WO2020108341A1 - Aircraft power booster wheel and landing gear - Google Patents

Aircraft power booster wheel and landing gear Download PDF

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Publication number
WO2020108341A1
WO2020108341A1 PCT/CN2019/119203 CN2019119203W WO2020108341A1 WO 2020108341 A1 WO2020108341 A1 WO 2020108341A1 CN 2019119203 W CN2019119203 W CN 2019119203W WO 2020108341 A1 WO2020108341 A1 WO 2020108341A1
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WO
WIPO (PCT)
Prior art keywords
aircraft
landing gear
electric motor
gear wheel
wheel
Prior art date
Application number
PCT/CN2019/119203
Other languages
French (fr)
Inventor
Lianying Zhang
Original Assignee
Lianying Zhang
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Lianying Zhang filed Critical Lianying Zhang
Publication of WO2020108341A1 publication Critical patent/WO2020108341A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/405—Powered wheels, e.g. for taxing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • 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
    • Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management

Definitions

  • An electric motor is added to the existing aircraft landing gear structure, and the existing aircraft landing gear is replaced by an aircraft landing gear which comprises an electric motor and landing gear wheels.
  • the landing gear wheels are driven by the electric motor to assist the aircraft to slide forward, and the taxiing distance and take-off process of the aircraft can be shorten.
  • the invention relates to landing gear of aircraft.
  • the landing gear of the prior art generally consists of a landing gear bracket 1 and landing gear wheels 2.
  • the landing gear wheels 2 are in contact with the ground directly to carry the weight of the aircraft.
  • the taxiing and takeoff process of the existing aircraft is generally carried out by the force of the jet engine to the rearward injection of gas to propel the aircraft to slide forward. Or the reaction force generated by the propeller to the rear exhaust winds can push the aircraft to slide forward.
  • the landing gear wheels are passively rotating and gliding, and the forward sliding force of the aircraft is completely provided by the aircraft engine.
  • methods such as ejection takeoff, skid takeoff, rocket booster, and light load takeoff have existed in the prior art.
  • the idea of the invention is to drive the wheel of the aircraft landing gear by an electric motor to change the wheel of the landing gear from passive rotation to active rotation to drive the aircraft forward, together with the thrust generated by the aircraft engine, by speeding up the forward taxiing of the aircraft.
  • the basic structure of the landing gear in this application is to mount a drive motor on the aircraft landing gear, on which the landing gear wheels and other auxiliary components are mounted.
  • the present invention aims to shorten the sliding distance and take-off process when the aircraft takes off.
  • the purpose of the invention is achieved by using electric motor to drive the landing gear wheels of the aircraft rotation, so as to the rotation of the landing gear wheels can be changed from passiveness to initiative to drive the aircraft to go forward, and together with the thrust generated by the aircraft engine, the forward taxiing speed of the aircraft can speed up.
  • the basic structure of the landing gear in the present application is to mount an electric motor on the landing gear of the aircraft, and landing gear wheels and other auxiliary components are provided on the electric motor. When the aircraft starts to taxi and take off, the electric motor runs and drives the landing gear wheel to rotate, and a forward driving force is generated which helps the aircraft to slide forward as a whole.
  • the electric motor stopped running and the aircraft landing gear is retracted, and the takeoff of the aircraft is complete.
  • the aircraft landing gear will be lowered when the aircraft is landing, and the landing gear wheels will rotate quickly after touching the ground.
  • the rotation of the landing gear wheels in the landing process of the aircraft can drive the electric motor to rotate rapidly, and the motor can recover the kinetic energy of the aircraft and convert it into electric energy. In this way, not only can the aircraft be decelerated, but energy can also be saved.
  • FIG. 1 shows a schematic view of the structure of the existing landing gear.
  • FIG. 2 illustrates an aircraft landing gear in accordance with one embodiment of the present application.
  • FIG. 3 illustrates an aircraft landing gear in accordance with another embodiment of the present application.
  • an aircraft landing gear is provided.
  • the aircraft landing gear includes a landing gear bracket 1, a landing gear wheel 2, and an electric motor 3.
  • a shell 31 of the electric motor 3 is provided on the landing gear bracket 1.
  • the landing gear wheel 2 is connected to a rotating shaft 32 of the electric motor 3.
  • Some other auxiliary components are also provided on the electric motor 3.
  • the rotating shaft 32 of the electric motor 3 can drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation.
  • the right landing gear wheel in the FIG. 2 is a cutaway view.
  • an aircraft landing gear is provided.
  • the aircraft landing gear of this embodiment also includes a landing gear bracket 1, a landing gear wheel 2, and an electric motor 3.
  • the difference between this embodiment and the above embodiment lies in a center axis 33 (the position of the center axis 33 on the electric motor in this embodiment corresponds to the position of the rotating shaft 32 on the electric motor 3 in the above embodiment) of the electric motor 3 is provided on the landing gear bracket 1, and the landing gear wheel 2 and some other auxiliary components are provided on a shell 34 of the electric motor 3.
  • the shell 34 of the electric motor rotates to drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation, and the center axis 33 of the electric motor 3 doesn’ t move in this process.
  • the characteristics of the innovative program are:
  • the payload of the aircraft can be increased.
  • the electric motor can recover the kinetic energy of the aircraft's deceleration.
  • the function of the aircraft landing gear and the electric booster wheel is to drive the landing gear wheel 2 to rotate, thereby increasing the takeoff power of the aircraft.
  • Embodiments of the patent application include:
  • An electric motor 3 is provided on the aircraft landing gear. Specifically, a shell 31 of the electric motor 3 is provided on the landing gear bracket 1. The landing gear wheel 2 is connected to a rotating shaft 32 of the electric motor 3. In order to assist the aircraft to take off, the rotating shaft 32 of the electric motor 3 can drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation.
  • a center axis 33 of the electric motor 3 is provided on the landing gear bracket 1, and the landing gear wheel 2 and some other auxiliary components are provided on a shell 34 of the electric motor 3.
  • the shell 34 of the electric motor 3 rotates to drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Catching Or Destruction (AREA)
  • Gear Transmission (AREA)

