CN106477030B - The application of heat dissipation electrodynamic device - Google Patents
The application of heat dissipation electrodynamic device Download PDFInfo
- Publication number
- CN106477030B CN106477030B CN201610902620.3A CN201610902620A CN106477030B CN 106477030 B CN106477030 B CN 106477030B CN 201610902620 A CN201610902620 A CN 201610902620A CN 106477030 B CN106477030 B CN 106477030B
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- CN
- China
- Prior art keywords
- heat dissipation
- landing gear
- main landing
- gear
- generator
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- 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.)
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Classifications
-
- 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
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
The application of heat dissipation electrodynamic device, is related to the braking equipment applied technical field that radiates.It is characterized in that：When aircraft lands on the airport, when being slided into taxiway, main landing gear wheel is rotated by the gear in main gear wheels shaft driven gear case；Kinetic energy is passed to dc generator by gear, and dc generator converts the kinetic energy into electrical energy, and dc generator transmits electrical power to braking resistor；With sliding for aircraft, air draught enters heat dissipation air duct, is radiated in heat dissipation air duct by radiating fin for braking resistor.The application can reduce the ground run distance of aircraft；The braking under abnormal condition can additionally be increased, improve the safety of aircraft landing phases.
Description
Technical field
The application of heat dissipation electrodynamic device, is related to braking equipment applied technical field.
Background technology
With the fast development of information industry, travel industry, the transport service being adapted therewith is also being grown rapidly.Trip,
All what is maked rapid progress change occurs for the speed of logistics, and the radius of action of people is increasing, the range of logistics
It is increasingly wider.Air-transport industry is quickly grown, and in recent years for domestic, is constantly expanded newly-increased course line, is expanded airport.
Ground installation related to shipping increasingly highlights incompatible with rapid development shipping.
Invention content
Aircraft is required to sliding race when taking off or landing.Increasingly increased flight frequency occupies runway so that many machines
Field, which has to extend, increases runway.Increase airport construction expense, ground maintenance expense.
To overcome the shortcomings of the prior art：The sliding heat dissipation problem braked when running, it is sliding run apart from the problems such as.
The first purpose of the application is to reduce the ground run distance of aircraft；
The second purpose of the application additionally increases the braking under abnormal condition；
The third purpose of the application is to improve aircraft landing and the safety of coast period.
The application adopts the following technical scheme that achieve the above object：
First, radiate electrodynamic device
1st, radiate electrodynamic device, including：Gear-box 1, braking resistor 2, heat dissipation air duct 3, branch cable 4, junction box
5th, heat dissipation air duct air intake duct 6, radiating fin 7, dc generator 8, bearing housing 11, main landing gear wheel shaft 12, main landing gear wheel
13rd, main landing gear crane span structure 14, main unit of landing gear 16, electronics bay 91, control cable 92；
It is characterized in that：
Main landing gear is symmetrical parallel two groups, and there are four duplicate main landing gear wheels for every group of main landing gear dress
13, before two main landing gear wheels and two main landing gear wheels below；
Gear-box 1 is connected on the inside of main landing gear below, gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects
Main landing gear wheel shaft 12 is connect, main landing gear wheel shaft 12 connects main landing gear wheel 13；
Dc generator 8 connects braking resistor 2；
The connection heat dissipation air duct 3 of braking resistor 2, radiating fin 7 is in heat dissipation air duct 3；
Dc generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 is by controlling cable 92 to be connected to electronics bay 91.
2nd, the heat dissipation electrodynamic device, it is characterised in that：The radiating fin 7 is copper radiating rib.
3rd, the heat dissipation electrodynamic device, it is characterised in that：The radiating fin 7 is aluminium radiator fin.
4th, the heat dissipation electrodynamic device, it is characterised in that：3 cylinder of heat dissipation air duct is rubber radiation air
Cylinder.
5th, the heat dissipation electrodynamic device, it is characterised in that：3 cylinder of heat dissipation air duct is heat dissipation metal wind
Cylinder.
6th, the heat dissipation electrodynamic device, it is characterised in that：Radiation air is connected at 3 air inlet of heat dissipation air duct
Cylinder air intake duct 6.
