Unmanned aerial vehicle arm winding and unwinding structure

Abstract

The utility model relates to unmanned plane technical field, and disclose a kind of unmanned plane arm retraction structure, including unmanned plane bearing frame, and four groups of support foot pole for supporting unmanned plane standing by being in contact with ground are installed in unmanned plane bearing frame inside, and the outside of unmanned plane bearing frame is equidistantly installed with four groups of elastic retraction limiting mechanism along circumference;Elastic retraction limiting mechanism includes multiple groups of shaft seat rotationally installed in the outside of unmanned plane bearing frame, and the inside of shaft seat is provided with jack. Operating personnel press shaft stem to release limiting and realize carbon fiber machine arm storage, after release, spring pushes limiting pin into shaft seat to complete locking, without manually tightening bolt or operating complex buckle, simplify retraction process, three groups of radially distributed limiting pin enhance locking stability, avoid retraction mechanism limiting failure to cause carbon fiber machine arm to shake when unmanned plane flies.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a UAV arm retraction and extension structure. Background Technology

[0002] As intelligent devices with autonomous flight capabilities, drones have been widely used in various fields such as engineering surveying, aerial reconnaissance, logistics transportation, and agricultural plant protection. As the core load-bearing and transmission unit that carries the power components, the ease of extension and retraction and the stability of locking the drone directly affect the deployment efficiency and flight safety of the drone.

[0003] In existing drone designs, the arm retraction and extension structures mostly achieve limiting and retraction operations through bolt fastening, snap-fit ​​engagement, or simple hinge cooperation. To ensure the structural stability of the arm after deployment, some designs require manual tightening of the limiting bolts with auxiliary tools such as wrenches and screwdrivers, which is a rather cumbersome process. Especially in emergency outdoor deployments or when the arm status needs to be quickly adjusted, the time-consuming operation reduces the drone's response efficiency. How to achieve convenient retraction and reliable locking of drone arms has become one of the important directions for optimizing drone performance. Therefore, it is urgent to develop a drone arm retraction and extension structure to solve these practical problems. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a drone arm retraction and extension structure, solving the technical problems of existing drone arm retraction and extension requiring tools, being cumbersome and inefficient.

[0005] To achieve the above objectives, this utility model provides a drone arm retraction and extension structure through the following technical solution: a drone support frame, wherein four sets of support legs for contacting the ground to support the drone standing are installed through the drone support frame, and four sets of elastic retraction and extension limiting mechanisms are installed at equal intervals along the circumference on the outer side of the drone support frame.

[0006] The elastic retraction and limiting mechanism includes multiple sets of bearing seats rotatably mounted on the outside of the UAV carrier frame. Each bearing seat has an insertion hole, and a through shaft is movably installed in the insertion hole. The outer surface of the top of the shaft is provided with multiple sets of limiting pins that slide and adapt to the insertion hole on the inner wall of the bearing seat. There are three sets of limiting pins, which are radially equidistant from the axis of the shaft. A spring is also sleeved at the bottom of the shaft, and the spring is located at the bottom of the outside of the UAV carrier frame.

[0007] One end of the shaft seat is also provided with a lightweight bracket for providing an installation position for the driver, and a propeller is driven to be mounted on the output end of the driver.

[0008] Preferably, four sets of anti-accidental contact frames are also installed at equal intervals along the circumference at the bottom of the outer side of the UAV carrier frame, and the anti-accidental contact frames are located outside the spring to protect the spring.

[0009] Preferably, the lightweight support includes a carbon fiber arm disposed at one end of the bearing seat, and the top end of the carbon fiber arm away from the bearing seat is fixedly connected to the bottom end of the driver. The carbon fiber arm has a hollow cavity inside, and keels for enhancing structural strength are installed equidistantly along the length direction inside the hollow cavity. Hollow grooves for further weight reduction are opened inside the keels.

[0010] Preferably, the keel is made of carbon fiber reinforced polyetheretherketone and has a rectangular shape.

[0011] Preferably, the support leg is made of titanium alloy, and the bottom end of the support leg is provided with an anti-slip rubber pad.

