 1, electric wire, electrical motor 5, electrical generator 1 is driven by driving engine/APU/ main reduction gear/rotor shaft, by electric wire to electrical motor 5 horsepower outputs, thereby drive tail-rotor to rotate.The pulling force (being power) of tail-rotor is handled by prior aries such as pedal, linkage, tail-rotor pitch-change-links.
Driven type helicopter tail rotor driving system of the present invention, replace mechanical drive by electric drive mode, can reduce structural weight, improve the capacity usage ratio of driving engine, the assembling maintainability of raising tail-rotor driving system, the noise and vibration level of reduction helicopter entirety, there is larger actual application value.
Claims (9)
1. a driven type helicopter tail rotor driving system, is characterized in that, native system comprises electrical motor, motor power source and control system; Wherein, the electrical motor that is positioned at helicopter afterbody is connected with helicopter tail rotor, the propulsion source that electrical motor is helicopter tail rotor, the rotating speed of control system control helicopter tail rotor.
2. a kind of driven type helicopter tail rotor driving system as claimed in claim 1, is characterized in that, described motor power source comprises electrical generator and electrical generator propulsion source.
3. a kind of driven type helicopter tail rotor driving system as claimed in claim 2, is characterized in that, described electrical generator propulsion source is driving engine, APU, main reduction gear or rotor shaft.
4. a kind of driven type helicopter tail rotor driving system as claimed in claim 1, is characterized in that, described motor power source is accumulator jar.
5. a kind of driven type helicopter tail rotor driving system as claimed in claim 1, it is characterized in that, described control system comprises pedal, angular-motion transducer and power controller, wherein, pedal is arranged in driving compartment, the angular transposition that pedal produces is converted into electric signal through angular-motion transducer, and this electric signal is by the rotating speed of power controller control helicopter tail rotor.
6. a kind of driven type helicopter tail rotor driving system as claimed in claim 5, is characterized in that, described control system is connected with electrical motor, controls the horsepower output of electrical motor.
7. a kind of driven type helicopter tail rotor driving system as claimed in claim 5, is characterized in that, described control system is connected with electrical generator, controls the horsepower output of electrical generator.
8. a kind of driven type helicopter tail rotor driving system as described in one of claim 1-7, it is characterized in that, described control system also has helicopter attitude sensor, and power controller is compared to helicopter attitude sensor and pedal input, carries out closed loop control.
9. a kind of driven type helicopter tail rotor driving system as claimed in claim 1, is characterized in that, described control system comprises pedal, linkage and tail-rotor pitch-change-link, and pedal is by linkage control tail-rotor pitch-change-link.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210563828.9A CN103879555B (en) | 2012-12-21 | 2012-12-21 | A kind of driven type helicopter tail rotor drive system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210563828.9A CN103879555B (en) | 2012-12-21 | 2012-12-21 | A kind of driven type helicopter tail rotor drive system |
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| Publication Number | Publication Date |
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| CN103879555A true CN103879555A (en) | 2014-06-25 |
| CN103879555B CN103879555B (en) | 2016-10-26 |
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| CN201210563828.9A Active CN103879555B (en) | 2012-12-21 | 2012-12-21 | A kind of driven type helicopter tail rotor drive system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667786A (en) * | 2016-01-12 | 2016-06-15 | 清华大学深圳研究生院 | Tail rotor driving system of helicopter, control method thereof and helicopter |
| CN107628257A (en) * | 2017-09-18 | 2018-01-26 | 合肥工业大学 | The motor reducer integrated structure and its control system of a kind of helicopter tail rotor |
| CN108750086A (en) * | 2018-04-24 | 2018-11-06 | 电子科技大学 | A kind of electronic tail-rotor displacement speed change cooperative control method of helicopter and device |
| CN108871773A (en) * | 2018-09-14 | 2018-11-23 | 合肥工业大学 | A kind of electronic tail gearbox testing stand of helicopter |
| CN109195866A (en) * | 2016-03-28 | 2019-01-11 | 亚马逊科技公司 | Selectively propel the propulsion unit for aviation carrier |
| US10696384B2 (en) | 2016-03-28 | 2020-06-30 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
| US11091246B2 (en) | 2016-03-28 | 2021-08-17 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
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| CN1080609A (en) * | 1992-06-29 | 1994-01-12 | 蔡渤啸 | Electric power helicopter |
| WO2002070098A2 (en) * | 2001-03-06 | 2002-09-12 | Heribert Vogel | Coupling |
| US20070205333A1 (en) * | 2006-02-15 | 2007-09-06 | Sikorsky Aircraft Corporation | Full authority fly-by-wire pedal system |
| US20090140095A1 (en) * | 2007-11-30 | 2009-06-04 | Jayant Sirohi | Electric powered rotary-wing aircraft |
| CN201395245Y (en) * | 2009-06-03 | 2010-02-03 | 中国航空动力机械研究所 | an electric helicopter |
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2012
- 2012-12-21 CN CN201210563828.9A patent/CN103879555B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1080609A (en) * | 1992-06-29 | 1994-01-12 | 蔡渤啸 | Electric power helicopter |
| WO2002070098A2 (en) * | 2001-03-06 | 2002-09-12 | Heribert Vogel | Coupling |
| US20070205333A1 (en) * | 2006-02-15 | 2007-09-06 | Sikorsky Aircraft Corporation | Full authority fly-by-wire pedal system |
| US20090140095A1 (en) * | 2007-11-30 | 2009-06-04 | Jayant Sirohi | Electric powered rotary-wing aircraft |
| CN201395245Y (en) * | 2009-06-03 | 2010-02-03 | 中国航空动力机械研究所 | an electric helicopter |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667786A (en) * | 2016-01-12 | 2016-06-15 | 清华大学深圳研究生院 | Tail rotor driving system of helicopter, control method thereof and helicopter |
| CN109195866A (en) * | 2016-03-28 | 2019-01-11 | 亚马逊科技公司 | Selectively propel the propulsion unit for aviation carrier |
| US10696384B2 (en) | 2016-03-28 | 2020-06-30 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
| CN109195866B (en) * | 2016-03-28 | 2020-08-25 | 亚马逊科技公司 | Selectively propelling a propulsion unit for an aerial vehicle |
| US11091246B2 (en) | 2016-03-28 | 2021-08-17 | Amazon Technologies, Inc. | Selectively thrusting propulsion units for aerial vehicles |
| CN107628257A (en) * | 2017-09-18 | 2018-01-26 | 合肥工业大学 | The motor reducer integrated structure and its control system of a kind of helicopter tail rotor |
| CN108750086A (en) * | 2018-04-24 | 2018-11-06 | 电子科技大学 | A kind of electronic tail-rotor displacement speed change cooperative control method of helicopter and device |
| CN108750086B (en) * | 2018-04-24 | 2021-04-30 | 电子科技大学 | Helicopter electric tail rotor variable-pitch variable-speed cooperative control method and device |
| CN108871773A (en) * | 2018-09-14 | 2018-11-23 | 合肥工业大学 | A kind of electronic tail gearbox testing stand of helicopter |
| CN108871773B (en) * | 2018-09-14 | 2024-02-02 | 合肥工业大学 | Helicopter electric tail speed reducer test bed |
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| Publication number | Publication date |
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| CN103879555B (en) | 2016-10-26 |
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