7th, the electric floor vehicle, it is characterised in that：The heat dissipation air duct air intake duct 6 is tubaeform air intake duct.
(in air inlet, flow velocity is slow, and as horn mouth is gradually transitions heat dissipation air duct, with the diminution of radius, sectional area becomes smaller, therefore,
Air-flow velocity increases, conducive to rapid cooling.)
8th, the heat dissipation electrodynamic device, it is characterised in that：6 outer rim of heat dissipation air duct air intake duct has reinforcement
Muscle.(plaing a part of to strengthen heat dissipation air duct)
2nd, the application of heat dissipation electrodynamic device
1st, the application of heat dissipation electrodynamic device, heat dissipation electrodynamic device include：Gear-box 1, braking resistor 2, heat dissipation
Air duct 3, branch cable 4, junction box 5, heat dissipation air duct air intake duct 6, radiating fin 7, dc generator 8, bearing housing 11, master rise and fall
Frame wheel shaft 12, main landing gear wheel 13, main landing gear crane span structure 14, main unit of landing gear 16, electronics bay 91, control cable
92；
Main landing gear is symmetrical parallel two groups, and there are four duplicate main landing gear wheels for every group of main landing gear dress
13, before two main landing gear wheels and two main landing gear wheels below；
Gear-box 1 is connected on the inside of main landing gear below, gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects
Undercarriage wheel shaft 12 is connect, undercarriage wheel shaft 12 connects main landing gear wheel 13；
Dc generator 8 connects braking resistor 2；
The connection heat dissipation air duct 3 of braking resistor 2, radiating fin 7 is in heat dissipation air duct 3；
Dc generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 is by controlling cable 92 to be connected to electronics bay 91；
It is characterized in that：
When aircraft lands on the airport, when being slided into taxiway, main landing gear wheel 13 passes through main landing gear wheel shaft 12
Drive the gear rotation in gear-box 1；
Kinetic energy is passed to dc generator 8 by gear, and dc generator 8 converts the kinetic energy into electrical energy, and dc generator 8 will
Electric energy passes to braking resistor 2；
With sliding for aircraft, air draught enters heat dissipation air duct 3, by radiating fin 7 to make in heat dissipation air duct 3
Dynamic resistance 2 radiates.
2nd, the application of the heat dissipation electrodynamic device, it is characterised in that：Signal is controlled to lead to from electronics bay 91
It crosses and cable 92, junction box 5 and branch cable 4 is controlled to realize the control to dc generator 8.
Advantageous effect
1st, since " gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects undercarriage wheel shaft 12, undercarriage wheel shaft
12 connection main landing gear wheel, 13 dc generator 8 connects braking resistor 2；" the application can reduce aircraft it is sliding run away from
From；
2nd, the application can additionally increase the braking under abnormal condition, if when the one of which brake fault of aircraft
When, the heat dissipation electrodynamic device of the application can be used as a kind of spare brake apparatus；
3rd, the safety of aircraft landing phases, the particularly safety in the improper landing of aircraft, example are improved
Such as, when the brake gear of the prior art is unavailable, the present invention can work independently as a kind of independent system and realize aviation
The braking of device landing branch ground taxi.
Description of the drawings
Fig. 1：Radiate electrodynamic device and aircraft position diagrammatic side view
Fig. 2：Radiate electrodynamic device and aircraft position diagrammatic top view
Fig. 3：Radiate electrodynamic device side view
Fig. 4：A-A views
Fig. 5：B-B views
Fig. 6：C-C views
In figure：1 gear-box, 2 braking resistors, 3 heat dissipation air ducts, 4 branch cables, 5 junction boxs, 6 heat dissipation air duct air intake ducts, 7
Radiating fin, 8 dc generators, 11 bearing housings, 12 main landing gear wheel shafts, 13 main landing gear wheels, 14 main landing gear crane span structures, 16
Main unit of landing gear, 91 electronics bays, 92 control cables.
