CN103879555B - A kind of driven type helicopter tail rotor drive system - Google Patents

A kind of driven type helicopter tail rotor drive system Download PDF

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Publication number
CN103879555B
CN103879555B CN201210563828.9A CN201210563828A CN103879555B CN 103879555 B CN103879555 B CN 103879555B CN 201210563828 A CN201210563828 A CN 201210563828A CN 103879555 B CN103879555 B CN 103879555B
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helicopter
motor
rotor
tail
pedal
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CN103879555A (en
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曹飞龙
王敏涛
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China Helicopter Research and Development Institute
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China Helicopter Research and Development Institute
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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

Abstract

The invention belongs to Aircraft Design field, relate to driven type helicopter tail rotor drive system during a kind of Aircraft Design.Native system includes motor, motor power source and control system；Wherein, the motor being positioned at helicopter afterbody is connected with helicopter tail rotor, and motor is the power source of helicopter tail rotor, and control system controls the rotating speed of helicopter tail rotor.Driven type helicopter tail rotor drive system of the present invention replaces machine driving by driven type transmission, by changing tail-rotor rotating speed replacement tradition tail-rotor away from drag link mechanism, construction weight can be reduced, improve the capacity usage ratio of electromotor, the assembling maintainability of raising tail-rotor drive system, the noise reducing helicopter entirety and level of vibration, there is bigger actual application value.

