CN202057230U - Heat dissipation plate for plane heat sink - Google Patents
Heat dissipation plate for plane heat sink Download PDFInfo
- Publication number
- CN202057230U CN202057230U CN201120049574XU CN201120049574U CN202057230U CN 202057230 U CN202057230 U CN 202057230U CN 201120049574X U CN201120049574X U CN 201120049574XU CN 201120049574 U CN201120049574 U CN 201120049574U CN 202057230 U CN202057230 U CN 202057230U
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- China
- Prior art keywords
- heat dissipation
- heat radiation
- fork
- heat
- fin
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- Expired - Fee Related
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Abstract
The utility model discloses a heat dissipation plate for a plane heat sink, which comprises a heat dissipation plate body; the heat dissipation plate body is in the shape of a circular sheet; a plurality of heat dissipation forks are radially distributed on the periphery of the heat dissipation plate body; each heat dissipation fork comprises a heat dissipation fork handle; one end of the heat dissipation fork handle is fixed on the heat dissipation plate body, and heat dissipation fork heads are arranged at the other end; and a plurality of heat dissipation ribs are arranged at one end of each heat dissipation fork head away from the heat dissipation fork handle. As the heat dissipation ribs and the heat dissipation forks are arranged on the heat dissipation plate body, the heat dissipation area of each heat dissipation plate is increased, so that the heat dissipation efficiency of the heat sink is improved. The heat dissipation plate has the advantages of simple structure and attractive appearance.
Description
Technical field
The utility model relates to a kind of fin of radiator, relates in particular to a kind of fin of aero radiator.
Background technology
Along with rapid economic development of China, aircraft more and more becomes the requisite vehicles in people's life, and most aircraft is made up of five major parts: wing, fuselage, empennage, take-off and landing device and power set.Power set are mainly used to produce pulling force or thrust, aircraft is advanced, can also provide electric power for the consumer on the aircraft, for gas equipments such as air-conditioning equipment provide source of the gas, power set etc. are when work, can produce a large amount of heats, as if untimely these heats be taken out of, the aircraft power device may damage because of high temperature.Therefore generally be provided with radiator on the aircraft power device, this radiator inside is provided with fin, collocation such as fin and fan is provided with, the heat that fin is produced when being used to absorb aircraft work, fan is forced the heat that fin absorbed to discharge outside the computer equipment, thereby reaches the purpose of heat radiation.
Radiator is dispersed into heat in the surrounding enviroment after absorbing heat, and wherein the contact area of fin and air is the most important.At present, in the prior art, the people generally number of the fin by increasing aero radiator increase area of dissipation, to improve the radiating effect of radiator, but the confined space for the airplane equipment power set, desire borrow to increase its fin sheet number and promotes radiating efficiency, on the principle be good at inaccessible.
Summary of the invention
The purpose of this utility model: in order to overcome the deficiencies in the prior art, the utility model provides the technical solution of the utility model: a kind of fin of aero radiator, comprise heat sink body, described heat sink body is a round sheet, the heat sink body ambient radiation is distributed with some heat radiation forks, and the heat radiation fork comprises the heat radiation fork handle, and an end of heat radiation fork handle is fixed on the heat radiator body, the other end is provided with the heat radiation jaw, and the heat radiation jaw is provided with some radiating ribs away from an end of heat radiation fork handle.
Further setting of the present utility model: described radiating ribs is positioned on the same circle away from the end points of an end of heat radiation fork handle.
Adopt above-mentioned further be provided with after, the fin of the utility model aero radiator is totally rounded, matches with the internal structure shape of aircraft, has made full use of the space of interior of aircraft, has improved efficiency of assembling.
Further setting of the present utility model: the heat radiation fork handle of described heat radiation fork is provided with 1～4 heat radiation jaw.
Further setting of the present utility model: the heat radiation fork handle of described heat radiation fork is provided with 2 heat radiation jaws.
Further setting of the present utility model: described heat radiation jaw is provided with 1～5 radiating ribs.
Further setting of the present utility model: described heat radiation jaw is provided with 2～3 radiating ribs.