Note 1：The purpose of Fig. 1, Fig. 2 only indicate heat dissipation electrodynamic device in the position of the rear undercarriage of aircraft,
Widget in Fig. 1, Fig. 2 can see details by Fig. 4, Fig. 5 of amplification.
Specific embodiment
The application is described further with reference to the accompanying drawings and examples.
Embodiment 1
1st, radiate electrodynamic device, including：Gear-box 1, braking resistor 2, heat dissipation air duct 3, branch cable 4, junction box
5th, heat dissipation air duct air intake duct 6, radiating fin 7, dc generator 8, bearing housing 11, main landing gear wheel shaft 12, main landing gear wheel
13rd, main landing gear crane span structure 14, main unit of landing gear 16, electronics bay 91, control cable 92；
It is characterized in that：
Main landing gear is symmetrical parallel two groups, and there are four duplicate main landing gear wheels for every group of main landing gear dress
13, before two main landing gear wheels and two main landing gear wheels below；
Gear-box 1 is connected on the inside of main landing gear below, gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects
Main landing gear wheel shaft 12 is connect, main landing gear wheel shaft 12 connects main landing gear wheel 13；
Dc generator 8 connects braking resistor 2；
The connection heat dissipation air duct 3 of braking resistor 2, radiating fin 7 is in heat dissipation air duct 3；
Dc generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 is by controlling cable 92 to be connected to electronics bay 91.
2nd, the heat dissipation electrodynamic device, it is characterised in that：The radiating fin 7 is copper radiating rib.
3rd, the heat dissipation electrodynamic device, it is characterised in that：The radiating fin 7 is aluminium radiator fin.
4th, the heat dissipation electrodynamic device, it is characterised in that：3 cylinder of heat dissipation air duct is rubber radiation air
Cylinder.
5th, the heat dissipation electrodynamic device, it is characterised in that：3 cylinder of heat dissipation air duct is heat dissipation metal wind
Cylinder.
6th, the heat dissipation electrodynamic device, it is characterised in that：Radiation air is connected at 3 air inlet of heat dissipation air duct
Cylinder air intake duct 6.
7th, the heat dissipation electrodynamic device, it is characterised in that：Described heat dissipation air duct air intake duct 6 for it is tubaeform into
Air flue.(in air inlet, flow velocity is slow, and as horn mouth is gradually transitions heat dissipation air duct, with the diminution of radius, sectional area becomes smaller,
Therefore, air-flow velocity increases, conducive to rapid cooling.)
8th, the heat dissipation electrodynamic device, it is characterised in that：6 outer rim of heat dissipation air duct air intake duct has reinforcement
Muscle.(plaing a part of to strengthen heat dissipation air duct)
Embodiment 2
1st, the application of heat dissipation electrodynamic device, heat dissipation electrodynamic device include：Gear-box 1, braking resistor 2, heat dissipation
Air duct 3, branch cable 4, junction box 5, heat dissipation air duct air intake duct 6, radiating fin 7, dc generator 8, bearing housing 11, master rise and fall
Frame wheel shaft 12, main landing gear wheel 13, main landing gear crane span structure 14, main unit of landing gear 16, electronics bay 91, control cable
92；
Main landing gear is symmetrical parallel two groups, and there are four duplicate main landing gear wheels for every group of main landing gear dress
13, before two main landing gear wheels and two main landing gear wheels below；
Gear-box 1 is connected on the inside of main landing gear below, gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects
Undercarriage wheel shaft 12 is connect, undercarriage wheel shaft 12 connects main landing gear wheel 13；
Dc generator 8 connects braking resistor 2；
The connection heat dissipation air duct 3 of braking resistor 2, radiating fin 7 is in heat dissipation air duct 3；
Dc generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 is by controlling cable 92 to be connected to electronics bay 91；
It is characterized in that：
When aircraft lands on the airport, when being slided into taxiway, main landing gear wheel 13 passes through main landing gear wheel shaft 12
Drive the gear rotation in gear-box 1；
Kinetic energy is passed to dc generator 8 by gear, and dc generator 8 converts the kinetic energy into electrical energy, and dc generator 8 will
Electric energy passes to braking resistor 2；
With sliding for aircraft, air draught enters heat dissipation air duct 3, by radiating fin 7 to make in heat dissipation air duct 3
Dynamic resistance 2 radiates.