Description

A kind of driven type helicopter tail rotor drive system
Technical field
The invention belongs to Aircraft Design field, relate to driven type helicopter tail rotor drive system during a kind of Aircraft Design.
Background technology
The drive system of existing helicopter tail rotor is typically made up of parts such as intermediate gearbox, tail transmission shaft, tail reducer, tail-rotor pitch-change-links, wherein, energy at main reducing gear 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, thus changes the angle of attack of tail-rotor leaf, changes tail blade thrust size thus realizes helicopter balance or the purpose of direction change.
The drive system of existing helicopter tail rotor is mechanical type, has the inherent characteristicses such as construction weight is big, energy loss is big, vibration noise is big, the possible jam of control leverage, assembling maintenance difficult.
Summary of the invention
It is an object of the invention to: a kind of driven type helicopter tail rotor drive system, change the transmission of existing tail-rotor energy and control mode, by electric drive mode with in the way of power (tail-rotor rotating speed) controls tail-rotor thrust, replace the structures such as existing tail transmission shaft, tail reducer, tail-rotor linkage, tail-rotor pitch-change-link, improve capacity usage ratio, reduce construction weight, reduction helicopter body vibration and noise, maintenance assembling simplicity.
The technical scheme is that
A kind of driven type helicopter tail rotor drive system, native system includes motor, motor power source and control system；Wherein, the motor being positioned at helicopter afterbody is connected with helicopter tail rotor, and motor is the power source of helicopter tail rotor, and control system controls the rotating speed of helicopter tail rotor.
Described a kind of driven type helicopter tail rotor drive system, is characterized in that, described motor power source includes electromotor and generator power source.Further, described a kind of driven type helicopter tail rotor drive system, it is characterized in that, described generator power source is electromotor, APU, main reducing gear or rotor shaft.
Described a kind of driven type helicopter tail rotor drive system, is characterized in that, described motor power source is accumulator jar.
Described a kind of driven type helicopter tail rotor drive system, it is characterized in that, described control system includes pedal, angular displacement sensor and power controller, wherein, pedal is arranged in driving cabin, the angular displacement that pedal produces is converted into the signal of telecommunication through angular displacement sensor, and this signal of telecommunication controls the rotating speed of helicopter tail rotor by power controller.Further, described a kind of driven type helicopter tail rotor drive system, described control system is connected with motor, controls the output of motor.Or, described a kind of driven type helicopter tail rotor drive system, described control system is connected with electromotor, controls the output of electromotor.
Described a kind of driven type helicopter tail rotor drive system, described control system also has helicopter attitude sensor, and helicopter attitude sensor is compared by power controller with pedal input, carries out closed loop control.
Described control system includes pedal, linkage and tail-rotor pitch-change-link, and pedal controls tail-rotor pitch-change-link by linkage.
The solution have the advantages that:
Driven type helicopter tail rotor drive system of the present invention replaces machine driving by driven type transmission, by changing tail-rotor rotating speed replacement tradition tail-rotor away from drag link mechanism, construction weight can be reduced, improve the capacity usage ratio of electromotor, the assembling maintainability of raising tail-rotor drive system, the noise reducing helicopter entirety and level of vibration, there is bigger actual application value.
Accompanying drawing explanation
Fig. 1 is the embodiment of the present invention 1 system principle diagram；
Wherein, 1-electromotor, 2-pedal, 3-angular displacement sensor, 4-power controller, 5-motor.
Fig. 2 is pedal motion schematic diagram；
Fig. 3 is the schematic diagram of Helicopter Main oar direction of rotation and tail-rotor direction of pull；
Fig. 4 is the embodiment of the present invention 2 system principle diagram；
Wherein, 1-electromotor, 2-pedal, 3-angular displacement sensor, 4-power controller, 5-motor.
Fig. 5 is the embodiment of the present invention 3 system principle diagram；
Wherein, 2-pedal, 3-angular displacement sensor, 4-power controller, 5-motor.
Fig. 6 is the embodiment of the present invention 4 system principle diagram；
Wherein, 1-electromotor, 2-pedal, 3-angular displacement sensor, 4-power controller, 5-motor.
Fig. 7 is the embodiment of the present invention 5 system principle diagram；Wherein, 1-electromotor, 5-motor.
Detailed description of the invention
Below by specific embodiment, the present invention is described in further details.
Embodiment 1:
Referring to Fig. 1, it is driven type helicopter tail rotor drive system schematic diagram of the present invention.Driven type helicopter tail rotor drive system of the present invention includes electromotor 1, pedal 2, angular displacement sensor 3, power controller 4, motor 5.
Wherein, described electromotor 1 is arranged on external engine, the part kinetic energy of electromotor is converted into electric energy, pedal 2 is arranged in driving cabin, and angular displacement sensor 3, power controller 4 are arranged on aircraft interior, and motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor drive system is made up of electromotor 1, electric wire, motor 5, electromotor 1, by driven by engine, by electric wire to motor 5 output, thus drives tail-rotor to rotate；Control system is made up of pedal 2, angular displacement sensor 3, power controller 4, angular displacement sensor 3 is arranged at pedal rotating shaft, the deflection angle theta (refering to Fig. 2) trampling pedal 2 is converted into the signal of telecommunication and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular displacement sensor and pedal maximum deflection angle θmaxRatio, in conjunction with the yawing moment of pedal, change the electric current in motor 5 magnet exciting coil, change magnet exciting coil magnetic field, control output W, thus control tail-rotor rotating speed and i.e. control the size of tail-rotor power, reach balance or change the purpose in helicopter direction.
In above-mentioned formula, W is the output of motor, WmaxThe peak power exporting the peak power to motor 5 or motor 5 self for electromotor 1 limits,Be to maintain helicopter steady time tail-rotor power, WminFor variable；θ is pedal deflection angle, depending on direction is according to main oar direction of rotation, and θmaxMaximum deflection angle for pedal.
W = 1 2 ( W min + W max ) + 1 2 ( W max - W min ) θ θ max
