Unmanned aerial vehicle spoiler, cabin and vehicle

Abstract

This application relates to the field of vehicle-mounted unmanned aerial vehicles (UAVs), and discloses a UAV spoiler cabin and a vehicle. The UAV spoiler cabin includes a cabin body, a spoiler cover, a UAV take-off and landing platform, and a motion mechanism; the spoiler cover is detachably adjacent to a first side portion and a second side portion of the vehicle's spoiler; the cabin body is fixed to the vehicle body, the spoiler cover is located on the top opening of the cabin body, and the UAV take-off and landing platform is located inside the cabin body; the spoiler cover is connected to the motion mechanism, and the UAV take-off and landing platform and the motion mechanism can move relative to each other, the motion mechanism being configured to synchronously drive the spoiler cover to open and close and the UAV take-off and landing platform to rise and fall. The UAV spoiler cabin provided by this application can form a convenient vehicle-mounted UAV cabin for take-off and landing without changing the vehicle body structure, while also expanding the functionality of the vehicle spoiler.

Description

Technical Field

[0001] This invention relates to the field of vehicle-mounted unmanned aerial vehicles (UAVs), specifically to a UAV spoiler cabin and vehicle. Background Technology

[0002] The application of drones mounted on vehicles and operating in conjunction with them has broad development prospects. Vehicle-mounted drone cabins can provide a take-off, landing, parking, and storage environment for drones. Some vehicle-mounted drone cabins can also charge electric drones, improving the endurance of electric drones for continuous operation alongside vehicles under heavy workloads.

[0003] However, in existing technologies, vehicle-mounted drone cabins need to be installed on the car as an external, independent accessory, which can damage the car's aerodynamic structure. Some vehicle-mounted drone cabins also require necessary modifications to the car's body structure before installation, which in turn affects the car's safety architecture. Summary of the Invention

[0004] In view of this, the present invention provides a drone spoiler cabin and vehicle, which can form a convenient vehicle-mounted drone cabin for take-off and landing without changing the vehicle body structure.

[0005] This application provides a drone spoiler cabin, which includes a cabin body, a spoiler canopy, a drone take-off and landing platform, and a motion mechanism.

[0006] The spoiler hatch 2 is detachably adjacent to the first side portion 202 and the second side portion 203 of the vehicle's spoiler;

[0007] The cabin body 1 is fixed to the vehicle body, the spoiler cover 2 is located on the top opening of the cabin body 1, and the UAV take-off and landing platform 3 is located inside the cabin body 1.

[0008] The spoiler hatch 2 is connected to the motion mechanism 4, and the UAV take-off and landing platform 3 can move relative to the motion mechanism 4. The motion mechanism 4 is configured to synchronously drive the spoiler hatch 2 to open and close and the UAV take-off and landing platform 3 to rise and fall.

[0009] Optionally, the motion mechanism 4 includes an arc-shaped motion bracket 403 and a slider 405. The top of the arc-shaped motion bracket 403 is connected to the spoiler hatch 2. The arc-shaped motion bracket 403 extends from the lower part of the first side of the cabin body 1 to the upper part of the opposite second side.

[0010] The UAV take-off and landing platform 3 has a transverse track groove 404, and the slider 405 extends from the arc-shaped motion bracket 403 and is slidably located in the transverse track groove 404.

[0011] Optionally, the motion mechanism includes an arc actuator 401;

[0012] The arc-shaped motion bracket 403 has an arc-shaped actuator engagement structure 4031. The arc-shaped actuator 401 and the arc-shaped actuator engagement structure 4031 cooperate to drive the arc-shaped motion bracket 403 to perform arc-shaped motion, lifting the spoiler cover 2 to expose the top opening of the cabin body 1 or returning to cover the top opening of the cabin body 1.

[0013] The arc-shaped motion bracket 403 causes the slider 405 to slide within the transverse rail groove 404. The slider 405 drives the transverse rail groove 404 to move in a straight line perpendicular to the normal of the UAV take-off and landing platform 3, thereby driving the UAV take-off and landing platform 3 to move in a straight line along the normal.

[0014] Optionally, the UAV take-off and landing platform 3 has a linear drive mechanism 402, which includes an actuating component 4021 and a vertical reciprocating component 4022. The vertical reciprocating component 4022 is fixedly connected to the cabin 1), and the actuating component 4021 is fixedly connected to the UAV take-off and landing platform 3.

[0015] The vertical reciprocating motion component 4022 is configured to move in a straight line perpendicular to the normal of the UAV take-off and landing platform 3 under the drive of the action component 4021, thereby causing the UAV take-off and landing platform 3 to rise to the top opening of the cabin body 1 or descend to the bottom of the cabin body 1.

[0016] Optionally, the arc-shaped motion bracket 403 is fixedly connected to the slider 405;

[0017] The lifting and lowering motion of the UAV take-off and landing platform 3 causes the slider 405 to slide within the transverse rail groove 404. The slider 405 drives the arc-shaped motion bracket 403 to move in an arc, thereby driving the spoiler hatch 2 to rise above the top opening of the cabin body 1 or return to cover the top opening of the cabin body 1.

[0018] Optionally, the UAV take-off and landing platform 3 is fixed with a centering mechanism 301 and a wired charger 302;

[0019] After the UAV 5 lands on the UAV take-off and landing platform 3, the centering mechanism 301 moves and / or clamps and fixes the UAV 5 on the UAV take-off and landing platform 3.

[0020] The wired charger 302 has a charging contact 3025 configured to be electrically connected to the drone power receiving contact 502 of the drone 5.

[0021] Optionally, the centering unit 301 can also be used to move the drone 5 to a preset charging position and clamp and fix it.

[0022] Optionally, the cabin body 1 has a lower edge 101, which is a stepped plane formed by deflecting the cabin body 1 at 90° to the first side direction where the first side portion 202 is located and the second side direction where the second side portion 203 is located, respectively, and is arranged symmetrically in the first side direction and the second side direction of the cabin body 1.

