GPS quick release structure and unmanned aerial vehicle applying same

Abstract

The utility model discloses a GPS quick release structure and an unmanned aerial vehicle applying the same, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a vehicle body, a GPS module and a GPS quick release structure, the GPS quick release structure comprises a mounting arm, a mounting position is arranged on the mounting arm, and the GPS module is detachably arranged on the mounting position. According to the unmanned aerial vehicle, when the unmanned aerial vehicle is impacted or damaged, a maintainer can quickly maintain and replace the GPS module, and the maintenance efficiency of the unmanned aerial vehicle is effectively improved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a GPS quick-release structure and a UAV using the same. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and their own program control devices. Currently, UAVs are typically equipped with GPS modules, which enable functions such as positioning, navigation, flight control, and safety assurance.

[0003] In existing drones, the GPS module and the fuselage are usually an integral, non-removable structure. When the drone is impacted or damaged during flight, maintenance personnel cannot quickly repair or replace the GPS module, which greatly reduces the maintenance efficiency of the drone. Utility Model Content

[0004] The first objective of this application is to provide a GPS quick-release structure that enables the rapid assembly and disassembly of a GPS module.

[0005] The GPS quick-release structure provided in this application adopts the following technical solution:

[0006] A GPS quick-release structure for quickly assembling and disassembling a GPS module includes a mounting arm with a mounting position on the mounting arm, on which the GPS module is detachably mounted.

[0007] By adopting the above technical solutions, when a drone is impacted or damaged, maintenance personnel can quickly repair and replace the GPS module, effectively improving the maintenance efficiency of the drone.

[0008] In one specific implementation, the mounting arm has a mounting slot for accommodating the GPS module, the mounting slot is located at the mounting position, and at least one side of the mounting slot is provided with a deformable limiting part, the limiting part abutting against the GPS module.

[0009] By adopting the above technical solution, when the GPS module is placed in the mounting slot, the limiting part can hold the GPS module in place to improve the installation strength of the GPS module; and when maintenance personnel disassemble or assemble the GPS module, the limiting part can make way for the GPS module under its own deformation to complete the quick disassembly or assembly of the GPS module.

[0010] In one specific implementation, the limiting part has a limiting groove on the side facing the GPS module. The limiting groove has a first groove wall and a second groove wall, and the first groove wall and the second groove wall respectively abut against the adjacent two sides of the GPS module.

[0011] By adopting the above technical solution, the first and second trench walls can respectively limit the adjacent two sides of the GPS module, effectively improving the installation strength of the GPS module.

[0012] In one specific implementation, at least one end of the mounting slot has an operating port, and at least one end of the GPS module is exposed in the operating port.

[0013] By adopting the above technical solution, maintenance personnel can push the GPS module outward through the operating port, which reduces the difficulty of disassembling the GPS module and improves the disassembly efficiency.

[0014] The second objective of this application is to provide a drone.

[0015] The UAV provided in this application adopts the following technical solution:

[0016] A drone includes a body and a GPS module, the drone also including a GPS quick-release structure as described above disposed on the body.

[0017] By adopting the above technical solutions, when a drone is impacted or damaged, maintenance personnel can quickly repair and replace the GPS module, effectively improving the maintenance efficiency of the drone.

[0018] In one specific implementation, the mounting arm has a first end and a second end, the first end being rotatably connected to the machine body, the second end being detachably connected to the machine body, and the mounting position being arranged at the second end.

[0019] By adopting the above technical solution, maintenance personnel can lift the second end upwards and disassemble and install the GPS module on it, so as to avoid interference from the main body to the disassembly and installation of the GPS module, and effectively improve the efficiency of GPS module disassembly and installation.

[0020] In one specific implementation scheme, the main body includes a housing, a camera module disposed at one end of the housing, and an installation chamber opened inside the housing. An image transmission module and a control module are respectively disposed at both ends of the installation chamber, and the image transmission module is disposed close to the camera module.

[0021] By adopting the above technical solution, on the one hand, setting the image transmission module and the control module at opposite ends of the installation chamber can avoid interference between the image transmission module and the control module during installation; on the other hand, placing the image transmission module close to the camera module can effectively shorten the connection thread between the image transmission module and the camera module.

[0022] In one specific implementation, at least one side of the housing is provided with a heat dissipation duct communicating with the installation chamber, and one end of the heat dissipation duct has an air inlet.

[0023] By adopting the above technical solution, the heat dissipation duct can guide the airflow encountered by the UAV during flight into the installation chamber, which can not only reduce the wind resistance encountered by the UAV during flight, but also dissipate heat from the image transmission module and control module by introducing the airflow into the installation chamber.

