CN220545402U - Many rotor unmanned aerial vehicle flight control ware - Google Patents
Many rotor unmanned aerial vehicle flight control ware Download PDFInfo
- Publication number
- CN220545402U CN220545402U CN202322201520.6U CN202322201520U CN220545402U CN 220545402 U CN220545402 U CN 220545402U CN 202322201520 U CN202322201520 U CN 202322201520U CN 220545402 U CN220545402 U CN 220545402U
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- Prior art keywords
- fixedly connected
- aerial vehicle
- unmanned aerial
- rotor unmanned
- flight controller
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title description 2
- 230000007246 mechanism Effects 0.000 claims abstract description 25
- 238000001816 cooling Methods 0.000 claims abstract description 16
- 239000007788 liquid Substances 0.000 claims abstract description 12
- 230000001681 protective effect Effects 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 5
- 230000017525 heat dissipation Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 239000000110 cooling liquid Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Abstract
The utility model discloses a multi-rotor unmanned aerial vehicle flight controller which comprises a controller main body, a cooling mechanism and a protection mechanism, wherein the cooling mechanism comprises a heat conducting plate, the right side of the heat conducting plate is fixedly connected with a mounting block, the side surface of the mounting block is provided with a pushing block, a storage battery and a liquid pump are arranged in the heat conducting plate, two sides of the liquid pump are fixedly connected with a flow guide pipe, the right side of the heat conducting plate is fixedly connected with a motor, the right side of the motor is provided with a fan blade, the right side of the fan blade is provided with a protection cover, the protection mechanism comprises a connecting column, and the inside of the connecting column is slidably connected with a piston. Through the structure, the cooling mechanism is disassembled and assembled, the occupied volume is effectively reduced, the carrying of a user is facilitated, the impact force generated by the cooling mechanism is buffered and absorbed when the cooling mechanism is knocked down, the internal precise component is effectively protected, and the service life of the flight controller is prolonged.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle controllers, in particular to a multi-rotor unmanned aerial vehicle flight controller.
Background
Many rotor unmanned aerial vehicle is a special unmanned rotor craft with three and above rotor shaft, and unmanned aerial vehicle needs flight controller control, the flight controller on the market generally contains main control chip, micro-electromechanical system sensor, and the interface of being connected with outside other electronic equipment, in addition, unmanned aerial vehicle can change along with the change of operational environment or flight altitude, in order to guarantee the interior main control chip of flight controller and other important parts surrounding temperature, still be provided with heating resistor in flight controller, when the interior temperature of flight controller is too high, the poor heat dissipation can lead to equipment to damage.
In the prior art, through searching, the Chinese patent finds that 'a multi-rotor unmanned aerial vehicle flight controller' is disclosed, the application number of the multi-rotor unmanned aerial vehicle flight controller is 'CN20212243468. X', the patent mainly uses a gas rod connected between a machine body and a cover plate, the travel of the gas rod restrains the opening distance of the cover plate, and the gas rod is contracted to enable the machine body and the cover plate to be embedded to form a closed space, so that the dustproof and waterproof capabilities of the flight controller are enhanced, the service life of the flight controller is prolonged, a display screen is arranged inside the cover plate, the display screen can be protected by the cover plate, accidental breakage is prevented, the display screen is in communication connection with the unmanned aerial vehicle, and the visual field of the unmanned aerial vehicle can be delivered to the display screen; the heat inside the machine body is blown out from the heat dissipation holes through the work of the radiator, so that the heat dissipation effect of the machine body is enhanced, the occurrence of faults of the flight controller due to overhigh temperature inside the machine body is prevented, the sleeve ropes are connected to the two sides of the machine body, and the sleeve ropes can be sleeved into the neck part when the machine is used, so that the pressure on the two hands is relieved.
When the scheme is used, although the heat in the machine body is blown out from the heat dissipation holes through the work of the radiator, the heat dissipation effect of the machine body is enhanced, the internal temperature of the machine body is prevented from being too high, but the air conditioner body is provided with a certain weight, the radiator is fixedly arranged on the air conditioner body, the pressure of two hands is increased, the occupied volume of the air conditioner body is enlarged, the air conditioner body is inconvenient to carry, in the using process of the air conditioner body, the air conditioner body is inevitably collided with and falls down, and when collision occurs, damage is caused to internal precise components, so that the air conditioner body cannot be used.
Disclosure of Invention
The utility model aims to provide a multi-rotor unmanned aerial vehicle flight controller, which can disassemble and assemble a cooling mechanism, effectively reduce occupied volume, facilitate the carrying of a user, and buffer and absorb impact force generated by the cooling mechanism when the cooling mechanism collides and falls, effectively protect internal precise components and prolong the service life of the flight controller.
