Vehicle-mounted multi-rotor unmanned aerial vehicle folding and unfolding device

Abstract

The invention discloses a vehicle-mounted multi-rotor unmanned aerial vehicle folding and unfolding device which is installed on the top or the side face of a compartment. The device comprises a device body, the device body is hollow, and a side cover device, a lifting platform, a restoration locking device, a sliding device, a charging device and an electric control box are carried on the device body. And the side cover device comprises a side cover, an electric push rod I for connecting the side cover and the device main body, and a support for fixing the electric push rod I. The sliding device is used for pushing the take-off and landing platform to slide out of the device body and comprises an electric push rod II and a sliding rail, and the take-off and landing platform used for carrying the unmanned aerial vehicle is installed on the sliding rail. The restoration locking device comprises restoration push rods, a lead screw module and a sensor, the multiple restoration push rods are installed on the top face of the lifting platform at intervals, and the lead screw module used for driving the restoration push rods to move is installed on the bottom face of the platform. The electrical control box controls the side cover device, the sliding device and the restoration locking device to complete corresponding actions according to received instructions of the upper computer.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and specifically to a vehicle-mounted multi-rotor unmanned aerial vehicle retractable device. Background Art

[0002] Nowadays, the application industries of multi-rotor unmanned aerial vehicles are becoming more and more extensive, and they have made remarkable achievements in industries such as photography, agriculture, logistics, rescue, and military, and more and more application modes are gradually emerging. How to apply unmanned aerial vehicles more efficiently and durably has also become the current key focus direction. Especially in the case of batch transportation operations, how to quickly achieve takeoff and landing has become one of the key difficulties to be solved, and it is also one of the topics widely discussed inside and outside the industry.

[0003] Generally, multi-rotor unmanned aerial vehicles are folded and stored in a special backpack. When going out for use, the user needs to get out of the vehicle first, and then take out the multi-rotor unmanned aerial vehicle from the special backpack before proceeding with subsequent work. Even for a skilled pilot, the whole process takes a long time to complete the takeoff preparation work of the multi-rotor unmanned aerial vehicle.

[0004] In addition, there are also unmanned aerial vehicles equipped with retractable devices, and the takeoff of the unmanned aerial vehicle is achieved through the lifting device of the retractable device. During vehicle-mounted transportation, usually restricted by height limit requirements, only smaller unmanned aerial vehicles can be selected, resulting in such unmanned aerial vehicles being unable to carry more and larger payloads. Moreover, due to power transmission or synchronization problems of the lifting device, when the area is large, problems such as large synchronous response time differences during cross-travel, jitter of the lifting device itself, and jitter caused by non-synchronization of multiple lifting devices all affect the use of the unmanned aerial vehicle. Summary of the Invention

[0005] The purpose of the present invention is to provide a vehicle-mounted multi-rotor unmanned aerial vehicle retractable device, and the retractable device is installed on the top or side of the carriage.

[0006] The retractable device includes a device main body, a side cover device, a takeoff and landing platform, a rectifying and locking device, a sliding device, a charging device, and an electrical control box.

[0007] The device main body is a hexahedron structure with one side open, the other sides closed, and hollow inside, and the takeoff and landing platform, rectifying and locking device, sliding device, charging device, and electrical control box are carried inside.

[0008] The open side of the device main body is blocked by the side cover device.

[0009] The side cover device includes an electric push rod I, a side cover, a support I, and a support II.

[0010] The side cover is connected to the device main body through the electric push rod I.

[0011] Both ends of the electric push rod I are respectively fixed on the support I and the support II. The support I is installed on the inner bottom plate of the device main body, and the support II is installed on the inner plate surface of the side cover.

[0012] The sliding device is used to push the take-off and landing platform out of the device main body. The device includes a number of electric push rods II and a number of slide rails.

[0013] The outer rail of the slide rail is fixed on the inner bottom plate of the device main body, and the inner rail is connected to the take-off and landing platform.

[0014] One end of the electric push rod II is fixed on the inner bottom plate of the device main body, and the end of the other end abuts against the side wall of the take-off and landing platform.

[0015] The alignment and locking device includes a return push rod I, a connecting block I, a return push rod II, a connecting block II, and a lead screw module.