[0012] Preferably, the shaft and the limiting pin are integrally formed, and the limiting pin is rectangular in shape.

[0013] This invention provides a retractable arm structure for a drone. Compared with the prior art, it has the following advantages.

[0014] 1. Through the coordinated operation of the shaft, limit pin, axle seat, and spring in the elastic retraction and extension limiting mechanism, the operator can release the limit by pressing the shaft to retract the carbon fiber arm. After release, the spring pushes the limit pin into the axle seat to complete the locking. There is no need to manually tighten the bolts or operate complicated buckles, simplifying the retraction and extension process. The three sets of radially distributed limit pins enhance the locking stability and prevent the carbon fiber arm from shaking during the flight of the drone due to the failure of the limit of the retraction and extension mechanism, thus ensuring the stability of the drone's flight attitude.

[0015] 2. Through the combination of carbon fiber arms, hollow cavities, keels and hollow slots in the lightweight bracket, the carbon fiber arms are integrally molded from lightweight high-strength carbon fiber. The hollow cavities reduce material usage and weight. The rectangular keels are connected to the inner wall of the carbon fiber arms to enhance bending and torsional stiffness. The hollow slots reduce weight again, achieving a balance between lightweight and strength of the arms. This avoids the problems of traditional arms that reduce endurance due to heavy weight or are prone to deformation due to insufficient strength, ensuring the drone's endurance and stable power output. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the appearance of the present utility model;

[0017] Figure 2 This is a schematic diagram showing the installation position of the elastic retraction and extension limiting mechanism of this utility model;

[0018] Figure 3This is a partial schematic diagram of the elastic retraction and extension limiting mechanism of this utility model;

[0019] Figure 4 This is a partial schematic diagram of the installation position of the lightweight bracket of this utility model;

[0020] Figure 5 This is a partial schematic diagram of the interior of the carbon fiber arm of this utility model;

[0021] Figure 6 This is a partial schematic diagram of point A of the present invention;

[0022] Figure 7 This is a schematic diagram of the carbon fiber arm extension and retraction of this utility model.

[0023] In the diagram: 1. UAV carrier frame; 101. Support leg; 2. Flexible retraction and extension limiting mechanism; 201. Shaft; 202. Limiting pin; 203. Shaft seat; 204. Spring; 205. Anti-accidental touch frame; 3. Lightweight bracket; 301. Carbon fiber arm; 302. Hollow cavity; 303. Keel; 304. Hollow groove; 4. Driver; 401. Propeller. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] First implementation method:

[0026] refer to Figure 1-4 , Figure 7 A drone arm retraction and extension structure includes a drone support frame 1. Four sets of support legs 101 for contacting the ground to support the drone standing are installed through the inside of the drone support frame 1. Four sets of elastic retraction and extension limiting mechanisms 2 are installed at equal intervals along the circumference on the outside of the drone support frame 1.

[0027] The flexible retraction and extension limiting mechanism 2 includes multiple sets of bearing seats 203 rotatably mounted on the outside of the UAV carrier frame 1. The bearing seats 203 have insertion holes inside, and a through shaft 201 is movably installed in the insertion holes. The outer surface of the top of the shaft 201 is provided with multiple sets of limiting pins 202 that slide and adapt to the insertion holes on the inner wall of the bearing seats 203. There are three sets of limiting pins 202, which are radially equidistantly distributed with the axis of the shaft 201 as the center. The bottom end of the shaft 201 is also sleeved with a spring 204, and the spring 204 is located at the bottom of the outside of the UAV carrier frame 1.

[0028] One end of the bearing 203 is also provided with a lightweight bracket 3 for providing a mounting position for the driver 4, and the output end of the driver 4 is driven to mount a propeller 401.

[0029] Four sets of anti-accidental contact frames 205 are also installed at equal intervals along the circumference at the bottom of the outer side of the drone support frame 1. The anti-accidental contact frames 205 are located on the outside of the spring 204 and are used to protect the spring 204.