In order to achieve the above purpose, the multi-rotor unmanned aerial vehicle flight controller comprises a controller main body, a cooling mechanism and a protection mechanism;
the cooling mechanism comprises a heat conducting plate, wherein the right side of the heat conducting plate is fixedly connected with a mounting block, the side surface of the mounting block is provided with a pushing block, a storage battery and a liquid pump are arranged in the heat conducting plate, two sides of the liquid pump are fixedly connected with a flow guide pipe, the right side of the heat conducting plate is fixedly connected with a motor, the right side of the motor is provided with a fan blade, and the right side of the fan blade is provided with a protection cover;
the protection mechanism comprises a connecting column, a piston is slidably connected in the connecting column, a push rod is fixedly connected to the right side of the piston, and an anti-collision block is fixedly connected to the head of the push rod.
According to the multi-rotor unmanned aerial vehicle flight controller, the back of the controller main body is provided with the inserting groove.
According to the multi-rotor unmanned aerial vehicle flight controller, the upper surface of ejector pad rotates and is connected with the sliphead, the lower surface fixedly connected with first spring of ejector pad, first spring fixed connection is in the inside of installation piece.
According to the multi-rotor unmanned aerial vehicle flight controller, a rotating rod is arranged at the output end of the motor, and the rotating rod is fixedly connected with the fan blades.
According to the multi-rotor unmanned aerial vehicle flight controller, the protection cover is fixedly connected with the heat conducting plate, and the right side of the protection cover is fixedly connected with the air inlet pipe.
According to the multi-rotor unmanned aerial vehicle flight controller, the connecting column is fixedly connected to the right side of the controller main body.
According to the multi-rotor unmanned aerial vehicle flight controller, the second spring is fixedly connected with the inner bottom wall of the connecting column, and the second spring is fixedly connected with the piston.
According to the multi-rotor unmanned aerial vehicle flight controller, the mounting blocks and the inserting grooves are mutually matched.
The utility model has the following beneficial effects:
1. compared with the prior art, this many rotor unmanned aerial vehicle flight controller has realized dismantling the function of equipment with cooling mechanism through having set up spliced groove, installation piece, ejector pad, sliphead and first spring, has effectually reduced and has taken up the volume, the effect that the user of being convenient for carried.
2. Compared with the prior art, this many rotor unmanned aerial vehicle flight controller has realized taking place to collide with when dropping through having set up spliced pole, second spring, piston, push rod and crashproof piece, carries out the buffering absorbing function to the impact that its produced, has effectually protected inside accurate part for flight controller life's effect has been promoted.
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 described below with reference to the drawings and examples;
FIG. 1 is a schematic diagram of the overall structure of a multi-rotor unmanned aerial vehicle flight controller according to the present utility model;
fig. 2 is a schematic diagram of a main structure of a controller of the multi-rotor unmanned aerial vehicle flight controller according to the present utility model;
FIG. 3 is a schematic view of a mounting block structure of a multi-rotor unmanned aerial vehicle flight controller according to the present utility model;
FIG. 4 is a cross-sectional view of the interior of a thermally conductive plate of a multi-rotor unmanned aerial vehicle flight controller of the present utility model;
FIG. 5 is a schematic diagram illustrating the structural connection of blades of a flight controller of a multi-rotor unmanned aerial vehicle according to the present utility model;
FIG. 6 is a schematic diagram of a slider structure of a multi-rotor unmanned aerial vehicle flight controller according to the present utility model;
fig. 7 is a cross-sectional view of the interior of a connector post of a multi-rotor unmanned aerial vehicle flight controller according to the present utility model.
Legend description:
1. a controller main body; 2. a cooling mechanism; 3. a protection mechanism; 4. a plug-in groove;
201. a heat conductive plate; 202. a mounting block; 203. a pushing block; 204. a slider; 205. a spring; 206. a storage battery; 207. a liquid pump; 208. a flow guiding pipe; 209. a motor; 210. a rotating lever; 211. a fan blade; 212. a protective cover; 213. an air inlet pipe;
31. a connecting column; 32. a spring; 33. a piston; 34. a push rod; 35. an anti-collision block.
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. 1-7, the embodiment of the utility model provides a multi-rotor unmanned aerial vehicle flight controller, which comprises a controller main body 1, a cooling mechanism 2 and a protection mechanism 3, wherein a plugging groove 4 is formed in the back surface of the controller main body 1 and is used for plugging and fixing a mounting block 202.
The cooling mechanism 2 comprises a heat conducting plate 201, a mounting block 202 is fixedly connected to the right side of the heat conducting plate 201, the mounting block 202 and a plug-in groove 4 are mutually matched, a push block 203 is arranged on the side face of the mounting block 202, a sliding head 204 is rotatably connected to the upper surface of the push block 203, a first spring 205 is fixedly connected to the lower surface of the push block 203, the first spring 205 is enabled to shrink inwards under the rolling action of the sliding head 204, the push block 203 is driven to extrude outwards, the mounting block 202 is enabled to be fixed in the plug-in groove 4, the first spring 205 is fixedly connected to the inside of the mounting block 202, a storage battery 206 and a liquid pump 207 are arranged in the heat conducting plate 201, energy storage for the liquid pump 207 is used for storing, and cooling liquid in a liquid guide pipe 208 is driven to circulate, a guide pipe 208 is fixedly connected to the two sides of the liquid pump 207, a motor 209 is fixedly connected to the right side of the heat conducting plate 201, a fan blade 211 is used for controlling the rotation of the rotating rod 210, a fan blade 211 is arranged at the right side of the motor 209, the fan blade 210 is fixedly connected with the fan blade 211, a protection cover 212 is arranged at the right side of the fan blade 211, the protection cover is used for protecting the protection cover, and the fan blade 201 is fixedly connected to the fan blade 212 when the fan blade is used for protecting the fan blade and the fan blade is fixedly connected to the inside of the air inlet pipe 212.
