Unmanned aerial vehicle automatic counterweight pod structure and unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle automatic counterweight pod structure and an unmanned aerial vehicle, and relates to the technical field of logistics unmanned aerial vehicles. The unmanned aerial vehicle automatic counterweight pod structure comprises a guide rail, a pod, a weight measuring mechanism and a driving mechanism. The guide rail is configured to be fixed with an unmanned aerial vehicle body; the nacelle is movably connected with the guide rail, and the nacelle moves along the guide rail; the weight measuring mechanism at least measures the stress at three positions of the guide rail so as to obtain the projection position of the gravity center of the pod on the plane where the guide rail is located; the driving mechanism drives the pod to move along the guide rail, so that the projection position of the gravity center of the pod in the plane where the guide rail is located is located in a threshold value area. A proper mounting point can be obtained through the weight measuring mechanism, so that mounting of the pod is facilitated, dependence on artificial experience is reduced, and mounting efficiency is improved. In the flight process, the position of the pod can be adjusted through the driving mechanism, and it is ensured that the unmanned aerial vehicle is in a safe flight state.

Description

Technical Field

[0001] This application relates to the field of logistics drone technology, specifically to an automatic counterweight pod structure for a drone and the drone itself. Background Technology

[0002] With the rapid development of e-commerce and modern logistics, the efficiency and timeliness of logistics delivery have become key competitive factors. Fixed-wing cargo drones have attracted much attention in the logistics field due to their advantages such as high flight speed, long range, large carrying capacity, and immunity to ground traffic congestion. They are widely used in scenarios such as transporting goods to remote areas, delivering emergency medical supplies, and rapidly transferring commercial goods.

[0003] However, a key issue exists in the cargo transportation process using fixed-wing cargo drones: the weight and location range of the loaded cargo are strictly limited. This is due to the flight performance and stability requirements of the drones. If the cargo weight exceeds the limit or the placement is improper, it will seriously affect the flight safety of the drone, leading to consequences such as a shift in the center of gravity, insufficient lift, decreased controllability, or even instability and crash.

[0004] The existing method mainly relies on manual calculation and experience to adjust the position of the cargo in the pod and select suitable mounting points. Operators first place the cargo in the pod based on its estimated weight and a general principle of center of gravity balance. Then, using simple measuring tools and methods, they estimate whether the pod's center of gravity is within the acceptable range for the drone. Before flight, multiple ground tests and adjustments are required to observe the stability of the drone during takeoff, landing, hovering, and low-speed flight. If instability is detected, the cargo position is fine-tuned. However, this method has many drawbacks. On the one hand, the accuracy of manual calculation and experience is limited, making it difficult to precisely control the weight of the cargo and the pod's center of gravity. On the other hand, the entire adjustment process is time-consuming, labor-intensive, inefficient, and cannot adapt to changes in the cargo's condition in real time during flight. Utility Model Content

[0005] In view of the problems existing in the prior art, this application provides an automatic counterweight pod structure for unmanned aerial vehicles (UAVs) and an UAV, so as to improve the situation that existing pods are difficult to determine the center of gravity and cannot adapt to changes in the status of cargo in real time during flight.

[0006] To achieve the above and other related objectives, a first aspect of this application provides an automatic counterweight pod structure for a drone, including a guide rail, a pod, a weighing mechanism, and a drive mechanism. The guide rail is configured to be fixed to the drone fuselage; the pod is movably connected to the guide rail and moves along the guide rail; the weighing mechanism measures the forces at at least three locations on the guide rail to obtain the projection position of the pod's center of gravity on the plane of the guide rail; the drive mechanism drives the pod to move along the guide rail so that the projection position of the pod's center of gravity on the plane of the guide rail is within a threshold region.

[0007] In an exemplary embodiment of this application, two guide rails are provided, and the weighing mechanism measures the force at least at one location on each guide rail.

[0008] In an exemplary embodiment of this application, the weighing mechanism includes multiple sensors and a controller. The multiple sensors are respectively disposed at the connection between the guide rail and the machine body; the controller is electrically connected to the sensors to receive the measurement values ​​from the sensors.