[0016] A number of lead screw modules are fixed on the bottom surface of the take-off and landing platform.

[0017] Two alignment grooves are oppositely arranged on the plate surface of the take-off and landing platform. The connecting block I is installed in the grooves. One end of the connecting block I is connected to the return push rod I located on the top surface of the take-off and landing platform, and the other end is connected to the slide table of the lead screw module installed on the bottom surface of the take-off and landing platform. The two return push rods II are oppositely installed at the edge of the top surface of the take-off and landing platform and are connected to the slide table of the lead screw module installed on the bottom surface of the take-off and landing platform through the connecting block II.

[0018] The charging device is used to supply power to the drone. When the take-off and landing platform is located inside the device main body, the drone charging metal contact located at the center of the top surface of the take-off and landing platform contacts the corresponding charging area of the charging device.

[0019] After receiving the instruction from the upper computer, the electrical control box controls the side cover device, the sliding device, and the alignment and locking device respectively according to the instruction from the upper computer to complete the corresponding actions.

[0020] Furthermore, the frame of the device main body is welded by a number of square tubes, and the closed surface is welded by plates or installed by screws

[0021] Furthermore, the rotatable angle of the side cover is ±90°.

[0022] Furthermore, four return push rods are installed at intervals around the center of the top surface of the take-off and landing platform, including two return push rods I and two return push rods II.

[0023] The return push rod I and the return push rod II are arranged at intervals, and the setting direction of the return push rod I is perpendicular to the setting direction of the return push rod II.

[0024] Further, when the electrical control box receives the take-off command sent by the upper computer, it controls the retraction push rod I and the retraction push rod II to move away from the UAV through the lead screw module. When the electrical control box receives the landing command sent by the upper computer, it controls the retraction push rod I and the retraction push rod II to lock the UAV through the lead screw module.

[0025] Further, the contact surface between the retraction push rod I and the landing gear of the UAV is an inclined surface.

[0026] Further, the motor of the lead screw module is equipped with a braking mode.

[0027] The starting method of the braking mode: the motor is powered off.

[0028] Further, the slide rail is an N-section slide rail, and the upper and lower inner rails are stacked together, and the take-off and landing platform is connected to the topmost inner rail.

[0029] Further, a slidable bottom plate is provided between the inner bottom plate of the device main body and the take-off and landing platform.

[0030] The electric push rod II is divided into two groups, each group includes two electric push rod IIs. One group of electric push rod IIs is installed on the inner bottom plate of the device main body, and the movable end is connected to the lower surface of the slidable bottom plate. The other group of electric push rod IIs is installed on the upper surface of the slidable bottom plate, and the movable end is connected to the lower surface of the take-off and landing platform, and the electric push rod IIs within the same group are located on the same horizontal plane.

[0031] Further, the charging device includes a flat-bottom U-shaped rod and a contact connection device.

[0032] The flat-bottom U-shaped rod is installed inside the device main body. The two vertical rods of the flat-bottom U-shaped rod are connected to the bottom of the device main body, and the contact connection device is installed at the central position of the cross bar of the flat-bottom U-shaped rod.

[0033] The technical effect of the present invention is beyond doubt, and the beneficial effects of the present invention are as follows:

[0034] 1. By installing the retracting and deploying device on the roof or the side of the carriage, the present invention realizes the rapid take-off and landing of the multi-rotor UAV, effectively reduces the operation time, and improves the take-off and landing efficiency.

[0035] 2. The present invention ensures the relative position stability between the UAV and the take-off and landing platform through the alignment and locking device, ensuring that the UAV is in a safe and reliable state;

[0036] 3. The sliding device of the present invention is a double-layer sliding device, which can achieve a longer stroke on the basis of saving space, so as to drive the take-off and landing platform to slide out of the retracting and deploying device, ensuring that there is no obstruction within the specified range during the take-off and landing process of the multi-rotor UAV. Description of the Drawings

[0037] Figure 1 Schematic diagram of the composition of the multi-rotor retractable device;

[0038] Figure 2 Schematic diagram of the side cover device;

[0039] Figure 3 Schematic diagram of the sliding device;

[0040] Figure 4 Schematic diagram of the composition of the homing and locking device (front view);

[0041] Figure 5 Schematic diagram of the composition of the homing and locking device (top view);

[0042] Figure 6 Schematic diagram of the movement of the homing and locking device.

