CN106477030A - The application of radiating electrodynamic device - Google Patents
The application of radiating electrodynamic device Download PDFInfo
- Publication number
- CN106477030A CN106477030A CN201610902620.3A CN201610902620A CN106477030A CN 106477030 A CN106477030 A CN 106477030A CN 201610902620 A CN201610902620 A CN 201610902620A CN 106477030 A CN106477030 A CN 106477030A
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- CN
- China
- Prior art keywords
- radiating
- landing gear
- main landing
- generator
- air duct
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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
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- 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 radiating electrodynamic device, is related to the braking equipment applied technical field that radiates.It is characterized in that：When airborne vehicle lands on the airport, when entrance taxiway slides, main landing gear wheel passes through the pinion rotation in main gear wheels shaft driven gear case；Kinetic energy is passed to DC generator by gear, and DC generator converts kinetic energy into electric energy, and DC generator transmits electrical power to braking resistor；Sliding with airborne vehicle, air draught enters radiating air duct, is radiated for braking resistor by radiating fin in radiating air duct.The application can reduce the ground run distance of airborne vehicle；The braking under abnormal condition can additionally be increased, improve the safety of airborne vehicle landing phases.
Description
Technical field
The application of radiating 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 in fast development.Trip,
The speed of logistics all occurs to change with rapid changepl. never-ending changes and improvements, and the radius of action of people is increasing, the scope of logistics
More and more wider.Air-transport industry quickly grows, and in recent years for domestic, constantly expands newly-increased course line, expands airport.
Ground installation related to shipping increasingly highlights and develops rapidly the incompatible of shipping.
Content of the invention
Airborne vehicle is required to sliding race when taking off or land.The flight frequency of increasingly increase takies runway so that many machines
Field has to extend increases runway.Increase airport construction expense, ground maintenance expense.
For overcoming the shortcomings of prior art presence：The sliding heat dissipation problem braked when running, sliding run apart from the problems such as.
One of purpose of the application is to reduce the ground run distance of airborne vehicle；
Braking under abnormal condition for the two extra increases of the purpose of the application；
The three of the purpose of the application are to improve airborne vehicle landing and the safety of coast period.
The application adopts the following technical scheme that for achieving the above object：
First, radiate electrodynamic device
1st, radiate electrodynamic device, including：Gear-box 1, braking resistor 2, radiating air duct 3, branch cable 4, junction box
5th, radiating 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 group, and every group of main landing gear is equipped with four duplicate main landing gear wheels
13, before two main landing gear wheels and two main landing gear wheels below；
It is connected with gear-box 1, gear-box 1 connects main landing gear wheel shaft 12, bearing housing 11 is even inside main landing gear below
Connect main landing gear wheel shaft 12, main landing gear wheel shaft 12 connects main landing gear wheel 13；
DC generator 8 connects braking resistor 2；
Braking resistor 2 connects radiating air duct 3, and radiating fin 7 is in radiating air duct 3；
DC generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 passes through to control cable 92 to be connected to electronics bay 91.
2nd, described radiating electrodynamic device it is characterised in that：Described radiating fin 7 is copper radiating rib.
3rd, described radiating electrodynamic device it is characterised in that：Described radiating fin 7 is aluminium radiator fin.
4th, described radiating electrodynamic device it is characterised in that：Described radiating air duct 3 cylinder is rubber radiation air
Cylinder.
5th, described radiating electrodynamic device it is characterised in that：Described radiating air duct 3 cylinder is heat dissipation metal wind
Cylinder.
6th, described radiating electrodynamic device it is characterised in that：Radiation air is connected at described radiating air duct 3 air inlet
Cylinder air intake duct 6.
7th, described electric floor car it is characterised in that：Described radiating air duct air intake duct 6 is flaring air intake duct.
(in air inlet, flow velocity is slow, is gradually transitions radiating air duct, reducing with radius with horn mouth, sectional area diminishes, therefore,
Air-flow velocity increases, beneficial to quick heat radiating.)
8th, described radiating electrodynamic device it is characterised in that：Described radiating air duct air intake duct 6 outer rim has reinforcement
Muscle.(acting the effect strengthening radiating air duct)
2nd, the application of radiating electrodynamic device
1st, radiating electrodynamic device application, radiating electrodynamic device includes：Gear-box 1, braking resistor 2, radiation air
Cylinder 3, branch cable 4, junction box 5, radiating 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 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 group, and every group of main landing gear is equipped with four duplicate main landing gear wheels
13, before two main landing gear wheels and two main landing gear wheels below；
It is connected with gear-box 1, gear-box 1 connects main landing gear wheel shaft 12, bearing housing 11 is even inside main landing gear below
Connect undercarriage wheel shaft 12, undercarriage wheel shaft 12 connects main landing gear wheel 13；
DC generator 8 connects braking resistor 2；
Braking resistor 2 connects radiating air duct 3, and radiating fin 7 is in radiating air duct 3；
DC generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 passes through to control cable 92 to be connected to electronics bay 91；
It is characterized in that：
When airborne vehicle lands on the airport, when entrance taxiway slides, main landing gear wheel 13 passes through main landing gear wheel shaft 12
Drive the pinion rotation in gear-box 1；
Kinetic energy is passed to DC generator 8 by gear, and DC generator 8 converts kinetic energy into electric energy, and DC generator 8 will
Electric energy passes to braking resistor 2；
Sliding with airborne vehicle, air draught enters radiating air duct 3, and passing through radiating fin 7 in radiating air duct 3 is system
Galvanic electricity resistance 2 radiating.