2nd, the application of the heat dissipation electrodynamic device, it is characterised in that：Signal is controlled to lead to from electronics bay 91
It crosses and cable 92, junction box 5 and branch cable 4 is controlled to realize the control to dc generator 8.
In addition to technical characteristic described herein, remaining is knowledge well known to one of ordinary skill in the art, is not existed herein
It repeats.
Claims (2)
1. the application for the electrodynamic device that radiates, heat dissipation electrodynamic device includes：Gear-box, heat dissipation air duct, divides at braking resistor
Road cable, junction box, heat dissipation air duct air intake duct, radiating fin, dc generator, bearing housing, main landing gear wheel shaft, main landing gear
Wheel, main landing gear crane span structure, main unit of landing gear, electronics bay, control cable；
Main landing gear is symmetrical parallel two groups, and every group of main landing gear is filled there are four duplicate main landing gear wheel, before
Two main landing gear wheels and below two main landing gear wheels；
Gear-box, gear-box connection main landing gear wheel shaft, bearing housing connection main landing gear are connected on the inside of main landing gear below
Wheel shaft, main gear wheels axis connection main landing gear wheel；
Dc generator connects braking resistor；
Braking resistor connection heat dissipation air duct, radiating fin is in heat dissipation air duct；
Dc generator connects branch cable, branch cable connection junction box；
Junction box is by controlling cable connection to electronics bay；
It is characterized in that：
When aircraft lands on the airport, when being slided into taxiway, main landing gear wheel passes through main gear wheels shaft driven gear
Gear rotation in case；
Kinetic energy is passed to dc generator by gear, and dc generator converts the kinetic energy into electrical energy, and dc generator passes electric energy
Pass braking resistor；
With sliding for aircraft, air draught enters heat dissipation air duct, heat dissipation air duct in by radiating fin be braking resistor
Heat dissipation.
2. the application of heat dissipation electrodynamic device as described in claim 1, it is characterised in that：It controls and believes from electronics bay
Number by the way that cable, junction box and branch cable is controlled to realize the control to dc generator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610902620.3A CN106477030B (en) | 2016-10-17 | 2016-10-17 | The application of heat dissipation electrodynamic device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610902620.3A CN106477030B (en) | 2016-10-17 | 2016-10-17 | The application of heat dissipation electrodynamic device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106477030A CN106477030A (en) | 2017-03-08 |
| CN106477030B true CN106477030B (en) | 2018-06-15 |
Family
ID=58270135
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610902620.3A Expired - Fee Related CN106477030B (en) | 2016-10-17 | 2016-10-17 | The application of heat dissipation electrodynamic device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106477030B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6758440B1 (en) * | 2003-03-21 | 2004-07-06 | Curtiss-Wright Electro-Mechanical Corporation | Electromagnetic aircraft arrestor system |
| US7237748B2 (en) * | 2003-12-15 | 2007-07-03 | Delos Aerospace, Llc | Landing gear method and apparatus for braking and maneuvering |
| CN101808871B (en) * | 2007-09-28 | 2014-02-05 | 桂林星辰电力电子有限公司 | Power apparatus for oil-electricity hybrid vehicle and operation control method thereof |
| CN104608921B (en) * | 2015-01-29 | 2017-12-12 | 广州铁路职业技术学院 | Airplane wheel and help drop method |
| CN104723887B (en) * | 2015-03-16 | 2017-01-04 | 王玮 | The auxiliary brake of towed vehicle and towed vehicle |
| CN105508020B (en) * | 2016-02-01 | 2018-05-29 | 清华大学 | The shared cooling system of engine and braking resistor |
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2016
- 2016-10-17 CN CN201610902620.3A patent/CN106477030B/en not_active Expired - Fee Related
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| Publication number | Publication date |
|---|---|
| CN106477030A (en) | 2017-03-08 |
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Granted publication date: 20180615 Termination date: 20181017 |
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