Abstract

Disclosed is an aircraft landing gear comprising a landing gear bracket (1), a landing gear wheel (2) and an electric motor (3). The electric motor (3) is provided on the landing gear bracket (1).When the aircraft starts to taxi and take off, the electric motor runs and drives the landing gear wheel to rotate, and a forward driving force is generated which works together with the thrust generated by the aircraft engine and helps the aircraft to slide forward as a whole. As the sliding action during the takeoff process of the aircraft is increased, the payload of the aircraft can be increased; the sliding distance and the take-off process can be shortened. Besides, the electric motor can recover the kinetic energy of the aircraft's deceleration during the landing of the aircraft.

Description

AIRCRAFT POWER BOOSTER WHEEL AND LANDING GEAR
An electric motor is added to the existing aircraft landing gear structure, and the existing aircraft landing gear is replaced by an aircraft landing gear which comprises an electric motor and landing gear wheels. During the takeoff of the aircraft, the landing gear wheels are driven by the electric motor to assist the aircraft to slide forward, and the taxiing distance and take-off process of the aircraft can be shorten.
TECHNICAL FIELD
The invention relates to landing gear of aircraft.
BACKGROUND TECHNOLOGY
The basic structure of the aircraft is equipped with a landing gear at the lower part of the fuselage. As shown in FIG. 1, the landing gear of the prior art generally consists of a landing gear bracket 1 and landing gear wheels 2. The landing gear wheels 2 are in contact with the ground directly to carry the weight of the aircraft.
The taxiing and takeoff process of the existing aircraft is generally carried out by the force of the jet engine to the rearward injection of gas to propel the aircraft to slide forward. Or the reaction force generated by the propeller to the rear exhaust winds can push the aircraft to slide forward. In the prior art, the landing gear wheels are passively rotating and gliding, and the forward sliding force of the aircraft is completely provided by the aircraft engine. In order to shorten the taxiing distance and take-off process of the aircraft takeoff, methods such as ejection takeoff, skid takeoff, rocket booster, and light load takeoff have existed in the prior art.
SUMMARY OF THE INVENTION
The idea of the invention is to drive the wheel of the aircraft landing gear by an  electric motor to change the wheel of the landing gear from passive rotation to active rotation to drive the aircraft forward, together with the thrust generated by the aircraft engine, by speeding up the forward taxiing of the aircraft. An innovative solution to shorten the taxiing distance and take-off process when the aircraft takes off.
The basic structure of the landing gear in this application is to mount a drive motor on the aircraft landing gear, on which the landing gear wheels and other auxiliary components are mounted.
The present invention aims to shorten the sliding distance and take-off process when the aircraft takes off. And the purpose of the invention is achieved by using electric motor to drive the landing gear wheels of the aircraft rotation, so as to the rotation of the landing gear wheels can be changed from passiveness to initiative to drive the aircraft to go forward, and together with the thrust generated by the aircraft engine, the forward taxiing speed of the aircraft can speed up. The basic structure of the landing gear in the present application is to mount an electric motor on the landing gear of the aircraft, and landing gear wheels and other auxiliary components are provided on the electric motor. When the aircraft starts to taxi and take off, the electric motor runs and drives the landing gear wheel to rotate, and a forward driving force is generated which helps the aircraft to slide forward as a whole. After the aircraft is lifted off