CN104608921A - Aircraft wheel and landing-assisting method - Google Patents
Aircraft wheel and landing-assisting method Download PDFInfo
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- CN104608921A CN104608921A CN201510047527.4A CN201510047527A CN104608921A CN 104608921 A CN104608921 A CN 104608921A CN 201510047527 A CN201510047527 A CN 201510047527A CN 104608921 A CN104608921 A CN 104608921A
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- wheel hub
- aircraft
- outer wheel
- controller
- coil assembly
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- 238000000034 method Methods 0.000 title claims abstract description 11
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 13
- 239000010959 steel Substances 0.000 claims abstract description 13
- 230000000694 effects Effects 0.000 claims description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 abstract 3
- 230000008569 process Effects 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
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- 230000001105 regulatory effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The invention discloses an aircraft wheel and a landing-assisting method. The aircraft wheel comprises a tire, an outer hub and a core part, wherein the tire is arranged on the outer hub in a sleeving manner; the core part is arranged in a cavity of the outer hub; a plurality of pieces of permanent magnet steel are arranged on the inner surface of the outer hub; the core part comprises a plurality of coil groups, a brake resistor, a controller and a wheel shaft; the plurality of coil groups are distributed in the outer edge area of the core part and correspond to the plurality of pieces of permanent magnet steel; the controller is electrically connected with the plurality of coil groups and the brake resistor respectively; the wheel shaft is located on the central axis of the core part; the outer hub is arranged on the wheel shaft in a sleeving manner; the core part further comprises a stator iron core and a fixed frame, the stator iron core is arranged on the fixed frame in a sleeving manner, the plurality of coil groups are arranged on the stator iron core, and the wheel shaft is arranged at the center of the fixed frame. The aircraft wheel is capable of effectively reducing the slide friction force and the deflection torque stressed by contacting to earth when an aircraft lands, thus greatly improving the safety.
Description
Technical field
The present invention relates to a kind of airplane wheel and help and fall method.
Background technology
When aircraft landing, after aircraft tyre kiss the earth, in very short time, frictionally is by the static sinking speed (being generally 250-350Km/h) accelerating to aircraft in meeting, and this tire to wheel, wheel hub, bearing all can cause great impact load.In the starting stage of tire motion, the firm kiss the earth of tire and twirl, but velocity of rotation does not reach the touchdown speed of aircraft, and thus tire is also in cliding friction state when rotating.On the one hand, cliding friction produces a large amount of heat, causes surface of tyre sharply to wear and tear or worn out, even causes wheel tire blow-out, harm flight safety; On the other hand, the main wheel of aircraft both sides can not contact to earth strictly speaking simultaneously, and the wheel first contacted to earth the relative center of gravity of airplane can form a deflecting torque, brings out safety misadventure.
Summary of the invention
Based on this, the object of the invention is to the defect overcoming prior art, provide a kind of airplane wheel and help and fall method, it effectively can reduce aircraft wheel when landing and to contact to earth the force of sliding friction and deflecting torque that are subject to, thus greatly promotes safety.
Its technical scheme is as follows:
A kind of airplane wheel, comprise tire, outer wheel hub and kernel portion, tire sleeve is located on outer wheel hub, kernel portion is arranged in the chamber of outer wheel hub, and the inside face of outer wheel hub is provided with polylith permanent-magnet steel, and kernel portion comprises multiple coil assembly, braking resistor, controller and wheel shaft, the outer edge area that multiple coil assembly is distributed in kernel portion is corresponding with polylith permanent-magnet steel, controller and multiple coil assembly, braking resistor electrically connect respectively, and wheel shaft is positioned on the central axis in kernel portion, and outer wheel hub is set on wheel shaft.
Preferably, described kernel portion also comprises stator core and fixed mount, and stator core is set on fixed mount, and described multiple coil assembly is arranged on stator core, and described wheel shaft is arranged on the center of fixed mount.
Preferably, be also provided with coding disk in described outer wheel hub, coding disk and described controller electrically connect.
Preferably, described outer wheel hub is connected with described wheel shaft by bearing.
Preferably, this wheel also comprises brake disc device, and this brake disc device is connected with described outer wheel hub.
Preferably, this wheel also comprises anti-skid device, and this anti-skid device is connected with described outer wheel hub.
A method falls in helping of aircraft, comprises the steps:
When aircraft landing, before tire interface ground on outer wheel hub, controller in kernel portion is opened and is run and be energized to multiple coil assembly, polylith permanent-magnet steel effect in multiple coil assembly and outer wheel hub drives outer wheel hub to accelerate to rotate on wheel shaft, make tire when kiss the earth its linear velocity close to the speed of now aircraft; When the linear velocity on aircraft landing rear tyre is identical with the speed of aircraft, controller interrupts the energising to multiple coil assembly, connects braking resistor; When aircraft reaches default low speed or stops, controller is out of service.