[0023] The spoiler cover 2 is fixed with a magnet 204 below it in the direction of the first side. An electromagnet 104 is fixed on the lower edge 101 of the cabin. The electromagnet 104 attracts the magnetic block 204 after being energized. A sealing structure 103 is fixed on the lower edge 101 of the cabin. The sealing structure 103 is located in the direction of the second side of the electromagnet 104.

[0024] The cabin body 1 has an upper edge 102, which is a stepped plane formed by first bending upward 90° and then bending 90° away from the UAV take-off and landing platform 3, and is symmetrically arranged on both sides of the cabin body 1.

[0025] The first side portion 202 and the second side portion 203 are respectively connected to the first side upper edge 1021 in the first side direction and the second side upper edge 1022 in the second side direction of the cabin upper edge 102. The first side portion 202 and the second side portion 203 extend a certain length in the direction close to the cabin body 1, wherein the extended end of the first side portion 202 is located in the first side direction of the electromagnet 104.

[0026] Another aspect of this application provides a vehicle having the aforementioned unmanned aerial vehicle spoiler nacelle.

[0027] Optionally, the vehicle has a vehicle central control platform, which is used to send control information to the drone spoiler nacelle and receive status information of the drone spoiler nacelle;

[0028] The vehicle central control platform is also used to receive control signals from the host computer to the drone spoiler cabin and to feed back the status information of the drone spoiler cabin to the host computer.

[0029] The beneficial effects of the product provided in this application embodiment include at least the following:

[0030] The drone spoiler cabin provided in this application utilizes a portion of the spoiler in the vehicle's own aerodynamic components as the cabin cover. Inside the cabin is a drone platform that automatically takes off and lands in sync with the opening and closing of the spoiler cabin cover. This drone platform provides a suitable takeoff and landing environment for vehicle-mounted drones. The drone spoiler cabin provided in this application does not require modification of the vehicle's existing structure, and the unique arrangement of the motion mechanism allows for the synchronized opening and closing of the cover with the raising and lowering of the drone platform. Therefore, it not only provides a convenient vehicle-mounted drone cabin for takeoff and landing but also expands the functionality of automotive spoilers. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This illustration shows a schematic diagram of the spoiler cabin hatch of a vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform provided in this application when it is open;

[0033] Figure 2 This illustration shows a schematic diagram of the spoiler and cabin hatch of a vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform provided in an embodiment of this application when the spoiler is closed.

[0034] Figure 3 This illustration shows a structural diagram of another vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform with its spoiler and cabin hatch open, according to an embodiment of this application.

[0035] Figure 4 This invention provides a schematic diagram of the structure of another vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform with its spoiler and cabin canopy closed, according to an embodiment of this application.

[0036] Figure 5 This illustration shows a partially enlarged schematic diagram of the structure at point A when the spoiler cabin hatch of a vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform provided in this application is closed;

[0037] Figure 6 This illustration shows a partially enlarged structural diagram at point B when the spoiler cabin hatch of a vehicle-mounted unmanned aerial vehicle (UAV) automatic take-off and landing platform provided in this application is opened;

[0038] Figure 7 This illustration shows a schematic diagram of a spoiler cabin control module for an automatic take-off and landing platform for a vehicle-mounted unmanned aerial vehicle (UAV) provided in an embodiment of this application.

[0039] Figure label:

[0040] 1. Cabin hull; 101. Lower edge of hull; 1011. Lower edge of first side; 1012. Lower edge of second side; 102. Upper edge of hull; 1021. Upper edge of first side; 1022. Upper edge of second side; 103. Sealing structure; 1031. Sealing structure of first side; 1032. Sealing structure of second side; 104. Electromagnet;

[0041] 2. Spoiler hatch cover; 202. First side section; 203. Second side section; 204. Magnetic block;

[0042] 3. Unmanned aerial vehicle (UAV) take-off and landing platform; 301. Centering mechanism; 3011. Centering push rod; 3012. Push rod end; 302. Wired charger; 3021. Charging push rod joint; 3022. Charging push rod; 3023. Contact connection point; 3024. Charging contact; 3025. Charging contact.

[0043] 4. Motion mechanism; 401. Arc actuator; 402. Linear drive mechanism; 4021. Actuating component; 4022. Vertical reciprocating motion component; 403. Arc-shaped motion bracket; 4031. Arc actuator mating structure; 404. Transverse rail groove; 405. Slider;

[0044] 5. Unmanned aerial vehicles (UAVs); 501. UAV landing gear; 502. UAV power receiving contacts;

[0045] 6. Automotive central control platform;

[0046] 7. Host computer. Detailed Implementation

[0047] The products of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application. To make the products and advantages of this application clearer, the constituent parts, motion mechanism cooperation methods, structural features, etc. of the UAV spoiler cabin will be described in detail below with reference to the accompanying drawings.

[0048] The application of drones mounted on vehicles and operating in conjunction with them has broad development prospects. Vehicle-mounted drone cabins can provide a take-off, landing, parking, and storage environment for drones. Some vehicle-mounted drone cabins can also charge electric drones, improving the endurance of electric drones for continuous operation alongside vehicles under heavy workloads.

[0049] However, in existing technologies, vehicle-mounted drone cabins need to be installed on the car as an external, independent accessory, which can damage the car's aerodynamic structure. Some vehicle-mounted drone cabins also require necessary modifications to the car's body structure before installation, which in turn affects the car's safety architecture.

[0050] In response, this application provides a vehicle-mounted drone cabin that can be easily taken off and landed without altering the vehicle body structure.

[0051] like Figure 1 and Figure 2 As shown, the UAV spoiler cabin provided in this application embodiment includes a cabin body 1, a spoiler cover 2, a UAV take-off and landing platform 3, and a motion mechanism 4.