the ground, the electric motor stopped running and the aircraft landing gear is retracted, and the takeoff of the aircraft is complete. The aircraft landing gear will be lowered when the aircraft is landing, and the landing gear wheels will rotate quickly after touching the ground. In the present application, the rotation of the landing gear wheels in the landing process of the aircraft can drive the electric motor to rotate rapidly, and the motor can recover the kinetic energy of the aircraft and convert it into electric energy. In this way, not only can the aircraft be decelerated, but energy can also be saved.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 shows a schematic view of the structure of the existing landing gear.
FIG. 2 illustrates an aircraft landing gear in accordance with one embodiment of the present application.
FIG. 3 illustrates an aircraft landing gear in accordance with another embodiment of the present application.
DETAILED DESCRIPTION
As shown in FIG. 2, an aircraft landing gear is provided. The aircraft landing gear includes a landing gear bracket 1, a landing gear wheel 2, and an electric motor 3. A shell 31 of the electric motor 3 is provided on the landing gear bracket 1. The landing gear wheel 2 is connected to a rotating shaft 32 of the electric motor 3. And some other auxiliary components are also provided on the electric motor 3. The rotating shaft 32 of the electric motor 3 can drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation. The right landing gear wheel in the FIG. 2 is a cutaway view.
As shown in FIG. 3, an aircraft landing gear is provided. The aircraft landing gear of this embodiment also includes a landing gear bracket 1, a landing gear wheel 2, and an electric motor 3. The difference between this embodiment and the above embodiment lies in a center axis 33 (the position of the center axis 33 on the electric motor in this embodiment corresponds to the position of the rotating shaft 32 on the electric motor 3 in the above embodiment) of the electric motor 3 is provided on the landing gear bracket 1, and the landing gear wheel 2 and some other auxiliary components are provided on a shell 34 of the electric motor 3. In this embodiment, the shell 34 of the electric motor rotates to drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation, and the center axis 33 of the electric motor 3 doesn’ t move in this process.
The characteristics of the innovative program are:
1. The structures of the above two types of motors have existed in the prior art.
2. The addition of electric boosting can effectively shorten the time the aircraft takes in the process of takeoff and shorten the distance of the taxiing.
3. As the sliding action during the takeoff process of the aircraft is increased, the  payload of the aircraft can be increased.
4. During the landing of the aircraft, the electric motor can recover the kinetic energy of the aircraft's deceleration.
In the present application, the function of the aircraft landing gear and the electric booster wheel is to drive the landing gear wheel 2 to rotate, thereby increasing the takeoff power of the aircraft. Embodiments of the patent application include:
1. An electric motor 3 is provided on the aircraft landing gear. Specifically, a shell 31 of the electric motor 3 is provided on the landing gear bracket 1. The landing gear wheel 2 is connected to a rotating shaft 32 of the electric motor 3. In order to assist the aircraft to take off, the rotating shaft 32 of the electric motor 3 can drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation.
2. A center axis 33 of the electric motor 3 is provided on the landing gear bracket 1, and the landing gear wheel 2 and some other auxiliary components are provided on a shell 34 of the electric motor 3. In order to assist the aircraft to take off, the shell 34 of the electric motor 3 rotates to drive the landing gear wheel 2 to rotate when the electric motor 3 is in operation.