[0009] In an exemplary embodiment of this application, the drive mechanism includes a drive unit and a transmission mechanism. The drive unit is disposed on the pod or the fuselage; the transmission mechanism is connected to the drive unit, such that the drive unit drives the transmission mechanism to move the pod along the guide rail.

[0010] In an exemplary embodiment of this application, the drive unit includes a motor disposed on the pod; the transmission mechanism includes a drive gear, a plurality of transmission gears, and a rack. The drive gear is connected to the output shaft of the motor; the plurality of transmission gears are rotatably disposed on the pod, and at least one transmission gear meshes with the drive gear; the rack is fixed to the guide rail, and the transmission gear meshes with the rack.

[0011] In an exemplary embodiment of this application, the rack is disposed on the guide rail near the pod, and the guide rail includes a first limiting portion. The first limiting portion is disposed on the guide rail near the pod and extends toward the pod; at least one of the first limiting portions is disposed on the side of the rack opposite to the other rack.

[0012] In an exemplary embodiment of this application, the guide rail includes a second limiting portion disposed on the side of the first limiting portion near the pod and extending toward the rack; the transmission gear includes a third limiting portion disposed at the rotation shaft of the transmission gear, the third limiting portion cooperating with the second limiting portion to restrict the transmission gear from disengaging from the guide rail.

[0013] In an exemplary embodiment of this application, each guide rail includes two first limiting portions, which are disposed on both sides of the rack; four transmission gears are provided, which are symmetrically disposed on the side of the pod near the fuselage, and each rack meshes with two transmission gears respectively.

[0014] In an exemplary embodiment of this application, the driving unit includes a motor disposed on the machine body, and the transmission mechanism includes a lead screw and a slider. The lead screw is fixed to the output shaft of the motor; the slider is fixed relative to the pod, and the slider cooperates with the lead screw, such that the motor drives the lead screw to rotate, thereby causing the slider to slide along the guide rail.

[0015] A second aspect of this application provides an unmanned aerial vehicle (UAV) including the UAV automatic counterweight pod structure described in any one of the preceding claims.

[0016] In combination with existing technologies, the beneficial effects of this application are as follows:

[0017] Currently, after cargo is placed in the pod, its position needs to be adjusted manually based on experience to select a suitable mounting point. Multiple bottom surface tests are also required before flight, resulting in low efficiency. The automatic counterweight pod mechanism of this application includes a weighing mechanism and a drive mechanism. The weighing mechanism measures the force at at least three points on the guide rail, thereby obtaining the projection position of the pod's center of gravity on the plane of the guide rail. The drive mechanism then moves the pod to ensure that the projection position of the pod's center of gravity on the plane of the guide rail is within a threshold region. This automatic counterweight pod for UAVs, through the weighing mechanism, can obtain a suitable mounting point, facilitating pod mounting, reducing reliance on manual experience, avoiding human error, reducing the number of mounting tests, and improving mounting efficiency. During flight, the weighing mechanism can continuously monitor the force on the guide rail. Therefore, when cargo displacement or changes in the center of gravity due to other factors occur, the drive mechanism can adjust the pod position, ensuring the UAV is in a safe flight state, effectively dealing with uncertainties during flight, and improving flight safety. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other embodiments can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of an exemplary unmanned aerial vehicle (UAV) automatic counterweight pod structure according to this application;

[0020] Figure 2 This is a top view of an exemplary UAV automatic counterweight pod structure according to this application;

[0021] Figure 3 This is a schematic diagram of a portion of an exemplary unmanned aerial vehicle (UAV) automatic counterweight pod structure according to this application;

[0022] Figure 4 This is a schematic diagram of another cargo of an exemplary unmanned aerial vehicle (UAV) automatic counterweight pod structure according to this application;

[0023] Figure 5 This is a top view of another cargo of an exemplary unmanned aerial vehicle (UAV) automatic counterweight pod structure according to this application;

[0024] Figure 6 This is an exploded view of an exemplary UAV automatic counterweight pod structure according to this application;

[0025] Figure 7 This is an exploded view from another angle of an exemplary UAV automatic counterweight pod structure of this application.