[0043] In the figure: device main body 1, side cover device 2, electric push rod I 201, side cover 202, support I 203, support II 204, takeoff and landing platform 3, alignment groove 301, homing and locking device 4, homing push rod I 401, connecting block I 402, homing push rod II 403, connecting block II 404, lead screw module 405, sliding device 5, electric push rod II 501, slide rail 502, charging device 6, electrical control box 7, unmanned aerial vehicle 8. Specific implementation mode

[0044] The present invention will be further described below in conjunction with embodiments, but it should not be understood that the above-mentioned subject matter scope of the present invention is limited to the following embodiments. Without departing from the above-mentioned technical idea of the present invention, various substitutions and changes made according to the common general knowledge and customary means in the art should be included within the protection scope of the present invention.

[0045] Embodiment 1:

[0046] A vehicle-mounted multi-rotor unmanned aerial vehicle retractable device, and the retractable device is installed on the top or side of the vehicle compartment.

[0047] The retractable device includes a device main body 1, a side cover device 2, a takeoff and landing platform 3, a homing and locking device 4, a sliding device 5, a charging device 6, and an electrical control box 7.

[0048] The device main body 1 has a hexahedron structure with one side open, the other sides closed, and the inside hollow, and a takeoff and landing platform 3, a homing and locking device 4, a sliding device 5, a charging device 6, and an electrical control box 7 are carried inside.

[0049] The open surface of the device main body 1 is blocked by the side cover device 2.

[0050] The side cover device 2 includes an electric push rod I201, a side cover 202, a support I203, and a support II204.

[0051] The side cover 202 is connected to the device main body 1 through the electric push rod I201.

[0052] Both ends of the electric push rod I201 are respectively fixed on the support I203 and the support II204. The support I203 is installed on the inner bottom plate of the device main body 1, and the support II204 is installed on the inner plate surface of the side cover 202.

[0053] The sliding device 5 is used to push the takeoff and landing platform 3 to slide out from the device main body 1. The device includes a plurality of electric push rods II501 and a plurality of slide rails 502.

[0054] The outer rail of the slide rail 502 is fixed on the inner bottom plate of the device main body 1, and the inner rail is connected to the takeoff and landing platform 3.

[0055] One end of the electric push rod II501 is fixed on the inner bottom plate of the device main body 1, and the other end (the pushing end) abuts against the side wall of the takeoff and landing platform 3.

[0056] The alignment and locking device 4 includes a return push rod I401, a connection block I402, a return push rod II403, a connection block II404, and a lead screw module 405.

[0057] A plurality of lead screw modules 405 are fixed on the bottom surface of the takeoff and landing platform 3.

[0058] Two alignment grooves 301 are oppositely arranged on the plate surface of the takeoff and landing platform 3. The connection block I402 is installed in the grooves. One end of the connection block I402 is connected to the return push rod I401 located on the top surface of the takeoff and landing platform 3, and the other end is connected to the slide table of the lead screw module 405 installed on the bottom surface of the takeoff and landing platform 3; the two return push rods II403 are oppositely installed at the edge of the top surface of the takeoff and landing platform 3 and are connected to the slide table of the lead screw module 405 installed on the bottom surface of the takeoff and landing platform 3 through the connection block II404.

[0059] The two return push rods I401 and the two return push rods II403 are respectively connected to different lead screw modules 405.

[0060] The charging device 6 is used to supply power to the drone 8. When the takeoff and landing platform 3 is located inside the device main body 1, the charging metal contacts of the drone 8 located at the center of the top surface of the takeoff and landing platform are in contact with the corresponding charging area of the charging device 6.

[0061] After receiving the instructions from the upper computer, the electrical control box 7 controls the side cover device 2, the sliding device 5, and the alignment and locking device 4 respectively according to the instructions from the upper computer to complete the corresponding actions.

[0062] Example 2:

[0063] The main structure of this embodiment is the same as that of Embodiment 1. Further, the frame of the device main body 1 is welded by several square pipes, and the closed surface is welded by plates or installed by screws.