[0052] The spoiler cover 2 is detachably adjacent to the first side portion 202 and the second side portion 203 of the vehicle's spoiler; the engine compartment 1 is fixed to the vehicle body, the spoiler cover 2 is located on the top opening of the engine compartment 1, and the UAV take-off and landing platform 3 is located inside the engine compartment. The spoiler cover 2 is connected to a motion mechanism 4, and the UAV take-off and landing platform and the motion mechanism 4 can move relative to each other. The motion mechanism 4 is configured to drive the spoiler cover 2 to open and close and synchronously raise and lower the UAV take-off and landing platform 3.

[0053] Due to the above configuration, the motion mechanism achieves a synchronized motion effect, causing the opening and closing of the spoiler hatch 2 and the lifting and lowering of the UAV take-off and landing platform 3. This allows the UAV spoiler nacelle to drive the synchronous movement of both load bodies with only one active drive mechanism. Furthermore, since only one active drive mechanism is used, only one motion signal loop needs to be established between the UAV spoiler nacelle and its control system, simplifying the control circuitry of the UAV spoiler nacelle and improving the reliability of the motion control system while reducing the overall system energy consumption.

[0054] like Figure 1 As shown, when the spoiler hatch 2 of the drone spoiler compartment provided in this embodiment is closed, the first side portion 202 and the second side portion 203 of the vehicle spoiler together with the spoiler hatch 2 form a complete car spoiler. Therefore, when the drone spoiler compartment is closed, the spoiler hatch 2 can serve as part of the car spoiler, thereby better reducing the lift generated by the overall vehicle structure when the vehicle is traveling at high speed and improving the vehicle's stability.

[0055] In some embodiments, such as Figure 1As shown, the motion mechanism includes an arc-shaped motion bracket 403 and a slider 405; the top of the arc-shaped motion bracket 403 is connected to the spoiler hatch 2, and the arc-shaped motion bracket 403 extends from the lower part of the first side of the cabin body 1 to the upper part of the opposite second side; the UAV take-off and landing platform 3 has a transverse track 404, and the slider 405 is slidably located in the transverse track 404.

[0056] During the assembly of the drone spoiler compartment, since the spoiler cover 2 needs to form a complete windward surface of the car spoiler with the first side part 202 and the second side part 203, if the spoiler cover 2 is misaligned during installation, the overall aerodynamic structure of the spoiler will be damaged, thus affecting its aerodynamic performance. Therefore, the spoiler cover 2 and the arc-shaped motion bracket 403 can be designed as an integrated structure, that is, the arc-shaped motion bracket 403 is part of the spoiler cover 2. This structure can produce a small positioning deviation during the installation of the spoiler cover 2, reducing the impact of the deviation on the function of the car spoiler.

[0057] Because a car spoiler can generate downforce sufficient to counteract the lift of the vehicle's overall structure, it must withstand both significant static pressure from the air and the vehicle's support force. In this embodiment, the vehicle's support force on the spoiler cover 2 originates from the direct support of the arc-shaped motion bracket 403. Therefore, if the spoiler cover 2 and the arc-shaped motion bracket 403 are an integral structure, the transition between them can be designed as a rounded corner with a large radius of curvature. If the spoiler cover 2 and the arc-shaped motion bracket 403 are separate assembly structures, the connection between them can be a mortise and tenon joint, or multiple evenly distributed connectors can be used when connecting them, thereby eliminating positioning deviations during installation to a certain extent.

[0058] Furthermore, the arc-shaped motion bracket 403 in this embodiment has an overall arc shape. When receiving pressure transmitted from the spoiler cover 2, the arc shape can prevent the pressure load from concentrating on a certain part of the arc-shaped motion bracket 403, thereby ensuring the reliability of the structure in transmitting pressure and extending the life of the UAV spoiler compartment. Optionally, the connection surface between the spoiler cover 2 and the arc-shaped motion bracket 403 can be configured as a structural arc perpendicular to the arc-shaped motion bracket 403 to ensure that the arc-shaped motion bracket 403 bears pressure evenly.

[0059] The slider 405 is slidably located in the transverse rail groove 404. It is not required that the slider 405 be entirely located in the transverse rail groove 404. As long as the part of the slider 405 that makes sliding contact with the transverse rail groove 404 is located in the transverse rail groove 404, it meets this requirement.

[0060] In some embodiments, such as Figure 1As shown, the motion mechanism includes an arc drive 401, which drives the arc-shaped motion bracket 403 to lift the spoiler cover 2 above the top opening of the cabin body 1 or return to cover the top opening of the cabin body 1.

[0061] With the above configuration, the arc drive 401 can directly drive the arc-shaped motion bracket 403 to open and close the spoiler hatch 2, so that when the spoiler hatch 2 is open, the UAV 5 can land into the cabin 1 or take off from the cabin 1, and when the spoiler hatch 2 is closed, it provides a relatively enclosed space for the UAV 5.

[0062] In this embodiment, as Figure 3 As shown, the arc-shaped motion bracket 403 has an arc-shaped actuator engagement structure 4031. The engagement between the arc-shaped actuator engagement structure 4031 and the arc-shaped actuator 401 is configured to cause the arc-shaped motion bracket 403 to perform arc-shaped motion. The arc-shaped motion causes the slider 405 to slide within the transverse track 404. The slider 405 drives the transverse track 404 to perform linear motion on a line perpendicular to the normal of the UAV take-off and landing platform 3, thereby causing the UAV take-off and landing platform 3 to perform linear motion on its own normal.

[0063] Due to the above configuration, the arc-shaped motion bracket 403 can perform arc-shaped motion under the drive of the arc-shaped actuator 401. Since there is a fixed connection between the slider 405 and the arc-shaped motion bracket 403, the motion trajectory of the slider 405 is also arc-shaped when the arc-shaped motion bracket 403 performs arc-shaped motion. Referring to the conventional method of describing motion in kinematics, the instantaneous velocity direction of the slider 405 is the tangent direction of the arc of the slider 405's motion trajectory at its position. The velocity of the slider 405 can be regarded as a pair of velocities that are perpendicular to each other and of the same magnitude. This pair of velocities changes according to the change of the motion direction of the arc-shaped motion bracket 403: when the arc-shaped motion bracket 403 lifts the spoiler cover 2, the slider 405 moves towards the top opening while moving towards the second side; when the arc-shaped motion bracket 403 drives the spoiler cover 2 back to cover the top opening of the cabin body 1, the slider 405 moves downward while moving towards the first side.