[0030] The support leg 101 is made of titanium alloy, and the bottom of the support leg 101 is equipped with an anti-slip rubber pad.

[0031] The shaft 201 and the limiting pin 202 are integrally formed, and the limiting pin 202 is rectangular in shape.

[0032] Working principle: When the carbon fiber arm 301 needs to be stored, the operator presses the bottom end of the shaft 201 with his hand. After the shaft 201 is subjected to force, it moves upward. Since the top of the spring 204 abuts against the bottom of the UAV carrier 1, the bottom end is compressed and stores elastic potential energy as the shaft 201 moves upward.

[0033] As the shaft 201 moves upward, the limiting pin 202 on the top outer surface of the shaft 201 moves upward synchronously and gradually moves out of the insertion hole inside the bearing 203. When the limiting pin 202 is completely disengaged from the insertion hole of the bearing 203, the limiting state formed by the bearing 203 and the outside of the drone carrier 1 through multiple sets of limiting pins 202 is released. At this time, the bearing 203 can rotate freely around the rotation connection point with the drone carrier 1. The operator pushes the bearing 203 to drive the lightweight bracket 3 to rotate as a whole until the carbon fiber arm 301 rotates to one side of the drone carrier 1, completing the storage operation.

[0034] When the carbon fiber arm 301 needs to be deployed, the operator pushes the bearing seat 203 in the opposite direction, causing the carbon fiber arm 301 to rotate to the working position. Then, the pressure on the shaft 201 is released, and the compressed spring 204 returns to its original position under its own elastic restoring force, pushing the shaft 201 to move downward. The shaft 201 drives the limiting pin 202 to move downward in sync until the limiting pin 202 is re-engaged in the insertion hole on the inner wall of the bearing seat 203. Through the tight cooperation between the limiting pin 202 and the insertion hole of the bearing seat 203, the bearing seat 203 is re-limited and fixed, thereby keeping the carbon fiber arm 301 stably in the deployed working position.

[0035] This structure, through the coordinated operation of the shaft 201, limit pins 202, bearing 203, and spring 204 in the elastic retraction and extension limiting mechanism 2, achieves the rapid retraction and extension and stable locking function of the carbon fiber arm 301. This avoids the cumbersome process of manually tightening bolts or operating complex buckles when retracting and extending the traditional arm. At the same time, the cooperation between the three sets of radially distributed limit pins 202 and the insertion holes of the bearing 203 enhances the structural stability after locking. This solves the technical problem that the carbon fiber arm 301 shakes during the flight of the UAV due to the failure of the retraction and extension limiting mechanism, which in turn affects the flight attitude stability of the UAV.

[0036] Among them, the driver 4 serves as a power output component. When powered on, it can drive the propeller 401 at the output end to rotate at high speed. When the propeller 401 rotates, it generates an interaction force with the air, forming an upward lift force, which provides power support for the take-off, flight and hovering of the UAV.

[0037] The support leg 101 directly contacts the ground during the take-off and landing of the drone, providing support for the drone carrier 1 and the overall structure, and preventing the drone body from directly contacting the ground and causing wear. The anti-slip rubber pad at its bottom can increase the coefficient of friction with the ground, effectively preventing the drone from sliding or deviating during take-off and landing due to the smooth ground or uneven force.

[0038] Second implementation method:

[0039] In the actual use of traditional drone arm retraction structures, due to the limitations of the material selection and structural design of the arms, the excessive weight of the arms can easily increase the overall load of the drone, affect its endurance, and thus lead to a decline in the drone's flight performance. To address this, this device is also designed with a lightweight support frame, the structure of which and its working principle are as follows.

[0040] refer to Figure 5-6 In the second embodiment of this utility model, the lightweight support 3 includes a carbon fiber arm 301 disposed at one end of the bearing seat 203, and the top end of the carbon fiber arm 301 away from the bearing seat 203 is fixedly connected to the bottom end of the driver 4. A hollow cavity 302 is provided inside the carbon fiber arm 301, and keels 303 for enhancing structural strength are installed equidistantly along the length direction inside the hollow cavity 302. A hollow groove 304 for further weight reduction is provided inside the keel 303.