Claims (3)

  1. An aircraft landing gear, wherein comprising a landing gear bracket, a landing gear wheel, and an electric motor, the electric motor is provided on the landing gear bracket, the electric motor is used to drive the landing gear wheel to rorate when the aircraft is taxiing and taking off to increase the takeoff impetus of the aircraft, the combined force of the aircraft engine, and shorten the takeoff distance of the aircraft.
  2. The aircraft landing gear of claim 1, wherein a shell of the electric motor is provided on the landing gear bracket, a rotating shaft of the electric motor is connected to the landing gear wheel, and the rotating shaft of the electric motor can drive the landing gear wheel to rotate when the electric motor is in operation so as to assist the aircraft to take off .
  3. The aircraft landing gear of claim 1, wherein a center axis of the electric motor is provided on the landing gear bracket, the landing gear wheel is provided on a shell of the electric motor, and the shell of the electric motor rotates to drive the landing gear wheel to rotate when the electric motor is in operation so as to assist the aircraft to take off.
PCT/CN2019/119203 2018-11-26 2019-11-18 Aircraft power booster wheel and landing gear WO2020108341A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201811412763.1 2018-11-26
CN201811412763.1A CN109515693A (en) 2018-11-26 2018-11-26 Aircraft electric pushing-aid wheel and undercarriage

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WO2020108341A1 true WO2020108341A1 (en) 2020-06-04

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Cited By (1)

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Publication number Priority date Publication date Assignee Title
WO2022081129A1 (en) * 2020-10-12 2022-04-21 Robert Blackmore Collins Vehicle battery carrier for aircraft ground support

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Publication number Priority date Publication date Assignee Title
CN109515693A (en) * 2018-11-26 2019-03-26 张连营 Aircraft electric pushing-aid wheel and undercarriage
CN114104272A (en) * 2021-12-31 2022-03-01 中国商用飞机有限责任公司 Aircraft landing gear

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CN101998921A (en) * 2008-04-11 2011-03-30 空中客车操作有限公司 An aircraft landing gear arrangement and a nose landing gear assembly
CN102083686A (en) * 2008-07-07 2011-06-01 空中客车营运有限公司 Wheel drive system for an aircraft comprising a fuel cell as an energy source
CN102700716A (en) * 2010-10-29 2012-10-03 霍尼韦尔国际公司 Compact electric taxi assembly for installation on an aircraft
JP2012116467A (en) * 2010-12-03 2012-06-21 Bae Systems Controls Inc Hydraulic ground propulsion system
EP2557035A2 (en) * 2011-08-08 2013-02-13 Honeywell International Inc. Landing gear with integrated electric motor for electric taxi system
CN104058090A (en) * 2013-03-24 2014-09-24 霍尼韦尔国际公司 Between-wheel Bogie Mounted Taxi System
CN104925246A (en) * 2015-06-26 2015-09-23 周勤 Ground driving and electromagnetic braking system for unmanned aerial vehicle
CN105752322A (en) * 2016-04-19 2016-07-13 上海交通大学 Electrically-driven undercarriage system and aircraft comprising same
CN106347641A (en) * 2016-10-17 2017-01-25 济南大学 Coupled type hydraulic driven energy-saving electrical storage device
CN109515693A (en) * 2018-11-26 2019-03-26 张连营 Aircraft electric pushing-aid wheel and undercarriage

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022081129A1 (en) * 2020-10-12 2022-04-21 Robert Blackmore Collins Vehicle battery carrier for aircraft ground support

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