[0064] Since the slider 405 can slide in the first and second directions within the transverse rail groove 404, but the slider 405 is restricted by the structure of the transverse rail groove 404 and cannot move upward or downward within the transverse rail groove 404, when the slider 405 moves upward, it will drive the transverse rail groove 404 to move upward or downward, and at the same time drive the UAV take-off and landing platform 3 to move upward or downward. This achieves the motion characteristics of the UAV take-off and landing platform 3 rising synchronously when the spoiler hatch 2 is open and falling synchronously when the spoiler hatch 2 is closed.

[0065] Optionally, the arc actuator 401 can be a transmission component with meshing transmission characteristics. For example, the arc actuator 401 can be a gear connected to a power source, and correspondingly, the arc actuator mating structure 4031 can be a rack or the like that can mesh with the arc actuator 401. Alternatively, the arc actuator 401 can be a transmission component with friction transmission characteristics. For example, the arc actuator 401 can be a friction wheel connected to a power source, and correspondingly, the arc actuator mating structure 4031 can be a friction surface that can form a frictional fit with the arc actuator 401.

[0066] In some embodiments, such as Figure 1 As shown, the UAV take-off and landing platform 3 has a linear drive mechanism 402. The linear drive mechanism 402 includes an actuator 4021 and a vertical reciprocating motion component 4022. The vertical reciprocating motion component 4022 is fixedly connected to the cabin body 1, and the actuator 4021 is fixedly connected to the UAV take-off and landing platform 3.

[0067] The vertical reciprocating motion component 4022 is configured to move in a straight line perpendicular to the normal line of the UAV take-off and landing platform 3 under the drive of the motion component 4021, thereby causing the UAV take-off and landing platform 3 to rise to the top opening of the cabin body 1 or descend to the bottom of the cabin body 1.

[0068] In some embodiments, the linear drive mechanism 402 may be a drive component that uses fluid as a working medium and utilizes its static pressure to achieve the driving function. For example, the linear drive mechanism 402 may be a hydraulic motion mechanism or a pneumatic motion mechanism.

[0069] When the linear drive mechanism 402 is a hydraulic motion mechanism, the vertical reciprocating motion component 4022 is a hydraulic cylinder. When the pressure of the working fluid inside the hydraulic cylinder increases, the vertical reciprocating motion component 4022 pushes the actuating component 4021 to move upward in the vertical direction, thereby driving the UAV take-off and landing platform 3 to move upward. When the pressure of the working fluid inside the hydraulic cylinder decreases, the vertical reciprocating motion component 4022 drives the actuating component 4021 to move downward in the linear direction, thereby driving the UAV take-off and landing platform 3 to move downward.

[0070] When using the reciprocating motion of a hydraulic cylinder to achieve the take-off and landing of the UAV take-off and landing platform 3, no additional auxiliary motion mechanisms such as reducers are required. The reciprocating motion offers high precision and fast response. The movement position of the UAV take-off and landing platform 3 can be adjusted by regulating the amount of reciprocating motion of the hydraulic cylinder, thereby adjusting the opening and closing degree of the spoiler hatch 2. At the same time, the hydraulic cylinder can withstand greater loads, providing reliable power support for the take-off and landing motion of the UAV take-off and landing platform 3, which carries large UAVs. Furthermore, the hydraulic cylinder can be directly connected to the vehicle's own hydraulic system, and then the hydraulic valve on the hydraulic circuit connected to the vertical reciprocating motion component 4022 can be controlled through the vehicle's own hydraulic control system. This allows the vertical reciprocating motion component 4022 to drive the UAV take-off and landing platform 3 to take off and land without the need for an additional power source.

[0071] When the linear drive mechanism 402 is a pneumatic motion mechanism, the vertical reciprocating motion component 4022 is a pneumatic cylinder. When the pressure of the working fluid inside the pneumatic cylinder increases, the vertical reciprocating motion component 4022 pushes the actuator 4021 to move upward in the vertical direction, thereby driving the UAV take-off and landing platform 3 to move upward. When the pressure of the working fluid inside the pneumatic cylinder decreases, the vertical reciprocating motion component 4022 drives the actuator 4021 to move downward in the linear direction, thereby driving the UAV take-off and landing platform 3 to move downward.

[0072] When using the reciprocating motion of a pneumatic cylinder to achieve the take-off and landing of the UAV take-off and landing platform 3, no additional auxiliary motion mechanisms such as reducers are required. This method offers high precision and fast response, allowing adjustment of the movement of the UAV take-off and landing platform 3 by regulating the amount of reciprocating motion of the pneumatic cylinder, thereby adjusting the opening and closing degree of the spoiler hatch 2. The pneumatic transmission system exhibits superior reliability compared to hydraulic motion mechanisms in harsh working environments such as severe vehicle vibrations. Furthermore, since the working fluid is air, the air can be directly discharged to the atmosphere after the stroke, eliminating the need for additional return air lines. Moreover, the pneumatic cylinder can be directly connected to the vehicle's own air compression system, thereby controlling the pneumatic valve on the compressed gas delivery circuit connected to the vertical reciprocating motion component 4022 through the vehicle's own control system. This allows the vertical reciprocating motion component 4022 to drive the UAV take-off and landing platform 3 without requiring an additional power source.

[0073] In some embodiments, the linear drive mechanism 402 may be a general form of linear motion mechanism such as a lead screw or a linear motor. For example, the linear drive mechanism 402 may be a trapezoidal lead screw or a linear motor.