Below the advantage of preceding solution or principle are described:
Above-mentioned airplane wheel, when preparing landing after aircraft drop, controller in kernel portion is opened and is run and be energized to multiple coil assembly, coil assembly produces electromagnetic force after powered up makes the outer wheel hub that inside face is equipped with permanent-magnet steel accelerate to rotate, namely tire is driven to accelerate to rotate, when tire interface ground, the linear velocity of its outside face has reached the speed be close with aircraft, now, the velocity contrast of outer surface of tire and aircraft will be very little, force of sliding friction between surface of tyre and ground will be little in the extreme, and the in-service time of this force of sliding friction also can be extremely short, therefore tire extremely reaches in this process of identical coasting speed with aircraft at beginning kiss the earth, the impact load be subject to can be smaller, little to the deflecting torque of center of gravity of airplane formation on the one hand, on the one hand the degree of tortuosity of tire is also greatly reduced, thus greatly can reduce the incidence of safety misadventure.When the linear velocity on aircraft landing rear tyre is identical with the speed of aircraft, controller interrupts the energising to multiple coil assembly, now outer wheel hub rotates along with tire, be electrical generator seemingly to the effect in kernel portion, controller then can connect braking resistor, and the electric energy that kinetic transformation becomes by this wheel is consumed rapidly, also create lock torque in consumption process simultaneously, wheel can be made to slow down quickly, and when aircraft reaches default low speed or stops, controller is out of service.
Accompanying drawing explanation
Fig. 1 is the structural representation in the airplane wheel cross section described in the embodiment of the present invention;
Description of reference numerals:
1, outer wheel hub, 11, permanent-magnet steel, 21, stator core, 22, fixed mount, 23, wheel shaft, 24, coil assembly, 25, bearing, 3, tire, 4, brake disc device, 5, anti-skid device.
Detailed description of the invention
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail:
As shown in Figure 1, for a kind of airplane wheel, comprise tire 3, outer wheel hub 1 and kernel portion, tire 3 is set on outer wheel hub 1, kernel portion is arranged in the chamber of outer wheel hub 1, the inside face of outer wheel hub 1 is provided with polylith permanent-magnet steel 11 equably, kernel portion comprises multiple coil assembly 24, braking resistor, controller and the wheel shaft 23 that can be connected with undercarriage, the outside face that multiple coil assembly 24 is evenly distributed in kernel portion is corresponding with polylith permanent-magnet steel 11, controller and multiple coil assembly 24, braking resistor, aircraft control system electrically connects respectively, wheel shaft 23 is positioned on the central axis in kernel portion, outer wheel hub 1 is set on wheel shaft 23.
When preparing landing after aircraft drop, the controller that aircraft control system can open this wheel kernel portion runs, controller is that multiple coil assembly 24 is energized, coil assembly 24 produces electromagnetic force after powered up makes the outer wheel hub 1 that inside face is equipped with permanent-magnet steel 11 accelerate to rotate, namely tire 3 is driven to accelerate to rotate, when tire 3 kiss the earth, the linear velocity of its outside face has reached the speed (this can be regulated and controled by aircraft control system) be close with aircraft, now, the velocity contrast of tire 3 outside face and aircraft will be very little, force of sliding friction between tire 3 surface and ground will be little in the extreme, and the in-service time of this force of sliding friction also can be extremely short, therefore tire 3 extremely reaches in this process of identical coasting speed with aircraft at beginning kiss the earth, the impact load be subject to can be smaller, little to the deflecting torque of center of gravity of airplane formation on the one hand, on the one hand the degree of tortuosity of tire 3 is also greatly reduced, thus greatly can reduce the incidence of safety misadventure.When aircraft on the ground stable slide time (when the linear velocity on tire is identical with the speed of aircraft), aircraft control system can make the energising of controller interruption to multiple coil assembly, now outer wheel hub 1 rotates along with tire 3, electrical generator seemingly to the effect in kernel portion, the controller in kernel portion then can connect braking resistor, the electric energy that kinetic transformation becomes is consumed by this wheel rapidly, also create lock torque in consumption process simultaneously, wheel can be made to slow down quickly, when aircraft reaches default low speed or stops, controller is out of service.
In the present embodiment, kernel portion also comprises stator core 21 and fixed mount 22, and stator core 21 is set on fixed mount 22, and multiple coil assembly 24 is arranged on stator core 21, and wheel shaft 23 is arranged on the center of fixed mount 22; Also be provided with coding disk in outer wheel hub 1, coding disk and controller electrically connect; Outer wheel hub 1 is docked with wheel shaft 23 by bearing 25.