2nd, described radiating electrodynamic device application it is characterised in that：Pass through from electronics bay 91 control signal
Cable 92, junction box 5 and branch cable 4 is controlled to realize the control to DC generator 8.
Beneficial effect
1st, because " gear-box 1 connects main landing gear wheel shaft 12, and bearing housing 11 connects undercarriage wheel shaft 12, undercarriage wheel shaft
12 connect main landing gear wheel 13 DC generator 8 connects braking resistor 2；" the application can reduce airborne vehicle sliding run away from
From；
2nd, the application can additionally increase the braking under abnormal condition, if the one of which brake fault when airborne vehicle
When, the radiating electrodynamic device of the application can use as a kind of standby brake unit；
3rd, improve the safety of airborne vehicle landing phases, the particularly safety in the improper landing of airborne vehicle, example
As when the brake gear of prior art is unavailable, the present invention, as a kind of independent system, can work independently and realize aviation
The braking of device landing ground taxi.
Brief description
Fig. 1：Radiating electrodynamic device and aircraft position diagrammatic side view
Fig. 2：Radiating electrodynamic device and aircraft position diagrammatic top view
Fig. 3：Radiating electrodynamic device side view
Fig. 4：A-A view
Fig. 5：B-B view
Fig. 6：C-C view
In figure：1 gear-box, 2 braking resistors, 3 radiating air ducts, 4 branch cables, 5 junction boxs, 6 radiating air duct air intake ducts, 7
Radiating fin, 8 DC generator, 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 is the position of the instruction radiating rear undercarriage in airborne vehicle for the electrodynamic device,
Widget in Fig. 1, Fig. 2 can see details by Fig. 4, Fig. 5 of amplifying.
Specific embodiment
With reference to the accompanying drawings and examples the application is described further.
Embodiment 1
1st, radiate electrodynamic device, including：Gear-box 1, braking resistor 2, radiating air duct 3, branch cable 4, junction box
5th, radiating 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 group, and every group of main landing gear is equipped with four duplicate main landing gear wheels
13, before two main landing gear wheels and two main landing gear wheels below；
It is connected with gear-box 1, gear-box 1 connects main landing gear wheel shaft 12, bearing housing 11 is even inside main landing gear below
Connect main landing gear wheel shaft 12, main landing gear wheel shaft 12 connects main landing gear wheel 13；
DC generator 8 connects braking resistor 2；
Braking resistor 2 connects radiating air duct 3, and radiating fin 7 is in radiating air duct 3；
DC generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 passes through to control cable 92 to be connected to electronics bay 91.
2nd, described radiating electrodynamic device it is characterised in that：Described radiating fin 7 is copper radiating rib.
3rd, described radiating electrodynamic device it is characterised in that：Described radiating fin 7 is aluminium radiator fin.
4th, described radiating electrodynamic device it is characterised in that：Described radiating air duct 3 cylinder is rubber radiation air
Cylinder.
5th, described radiating electrodynamic device it is characterised in that：Described radiating air duct 3 cylinder is heat dissipation metal wind
Cylinder.
6th, described radiating electrodynamic device it is characterised in that：Radiation air is connected at described radiating air duct 3 air inlet
Cylinder air intake duct 6.
7th, described radiating electrodynamic device it is characterised in that：Described radiating air duct air intake duct 6 be flaring enter
Air flue.(in air inlet, flow velocity is slow, is gradually transitions radiating air duct, reducing with radius with horn mouth, sectional area diminishes,
Therefore, air-flow velocity increases, beneficial to quick heat radiating.)