[0074] When the linear drive mechanism 402 is a trapezoidal lead screw, the vertical reciprocating motion component 4022 is the rod body, and the actuating component 4021 is the lead screw nut. When the rod body rotates around its own axis, the lead screw nut is driven to generate reciprocating motion, thereby driving the UAV take-off and landing platform 3 to move up and down. Since the trapezoidal lead screw has a simple structure and low cost, it can reduce the cost of the UAV spoiler cabin. Furthermore, when the UAV take-off and landing platform 3 is raised to its highest point to provide take-off or parking conditions for the UAV 5, since the trapezoidal lead screw has a self-locking function, there is no need to provide additional braking or motion holding means for the actuating component 4021. Its own friction angle can prevent the actuating component 4021 from moving downward, thereby maintaining the attitude of the UAV take-off and landing platform 3.

[0075] In some embodiments, such as Figure 1 As shown, the linear motion of the UAV take-off and landing platform 3 causes the slider 405 to slide within the transverse track 404. The slider 405 drives the arc-shaped motion bracket 403 to move in an arc, thereby driving the spoiler cover 2 to rise above the top opening of the cabin body 1 or return to cover the top opening of the cabin body 1.

[0076] Due to the above configuration, the UAV landing platform 3 moves up and down under the drive of the linear drive mechanism 402. Since the transverse track 404 restricts the vertical movement of the slider 405, the transverse track 404 moves up and down along with the UAV landing platform 3, simultaneously driving the slider 405 to move up and down. Furthermore, since the slider 405 is fixedly connected to the arc-shaped motion bracket 403, the actual trajectory of the slider 405's movement is the arc-shaped motion bracket 403's arc-shaped motion trajectory. Therefore, while moving up and down with the UAV landing platform 3, the slider 405 simultaneously slides in the transverse track 404 in either the first or second lateral direction. The up-and-down movement and sliding movement of the slider 405 are perpendicular to each other, thus combining to form the arc-shaped motion bracket 403's arc-shaped motion. Therefore:

[0077] When the UAV take-off and landing platform 3 rises, the slider 405 moves upward and slides to the second side, causing the arc-shaped motion bracket 403 to lift the spoiler hatch 2; when the UAV take-off and landing platform 3 descends, the slider 405 moves downward and slides to the first side in the opposite direction, causing the arc-shaped motion bracket 403 to drive the spoiler hatch 2 back to cover the top opening of the cabin body 1, thus achieving the motion characteristics of the UAV take-off and landing platform 3 rising synchronously when the spoiler hatch 2 is open and descending synchronously when the spoiler hatch 2 is closed.

[0078] like Figure 3 and Figure 4In the embodiment shown, in the transmission method in which the arc-shaped motion bracket 403 moves in an arc, causing the slider 405 to move in an arc, thereby driving the UAV take-off and landing platform 3 to move up and down, the two components of the direct decomposition of the slider 405's motion have the effects of driving the slider 405 to slide in the transverse track groove 404 and driving the UAV take-off and landing platform 3 to move up and down.

[0079] In such Figure 1 and Figure 2 In the embodiment shown, the linear drive mechanism 402 drives the UAV take-off and landing platform 3 to move up and down, which in turn drives the slider 405 to move up and down while sliding in the transverse track 404, thereby driving the arc-shaped motion bracket 403 to move in an arc. It can be regarded as the two movements of the slider 405 combined to form the arc-shaped motion bracket 403.

[0080] exist Figure 1 and Figure 2 In the actual movement of the embodiment shown, the linear drive mechanism 402 does not directly drive the slider 405 to slide. This embodiment utilizes the specific movement tendency of the slider 405 after it is fixedly connected to the arc-shaped motion bracket 403. The smaller the angle between the arc-shaped motion bracket 403 and the vertical movement direction of the slider 405, the smaller the sliding tendency of the slider 405. The larger the angle between the arc-shaped motion bracket 403 and the vertical movement direction of the slider 405, the greater the sliding tendency of the slider 405. This sliding tendency is not restricted in the transverse rail groove 404, so the slider 405 slides.

[0081] In some embodiments, such as Figure 5 and Figure 6 As shown, the UAV takeoff and landing platform 3 in the UAV spoiler cabin has a centering mechanism 301, which clamps and secures the UAV 5 after it lands on the UAV takeoff and landing platform 3. The centering mechanism 301 consists of a centering push rod 3011 and a push rod end 3012. When the UAV 5 is not mounted, the push rod end 3012 retracts into the centering push rod 3011, reserving a certain landing space for the UAV 5 on the UAV takeoff and landing platform 3.

[0082] When the spoiler hatch 2 is fully opened and the UAV landing platform 3 rises synchronously to its maximum travel, the spoiler hatch completes the preparation for UAV 5 to land. At this point, UAV 5 can land on UAV landing platform 3 without obstruction in its landing direction. Then, the centering push rod 3011 pushes the push rod end 3012 towards UAV 5, making direct contact between the push rod end 3012 and UAV landing gear 501. The landing gear 501, under the thrust, causes UAV 5 to follow the push rod end 3012, thereby adjusting the position of UAV 5 on UAV landing platform 3. Once UAV 5 enters the predetermined position on UAV landing platform 3, the centering mechanism 301 clamps and secures UAV 5.

[0083] Optionally, the contact surface between the push rod end 3012 and the UAV 5 can be fixedly provided or covered with a flexible material such as silicone or rubber that can produce a certain degree of elastic deformation. When the push rod end 3012 is pushed by the centering push rod 3011 to apply pressure to the UAV landing gear 501, on the one hand, the flexible material can prevent the push rod end 3012 from producing indentations or scratches on the surface of the UAV landing gear 501 during the clamping process; on the other hand, the flexible material can produce a certain degree of elastic deformation, which increases the static friction between the push rod end 3012 and the UAV landing gear 501 when the output thrust of the centering push rod 3011 remains unchanged. When the vehicle is bumped or impacted during driving, the clamping function of the centering mechanism 301 on the UAV 5 can still be guaranteed. Furthermore, a pressure-sensitive sensor can be installed between the push rod end 3012 and the flexible material. The pressure-sensitive sensor is used to transmit the feedback force generated after the push rod end 3012 clamps the drone 5 to the centering mechanism 301, thereby quantitatively determining the tightness of the clamping of the drone 5, so as to form a semi-closed-loop control feedback chain to prevent the drone 5 from being damaged due to excessive pressure or the drone 5 from being not securely fixed on the drone take-off and landing platform 3 due to insufficient clamping force.