The protection mechanism 3 includes spliced pole 31, spliced pole 31 fixed connection is in the right side of controller main part 1, spliced pole 31's interior bottom wall fixedly connected with second spring 32 for play the effect of resilience promotion, second spring 32 and piston 33 fixed connection, spliced pole 31's inside sliding connection has piston 33, be used for holding inside hydraulic oil and cushion the absorption to its impact force that produces, thereby piston 33's right side fixedly connected with push rod 34, thereby be used for transmitting the impact force drives the removal of piston 33, push rod 34's head fixedly connected with crashproof piece 35, be used for expanding area of contact and make protection controller main part 1.
Working principle: when the anti-collision device is used, the installation block 202 is aligned to the inserting groove 4, the first spring 205 is contracted inwards under the rolling of the sliding head 204, so that the push block 203 is driven to be extruded outwards, the installation block 202 is fixed in the inserting groove 4, heat generated by the controller main body 1 is transferred to the heat conducting plate 201, then the liquid pump 207 is started to circulate cooling liquid in the guide pipe 208 of the installation block, the heat of the heat conducting plate 201 is cooled through the cooling liquid, then the motor 209 is started to drive the rotating rod 210 to control the fan blade 211 to rotate, external air is blown onto the heat conducting plate 201 along with the suction of the air inlet pipe 213, the cooling liquid is kept continuously cooled, when the anti-collision device falls down, the anti-collision block 35 is firstly contacted to the ground, the push rod 34 is driven to move the piston 33 inwards to press internal hydraulic oil, the impact force brought by the piston 33 is buffered and absorbed, and then the second spring 32 rebounds to push the piston 33 to restore the original position.
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. The multi-rotor unmanned aerial vehicle flight controller is characterized by comprising a controller main body (1), a cooling mechanism (2) and a protection mechanism (3);
the cooling mechanism (2) comprises a heat conducting plate (201), wherein a mounting block (202) is fixedly connected to the right side of the heat conducting plate (201), a pushing block (203) is arranged on the side face of the mounting block (202), a storage battery (206) and a liquid pump (207) are arranged in the heat conducting plate (201), a flow guide pipe (208) is fixedly connected to the two sides of the liquid pump (207), a motor (209) is fixedly connected to the right side of the heat conducting plate (201), fan blades (211) are arranged on the right side of the motor (209), and a protection cover (212) is arranged on the right side of the fan blades (211);
the protection mechanism (3) comprises a connecting column (31), a piston (33) is slidably connected in the connecting column (31), a push rod (34) is fixedly connected to the right side of the piston (33), and an anti-collision block (35) is fixedly connected to the head of the push rod (34).
2. The multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the back of the controller main body (1) is provided with a plugging slot (4).
3. The multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the upper surface of the push block (203) is rotatably connected with a slider (204), the lower surface of the push block (203) is fixedly connected with a first spring (205), and the first spring (205) is fixedly connected with the inside of the mounting block (202).
4. The multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the output end of the motor (209) is provided with a rotating rod (210), and the rotating rod (210) is fixedly connected with the fan blades (211).
5. The multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the protective cover (212) is fixedly connected with the heat conducting plate (201), and an air inlet pipe (213) is fixedly connected to the right side of the protective cover (212).
6. A multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the connection post (31) is fixedly connected to the right side of the controller body (1).
7. The multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the inner bottom wall of the connecting column (31) is fixedly connected with a second spring (32), and the second spring (32) is fixedly connected with a piston (33).
8. A multi-rotor unmanned aerial vehicle flight controller according to claim 1, wherein the mounting block (202) and the socket (4) are mutually adapted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322201520.6U CN220545402U (en) | 2023-08-16 | 2023-08-16 | Many rotor unmanned aerial vehicle flight control ware |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322201520.6U CN220545402U (en) | 2023-08-16 | 2023-08-16 | Many rotor unmanned aerial vehicle flight control ware |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220545402U true CN220545402U (en) | 2024-02-27 |
Family
ID=89972865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322201520.6U Active CN220545402U (en) | 2023-08-16 | 2023-08-16 | Many rotor unmanned aerial vehicle flight control ware |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220545402U (en) |
-
2023
- 2023-08-16 CN CN202322201520.6U patent/CN220545402U/en active Active
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| GR01 | Patent grant |