[0024] In one specific implementation, wings are respectively provided on opposite sides of the main body. Each wing has a third end that is rotatably connected to the main body. Two limiting blocks are also provided on the main body. The two limiting blocks correspond one-to-one with the two third ends, and each limiting block is located on the rotation path of the corresponding third end.

[0025] By adopting the above technical solution, the limiting block can limit the wing when it is deployed, so as to prevent the wing from being over-deployed and causing damage.

[0026] In one specific implementation scheme, the main body has two first pin holes, each containing a pin. The two first pin holes correspond one-to-one with the two wings. A second pin hole is provided at the third end. The wings also have slots extending along their length. The wings have an deployed state and a retracted state during their rotation. When the wings are in the deployed state, the two pins are aligned with the two second pin holes. When the wings are in the retracted state, the two pins are inserted into the two slots.

[0027] By adopting the above technical solution, when the wing is in the deployed state, the pin and the second pin hole can cooperate with each other to fix the wing in the deployed state, preventing the wing from being accidentally retracted and affecting its flight process; when the wing is in the retracted state, the pin and the slot can cooperate with each other to limit the wing, preventing the wing from being accidentally deployed and causing damage.

[0028] In summary, this application includes at least one of the following beneficial technical effects:

[0029] When a drone is impacted or damaged, maintenance personnel can quickly repair or replace the GPS module, effectively improving the maintenance efficiency of the drone. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the GPS quick-release structure in Embodiment 1 of this application.

[0031] Figure 2 yes Figure 1A schematic diagram of the longitudinal section.

[0032] Figure 3 This is a top view of the drone in Embodiment 2 of this application with its wings in the deployed state.

[0033] Figure 4 yes Figure 3 A schematic diagram of the longitudinal section.

[0034] Figure 5 This is a bottom view of the drone in Embodiment 2 of this application with its wings in the deployed state.

[0035] Figure 6 This is a bottom view of the drone in Embodiment 2 of this application with its wings folded.

[0036] Explanation of reference numerals in the attached figures:

[0037] 1. Mounting arm; 1a. First end; 1b. Second end; 2. Mounting groove; 3. Limiting part; 4. Limiting groove; 4a. First groove wall; 4b. Second groove wall; 5. Operating port; 6. Main body; 6a. Housing; 6b. Camera module; 6c. Mounting chamber; 6d. Image transmission module; 6e. Control module; 7. GPS module; 8. Cooling duct; 8a. First air duct; 8b. Second air duct; 9. Air inlet; 9a. First air outlet; 9b. Second air outlet; 10. Wing; 10a. Third end; 11. Limiting block; 12. First pin hole; 13. Second pin hole; 14. Empty groove; 14a. Limiting end; 15. First connecting plate; 16. Cooling fin; 17. Air outlet; 18. Second connecting plate. Detailed Implementation

[0038] The present application will be further described in detail below with reference to the accompanying drawings.

[0039] Example 1: See Figure 1-2 As shown, this embodiment discloses a GPS quick-release structure for rapid assembly and disassembly of the GPS module 7. This GPS quick-release structure is mounted on a drone and includes a mounting arm 1 with a mounting position on the arm 1. The GPS module 7 is detachably mounted on the mounting position. When the drone is subjected to impact or damage, maintenance personnel can quickly repair or replace the GPS module 7 on the mounting position, effectively improving the maintenance efficiency of the drone.

[0040] In this embodiment, the mounting arm 1 has a mounting groove 2 for accommodating the GPS module 7. The mounting groove 2 is located at the mounting position, and deformable limiting parts 3 are respectively provided on both sides of the mounting groove 2. The arrangement direction of the two limiting parts 3 is the same as the length direction of the mounting arm 1, and the two limiting parts 3 respectively abut against the opposite sides of the GPS module 7. The limiting parts 3 are made of a deformable material, which is a prior art material and can be plastic. The specific material is not limited here.

[0041] When the GPS module 7 is housed in the mounting slot 2, the two limiting parts 3 can abut against the GPS module 7 to improve the installation strength of the GPS module 7; while when maintenance personnel disassemble or assemble the GPS module 7, the limiting parts 3 can make way for the GPS module 7 under their own deformation to complete the quick disassembly or assembly of the GPS module 7.

[0042] In this embodiment, combined with Figure 2 As shown, the two limiting parts 3 are symmetrically arranged in an inverted L shape. The two limiting parts 3 are respectively provided with an inverted L-shaped limiting groove 4 on their opposite sides. Each limiting groove 4 has a horizontally arranged first groove wall 4a and a vertically arranged second groove wall 4b. The two first groove walls 4a abut against the upper parts of both ends of the GPS module 7, and the two second groove walls 4b abut against the two ends of the GPS module 7.