[0084] In some embodiments, such as Figure 2 , Figure 5 As shown, the drone landing platform 3 is equipped with a centering mechanism (301) and a wired charger (302). After the drone lands on the drone landing platform 3, the centering mechanism 301 moves and / or clamps and secures the drone 5 on the platform 3. The wired charger 302 has charging contacts 3025 configured to electrically connect to the drone power receiving contacts 502 of the drone 5.

[0085] When the drone 5 needs charging, the charging push rod joint 3021 rotates, causing the charging push rod 3022 to rotate synchronously. The charging push rod 3022 extends so that the charging contact 3024 reaches the vicinity of the drone's power receiving contact 502. At this time, the charging push rod joint 3021 makes a slight movement to further adjust the charging push rod 3022 so that the charging contact 3024 and the charging contact 3025 are roughly aligned. Then, the charging push rod 3022 further advances, pressing the charging contact 3025 of the charging contact 3024 onto the drone's power receiving contact 502. The contact connection point 3023 allows the charging contact 3024 to rotate within a certain range.

[0086] When the drone 5 needs to be charged frequently to improve its range under vehicle-drone collaborative operation conditions, or when the drone 5 is in operation conditions where it is difficult to find a fixed charging power source that is compatible with its power adapter, although the existing vehicle-mounted drone cabin can charge the drone without contact while carrying it after integrating wireless charging equipment, the maximum charging power of the wireless charging equipment is limited by national regulations and cannot meet the drone's fast charging needs.

[0087] With the aforementioned setup, when the drone 5 needs charging, it can enter the drone spoiler compartment for charging, and the wired charger 302 can accurately align with the drone 5's charging contacts 3025 to supply power. Furthermore, since the drone is charged via wired charging, there is no need to restrict the drone's charging power according to relevant national regulations, thus enabling fast charging. Because all types of electric drone batteries require direct DC charging, the wired charger 302 can be powered by the car's battery after installing a DC transformer, or connected to the car's own inverter and then a rectifier when high-power charging is needed, to meet the drone's various charging needs under different circumstances.

[0088] In some embodiments, such as Figure 2 , Figure 5 As shown, the centering mechanism 301 can also be used to move the drone 5 to a preset charging position and clamp and fix it.

[0089] Due to the above settings, such as Figure 3 As shown, when the wired charger 302 enters the preparation stage for charging the drone 5, the rotation range requirement of the charging push rod joint 3021 can be significantly reduced. Furthermore, the rotation of the charging push rod joint 3021 can be restricted such that, after the drone 5 is fixed by the centering mechanism 301, the line connecting the charging contact 3025 and the charging push rod joint 3021 is coplanar and perpendicular to the plane of the drone take-off and landing platform 3. Because the degree of freedom required for the charging push rod joint 3021 is low under this condition, the cost of selecting the charging push rod joint 3021 can be reduced.

[0090] In some embodiments, such as Figure 1 As shown, the cabin body 1 has a lower edge 101, which is a stepped plane formed by deflecting the cabin body 1 at 90° to the first side direction where the first side portion 202 is located and the second side direction where the second side portion 203 is located, respectively, and is arranged symmetrically in the first side direction and the second side direction of the cabin body 1.

[0091] A magnetic block 204 is fixed to the lower part of the spoiler hatch 2 near the first side direction, and an electromagnet 104 is fixed to the lower edge 101 of the hatch body. The electromagnet 104 attracts the magnetic block 204 after being energized. A sealing structure 103 is fixed to the lower edge 101 of the hatch body, and the sealing structure 103 is located on the second side direction of the electromagnet 104.

[0092] The cabin body 1 has an upper edge 102, which is a stepped plane formed by first bending upwards by 90° and then bending away from the UAV take-off and landing platform 3 by 90°, and is symmetrically arranged on both sides of the cabin body 1.

[0093] The first side portion 202 and the second side portion 203 are respectively connected to the upper edge 102 of the cabin body in the first side direction and the upper edge 1021 of the first side direction and the upper edge 1022 of the second side direction. The first side portion 202 and the second side portion 203 extend a certain length in the direction close to the cabin body 1, wherein the extended end of the first side portion 202 is located in the first side direction of the electromagnet 104.

[0094] Due to the above settings, such as Figure 1 As shown, when the drone spoiler cabin is closed, the spoiler cabin cover 2 abuts against the sealing structure 103, forming a protective sealed space with the sealing structure 103 and the cabin body 1, which isolates rainwater, sand and dust, etc. This prevents the drone 5 from leaking electricity or short-circuiting due to the influence of the external humid environment when it is parked and charging on the drone take-off and landing platform 3, thus preventing the drone 5 from suffering from motherboard burn-out, battery failure and other malfunctions. At the same time, it also protects the mating interfaces of various moving mechanisms inside the cabin body 1 from damage and failure due to the intrusion of foreign objects such as sand and gravel.

[0095] Meanwhile, when the electromagnet 104 arranged on the lower edge 101 of the cabin is energized and generates magnetism, the magnetic block 204 with permanent magnetism on the spoiler cover 2 is attracted by the electromagnet 104, and thus an attraction is generated between the electromagnet 104 and the magnetic block 204. This further increases the downforce when the spoiler cover 2 is closed, and also enhances the sealing effect between the spoiler cover 2 and the sealing structure 103. The magnetic block 204 can be a ferromagnetic metal structure such as iron, cobalt and nickel, or a permanent magnet selected to enhance the attraction between it and the electromagnet 104. If the magnetic block 204 is a permanent magnet, its magnetic pole direction must be opposite to the magnetic pole direction of the electromagnet 104 after it is energized.