In the present embodiment, this wheel also comprises brake disc device 4 and anti-skid device 5, and this brake disc device 4, anti-skid device 5 are connected with wheel hub and electrically connect with aircraft control system respectively.Jointly carry out brake action, make the better effects if of deceleration.
The above embodiment only have expressed the specific embodiment of the present invention, and it describes comparatively concrete and detailed, but therefore can not be interpreted as the restriction to the scope of the claims of the present invention.It should be pointed out that for the person of ordinary skill of the art, without departing from the inventive concept of the premise, can also make some distortion and improvement, these all belong to protection scope of the present invention.
Claims (7)
1. an airplane wheel, comprise tire, it is characterized in that, also comprise outer wheel hub and kernel portion, tire sleeve is located on outer wheel hub, kernel portion is arranged in the chamber of outer wheel hub, the inside face of outer wheel hub is provided with polylith permanent-magnet steel, kernel portion comprises multiple coil assembly, braking resistor, controller and wheel shaft, the outer edge area that multiple coil assembly is distributed in kernel portion is corresponding with polylith permanent-magnet steel, controller and multiple coil assembly, braking resistor electrically connect respectively, and wheel shaft is positioned on the central axis in kernel portion, and outer wheel hub is set on wheel shaft.
2. airplane wheel according to claim 1, is characterized in that, described kernel portion also comprises stator core and fixed mount, and stator core is set on fixed mount, and described multiple coil assembly is arranged on stator core, and described wheel shaft is arranged on the center of fixed mount.
3. airplane wheel according to claim 1, is characterized in that, is also provided with coding disk in described outer wheel hub, and coding disk and described controller electrically connect.
4. airplane wheel according to claim 1, is characterized in that, described outer wheel hub is connected with described wheel shaft by bearing.
5. airplane wheel according to any one of claim 1 to 4, is characterized in that, also comprises brake disc device, and this brake disc device is connected with described outer wheel hub.
6. airplane wheel according to any one of claim 1 to 4, is characterized in that, also comprises anti-skid device, and this anti-skid device is connected with described outer wheel hub.
7. method falls in helping of an aircraft, it is characterized in that, comprise the steps: when aircraft landing, before tire interface ground on outer wheel hub, controller in kernel portion is opened and is run and be energized to multiple coil assembly, polylith permanent-magnet steel effect in multiple coil assembly and outer wheel hub drives outer wheel hub to accelerate to rotate on wheel shaft, make tire when kiss the earth its linear velocity close to the speed of now aircraft; When the linear velocity on aircraft landing rear tyre is identical with the speed of aircraft, controller interrupts the energising to multiple coil assembly, connects braking resistor; When aircraft reaches default low speed or stops, controller is out of service.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510047527.4A CN104608921B (en) | 2015-01-29 | 2015-01-29 | Airplane wheel and help drop method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510047527.4A CN104608921B (en) | 2015-01-29 | 2015-01-29 | Airplane wheel and help drop method |
Publications (2)
| Publication Number | Publication Date |
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| CN104608921A true CN104608921A (en) | 2015-05-13 |
| CN104608921B CN104608921B (en) | 2017-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510047527.4A Expired - Fee Related CN104608921B (en) | 2015-01-29 | 2015-01-29 | Airplane wheel and help drop method |
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| CN (1) | CN104608921B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897922A (en) * | 2015-06-29 | 2015-09-09 | 贵州新安航空机械有限责任公司 | Non-contact Hall magnetic induction-type airplane wheel speed sensor |
| CN106394257A (en) * | 2016-10-17 | 2017-02-15 | 济南大学 | Application of energy-saving electricity storage device of coupling hydraulic transmission |
| CN106394878A (en) * | 2016-10-18 | 2017-02-15 | 济南大学 | Air-and-water mixing resistance brake |
| CN106394255A (en) * | 2016-10-17 | 2017-02-15 | 济南大学 | Heat-dissipating electric braking device |