The fin of aero radiator of the present utility model has increased the cooling surface area of every fin, thereby has improved the radiating efficiency of radiator by heat radiation fork distributary radiating ribs is set on heat sink body, and the utility model apparatus structure is simple, good looking appearance.
Description of drawings
Fig. 1 is the structural representation of the utility model embodiment.
The specific embodiment
As shown in Figure 1, specific embodiment of the utility model is a kind of fin of aero radiator, comprise heat sink body 1, heat sink body 1 is a round sheet, heat sink body 1 ambient radiation is distributed with heat radiation fork 2, heat radiation fork 2 comprises heat radiation fork handle 21 and heat radiation jaw 22, one end of heat radiation fork handle 21 is fixed on the heat radiator body 1, the other end of heat radiation fork handle 21 is provided with 2 heat radiation jaws 22, in order to reach better radiating effect, heat radiation jaw 22 is provided with radiating ribs 3 away from an end of heat radiation fork handle 21, can not cause the intensive of radiating ribs 3 when making full use of the space, heat radiation jaw 22 is provided with 2 or 3 radiating ribs 3 away from an end of heat radiation fork handle 21, and certainly, the quantity of radiating ribs 3 of the present utility model also can be adjusted according to concrete actual conditions.Radiating ribs 3 is positioned on the same circle away from the end points of an end of heat radiation fork handle 21, is equipped with the inner space of aircraft.
During the aircraft operation, radiator is also carrying out heat radiation work simultaneously, radiator is provided with the fin of some, because the heat sink body 1 of fin is provided with a large amount of heat radiation forks 2, the heat radiation jaw 22 of heat radiation fork 2 is provided with radiating ribs 3, increase the cooling surface area of fin, improved the radiating effect of aero radiator.
Claims (6)
1. the fin of an aero radiator, comprise heat sink body (1), it is characterized in that: described heat sink body (1) is round sheet, heat sink body (1) ambient radiation is distributed with some heat radiation forks (2), heat radiation fork (2) comprises heat radiation fork handle (21), one end of heat radiation fork handle (21) is fixed on the heat radiator body (1), and the other end is provided with heat radiation jaw (22), and heat radiation jaw (22) is provided with some radiating ribs (3) away from an end of heat radiation fork handle (21).
2. the fin of aero radiator according to claim 1 is characterized in that: described radiating ribs (3) is positioned on the same circle away from the end points of an end of heat radiation fork handle (22).
3. the fin of aero radiator according to claim 1 is characterized in that: the heat radiation fork handle (21) of described heat radiation fork (2) is provided with 1～4 heat radiation jaw (22).
4. the fin of aero radiator according to claim 3 is characterized in that: the heat radiation fork handle (21) of described heat radiation fork (2) is provided with 2 heat radiation jaws (22).
5. according to the fin of the described aero radiator of claim 1, it is characterized in that: described heat radiation jaw (22) is provided with 1～5 radiating ribs (3).
6. the fin of aero radiator according to claim 5, it is characterized in that: described heat radiation jaw (22) is provided with 2～3 radiating ribs (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120049574XU CN202057230U (en) | 2011-02-28 | 2011-02-28 | Heat dissipation plate for plane heat sink |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120049574XU CN202057230U (en) | 2011-02-28 | 2011-02-28 | Heat dissipation plate for plane heat sink |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202057230U true CN202057230U (en) | 2011-11-30 |
Family
ID=45017201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120049574XU Expired - Fee Related CN202057230U (en) | 2011-02-28 | 2011-02-28 | Heat dissipation plate for plane heat sink |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202057230U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107331072A (en) * | 2017-06-22 | 2017-11-07 | 成都智慧家信息技术有限公司 | The logistics counter of low temperature can be kept |
-
2011
- 2011-02-28 CN CN201120049574XU patent/CN202057230U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107331072A (en) * | 2017-06-22 | 2017-11-07 | 成都智慧家信息技术有限公司 | The logistics counter of low temperature can be kept |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111130 Termination date: 20140228 |