[0026] Component designation explanation:

[0027] 100. Fuselage;

[0028] 200. Guide rail; 210. First limiting part;

[0029] 300. Pod;

[0030] 400. Weighing mechanism; 410. Sensor; 420. Controller;

[0031] 500. Drive mechanism; 510. Drive unit; 520. Transmission mechanism; 521. Drive gear; 522. Transmission gear; 523. Rack;

[0032] 600. Goods. Detailed Implementation

[0033] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. This application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, unless otherwise specified, the following embodiments and features can be combined with each other. It should also be understood that the terminology used in the embodiments of this application is for describing specific implementation schemes and not for limiting the scope of protection of this application. Test methods in the following embodiments that do not specify specific conditions are generally performed under conventional conditions or according to the conditions recommended by the respective manufacturers.

[0034] When numerical ranges are given in the embodiments, it should be understood that, unless otherwise stated in this application, both endpoints of each numerical range and any value between the two endpoints may be selected. Unless otherwise defined, all technical and scientific terms used in this application, as well as the prior art known to those skilled in the art and the descriptions in this application, may be implemented using any prior art methods, devices, and materials similar to or equivalent to the methods, devices, and materials in the embodiments of this application.

[0035] It should be noted that the terms such as "upper," "lower," "left," "right," "middle," and "one" used in this specification are merely for clarity of description and are not intended to limit the scope of this application. Any changes or adjustments to their relative relationships, without substantially altering the technical content, shall also be considered as part of the scope of this application.

[0036] Please see Figures 1 to 7 This application provides a structure for an automatic counterweight pod 300 for a drone, including a guide rail 200, a pod 300, a weighing mechanism 400, and a drive mechanism 500. The guide rail 200 is fixed to the drone fuselage 100 and extends longitudinally along the fuselage 100. The pod 300 is movably connected to the guide rail 200 and moves along the guide rail 200. The weighing mechanism 400 measures the forces at at least three locations on the guide rail 200 to obtain the projection position of the center of gravity of the pod 300 on the plane of the guide rail 200. The drive mechanism 500 drives the pod 300 to move along the guide rail 200 so that the projection position of the center of gravity of the pod 300 on the plane of the guide rail 200 is within a threshold region.

[0037] The automatic counterweight pod 300 for the UAV disclosed in this application can obtain a suitable mounting point through the weighing mechanism 400, thereby facilitating the mounting of the pod 300, reducing reliance on human experience, avoiding human error, reducing the number of mounting tests, and improving mounting efficiency. During flight, the weighing mechanism 400 can continuously monitor the force on the guide rail 200, and when the cargo 600 shifts or the center of gravity changes due to other factors, it can adjust the position of the pod 300 through the drive mechanism 500 to ensure that the UAV is in a safe flight state, effectively cope with uncertainties during flight, and improve flight safety.

[0038] Please see Figure 1 and Figure 4In one embodiment, two guide rails 200 are provided, which makes the movement of the pod 300 more stable. The weight measuring mechanism 400 measures the force at least at one position on each guide rail 200. In other words, the three positions measured by the weight measuring mechanism 400 are not on the same straight line, which makes it easier to obtain the projection position of the current center of gravity of the pod 300 on the plane where the guide rail 200 is located, thereby determining whether the current position of the pod 300 is appropriate and whether it meets the requirements for safe flight.

[0039] Please see Figure 3 In one embodiment, the guide rail 200 is located below the pod 300 during drone flight; in other words, the pod 300 is located inside the drone fuselage 100. In other embodiments, the guide rail 200 may also be located below the pod 300 during drone flight, with the pod 300 externally mounted to the drone fuselage 100.

[0040] Please see Figure 1 and Figure 4 In one embodiment, the weighing mechanism 400 includes a plurality of sensors 410 and a controller 420. The sensors 410 are disposed at the connection between the guide rail 200 and the machine body 100. The machine body 100 and the guide rail 200 are connected via the sensors 410, which serve both as a connection and facilitate the acquisition of the force on the guide rail 200. The controller 420 is electrically connected to the sensors 410 to receive the measured values ​​from the sensors 410.