| CN106477030A (en) * | 2016-10-17 | 2017-03-08 | 济南大学 | The application of radiating electrodynamic device |
| CN106516091A (en) * | 2016-10-18 | 2017-03-22 | 济南大学 | Application of wind-water mixed resistance brake |
| CN107776876A (en) * | 2016-08-24 | 2018-03-09 | 赛峰起落架系统公司 | Aircraft wheel equipped with separable bearing case |
| CN111301667A (en) * | 2018-12-11 | 2020-06-19 | 海鹰航空通用装备有限责任公司 | Electromagnetic brake system for unmanned aerial vehicle and unmanned aerial vehicle |
| WO2023173202A1 (en) * | 2022-03-15 | 2023-09-21 | Safran Landing Systems Canada Inc. | Passive eddy-current wheel brake with conical form |
| US11994164B2 (en) | 2019-09-30 | 2024-05-28 | Airbus Operations Limited | Bearing unit for an aircraft wheel |
Citations (8)
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|---|---|---|---|---|
| GB587995A (en) * | 1945-01-03 | 1947-05-12 | Otto Elsworth Dever | Electric motor driven landing wheel for airplanes |
| CN2654510Y (en) * | 2003-08-13 | 2004-11-10 | 王俊元 | Aeroplane alighting carriage additional power device |
| CN1906082A (en) * | 2003-12-15 | 2007-01-31 | 史蒂文·沙利文 | Method and apparatus for braking and maneuvering |
| US20070284478A1 (en) * | 2006-06-08 | 2007-12-13 | Soderberg Rod F | Magnetically induced aircraft landing wheel rotation |
| CN102265483A (en) * | 2008-12-18 | 2011-11-30 | 斯马工程有限公司 | Axial flux motor and generator assemblies |
| 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 |
| WO2014029962A1 (en) * | 2012-08-21 | 2014-02-27 | Messier-Dowty Limited | A brake assembly and a method of operating a brake assembly |
| CN204507250U (en) * | 2015-01-29 | 2015-07-29 | 广州铁路职业技术学院 | Airplane wheel |
-
2015
- 2015-01-29 CN CN201510047527.4A patent/CN104608921B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB587995A (en) * | 1945-01-03 | 1947-05-12 | Otto Elsworth Dever | Electric motor driven landing wheel for airplanes |
| CN2654510Y (en) * | 2003-08-13 | 2004-11-10 | 王俊元 | Aeroplane alighting carriage additional power device |
| CN1906082A (en) * | 2003-12-15 | 2007-01-31 | 史蒂文·沙利文 | Method and apparatus for braking and maneuvering |
| US20070284478A1 (en) * | 2006-06-08 | 2007-12-13 | Soderberg Rod F | Magnetically induced aircraft landing wheel rotation |
| CN102265483A (en) * | 2008-12-18 | 2011-11-30 | 斯马工程有限公司 | Axial flux motor and generator assemblies |
| 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 |
| WO2014029962A1 (en) * | 2012-08-21 | 2014-02-27 | Messier-Dowty Limited | A brake assembly and a method of operating a brake assembly |
| CN204507250U (en) * | 2015-01-29 | 2015-07-29 | 广州铁路职业技术学院 | Airplane wheel |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897922B (en) * | 2015-06-29 | 2017-12-05 | 贵州新安航空机械有限责任公司 | A kind of contactless Hall magnetic induction type wheel spin-up transducer |
| CN104897922A (en) * | 2015-06-29 | 2015-09-09 | 贵州新安航空机械有限责任公司 | Non-contact Hall magnetic induction-type airplane wheel speed sensor |
| CN107776876B (en) * | 2016-08-24 | 2021-03-12 | 赛峰起落架系统公司 | Aircraft wheel equipped with separable bearing housing |
| CN107776876A (en) * | 2016-08-24 | 2018-03-09 | 赛峰起落架系统公司 | Aircraft wheel equipped with separable bearing case |
| CN106394255A (en) * | 2016-10-17 | 2017-02-15 | 济南大学 | Heat-dissipating electric braking device |
| CN106477030A (en) * | 2016-10-17 | 2017-03-08 | 济南大学 | The application of radiating electrodynamic device |
| CN106394255B (en) * | 2016-10-17 | 2018-08-17 | 济南大学 | Radiate electrodynamic device |
| CN106394257A (en) * | 2016-10-17 | 2017-02-15 | 济南大学 | Application of energy-saving electricity storage device of coupling hydraulic transmission |
| CN106516091A (en) * | 2016-10-18 | 2017-03-22 | 济南大学 | Application of wind-water mixed resistance brake |
| CN106394878A (en) * | 2016-10-18 | 2017-02-15 | 济南大学 | Air-and-water mixing resistance brake |
| CN106394878B (en) * | 2016-10-18 | 2018-06-08 | 济南大学 | Geomantic omen hybrid resistor brake |
| CN106516091B (en) * | 2016-10-18 | 2018-07-20 | 济南大学 | The application of geomantic omen hybrid resistor brake |
| CN111301667A (en) * | 2018-12-11 | 2020-06-19 | 海鹰航空通用装备有限责任公司 | Electromagnetic brake system for unmanned aerial vehicle and unmanned aerial vehicle |
| US11994164B2 (en) | 2019-09-30 | 2024-05-28 | Airbus Operations Limited | Bearing unit for an aircraft wheel |
| WO2023173202A1 (en) * | 2022-03-15 | 2023-09-21 | Safran Landing Systems Canada Inc. | Passive eddy-current wheel brake with conical form |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104608921B (en) | 2017-12-12 |
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Granted publication date: 20171212 |
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