[0096] like Figure 2 As shown, when the drone spoiler cabin needs to be opened, the electromagnet 104 is de-energized and loses its attraction to the magnetic block 204, allowing the spoiler cabin cover 2 to be opened freely without any other external force. At this time, the sealed maintenance space formed by the spoiler cabin cover 2, the sealing structure 103, and the cabin body 1 is invalid, and the drone 5 is in an unrestricted state and can freely execute action commands such as take-off and hovering.

[0097] In some embodiments, such as Figure 7 As shown, the vehicle has a central control platform 6, which is used to send control information to the drone spoiler cabin and receive status information from the drone spoiler cabin.

[0098] The vehicle's central control platform 6 is also used to receive control signals from the host computer 7 to the drone spoiler bay and to feed back the status information of the drone spoiler bay to the host computer 7.

[0099] When establishing the control loop for the drone spoiler bay from the automotive central control platform 6, the data interface of the platform's own wiring board can be used to centralize the signals from all the input and output wiring of the drone spoiler bay, and then connect them to the central control unit of the platform. Correspondingly, during the design phase of the drone spoiler bay and the selection of control components for each component, the wiring layout characteristics of the vehicle requiring the drone spoiler bay can be referenced to select the appropriate connection method for the control components to the vehicle's electrical circuit.

[0100] The host computer 7 can be a portable mobile terminal, such as a mobile phone or tablet computer; the host computer 7 can exchange data with the car's central control platform 6 through short-range wireless connections such as Bluetooth interconnection technology, or through long-range wireless connections such as cellular networks.

[0101] The following provides further supplementary explanations of the control method and interactive scenarios of the drone spoiler cabin provided in the embodiments of this application.

[0102] When the drone 5 needs the drone spoiler bay to provide parking and storage space and charge it, if the vehicle is in motion and the operator of the drone 5 is inside the car, directly operating the car's central control platform 6 may affect the driver's driving operation and thus create driving risks. At this time, the operator of the drone 5 can use a portable mobile terminal in the form of a host computer 7 to establish a short-range wireless transmission path between the vehicle and the car's central control platform 6 to send the operation command to the backend of the car's central control platform 6 to accept the drone 5. First, control the electromagnet 104 to disconnect. At this time, after the backend of the car's central control platform 6 receives the operation command, it directly sends the control circuit of the drone spoiler bay to the arc driver 401 or the linear drive mechanism 402, thereby controlling the lifting of the drone take-off and landing platform 3 and the opening of the spoiler bay cover 2.

[0103] When the drive power circuit of the arc drive 401 or the linear drive mechanism 402 is self-locking, after the control command issued by the vehicle's central control platform 6 powers the arc drive 401 or the linear drive mechanism 402, the movement of the spoiler cover 2 and the drone landing platform 3 will not stop unless the arc drive 401 drives the spoiler cover 2 or the linear drive mechanism 402 drives the drone landing platform 3 to a predetermined position. That is, a single command is sufficient to move the spoiler cover 2 and the drone landing platform 3 into position. Furthermore, if the spoiler cover 2 and the drone landing platform 3 experience a power failure or other accident during movement and are then powered on again, they will not move unless they receive another command from the vehicle's central control platform 6. This prevents the spoiler cover 2 from continuing to move after power is restored, which could cause accidents such as injuring maintenance personnel or the drone 5.

[0104] When the drive power circuit of the arc driver 401 or the linear drive mechanism 402 is connected in a jog mode, the arc driver 401 or the linear drive mechanism 402 will only move when the signal input terminal of the arc driver 401 or the linear drive mechanism 402 has a high level. That is, the opening and closing degree of the spoiler hatch 2 and the position of the UAV take-off and landing platform 3 can be adjusted more precisely by sending commands multiple times.

[0105] After the spoiler hatch 2 and the drone landing platform 3 reach their predetermined positions, the drone 5 can land on the drone landing platform. At this time, the operator issues a command to the vehicle's central control platform 6 via the host computer 7. The vehicle's central control platform 6 then controls the centering mechanism 301 to perform a centering action, moving the drone 5 to the fixed position on the drone landing platform 3 and clamping it in place. Feedback information indicating that the drone 5 is securely fixed is transmitted from the signal transmission line to the vehicle's central control platform 6 and then to the host computer 7. Subsequently, the operator can control the drone spoiler hatch to close and house the drone 5. Since only changing the current direction of the drive circuit is needed to reverse the movement direction of the arc driver 401 or the linear drive mechanism 402, thereby causing the spoiler hatch 2 and the drone landing platform 3 to move synchronously in opposite directions, the closing method of the drone spoiler hatch will not be described in detail here. After the spoiler hatch is closed, the electromagnet 104 is energized to attract the magnetic block 204, enhancing the sealing effect.

[0106] When the vehicle is parked, the vehicle's central control platform 6 can be directly operated to issue operating commands to the drone spoiler nacelle, thereby controlling the drone spoiler nacelle to perform various actions. At the same time, if the operator needs to operate the drone spoiler nacelle while away from the vehicle and the vehicle is turned off (i.e., the ignition switch is off), the host computer 7 can be operated to activate the memory power of the vehicle's central control platform 6 so that the vehicle's central control platform 6 can issue commands to the drone spoiler nacelle.

[0107] Because of the above setup, operators can remotely control the vehicle's central control platform 6 via the host computer 7 to indirectly control the drone's spoiler cabin under various operating conditions, or directly control the vehicle's central control platform 6 to indirectly control the drone's spoiler cabin.

[0108] Correspondingly, the signal input port of the UAV spoiler nacelle can also be directly connected to the controller's input line to achieve direct control of the UAV spoiler nacelle, thereby expanding the signal input methods of the UAV spoiler nacelle and better realizing its functions.

[0109] It should be noted that any product or technical feature in this embodiment is one or more of a variety of optional technical features or optional products. For the sake of brevity, this document cannot exhaustively list all alternative technical features and alternative products of the present invention, nor is it convenient to emphasize that each implementation of a technical feature is one of a variety of optional implementations. Therefore, those skilled in the art should know that any technical feature or product in this embodiment does not limit the scope of protection of the present invention. The scope of protection of the present invention should include any alternative products that those skilled in the art can conceive of without creative effort.