[0041] The 303 keel is made of carbon fiber reinforced polyetheretherketone and has a rectangular shape.

[0042] Working principle: In the lightweight support 3, the carbon fiber arm 301 serves as the main structure. It is integrally molded using lightweight and high-strength carbon fiber material. The hollow cavity 302 inside it greatly reduces the amount of material used, thereby reducing the overall weight of the arm while ensuring the integrity of the basic structure.

[0043] The rectangular ribs 303, evenly distributed along the length of the hollow cavity 302, are fixedly connected to the inner wall of the carbon fiber arm 301 to form a frame support structure. Utilizing the high strength properties of the carbon fiber reinforced polyetheretherketone material itself, the overall bending resistance and torsional stiffness of the carbon fiber arm 301 are enhanced, which can effectively resist the torque and airflow impact generated by the operation of the actuator 4 and the propeller 401 during flight. At the same time, the hollow grooves 304 inside the ribs 303 further reduce material consumption without affecting the support strength of the ribs 303, achieving secondary weight reduction.

[0044] The overall design achieves a balance between lightweight and structural strength through the synergistic cooperation of the hollow structure of the carbon fiber arm 301, the frame support and material properties of the keel 303, and the secondary weight reduction of the hollow groove 304. This avoids the contradiction between traditional arms that sacrifice strength in the pursuit of lightweight and excessive weight in the pursuit of strength. It also solves the technical problem that excessive arm weight reduces the drone's endurance and affects the stability of the drone's power output.

[0045] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A retractable arm structure for a drone, characterized in that: The device includes a drone support frame (1), which has four sets of support legs (101) installed inside to support the drone standing against the ground, and four sets of elastic retraction and extension limiting mechanisms (2) are installed at equal intervals along the circumference on the outside of the drone support frame (1). The elastic retraction and extension limiting mechanism (2) includes multiple sets of bearing seats (203) rotatably mounted on the outside of the UAV carrier frame (1). The bearing seats (203) have insertion holes inside, and a through shaft (201) is movably installed in the insertion holes. Multiple sets of limiting pins (202) are provided on the outer surface of the top of the shaft (201) and are slidably adapted to the insertion holes on the inner wall of the bearing seats (203). There are three sets of limiting pins (202), which are radially equidistantly distributed with the axis of the shaft (201) as the center. A spring (204) is also sleeved at the bottom of the shaft (201), and the spring (204) is located at the bottom of the outside of the UAV carrier frame (1). One end of the bearing (203) is also provided with a lightweight bracket (3) for providing an installation position for the driver (4), and the output end of the driver (4) is driven to install a propeller (401).

2. The UAV arm retraction and extension structure according to claim 1, characterized in that: Four sets of anti-accidental touch frames (205) are also installed at equal intervals along the circumference at the bottom of the outer side of the UAV carrier frame (1), and the anti-accidental touch frames (205) are located on the outside of the spring (204) to protect the spring (204).

3. The UAV arm retraction and extension structure according to claim 1, characterized in that: The lightweight support (3) includes a carbon fiber arm (301) disposed at one end of the bearing seat (203), and the top end of the carbon fiber arm (301) away from the bearing seat (203) is fixedly connected to the bottom end of the driver (4). A hollow cavity (302) is provided inside the carbon fiber arm (301), and keels (303) for enhancing structural strength are installed equidistantly along the length direction inside the hollow cavity (302). Hollow grooves (304) for further weight reduction are provided inside the keels (303).

4. The UAV arm retraction and extension structure according to claim 3, characterized in that: The keel (303) is made of carbon fiber reinforced polyetheretherketone and has a rectangular shape.

5. The UAV arm retraction and extension structure according to claim 1, characterized in that: The support leg (101) is made of titanium alloy, and the bottom end of the support leg (101) is provided with an anti-slip rubber pad.

6. The UAV arm retraction and extension structure according to claim 1, characterized in that: The shaft (201) and the limiting pin (202) are integrally formed, and the limiting pin (202) is rectangular in shape.

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