[0041] The controller 420 and the sensor 410 can be connected by wired electricity to ensure the speed and stability of data transmission; the controller 420 and the sensor 410 can also be connected wirelessly to facilitate the arrangement of the sensor 410 and the controller 420.

[0042] The sensor 410 is a force sensor 410, which can be a piezoelectric force sensor 410, a capacitive force sensor 410, a photoelectric force sensor 410, etc.

[0043] Please see Figure 7 In one embodiment, there are four sensors 410. Each guide rail 200 is connected to the fuselage 100 through two sensors 410. On the one hand, this ensures the stability of the connection between the guide rail 200 and the fuselage 100. On the other hand, it makes it easier to obtain the force at different positions of the guide rail 200, thereby more accurately determining the center of gravity of the pod 300.

[0044] Please see Figure 2 and Figure 5When different cargoes 600 are placed on the pod 300, the pod 300, under its own weight and the weight of the cargoes 600, transmits force signals to the controller 420 through sensors 410 at four connection points. Based on the magnitude and direction of these forces, the controller 420 calculates parameters such as the resultant force and resultant torque acting on the pod 300, and then derives the total weight and center of gravity coordinates of the pod 300. Then, combining the UAV's structural parameters (such as fuselage length 100, wingspan, empty weight distribution, etc.) and flight performance limitations (such as maximum takeoff weight, safe center of gravity range, lift coefficient, etc.), the controller determines the optimal mounting position of the pod 300 to ensure the UAV is in the best flight condition. Finally, the control ball sends a command to the drive mechanism 500, controlling the drive mechanism 500 to operate and slide the pod 300 along the guide rail 200 to the designated position, completing the automatic counterweight process.

[0045] As some alternatives, the guide rail 200 and the body 100 can also be connected directly without the sensor 410. The connection methods include, but are not limited to, bolt connection, adhesive connection, welding connection, and integral molding.

[0046] As an alternative, the sensor 410 may not be located at the connection between the guide rail 200 and the fuselage 100. The sensor 410 can measure the force at different positions of the guide rail 200, thereby obtaining the projection of the current center of gravity of the pod 300 onto the plane where the guide rail 200 is located.

[0047] In one embodiment, the drive mechanism 500 includes a drive unit 510 and a transmission mechanism 520. The drive unit 510 is disposed on the pod 300 or the fuselage 100. The transmission mechanism 520 is connected to the drive unit 510, such that the drive unit 510 drives the transmission mechanism 520 to move the pod 300 along the guide rail 200. The mechanical energy output by the drive unit 510 is transmitted through the transmission mechanism 520, thereby realizing the drive unit 510 driving the pod 300.

[0048] Please see Figure 3 In one embodiment, the drive unit 510 includes a motor, which is disposed on the pod 300 and fixed relative to the pod 300. The fixing method includes, but is not limited to, bolt connection.

[0049] The transmission mechanism 520 includes a drive gear 521, multiple transmission gears 522, and a rack 523. The drive gear 521 is connected to the output shaft of the motor, for example, the drive gear 521 is sleeved on the output shaft of the motor.

[0050] Multiple transmission gears 522 are rotatably mounted on the pod 300. When the pod 300 is located inside the fuselage 100, the transmission gears 522 are located at the lower part of the pod 300, and under the gravity of the pod 300, the transmission gears 522 are pressed against the rack 523. At least one transmission gear 522 meshes with the drive gear 521, so that the drive gear 521 drives the transmission gear 522 to move.

[0051] The rack 523 is fixed to the guide rail 200, and the direction of the rack 523 is consistent with the direction of the guide rail 200. The transmission gear 522 meshes with the rack 523. Under the meshing action of the transmission gear 522 and the rack 523, the transmission gear 522 rolls along the rack 523, thereby causing the pod 300 to move along the guide rail 200, realizing the adjustment of the position of the pod 300 and maintaining the stability of the UAV flight. When the position of the pod 300 does not need to change, the motor locks the drive gear 521, thereby preventing the transmission gear 522 from rotating, ensuring the stability of the position of the pod 300, and preventing the pod 300 from moving.