[0110] In this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "multiple" refers to two or more unless otherwise expressly defined.

[0111] The above description of the disclosed embodiments enables those skilled in the art to readily implement or use the present invention. The above description is merely a general embodiment of the present invention and is not intended to limit the invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0112] The above description is merely for the purpose of enabling those skilled in the art to understand the products of this invention and is not intended to limit the invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A spoiler nacelle for an unmanned aerial vehicle (UAV), characterized in that, The UAV spoiler cabin includes a cabin body (1), a spoiler cover (2), a UAV take-off and landing platform (3), and a motion mechanism (4); The spoiler hatch (2) is detachably adjacent to the first side portion (202) and the second side portion (203) of the vehicle's spoiler; The cabin body (1) is fixed to the vehicle body, the spoiler cover (2) is located on the top opening of the cabin body (1), and the UAV take-off and landing platform (3) is located inside the cabin body (1). The spoiler hatch (2) is connected to the motion mechanism (4), and the UAV take-off and landing platform (3) can move relative to the motion mechanism (4). The motion mechanism (4) is configured to synchronously drive the spoiler hatch (2) to open and close and the UAV take-off and landing platform (3) to rise and fall. The motion mechanism (4) includes an arc-shaped motion bracket (403) and a slider (405). The top of the arc-shaped motion bracket (403) is connected to the spoiler hatch (2). The arc-shaped motion bracket (403) extends from the lower part of the first side of the cabin body (1) to the upper part of the opposite second side. The UAV take-off and landing platform (3) has a transverse track (404), and the slider (405) extends from the arc-shaped motion bracket (403) and is slidably located in the transverse track (404); The motion mechanism includes an arc drive (401); The arc-shaped motion bracket (403) has an arc-shaped actuator engagement structure (4031). The arc-shaped actuator (401) engages with the arc-shaped actuator engagement structure (4031) to drive the arc-shaped motion bracket (403) to move in an arc, thereby lifting the spoiler hatch cover (2) to expose the top opening of the cabin body (1) or returning to cover the top opening of the cabin body (1). The arc-shaped motion bracket (403) causes the slider (405) to slide within the transverse rail groove (404). The slider (405) drives the transverse rail groove (404) to move in a straight line perpendicular to the normal of the UAV take-off and landing platform (3), thereby driving the UAV take-off and landing platform (3) to move in a straight line along the normal.

2. The UAV spoiler cabin according to claim 1, characterized in that, The UAV take-off and landing platform (3) has a linear drive mechanism (402), which includes an actuating component (4021) and a vertical reciprocating component (4022). The vertical reciprocating component (4022) is fixedly connected to the cabin body (1), and the actuating component (4021) is fixedly connected to the UAV take-off and landing platform (3). The vertical reciprocating motion component (4022) is configured to move in a straight line perpendicular to the normal of the UAV take-off and landing platform (3) under the drive of the motion component (4021), thereby causing the UAV take-off and landing platform (3) to rise to the top opening of the cabin body (1) or descend to the bottom of the cabin body (1).

3. The UAV spoiler cabin according to claim 2, characterized in that, The arc-shaped motion bracket (403) is fixedly connected to the slider (405); The lifting and lowering motion of the UAV take-off and landing platform (3) causes the slider (405) to slide in the transverse rail groove (404). The slider (405) drives the arc-shaped motion bracket (403) to move in an arc, thereby driving the spoiler hatch (2) to rise above the top opening of the cabin body (1) or return to cover the top opening of the cabin body (1).

4. The UAV spoiler cabin according to claim 1, characterized in that, The UAV take-off and landing platform (3) is fixed with a centering mechanism (301) and a wired charger (302); After the UAV (5) lands on the UAV take-off and landing platform (3), the centering mechanism (301) moves and / or clamps and fixes the UAV (5) on the UAV take-off and landing platform (3); The wired charger (302) has a charging contact (3025) configured to be electrically connected to the drone power receiving contact (502) of the drone (5).

5. The UAV spoiler cabin according to claim 4, characterized in that, The centering mechanism (301) can also be used to move the drone (5) to a preset charging position and clamp and fix it.

6. The UAV spoiler cabin according to claim 1, characterized in that, The cabin body (1) has a lower edge (101), which is a stepped plane formed by deflecting the cabin body (1) at 90° to the first side direction where the first side portion (202) is located and the second side direction where the second side portion (203) is located, and is arranged symmetrically in the first side direction and the second side direction of the cabin body (1). A magnetic block (204) is fixed to the lower part of the spoiler hatch (2) near the first side direction. An electromagnet (104) is fixed to the lower edge (101) of the hatch body. The electromagnet (104) attracts the magnetic block (204) after being energized. A sealing structure (103) is fixed to the lower edge (101) of the hatch body. The sealing structure (103) is located on the second side direction of the electromagnet (104). The cabin body (1) has an upper edge (102), which is a stepped plane formed by first bending upwards by 90° and then bending away from the UAV take-off and landing platform (3) by 90°, and is symmetrically arranged on both sides of the cabin body (1). The first side portion (202) and the second side portion (203) are respectively connected to the first side upper edge (1021) and the second side upper edge (1022) of the upper edge (102) in the first side direction and the second side upper edge (1022) in the second side direction. The first side portion (202) and the second side portion (203) extend a certain length in the direction close to the cabin body (1), wherein the end of the extended first side portion (202) is located in the first side direction of the electromagnet (104).

7. A vehicle, characterized in that, The vehicle has a drone spoiler cabin as described in any one of claims 1-6.

8. The vehicle according to claim 7, characterized in that, The vehicle has a central control platform (6), which is used to send control information to the UAV spoiler cabin and receive status information of the UAV spoiler cabin; The vehicle central control platform (6) is also used to receive control signals from the host computer (7) to the UAV spoiler cabin and to feed back the status information of the UAV spoiler cabin to the host computer (7).

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