[0043] In this embodiment, combined again Figure 1-2 As shown, an operation port 5 is provided at the lower part of one end of the mounting slot 2. The operation port 5 is located below one of the limiting parts 3, and one end of the GPS module 7 is exposed in the operation port 5. When disassembling the GPS module 7, the maintenance personnel can push the GPS module 7 through the operation port 5 to push one end of the GPS module 7 away from the limiting part 3, and then remove the end and take out the GPS module 7. This effectively reduces the difficulty of disassembling the GPS module 7 and improves the disassembly efficiency of the GPS module 7.

[0044] Example 2: See Figure 3-6 As shown, this embodiment discloses a drone, including a body 6 and a GPS module 7. The body 6 is provided with the GPS quick-release structure in embodiment 1.

[0045] In this embodiment, combined with Figure 3As shown, the mounting arm 1 of the GPS quick-release structure has a first end 1a and a second end 1b. The first end 1a is rotatably connected to the main body 6 via a pivot. The axes of rotation of both extend horizontally and are perpendicular to the length direction of the main body 6. The second end 1b is detachably connected to the main body 6, and the mounting position is arranged at the second end 1b. When disassembling or assembling the GPS module 7, maintenance personnel can lift the second end 1b upwards and disassemble or assemble the GPS module 7 thereon, thus avoiding interference from the main body 6 and effectively improving the efficiency of disassembling or assembling the GPS module 7.

[0046] Furthermore, the second end 1b is close to the front end of the machine body 6, and a first connecting plate 15 is provided thereon. The first connecting plate 15 is detachably connected to the machine body 6 by bolts.

[0047] In this embodiment, combined with Figure 4 As shown, the main body 6 includes a casing 6a, a camera module 6b located at the front end of the casing 6a, and a mounting chamber 6c opened within the casing 6a. An image transmission module 6d is located at the front end of the mounting chamber 6c, and a control module 6e is located at the rear end. The image transmission module 6d is positioned close to the camera module 6b. The camera module 6b is a camera, and the image transmission module 6d is an image transmission module used for electrical connection to the camera module 6b via wires. The control module 6e includes a flight control module and an electronic speed controller (ESC) module; these modules are existing technologies, and their specific principles are not detailed here. Positioning the image transmission module 6d at the front end of the mounting chamber 6c prevents it from encroaching on the mounting space of the control module 6e and prevents interference between the image transmission module 6d and the control module 6e during installation. Simultaneously, the proximity of the image transmission module 6d to the camera module 6b effectively shortens the wire length, facilitating module arrangement within the mounting chamber 6c and saving costs.

[0048] Furthermore, the image transmission module 6d is erected in the mounting chamber 6c. This arrangement increases the overall height of the main body 6, thereby increasing the installation space for electronic components within the mounting chamber 6c, expanding the range of electronic component options, and making the overall appearance of the machine more harmonious.

[0049] In this embodiment, combined with Figure 3-4 As shown, a heat dissipation duct 8 communicating with the mounting chamber 6c is also provided on the periphery of the housing 6a, and one end of the heat dissipation duct 8 has an air inlet 9. The heat dissipation duct 8 can guide the airflow encountered by the UAV during flight into the mounting chamber 6c, which can not only reduce the wind resistance encountered by the UAV during flight, but also the airflow introduced into the mounting chamber 6c can dissipate heat from the image transmission module 6d and the control module 6e.

[0050] Specifically, the heat dissipation duct 8 includes a first duct 8a located on the upper side of the housing 6a and two second ducts 8b located on the horizontal sides of the housing 6a. The air inlet 9 includes a first air outlet 9a located at the front end of the first duct 8a and a second air outlet 9b located at the front end of the second ducts 8b. The rear end of the first duct 8a is connected to the front end of the mounting chamber 6c, which can dissipate heat from the image transmission module 6d. The outer shell of the image transmission module 6d is also provided with heat dissipation fins 16, which can facilitate the dissipation of heat from inside the image transmission module 6d. The rear end of the second duct 8b has an air outlet 17. The side of the second duct 8b is connected to the mounting chamber 6c. As the airflow flows from the second air outlet 9b to the air outlet 17, it can dissipate heat from the image transmission module 6d and the control module 6e inside the mounting chamber 6c.

[0051] In this embodiment, combined with Figure 5-6 As shown, wings 10 are respectively provided on both sides of the body 6 in the horizontal direction. The wings 10 have a third end 10a that is rotatably connected to the bottom of the body 6. Limiting blocks 11 are also provided on the bottom of both sides of the body 6 in the horizontal direction. The limiting blocks 11 are made of ABS plastic and are fixed to the body 6 by hot melt screws.