Specific embodiment is as follows: assume that Helicopter Main blade is to rotate counterclockwise, then tail-rotor needs to produce the pulling force (refering to Fig. 3) making helicopter rotate counterclockwise trend, when definition left foot pedals generation downward angular displacement, θ is for just, and when right pedal produces downward angular displacement, θ is negative.Trampling left foot when pedaling, the W of output is than power during pedal normal bitGreatly, tail-rotor pulling force becomes big, and helicopter afterbody rotates counterclockwise and causes Nose Left to be gone off course, and in like manner tramples right pedal and causes Airplane Nose Right to be gone off course.
Embodiment 2:
Referring to Fig. 4, it is driven type helicopter tail rotor drive system schematic diagram of the present invention.Driven type helicopter tail rotor drive system of the present invention includes electromotor 1, pedal 2, angular displacement sensor 3, power controller 4, motor 5.
The power source of described electromotor 1 can be also the rotary parts such as APU, main reducing gear or rotor shaft, drives electromotor to rotate (refering to Fig. 4) by gear/shaft, thus produces electric energy.Described electromotor 1 is arranged on outside APU/ main reducing gear/rotor shaft, part kinetic energy is converted into electric energy, pedal 2 is arranged in driving cabin, angular displacement sensor 3, power controller 4 are arranged on aircraft interior, motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor drive system is made up of APU/ main reducing gear/rotor shaft, electric wire, motor 5, electromotor 1 is driven by APU/ main reducing gear/rotor shaft, by electric wire to motor 5 output, thus tail-rotor is driven to rotate；Control system is made up of pedal 2, angular displacement sensor 3, power controller 4, angular displacement sensor 3 is arranged at pedal rotating shaft, the deflection angle theta (refering to Fig. 2) trampling pedal 2 is converted into the signal of telecommunication and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular displacement sensor and pedal maximum deflection angle θmaxRatio, in conjunction with the yawing moment of pedal, change the electric current in motor 5 magnet exciting coil, change magnet exciting coil magnetic field, control output W, thus control tail-rotor rotating speed and i.e. control the size of tail-rotor power, reach balance or change the purpose in helicopter direction.
Embodiment 3:
Referring to Fig. 5, it is driven type helicopter tail rotor drive system schematic diagram of the present invention.Driven type helicopter tail rotor drive system of the present invention includes accumulator jar, pedal 2, angular displacement sensor 3, power controller 4, motor 5.
The power source of described motor 5, in addition to electromotor, can be also accumulator jar (refering to Fig. 5), and accumulator jar provides DC source for motor, thus drives tail-rotor to rotate.Described accumulator jar is arranged on inside helicopter, pedal 2 is arranged in driving cabin, angular displacement sensor 3, power controller 4 are arranged on aircraft interior, motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor drive system is made up of accumulator jar, electric wire, motor 5, accumulator jar to motor 5 output, thus drives tail-rotor to rotate by electric wire；Control system is made up of pedal 2, angular displacement sensor 3, power controller 4, angular displacement sensor 3 is arranged at pedal rotating shaft, the deflection angle theta (refering to Fig. 2) trampling pedal 2 is converted into the signal of telecommunication and sends power controller 4 to, the pedal deflection angle theta that power controller 4 records according to angular displacement sensor and pedal maximum deflection angle θmaxRatio, in conjunction with the yawing moment of pedal, change the electric current in motor 5 magnet exciting coil, change magnet exciting coil magnetic field, control output W, thus control tail-rotor rotating speed and i.e. control the size of tail-rotor power, reach balance or change the purpose in helicopter direction.
Embodiment 4:
Referring to Fig. 6, it is driven type helicopter tail rotor drive system schematic diagram of the present invention.Driven type helicopter tail rotor drive system of the present invention includes electromotor 1, pedal 2, angular displacement sensor 3, power controller 4, motor 5.
Described power controller 2 also can be connected with electromotor, controls generator power, thus controls motor power (output) and tail-rotor rotating speed.Described electromotor [1] is arranged on external engine, the part kinetic energy of electromotor is converted into electric energy, pedal [2] is arranged in driving cabin, angular displacement sensor [3], power controller [4] are arranged on aircraft interior, motor [5] is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor drive system is made up of electromotor [1], electric wire, motor [5], electromotor [1] is by driven by engine, by electric wire to motor [5] output, thus tail-rotor is driven to rotate；Control system is made up of pedal [2], angular displacement sensor [3], power controller [4], angular displacement sensor [3] is arranged at pedal rotating shaft, the deflection angle theta trampling pedal [2] is converted into the signal of telecommunication and sends power controller [4], the pedal deflection angle theta that power controller [4] records according to angular displacement sensor and pedal maximum deflection angle θ tomaxRatio, in conjunction with the yawing moment of pedal, change the electric current in dynamo field coil, change magnet exciting coil magnetic field, control output W, thus change the size of motor [5] power, control tail-rotor rotating speed and i.e. control the size of tail-rotor power, reach balance or change the purpose in helicopter direction.
Embodiment 5:
Referring to Fig. 7, it is driven type helicopter tail rotor drive system schematic diagram of the present invention.Driven type helicopter tail rotor drive system of the present invention includes electromotor 1, motor 5.
Wherein, described electromotor 1 is arranged on outside electromotor/APU/ main reducing gear/rotor shaft, part kinetic energy is converted into electric energy, motor 5 is arranged on helicopter afterbody, it is characterized in that: helicopter driven type tail-rotor drive system is made up of electromotor 1, electric wire, motor 5, electromotor 1 is driven by electromotor/APU/ main reducing gear/rotor shaft, by electric wire to motor 5 output, thus drives tail-rotor to rotate.The pulling force (i.e. power) of tail-rotor is handled by prior aries such as pedal, linkage, tail-rotor pitch-change-links.
Driven type helicopter tail rotor drive system of the present invention, machine driving is replaced by electric drive mode, construction weight can be reduced, improve the capacity usage ratio of electromotor, the assembling maintainability of raising tail-rotor drive system, the noise reducing helicopter entirety and level of vibration, there is bigger actual application value.