[0064] Example 3:

[0065] The main structure of this embodiment is the same as any one of Embodiments 1 to 2. Further, two supports I 203 and two supports II 204 are respectively arranged at intervals on the inner bottom plate of the device main body 1 and on the inner plate surface of the side cover 202.

[0066] The fixed end of the electric push rod I 201 is installed on the support I 203, and the pushing end is installed on the support II 204, so that the side cover 202 is opened or closed under the telescopic control of the electric push rod I 201.

[0067] Example 4:

[0068] The main structure of this embodiment is the same as any one of Embodiments 1 to 3. Further, the rotatable angle of the side cover 202 is ±90°.

[0069] Example 5:

[0070] The main structure of this embodiment is the same as any one of Embodiments 1 to 4. Further, four positioning push rods are installed at intervals around the center of the top surface of the take-off and landing platform 3, including two positioning push rods I 401 and two positioning push rods II 403.

[0071] The positioning push rods I 401 and the positioning push rods II 403 are arranged at intervals, and the arrangement direction of the positioning push rods I 401 is perpendicular to the arrangement direction of the positioning push rods II 403.

[0072] When the positioning push rod I 401 locks the UAV, the two positioning push rods I 401 form a dovetail structure. Refer to Figure 6 , the positioning push rods I 401 are symmetrically arranged, and together they form a dovetail groove structure from left to right. The cross-sectional shape of the positioning push rod I 401 is trapezoidal, and the shape of the UAV landing gear is also trapezoidal. After the positioning push rods I 401 and the positioning push rods II 403 push the UAV to the center of the platform, the dovetail structure of the positioning push rod I 401 is tightly combined with the UAV landing gear, forming a dovetail fastening structure, which restricts the displacement of the UAV in the X and Z directions, and the positioning push rod II 403 restricts the displacement of the UAV in the Y direction.

[0073] Among them, the X direction is parallel to the arrangement direction of the positioning push rod II 403; the Y direction is parallel to the arrangement direction of the positioning push rod I 401; the Z direction is the vertical direction.

[0074] Example 6:

[0075] The main structure of this embodiment is the same as any one of Embodiments 1 to 5. Further, when the electrical control box 7 receives the take-off command issued by the host computer, the return push rod I 401 and the return push rod II 403 are controlled by the lead screw module 405 to move away from the unmanned aerial vehicle.

[0076] When the electrical control box 7 receives the landing command issued by the host computer, the return push rod I 401 and the return push rod II 403 are controlled by the lead screw module 405 to lock the unmanned aerial vehicle.

[0077] Embodiment 7:

[0078] The main structure of this embodiment is the same as any one of Embodiments 1 to 6. Further, the contact surface between the return push rod I 401 and the landing gear of the unmanned aerial vehicle is an inclined surface.

[0079] Embodiment 8:

[0080] The main structure of this embodiment is the same as any one of Embodiments 1 to 7. Further, the motor of the lead screw module 405 is equipped with a braking mode, which is used to lock the return push rod I 401 and the return push rod II 403 to limit the displacement of the unmanned aerial vehicle.

[0081] The starting method of the braking mode: the motor is powered off.

[0082] Embodiment 9:

[0083] The main structure of this embodiment is the same as any one of Embodiments 1 to 8. Further, the slide rail 502 is an N-section slide rail, and the upper and lower inner rails are stacked together, and the take-off and landing platform 3 is connected to the topmost inner rail.

[0084] Embodiment 10:

[0085] The main structure of this embodiment is the same as any one of Embodiments 1 to 9. Further, a slidable bottom plate is provided between the inner bottom plate of the device main body 1 and the take-off and landing platform 3.

[0086] The electric push rod II 501 is divided into two groups, each group includes two electric push rods II 501. One group of electric push rods II 501 is installed on the inner bottom plate of the device main body 1, and the movable end is connected to the lower surface of the slidable bottom plate. The other group of electric push rods II 501 is installed on the upper surface of the slidable bottom plate, and the movable end is connected to the lower surface of the take-off and landing platform 3, and the electric push rods II 501 within the same group are located on the same horizontal plane.

[0087] The ends of the pushing ends of the two groups of electric push rods II 501 both abut against the side wall of the take-off and landing platform 3.

