CN220402218U - Heat radiation structure of flight controller - Google Patents
Heat radiation structure of flight controller Download PDFInfo
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- CN220402218U CN220402218U CN202321860123.3U CN202321860123U CN220402218U CN 220402218 U CN220402218 U CN 220402218U CN 202321860123 U CN202321860123 U CN 202321860123U CN 220402218 U CN220402218 U CN 220402218U
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- heat
- fixedly connected
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- flight controller
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- 230000005855 radiation Effects 0.000 title abstract description 13
- 238000009423 ventilation Methods 0.000 claims abstract description 30
- 230000017525 heat dissipation Effects 0.000 claims description 22
- 239000000428 dust Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 238000000926 separation method Methods 0.000 claims description 3
- 238000010521 absorption reaction Methods 0.000 claims description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
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- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The utility model discloses a heat radiation structure of a flight controller, which comprises: the solar energy collection device comprises a main body, wherein a cover plate is fixedly connected to the middle position of the upper side of the main body, a first ventilation opening is formed in the left side of the cover plate, a solar panel is fixedly connected to the upper side of the main body, an opening is formed in the rear side of the main body, a baffle plate is fixedly connected to the inside of the opening, second ventilation openings are formed in two sides of the main body, the opening faces the rear side, a mounting plate is arranged at the bottom in the main body, a shell is fixedly connected to the upper side of the mounting plate, a second heat-conducting plate is fixedly connected to the inner side of the shell, a heat-absorbing layer is fixedly connected to the inner side bottom of the heat-absorbing layer, a flight controller is fixedly connected to the upper side of the first heat-conducting plate, a heat-dissipating plate is arranged on the left side of the shell, and one end, close to the shell, of the heat-dissipating plate penetrates through the second heat-conducting plate and is fixedly connected to the shell. Through the structure, the first heat conducting plate, the heat absorbing layer, the second heat conducting plate and the heat radiating plate are arranged on the outer side of the controller, so that heat is conducted and radiated in sequence, and the effect is better.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a heat dissipation structure of a flight controller.
Background
The controller refers to a master device that changes the wiring of a main circuit or a control circuit and changes the resistance value in the circuit in a predetermined order to control the starting, speed regulation, braking and reversing of the motor. The computer system consists of program counter, instruction register, instruction decoder, time sequence generator and operation controller, and is a "decision mechanism" for issuing command, i.e. for completing the operation of coordinating and commanding the whole computer system.
A large number of controllers can be used on the unmanned aerial vehicle, and when the controllers work, the controllers can continuously generate heat due to large operation data quantity, and the controllers work in a high-temperature environment for a long time, so that electronic equipment in the controllers can be damaged, and the use of the controllers is affected. Therefore, a heat dissipation structure of a flight controller is provided.
Disclosure of Invention
Aiming at the defects of the prior art, the utility model provides a heat dissipation structure of a flight controller, which solves the problem of poor heat dissipation effect.
The utility model also provides a heat radiation structure with the flight controller, which comprises: the solar energy heat collector comprises a main body, wherein a cover plate is fixedly connected to the middle position of the upper side of the main body, a first ventilation opening is formed in the left side of the cover plate, a solar panel is fixedly connected to the upper side of the main body, an opening is formed in the rear side of the main body, a baffle is fixedly connected to the inside of the opening, second ventilation openings are formed in the two sides of the main body, the opening of the second ventilation openings faces towards the rear side of the main body, a mounting plate is arranged in the bottom of the main body, a shell is fixedly connected to the upper side of the mounting plate, a second heat conducting plate is fixedly connected to the inner side of the shell, a heat absorbing layer is fixedly connected to the inner side bottom of the heat absorbing layer, a flight controller is fixedly connected to the upper side of the first heat conducting plate, a heat dissipating plate is arranged on the left side of the shell, and one end of the heat dissipating plate, which is close to the shell, penetrates through the second heat conducting plate and is fixedly connected to the shell.
According to the heat radiation structure of the flight controller, the heat-absorbing layer is fixedly connected with a heat-conducting pipe, and heat-conducting liquid is arranged in the heat-conducting pipe.
According to the heat radiation structure of the flight controller, the whole cover plate is of an L-shaped structure, and the corner is arc-shaped.
According to the heat radiation structure of the flight controller, a through hole is formed in the mounting plate, a nut is connected to the through hole in a sliding mode, and the mounting plate and the main body are fixed through the through hole by the nut.
According to the heat radiation structure of the flight controller, the first ventilation opening is positioned right in front of the heat radiation plate, and the second ventilation opening is positioned at two sides of the heat radiation plate.