Claims (5)

1. a driven type helicopter tail rotor drive system, native system includes motor, motor power source and control system；Wherein, the motor being positioned at helicopter afterbody is connected with helicopter tail rotor, and motor is the power source of helicopter tail rotor, and control system controls the rotating speed of helicopter tail rotor；Described motor power source includes electromotor and generator power source, or, described motor power source is accumulator jar；Described generator power source is electromotor, APU, main reducing gear or rotor shaft；
It is characterized in that, described control system includes pedal, angular displacement sensor and power controller, and wherein, pedal is arranged in driving cabin, the angular displacement that pedal produces is converted into the signal of telecommunication through angular displacement sensor, and this signal of telecommunication controls the rotating speed of helicopter tail rotor by power controller.
2. a kind of driven type helicopter tail rotor drive system as claimed in claim 1, is characterized in that, described control system is connected with motor, controls the output of motor.
3. a kind of driven type helicopter tail rotor drive system as claimed in claim 1, is characterized in that, described control system is connected with electromotor, controls the output of electromotor.
4. a kind of driven type helicopter tail rotor drive system as described in one of claim 1-3, is characterized in that, described control system also has helicopter attitude sensor, and helicopter attitude sensor is compared by power controller with pedal input, carries out closed loop control.
5. a kind of driven type helicopter tail rotor drive system as claimed in claim 4, is characterized in that, described control system includes pedal, linkage and tail-rotor pitch-change-link, and pedal controls tail-rotor pitch-change-link by linkage.
CN201210563828.9A 2012-12-21 2012-12-21 A kind of driven type helicopter tail rotor drive system Active CN103879555B (en)

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Publication number Priority date Publication date Assignee Title
CN105667786B (en) * 2016-01-12 2017-11-10 深圳清华大学研究院 The tail-rotor drive system and its control method of helicopter, helicopter
US9840324B2 (en) 2016-03-28 2017-12-12 Amazon Technologies, Inc. Selectively thrusting propulsion units for aerial vehicles
EP3436349B1 (en) * 2016-03-28 2020-05-06 Amazon Technologies Inc. Selectively thrusting propulsion units for aerial vehicles
US9663236B1 (en) 2016-03-28 2017-05-30 Amazon Technologies, Inc. Selectively thrusting propulsion units for aerial vehicles
CN107628257B (en) * 2017-09-18 2020-06-26 合肥工业大学 Control system of motor reducer integrated structure of helicopter tail rotor
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
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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CN1080609A (en) * 1992-06-29 1994-01-12 蔡渤啸 Electric power helicopter
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CN201395245Y (en) * 2009-06-03 2010-02-03 中国航空动力机械研究所 Helicopter powered with electricity

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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
CN201395245Y (en) * 2009-06-03 2010-02-03 中国航空动力机械研究所 Helicopter powered with electricity

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