[0088] Embodiment 11:

[0089] The main structure of this embodiment is the same as any one of Embodiments 1 to 10. Further, the charging device 6 includes a flat-bottom U-shaped rod and a contact connection device.

[0090] The flat-bottom U-shaped rod is installed inside the device main body 1. The two vertical rods of the flat-bottom U-shaped rod are connected to the bottom of the device main body 1, and a contact connection device is installed at the central position of the cross bar of the flat-bottom U-shaped rod.

[0091] Embodiment 12:

[0092] The main structure of this embodiment is the same as any one of Embodiments 1 to 11. Further, the purpose of the present invention is to provide a vehicle-mounted multi-rotor UAV retracting and deploying device, which can realize the rapid take-off and landing of the multi-rotor UAV by installing the device on the roof or the side of the carriage.

[0093] Another purpose of the present invention is to provide a vehicle-mounted multi-rotor UAV take-off and landing system that uses the vehicle-mounted multi-rotor UAV retracting and deploying device in combination with a multi-rotor UAV.

[0094] The vehicle-mounted multi-rotor UAV retracting and deploying device is composed of a device main body, a side cover part, a take-off and landing platform, a rectifying and locking device, a sliding device, a charging device, an electrical control box, etc. The take-off and landing platform, the rectifying and locking device, the sliding device, the charging device, and the electrical control box are all integrated inside the device main body. While the structure is compact, it also takes into account the reasonable layout, fully considering the miniaturization design, and controlling the volume of the vehicle-mounted multi-rotor UAV retracting and deploying device within the minimum range, greatly saving the space occupied by the vehicle-mounted multi-rotor UAV retracting and deploying device.

[0095] The device main body is the main force-bearing support structure, which is welded by square tubes made of carbon steel and has good adaptability to various harsh environments caused during driving. The skin can be made of metal materials or other materials according to the application environment and usage conditions to meet specific usage requirements.

[0096] The side cover part is composed of an electric push rod, a support, a side cover, etc., and can realize automatic 90° side opening and closing.

[0097] The take-off and landing platform is a take-off and landing platform for the multi-rotor UAV, providing an ideal landing area for the take-off, landing, and storage of the multi-rotor UAV. There are no any protrusions and grooves larger than the landing gear legs in this area, ensuring that the multi-rotor UAV can land at any position in this area.

[0098] The alignment and locking device is connected to the takeoff and landing platform. The upper surface of the platform mainly has alignment push rods, with 2 in each of the X and Y directions, arranged symmetrically. The multi-rotor unmanned aerial vehicle gradually landing on the platform is pushed from the X and Y directions to the central position of the takeoff and landing platform. The alignment and locking drive part is located at the bottom surface of the platform and is composed of a motor, a ball screw, a linear slide rail, a sensor, etc. The rotation of the motor drives the module composed of the ball screw and the linear slide rail to move, thereby driving the push rod to move. Moreover, the motor is equipped with a brake. After the motor is powered off, the brake is activated to ensure that the motor is locked and the push rod is also in a locked state, restricting any displacement of the multi-rotor unmanned aerial vehicle in the X and Y directions. The contact surface between the push rod and the landing gear of the rotor unmanned aerial vehicle is an inclined surface. The two symmetric push rods form a dovetail structure. After the multi-rotor unmanned aerial vehicle is pushed to the center of the platform, the motor brake works and the push rod is locked. The dovetail structure restricts the displacement of the multi-rotor unmanned aerial vehicle in the Z direction. The alignment and locking mechanism pushes the multi-rotor unmanned aerial vehicle to the center of the platform and then locks it to protect the unmanned aerial vehicle from damage.

[0099] The sliding device is a double-layer sliding device, stacked in an up-and-down manner. The drive part is composed of 4 electric push rods in total. Two electric push rods on the same horizontal plane form a group and start working synchronously, and are matched with the slide rail to achieve smooth operation. The double-layer slide rail can achieve a longer stroke on the basis of saving space, thereby driving the takeoff and landing platform to slide out of the retracting and deploying device, ensuring that there is no obstruction within the specified range during the takeoff and landing process of the multi-rotor unmanned aerial vehicle.