According to the heat radiation structure of the flight controller, the first ventilation opening, the second ventilation opening and the opening are fixedly connected with dustproof nets.
According to the heat radiation structure of the flight controller, the connectors are arranged below two sides of the main body.
According to the heat radiation structure of the flight controller, a display screen is arranged between the cover plate and the solar panel on the upper side of the main body.
The utility model has the following beneficial effects:
1. according to the utility model, the first heat-conducting plate, the heat-absorbing layer, the second heat-conducting plate and the heat-dissipating plate are arranged on the outer side of the controller, so that generated heat is sequentially conducted to the heat-dissipating plate to dissipate heat when the controller works.
2. In the utility model, the first ventilation opening and the second ventilation opening are arranged outside the main body, so that the wind dissipates heat of the heat dissipation plate, and the controller inside the shell is cooled and dissipated for protection.
3. According to the utility model, the dustproof net is arranged in the first ventilation opening, the second ventilation opening and the opening, so that the heat dissipation effect is prevented from being reduced due to the fact that dust enters the first ventilation opening, the second ventilation opening and the opening.
Additional aspects and advantages of the utility model will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the utility model.
Drawings
The utility model is further illustrated by the following figures and examples;
FIG. 1 is a front block diagram of a heat dissipating structure of a flight controller according to the present utility model;
FIG. 2 is a rear block diagram of a heat dissipating structure of a flight controller according to the present utility model;
FIG. 3 is a cut-away view of a heat dissipating structure of a flight controller according to the present utility model;
fig. 4 is a controller structure diagram of a heat dissipation structure of a flight controller according to the present utility model.
Legend description:
1. a main body; 2. a cover plate; 3. a solar panel; 4. a first vent; 5. a connection port; 6. a second vent; 7. an opening; 8. a baffle; 9. a storage battery; 10. a mounting plate; 11. a housing; 12. a second heat-conducting plate; 13. a heat absorbing layer; 14. a heat dissipation plate; 15. a controller; 16. a nut; 17. a display screen; 18. a heat conduction pipe; 19. a first heat-conducting plate; 20. and a through hole.
Detailed Description
Reference will now be made in detail to the present embodiments of the present utility model, examples of which are illustrated in the accompanying drawings, wherein the accompanying drawings are used to supplement the description of the written description so that one can intuitively and intuitively understand each technical feature and overall technical scheme of the present utility model, but not to limit the scope of the present utility model.
Referring to fig. 1-4, the heat dissipation structure of a flight controller according to the embodiment of the utility model comprises a main body 1, connectors 5 are arranged below two sides of the main body 1, a cover plate 2 is fixedly connected to the middle position of the upper side of the main body 1, the whole cover plate 2 is of an L-shaped structure, the corners are arc-shaped, the resistance of wind is reduced, a first ventilation opening 4 is arranged on the left side of the cover plate 2, the first ventilation opening 4 is an air inlet,
the solar panel 3 of main part 1 upside fixedly connected with, and the rear side is equipped with opening 7, solar panel 3 makes unmanned aerial vehicle duration when flight stronger, opening 7 is the air outlet, main part 1 upside is located and is equipped with display screen 17 between apron 2 and the solar panel 3, display screen 17 can show electric quantity and time, fixedly connected with separation blade 8 in the opening 7, separation blade 8 is slope downward design, make it have ascending thrust to main part 1 when airing exhaust, it is more energy-conserving, main part 1 both sides are equipped with second ventilation opening 6, second ventilation opening 6 is the air intake, second ventilation opening 6 opening orientation rear side, equal fixedly connected with dust screen in first ventilation opening 4, second ventilation opening 6 and the opening 7 prevents that the dust from getting into and leading to the radiating effect to reduce.
The inside bottom of the main body 1 is provided with a mounting plate 10 and a storage battery 9, the storage battery 9 is fixedly connected with the inside bottom of the main body 1 and is positioned at the front side of the mounting plate 10, a through hole 20 is formed in the mounting plate 10, a nut 16 is connected to the through hole 20 in a sliding manner, the mounting plate 10 and the main body 1 are fixedly connected to the upper side of the mounting plate 10 through the through hole 20, a shell 11 is fixedly connected to the inner side of the shell 11, a second heat conducting plate 12 is fixedly connected to the inner side of the second heat conducting plate 12, a heat absorbing layer 13 is fixedly connected to the inner side of the heat absorbing layer 13, a heat conducting pipe 18 is fixedly connected to the inner side of the heat absorbing layer 13, a heat conducting liquid is arranged in the heat conducting pipe 18, a first heat conducting plate 19 is fixedly connected to the inner bottom of the heat absorbing layer 13, a flight controller 15 is fixedly connected to the upper side of the first heat conducting plate 19, a heat dissipating plate 14 is arranged on the left side of the shell 11, a first vent 4 is positioned right in front of the heat dissipating plate 14, one end of the heat dissipating plate 14, which is close to the shell 11 is fixedly connected to the second heat conducting plate 12 is penetrated through the shell 11, the second vent 6 is positioned at two sides of the heat dissipating plate 14, and the first vent 4 and the heat dissipating plate 14 dissipates heat under the effect of the first vent 4 and the second vent 6, so that the heat dissipating heat is dissipated by the effect of the heat is protected by the controller 15 inside the shell 11.
