CN106394255A - Heat-dissipating electric braking device - Google Patents
Heat-dissipating electric braking device Download PDFInfo
- Publication number
- CN106394255A CN106394255A CN201610903089.1A CN201610903089A CN106394255A CN 106394255 A CN106394255 A CN 106394255A CN 201610903089 A CN201610903089 A CN 201610903089A CN 106394255 A CN106394255 A CN 106394255A
- Authority
- CN
- China
- Prior art keywords
- main landing
- landing gear
- radiating
- air duct
- electrodynamic device
- Prior art date
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L7/00—Electrodynamic brake systems for vehicles in general
- B60L7/02—Dynamic electric resistor braking
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Braking Arrangements (AREA)
Abstract
The invention provides a heat-dissipating electric braking device, and relates to the technical field of braking equipment. The heat-dissipating electric braking device is characterized in that two sets of symmetrical and parallel main landing gears are arranged, and four same main landing gear airplane wheels are installed on each set of main landing gears and include two front main landing gear airplane wheels and two rear main landing gear airplane wheels. Gearboxes are connected to the inner sides of the main landing gears on the rear portion, and connected with main landing gear wheel shafts, bearing boxes are connected with the main landing gear wheel shafts, and the main landing gear wheel shafts are connected with the main landing gear airplane wheels. Direct-current generators are connected with braking resistors, the braking resistors are connected with heat dissipation air ducts, and cooling fins are arranged in the heat dissipation air ducts. The direct-current generators are connected with branch cables, the branch cables are connected with a branch box, and the branch box is connected to an electronic equipment compartment of an electronic compartment through a control cable. According to the heat-dissipating electric braking device, the taxiing distance of an aircraft can be reduced, the braking performance in the abnormal state can be additionally improved, and the safety of the aircraft in the landing stage can be improved.
Description
Technical field
Radiating electrodynamic device, is related to art of braking devices.
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 when taking off or land slide.The flight frequency of increasingly increase takies taxiway so that many
Airport has to extend increases taxiway.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 safety.
The application adopts the following technical scheme that for achieving the above object：
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)
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)
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 (8)
1. radiate electrodynamic device, including：Gear-box, braking resistor, radiating air duct, branch 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, lead
Fall post setting, electronics bay, control cable；
It is characterized in that：
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 electronic compartment electronics bay.
2. as claimed in claim 1 radiating electrodynamic device it is characterised in that：Described radiating fin is copper radiating rib.
3. as claimed in claim 1 radiating electrodynamic device it is characterised in that：Described radiating fin is aluminium radiator fin.
4. as claimed in claim 1 radiating electrodynamic device it is characterised in that：Described radiating air duct cylinder dissipates for rubber
Thermal chimney.
5. as claimed in claim 1 radiating electrodynamic device it is characterised in that：Described radiating air duct cylinder dissipates for metal
Thermal chimney.
6. as claimed in claim 1 radiating electrodynamic device it is characterised in that：Connect at described radiating air duct air inlet
Radiating air duct air intake duct.
7. as claimed in claim 6 radiating electrodynamic device it is characterised in that：Described radiating air duct air intake duct is loudspeaker
The air intake duct of shape.
8. as claimed in claim 7 radiating electrodynamic device it is characterised in that：Described radiating air duct air intake duct outer rim has
Reinforcement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610903089.1A CN106394255B (en) | 2016-10-17 | 2016-10-17 | Radiate electrodynamic device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610903089.1A CN106394255B (en) | 2016-10-17 | 2016-10-17 | Radiate electrodynamic device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106394255A true CN106394255A (en) | 2017-02-15 |
| CN106394255B CN106394255B (en) | 2018-08-17 |
Family
ID=58013361
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610903089.1A Expired - Fee Related CN106394255B (en) | 2016-10-17 | 2016-10-17 | Radiate electrodynamic device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106394255B (en) |
Citations (7)
| 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 |
| US20060038068A1 (en) * | 2003-12-15 | 2006-02-23 | Steven Sullivan | Landing gear 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 |
| US20110198439A1 (en) * | 2008-07-07 | 2011-08-18 | Airbus Operations Gmbh | Wheel drive system for an aircraft comprising a fuel cell as an energy source |
| 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 CN201610903089.1A patent/CN106394255B/en not_active Expired - Fee Related
Patent Citations (7)
| 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 |
| US20060038068A1 (en) * | 2003-12-15 | 2006-02-23 | Steven Sullivan | Landing gear 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 |
| US20110198439A1 (en) * | 2008-07-07 | 2011-08-18 | Airbus Operations Gmbh | Wheel drive system for an aircraft comprising a fuel cell as an energy source |
| 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 |
|---|---|
| CN106394255B (en) | 2018-08-17 |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180817 Termination date: 20191017 |
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| CF01 | Termination of patent right due to non-payment of annual fee |