[0100] The charging device is installed inside the device main body of the retracting and deploying device. When the multi-rotor unmanned aerial vehicle lands on the takeoff and landing platform, after the alignment and locking mechanism fixes the rotor unmanned aerial vehicle to the central position of the takeoff and landing platform, the sliding device drives the takeoff and landing platform to contract into the retracting and deploying device, and the charging metal contacts of the multi-rotor unmanned aerial vehicle come into contact with the corresponding area of the charging device, and the multi-rotor unmanned aerial vehicle starts charging.

[0101] The electrical control box is installed inside the device main body. After receiving the instruction from the upper computer, according to the instruction from the upper computer, it controls the alignment and locking device, the sliding device, the charging device, and the side cover part respectively, and completes the corresponding actions according to the takeoff and landing logic and steps.

[0102] Embodiment 13:

[0103] The main structure of this embodiment is the same as any one of Embodiments 1 to 12. Further, when the electrical control box receives the takeoff instruction of the rotor unmanned aerial vehicle sent by the upper computer, the electrical control box controls each part of the retracting and deploying device to start running according to the following steps.

[0104] First, the push rod of the side cover part extends, driving the side cover to open 90°;

[0105] Next, the sliding device responds, and the electric push rod extends step by step outwards. Cooperating with the slide rail, it pushes the takeoff and landing platform to a suitable takeoff position, and the contact position between the rotary-wing unmanned aircraft and the charging device is synchronously disconnected;

[0106] Next, the alignment and locking device starts to work. The motor rotates to transmit power to the linear movement module composed of the ball screw and the linear slide rail, thereby driving the return push rod away from the multi-rotor unmanned aircraft, and the multi-rotor unmanned aircraft has no constraints in the X, Y, and Z directions;

[0107] Finally, the multi-rotor unmanned aircraft starts power-on self-check. After the self-check is passed, the multi-rotor unmanned aircraft quickly takes off and executes the established task;

[0108] The return of the return push rod, the sliding back of the takeoff and landing platform, and the closing of the side cover are controlled by the electrical control box.

[0109] When the electrical control box receives the return instruction of the multi-rotor unmanned aircraft sent by the upper computer, the electrical control box controls each part of the retracting and deploying device to start running according to the following steps.

[0110] First, the push rod of the side cover part extends, driving the side cover to open 90°;

[0111] Next, the sliding device responds, and the electric push rod extends step by step outwards. Cooperating with the slide rail, it pushes the takeoff and landing platform to a suitable landing position;

[0112] Next, the motor of the alignment and locking device starts to rotate, bringing the return push rod to the edge position of the takeoff and landing platform;

[0113] Next, the multi-rotor unmanned aircraft starts to land on the takeoff and landing platform. After the electrical control box receives the instruction that the multi-rotor unmanned aircraft has completed landing, the motor rotates to transmit power to the linear movement module composed of the ball screw and the linear slide rail, thereby driving the return push rod to push the multi-rotor unmanned aircraft to the central position of the takeoff and landing platform. The motor brake is started, and the multi-rotor unmanned aircraft is locked in the X and Y directions; the dovetail design structure synchronously restricts the displacement of the multi-rotor unmanned aircraft in the Z direction.

[0114] Next, the electric push rod of the sliding device contracts step by step inwards. Cooperating with the slide rail, the takeoff and landing platform and the multi-rotor unmanned aircraft contract into the retracting and deploying device accordingly. The charging metal contacts of the multi-rotor unmanned aircraft contact the corresponding area of the charging device, and the multi-rotor unmanned aircraft starts to charge; the push rod of the side cover part starts to contract, driving the side cover to complete a 90° upward closing.