[0052] Two limiting blocks 11 correspond one-to-one with two third ends 10a, with each limiting block 11 located on the rotation path of the corresponding third end 10a. When the wing 10 is deployed, the limiting block 11 can abut against one side of the third end 10a when it rotates to the corresponding position, thereby limiting the deployment angle of the wing 10 and preventing the wing 10 from being over-deployed and causing damage. The specific position of the limiting block 11 can be flexibly set as needed. The side of the limiting block 11 is also provided with an arc surface that matches the outer contour of the third end 10a to facilitate the folding of the wing 10.

[0053] In this embodiment, the two sides of the main body 6 in the horizontal direction are respectively provided with second connecting plates 18 for mounting wings 10, and the wings 10 are rotatably connected to the second connecting plates 18. Each second connecting plate 18 is provided with a first pin hole 12, and a pin (not shown in the figure) is inserted into the first pin hole 12. The two first pin holes 12 correspond one-to-one with the two wings 10. A second pin hole 13 is provided at the third end 10a. A slot 14 extending along its length is also provided on the wing 10. The slot 14 has a limiting end 14a located at the third end 10a. The limiting end 14a and the second pin hole 13 are arranged along the rotation direction of the third end 10a.

[0054] The wing 10 has an extended state and a retracted state during its rotational stroke. For example... Figure 5As shown, when the wing 10 is in the deployed state, the two pins are respectively aligned with the two second pin holes 13. The pins are inserted into the second pin holes 13 and fix the wing 10 in the deployed state, preventing the wing 10 from accidentally retracting and affecting its flight process; as Figure 6 As shown, when the wing 10 is in the retracted state, the pin is inserted into the limiting end 14a and limits the wing 10 to prevent the wing 10 from being accidentally deployed and causing damage.

[0055] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A GPS quick-release structure for quickly assembling and disassembling a GPS module (7), characterized in that: Includes a mounting arm (1), on which a mounting position is arranged, and a GPS module (7) is detachably mounted on the mounting position; The mounting arm (1) is provided with a mounting slot (2) for accommodating the GPS module (7). The mounting slot (2) is located at the mounting position. At least one side of the mounting slot (2) is provided with a deformable limiting part (3). The limiting part (3) abuts against the GPS module (7). The limiting part (3) has a limiting groove (4) on the side facing the GPS module (7). The limiting groove (4) has a first groove wall (4a) and a second groove wall (4b). The first groove wall (4a) and the second groove wall (4b) respectively abut against the adjacent two sides of the GPS module (7).

2. The GPS quick-release structure according to claim 1, characterized in that: At least one end of the mounting slot (2) is provided with an operation port (5), and at least one end of the GPS module (7) is exposed in the operation port (5).

3. A drone, comprising a fuselage (6) and a GPS module (7), characterized in that: The drone also includes a GPS quick-release structure as described in any one of claims 1-2, which is provided on the main body (6).

4. The unmanned aerial vehicle (UAV) according to claim 3, characterized in that: The mounting arm (1) has a first end (1a) and a second end (1b), the first end (1a) being rotatably connected to the machine body (6), the second end (1b) being detachably connected to the machine body (6), and the mounting position being arranged at the second end (1b).

5. The unmanned aerial vehicle (UAV) according to claim 3, characterized in that: The main body (6) includes a housing (6a), a camera module (6b) located at one end of the housing (6a), and an installation chamber (6c) opened inside the housing (6a). A video transmission module (6d) and a control module (6e) are respectively provided at both ends of the installation chamber (6c). The video transmission module (6d) is located close to the camera module (6b).

6. The unmanned aerial vehicle according to claim 5, characterized in that: The housing (6a) has a heat dissipation duct (8) communicating with the installation chamber (6c) on at least one side, and one end of the heat dissipation duct (8) has an air inlet (9).

7. The unmanned aerial vehicle (UAV) according to claim 3, characterized in that: The main body (6) is provided with wings (10) on opposite sides. The wings (10) have a third end (10a) that is rotatably connected to the main body (6). The main body (6) is also provided with two limiting blocks (11). The two limiting blocks (11) correspond one-to-one with the two third ends (10a). Each limiting block (11) is located on the rotation path of the corresponding third end (10a).

8. The unmanned aerial vehicle according to claim 7, characterized in that: The main body (6) has two first pin holes (12), and each first pin hole (12) is inserted with a pin. The two first pin holes (12) correspond one-to-one with the two wings (10). The third end (10a) has a second pin hole (13). The wing (10) also has a slot (14) extending along its length. The wing (10) has an extended state and a retracted state during its rotation stroke. When the wing (10) is in the extended state, the two pins are aligned with the two second pin holes (13). When the wing (10) is in the retracted state, the two pins are inserted into the two slots (14).

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