8th, described radiating electrodynamic device it is characterised in that：Described radiating air duct air intake duct 6 outer rim has reinforcement
Muscle.(acting the effect strengthening radiating air duct)
Embodiment 2
1st, radiating electrodynamic device application, radiating electrodynamic device includes：Gear-box 1, braking resistor 2, radiation air
Cylinder 3, branch cable 4, junction box 5, radiating 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 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 group, and every group of main landing gear is equipped with four duplicate main landing gear wheels
13, before two main landing gear wheels and two main landing gear wheels below；
It is connected with gear-box 1, gear-box 1 connects main landing gear wheel shaft 12, bearing housing 11 is even inside main landing gear below
Connect undercarriage wheel shaft 12, undercarriage wheel shaft 12 connects main landing gear wheel 13；
DC generator 8 connects braking resistor 2；
Braking resistor 2 connects radiating air duct 3, and radiating fin 7 is in radiating air duct 3；
DC generator 8 connects branch cable 4, and branch cable 4 connects junction box 5；
Junction box 5 passes through to control cable 92 to be connected to electronics bay 91；
It is characterized in that：
When airborne vehicle lands on the airport, when entrance taxiway slides, main landing gear wheel 13 passes through main landing gear wheel shaft 12
Drive the pinion rotation in gear-box 1；
Kinetic energy is passed to DC generator 8 by gear, and DC generator 8 converts kinetic energy into electric energy, and DC generator 8 will
Electric energy passes to braking resistor 2；
Sliding with airborne vehicle, air draught enters radiating air duct 3, and passing through radiating fin 7 in radiating air duct 3 is system
Galvanic electricity resistance 2 radiating.
2nd, described radiating electrodynamic device application it is characterised in that：Pass through from electronics bay 91 control signal
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 known to one of ordinary skill in the art, and here does not exist
Repeat.
Claims (2)
1. the application of radiating electrodynamic device, radiating electrodynamic device includes：Gear-box, braking resistor, radiating air duct, point
Road cable, junction box, radiating 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 group, every group of main landing gear equipped with four duplicate main landing gear wheels, before
Two main landing gear wheels and below two main landing gear wheels；
It is connected with gear-box, gear-box connects main landing gear wheel shaft, bearing housing connects main landing gear inside main landing gear below
Wheel shaft, main landing gear wheel shaft connects main landing gear wheel；
DC generator connects braking resistor；
Braking resistor connects radiating air duct, and radiating fin is in radiating air duct；
DC generator connects branch cable, and branch cable connects junction box；
Junction box passes through to control cable connection to electronics bay；
It is characterized in that：
When airborne vehicle lands on the airport, when entrance taxiway slides, main landing gear wheel passes through main gear wheels shaft driven gear
Pinion rotation in case；
Kinetic energy is passed to DC generator by gear, and DC generator converts kinetic energy into electric energy, and electric energy is passed by DC generator
Pass braking resistor；
Sliding with airborne vehicle, air draught enters radiating air duct, and passing through radiating fin in radiating air duct is braking resistor
Radiating.
2. as claimed in claim 1 radiating electrodynamic device application it is characterised in that：From electronics bay control signal
Realize the control to DC generator by controlling cable, junction box and branch cable.
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 true CN106477030A (en) | 2017-03-08 |
| CN106477030B 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 |
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Citations (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 |
| US20080179146A1 (en) * | 2003-12-15 | 2008-07-31 | Delos Aerospace, Llc | Method and apparatus for braking and maneuvering |
| CN101808871A (en) * | 2007-09-28 | 2010-08-18 | 桂林吉星电子等平衡动力有限公司 | A power apparatus for oil-electricity hybrid vehicle and the operation control method thereof |
| CN104608921A (en) * | 2015-01-29 | 2015-05-13 | 广州铁路职业技术学院 | Aircraft wheel and landing-assisting method |
| CN104723887A (en) * | 2015-03-16 | 2015-06-24 | 三门峡荣通车辆应用技术开发有限公司 | Auxiliary brake device for trailer and trailer |
| CN105508020A (en) * | 2016-02-01 | 2016-04-20 | 清华大学 | Common cooling system for engine and braking resistor |
-
2016
- 2016-10-17 CN CN201610902620.3A patent/CN106477030B/en not_active Expired - Fee Related
Patent Citations (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 |
| US20080179146A1 (en) * | 2003-12-15 | 2008-07-31 | Delos Aerospace, Llc | Method and apparatus for braking and maneuvering |
| CN101808871A (en) * | 2007-09-28 | 2010-08-18 | 桂林吉星电子等平衡动力有限公司 | A power apparatus for oil-electricity hybrid vehicle and the operation control method thereof |
| CN104608921A (en) * | 2015-01-29 | 2015-05-13 | 广州铁路职业技术学院 | Aircraft wheel and landing-assisting method |
| CN104723887A (en) * | 2015-03-16 | 2015-06-24 | 三门峡荣通车辆应用技术开发有限公司 | Auxiliary brake device for trailer and trailer |
| CN105508020A (en) * | 2016-02-01 | 2016-04-20 | 清华大学 | Common cooling system for engine and braking resistor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106477030B (en) | 2018-06-15 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180615 Termination date: 20181017 |
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