[0052] In one embodiment, the rack 523 is disposed on the side of the guide rail 200 near the pod 300, and the guide rail 200 includes a first limiting portion 210. The first limiting portion 210 is disposed on the side of the guide rail 200 near the pod 300 and extends toward the pod 300, and at least one first limiting portion 210 is disposed on the side of the rack 523 opposite to the other rack 523. The two guide rails 200 have at least two first limiting portions 210, and the two first limiting portions 210 are respectively disposed on the outer side of the rack 523. The transmission gear 522 is disposed between the two first limiting portions 210, so that the first limiting portions 210 limit the transmission gear 522, preventing the transmission gear 522 from disengaging from the rack 523 in a direction perpendicular to the rack 523, ensuring the stability of the transmission and the stability of the position of the pod 300.

[0053] Please see Figure 4 In one embodiment, each guide rail 200 includes two first limiting portions 210, which are respectively disposed on both sides of the rack 523. The transmission gear 522 is disposed between the two first limiting portions 210 of each guide rail 200, thereby limiting the transmission gear 522 on each rack 523, preventing the transmission gear 522 from disengaging from the rack 523 in a direction perpendicular to the rack 523, and also reducing the shaking of the transmission gear 522 and improving the stability of the pod 300.

[0054] Four transmission gears 522 are provided, symmetrically arranged on the side of the pod 300 near the fuselage 100. Each rack 523 meshes with two transmission gears 522. The four transmission gears 522 support the pod 300, ensuring that the pod 300 can be stably supported on the guide rail 200. The four transmission gears 522 also improve the stability of the pod 300's movement, facilitating timely and stable adjustment of the pod 300's position.

[0055] In one embodiment, the guide rail 200 includes a second limiting portion disposed on the side of the first limiting portion 210 near the pod 300 and extending toward the rack 523. The second limiting portion is disposed on the first limiting portion 210 on the side of the rack 523 opposite to the other rack 523 and extends toward the rack 523.

[0056] The transmission gear 522 includes a third limiting part, which is disposed at the rotation shaft of the transmission gear 522. The third limiting part cooperates with the second limiting part to prevent the transmission gear 522 from disengaging from the guide rail 200. Through the cooperation of the third limiting part and the second limiting part, the transmission gear 522 is prevented from disengaging from the rack 523 in the vertical direction, thereby improving the stability of the pod 300, reducing the swaying of the pod 300 under turbulent conditions, and effectively improving flight stability and safety.

[0057] In another embodiment, the drive unit 510 includes a motor disposed on the fuselage 100, and the transmission mechanism 520 includes a lead screw and a slider. The lead screw is fixed to the output shaft of the motor; the slider is fixed relative to the pod 300, and the slider cooperates with the lead screw, so that the motor drives the lead screw to rotate, thereby causing the slider to slide along the guide rail 200. Through the cooperation of the motor, lead screw, and slider, the pod 300 can slide along the guide rail 200, which facilitates the adjustment of the position of the pod 300, ensures that the projection of the center of gravity of the pod 300 on the plane of the guide rail 200 is within the threshold area, improves flight stability and safety, and reduces the risk of uncontrolled flight of the UAV.

[0058] The second aspect of this application provides a drone, including the drone automatic counterweight pod 300 structure described in any one of the preceding descriptions. The drone also includes other structures, such as a power unit, wings, etc. Please refer to existing drone structures; these will not be elaborated upon here.

[0059] Compared to traditional methods of manual calculation and experience-based judgment, this application utilizes a weighing mechanism 400 to collect data in real time and calculate the center of gravity and total weight of the pod 300. This minimizes errors and significantly improves the accuracy of cargo 600 counterweight measurement. For example, in traditional methods, the estimation error of the center of gravity position may reach several centimeters or even higher, while this application can reduce the error to the millimeter level, thus more accurately meeting the requirements of drone flight performance for the center of gravity.