Working principle: when the heating element on the controller 15 works for a long time to generate heat, the heat is transferred to the heat conduction pipe 18 in the heat absorption layer 13 through the first heat conduction plate 19, the heat conduction pipe 18 transfers the heat to the second heat conduction plate 12, the second heat conduction plate 12 transfers the heat to the heat dissipation plate 14, and the air dissipates the heat dissipation plate 14 under the action of the first ventilation opening 4 and the second ventilation opening 6, so that the controller 15 in the shell 11 is cooled and heat dissipation protected, the air entering the main body 1 from the first ventilation opening 4 and the second ventilation opening 6 is finally discharged through the opening 7, and the baffle plate 8 in the opening 7 is designed obliquely downwards, so that the baffle plate 8 has upward thrust on the main body 1 during air exhaust, and the energy is saved.
The embodiments of the present utility model have been described in detail with reference to the accompanying drawings, but the present utility model is not limited to the above embodiments, and various changes can be made within the knowledge of one of ordinary skill in the art without departing from the spirit of the present utility model.
Claims (8)
1. A heat dissipation structure for a flight controller, comprising: main part (1), main part (1) upside intermediate position fixedly connected with apron (2), apron (2) left side is equipped with first vent (4), main part (1) upside fixedly connected with solar panel (3), and the rear side is equipped with opening (7), fixedly connected with separation blade (8) in opening (7), main part (1) both sides are equipped with second vent (6), second vent (6) opening orientation rear side, be equipped with mounting panel (10) in main part (1), mounting panel (10) upside fixedly connected with casing (11), the inboard fixedly connected with second heat-conducting plate (12) of casing (11), second heat-conducting plate (12) inboard fixedly connected with heat-absorbing layer (13), heat-absorbing layer (13) inboard bottom fixedly connected with first heat-conducting plate (19), first heat-conducting plate (19) upside fixedly connected with flight control ware (15), casing (11) left side is equipped with heating panel (14), heating panel (14) are close to casing (11) one end fixedly connected with casing (11) second heat-conducting plate (12) of heat-conducting plate (11).
2. The heat dissipation structure of a flight controller according to claim 1, wherein a heat conduction pipe (18) is fixedly connected in the heat absorption layer (13), and a heat conduction liquid is arranged in the heat conduction pipe (18).
3. A heat dissipation structure for a flight controller according to claim 2, wherein the cover plate (2) is integrally formed in an L-shaped structure, and the corners are arc-shaped.
4. A heat dissipation structure for a flight controller according to claim 3, wherein a through hole (20) is provided in the mounting plate (10), a nut (16) is slidably connected to the through hole (20), and the nut (16) fixes the mounting plate (10) to the main body (1) through the through hole (20).
5. The heat dissipation structure of a flight controller according to claim 4, wherein the first ventilation opening (4) is located right in front of the heat dissipation plate (14), and the second ventilation openings (6) are located at two sides of the heat dissipation plate (14).
6. The heat dissipation structure of a flight controller according to claim 5, wherein dust screens are fixedly connected in the first ventilation opening (4), the second ventilation opening (6) and the opening (7).
7. The heat dissipation structure of a flight controller according to claim 6, wherein connectors (5) are provided below both sides of the main body (1).
8. A heat dissipation structure for a flight controller according to claim 7, characterized in that the upper side of the main body (1) is provided with a display screen (17) between the cover plate (2) and the solar panel (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321860123.3U CN220402218U (en) | 2023-07-16 | 2023-07-16 | Heat radiation structure of flight controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321860123.3U CN220402218U (en) | 2023-07-16 | 2023-07-16 | Heat radiation structure of flight controller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220402218U true CN220402218U (en) | 2024-01-26 |
Family
ID=89598789
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321860123.3U Active CN220402218U (en) | 2023-07-16 | 2023-07-16 | Heat radiation structure of flight controller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220402218U (en) |
-
2023
- 2023-07-16 CN CN202321860123.3U patent/CN220402218U/en active Active
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