Claims

1. A vehicle-mounted multi-rotor UAV retracting and deploying device, characterized in that: The retractable device is installed on the top or side of the carriage; The retractable device comprises a device body (1), a side cover device (2), a lifting and lowering platform (3), a return locking device (4), a sliding device (5), a charging device (6) and an electrical control box (7); The device body (1) is a hexahedral structure with one side open and the other sides closed, and the interior is hollow, and is equipped with a lifting and lowering platform (3), a return locking device (4), a sliding device (5), a charging device (6) and an electrical control box (7); The open surface of the device body (1) is sealed by a side cover device (2); The side cover device (2) comprises an electric push rod I (201), a side cover (202), a support I (203) and a support II (204); The side cover (202) is connected to the device body (1) via an electric push rod I (201); The two ends of the electric push rod I (201) are respectively fixed on a support I (203) and a support II (204); the support I (203) is mounted on the inner bottom plate of the device body (1), and the support II (204) is mounted on the inner plate surface of the side cover (202); The sliding device (5) is used to push the lifting platform (3) to slide out from the device body (1), and the device comprises a plurality of electric push rods II (501) and a plurality of slide rails (502); The outer rail of the slide rail (502) is fixed to the inner bottom plate of the device body (1), and the inner rail is connected to the lifting and lowering platform (3); One end of the electric push rod II (501) is fixed to the inner bottom plate of the device body (1), and the other end is against the side wall of the lifting and lowering platform (3); The return locking device (4) comprises a return push rod I (401), a connecting block I (402), a return push rod II (403), a connecting block II (404), and a lead screw module (405); A plurality of lead screw modules (405) are fixed on the bottom surface of the lifting and lowering platform (3); Two return grooves (301) are arranged on the plate surface of the lifting and landing platform (3) in opposite directions, and a connecting block I (402) is installed in the groove. One end of the connecting block I (402) is connected to the return push rod I (401) located on the top surface of the lifting and landing platform (3), and the other end is connected to the slide of the screw module (404) installed on the bottom surface of the lifting and landing platform (3); the two return push rods II (403) are relatively installed at the edge of the top surface of the lifting and landing platform (3), and are connected to the slide of the screw module (404) installed on the bottom surface of the lifting and landing platform (3) through the connecting block II (404); The charging device (6) is used to supply power to the drone (8), and when the take-off and landing platform (3) is located inside the device body (1), the charging metal contact of the drone (8) located at the center of the top surface of the take-off and landing platform contacts the corresponding charging area of ​​the charging device (6); After receiving the host computer command, the electrical control box (7) controls the side cover device (2), the sliding device (5), and the return locking device (4) respectively according to the host computer command to complete the corresponding actions.

2. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The frame of the device body (1) is formed by welding a plurality of square tubes, and the closed surface is welded by plate or installed by screws.

3. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The side cover (201) can rotate at an angle of ±90°.

4. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: Four return push rods are installed on the top surface of the lifting and lowering platform (3) at intervals around the center of the platform, including two return push rods I (401) and two return push rods II (403); The homing push rod I (401) and the homing push rod II (403) are arranged at intervals, and the arrangement direction of the homing push rod I (401) is perpendicular to the arrangement direction of the homing push rod II (403).

5. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: When the electrical control box (7) receives a take-off command issued by the host computer, the lead screw module (404) controls the homing push rod I (401) and the homing push rod II (403) to move away from the drone; when the electrical control box (7) receives a landing command issued by the host computer, the lead screw module (404) controls the homing push rod I (401) and the homing push rod II (403) to lock the drone.

6. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The contact surface between the homing push rod 1 (401) and the landing gear of the UAV is an inclined surface.

7. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The motor of the lead screw module (404) is equipped with a brake mode; The braking mode is started by cutting off the power supply of the motor.

8. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The slide rail (502) is a slide rail with N sections, the upper and lower inner rails are stacked together, and the lifting and lowering platform (3) is connected to the top inner rail.

9. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: A slidable bottom plate is provided between the inner bottom plate of the device body (1) and the lifting and lowering platform (3); The electric push rods II (501) are divided into two groups, each group includes two electric push rods II (501), one group of electric push rods II (501) is installed on the inner bottom plate of the device body (1), and the movable end is connected to the lower surface of the slidable bottom plate, and the other group of electric push rods II (501) is installed on the upper surface of the slidable bottom plate, and the movable end is connected to the lower surface of the lifting and lowering platform (3), and the electric push rods II (501) in the same group are located on the same horizontal plane.

10. The vehicle-mounted multi-rotor UAV retracting and deploying device according to claim 1, characterized in that: The charging device (6) comprises a flat-bottomed U-shaped rod and a contact connection device. The flat-bottomed U-shaped rod is installed inside the device body (1), the two vertical rods of the flat-bottomed U-shaped rod are connected to the bottom of the device body (1), and a contact connection device is installed at the center position of the horizontal rod of the flat-bottomed U-shaped rod.

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