[0060] During loading, the drone of this application can quickly determine the appropriate position of the pod 300, eliminating the need for repeated manual measurements, calculations, and adjustments, thus significantly shortening loading time and improving loading efficiency. During flight, the drone possesses real-time dynamic adjustment capabilities, enabling it to respond immediately to changes in the cargo 600's condition, preventing flight interruptions or accidents caused by cargo 600 issues, and improving the efficiency and reliability of the entire logistics delivery process. Through precise weight distribution and real-time adjustments, this application ensures the drone's center of gravity remains within a safe range, effectively preventing flight safety accidents caused by center of gravity shifts. In complex logistics transportation environments, such as encountering sudden turbulence or slight swaying of the cargo 600, the drone of this application can still maintain stable flight, mitigating the risk of loss of control that can easily occur with traditional methods in such situations.

[0061] The automatic counterweight pod 300 mechanism for unmanned aerial vehicles (UAVs) of this application can obtain a suitable mounting point through the weighing mechanism 400, thereby facilitating the mounting of the pod 300, reducing reliance on human experience, avoiding human error, reducing the number of mounting tests, and improving mounting efficiency. During flight, the weighing mechanism 400 can continuously monitor the force on the guide rail 200, and when the cargo 600 shifts or the center of gravity changes due to other factors, it can adjust the position of the pod 300 through the drive mechanism 500 to ensure that the UAV is in a safe flight state, effectively dealing with uncertainties during flight and improving flight safety. Therefore, this application effectively overcomes some practical problems in the prior art and has high utilization value and significance. The above embodiments are only illustrative of the principles and effects of this application and are not intended to limit this application. Any person skilled in the art can modify or change the above embodiments without departing from the spirit and scope of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this application shall still be covered by the claims of this application.

Claims

1. An automatic counterweight pod structure for an unmanned aerial vehicle (UAV), characterized in that, include: The guide rail is configured to be fixed to the drone fuselage; A pod is movably connected to the guide rail, and the pod moves along the guide rail; The weighing mechanism measures the force at at least three points on the guide rail to obtain the projection position of the center of gravity of the pod on the plane of the guide rail. A drive mechanism drives the pod to move along the guide rail, so that the projection of the pod's center of gravity onto the plane of the guide rail is within a threshold region.

2. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 1, characterized in that, The guide rails are provided in two sections, and the weighing mechanism measures the force at least at one location on each guide rail.

3. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 1 or 2, characterized in that, The weighing mechanism includes: Multiple sensors are located at the connection between the guide rail and the body; The controller is electrically connected to the sensor to receive the sensor's measured values.

4. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 2, characterized in that, The drive mechanism includes: The drive unit is located in the pod or the fuselage; A transmission mechanism is connected to the drive unit so that the drive unit drives the transmission mechanism to move the pod along the guide rail.

5. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 4, characterized in that, The drive unit includes a motor, which is disposed in the pod; the transmission mechanism includes: A drive gear is connected to the output shaft of the motor; Multiple transmission gears are rotatably mounted on the pod, and at least one transmission gear meshes with the drive gear; The rack is fixed to the guide rail, and the transmission gear meshes with the rack.

6. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 5, characterized in that, The rack is disposed on the side of the guide rail near the pod, and the guide rail includes: A first limiting part is disposed on the side of the guide rail near the pod and extends toward the pod; at least one of the first limiting parts is disposed on the side of the rack away from the other rack.

7. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 6, characterized in that, The guide rail includes: The second limiting part is disposed on the side of the first limiting part near the pod and extends toward the rack; The transmission gear includes: The third limiting part is disposed at the rotation shaft of the transmission gear. The third limiting part cooperates with the second limiting part to prevent the transmission gear from disengaging from the guide rail.

8. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 6 or 7, characterized in that, Each of the guide rails includes two first limiting portions, which are disposed on both sides of the rack. The transmission gears are provided in four symmetrical arrangements on the side of the pod near the fuselage, and each rack meshes with two transmission gears respectively.

9. The automatic counterweight pod structure for unmanned aerial vehicles according to claim 4, characterized in that, The drive unit includes a motor, which is disposed on the body, and the transmission mechanism includes: The lead screw is fixed to the output shaft of the motor; The slider is fixed relative to the pod, and the slider cooperates with the lead screw, so that the motor drives the lead screw to rotate, thereby causing the slider to slide along the guide rail.

10. A drone, characterized in that, The unmanned aerial vehicle (UAV) automatic counterweight pod structure includes any one of claims 1 to 9.

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