Flying Car and Docking Device

Abstract

The present invention discloses an aerial vehicle and a docking device. The docking device is for an aerial vehicle and includes a movable component and a locking structure. The movable component is installed below the aircraft module of the aerial vehicle and can swing relative to the aircraft module. The locking structure at least includes a first upper locking module, and the first upper locking module is used to be installed at the bottom end of the movable bracket. By providing a movable component that can swing relative to the aircraft module in the present application, when the upper device and the lower device are docked and locked, the situation that the upper locking module located on the movable component is affected by the inclination of the aircraft module and thus affects the docking is reduced, thereby facilitating the locking and docking of the locking structure.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a docking device. The present invention also relates to a flying car including the above docking device. Background Art

[0002] For a segmented flying car, the aircraft module, payload module, and ground driving module of the flying car. When the aircraft module of the flying car needs to approach the payload module and be combined with it through a locking structure.

[0003] The traditional locking structure is the docking of a grab hook and a card slot, a plug rod and a plug slot, a pin and a pin slot, and a lock core and a lock groove. Even when the aircraft and the cockpit are both stationary, during the landing process, affected by air flow and natural wind disturbance, rapid positioning and docking cannot be achieved.

[0004] Therefore, how to facilitate the docking of the locking structure of the flying car is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the Invention

[0005] The purpose of the present invention is to provide a docking device to facilitate the docking of the locking structure of the flying car. Another purpose of the present invention is to provide a flying car including the above docking device.

[0006] To achieve the above purpose, the present invention provides a docking device for a flying car, including:

[0007] An active component installed below the aircraft module of the flying car and capable of swinging relative to the aircraft module;

[0008] A main locking device including at least a first upper locking module for installing at the bottom end of the active component.

[0009] Preferably, the main locking device further includes a first lower locking module for connecting with the lower end device and capable of being snap-locked with the first upper locking module. The first upper locking module and the first lower locking module are provided with a magnetic attraction guiding structure capable of attracting each other.

[0010] Preferably, it further includes an auxiliary locking device. The auxiliary locking device includes a second upper locking module for connecting with the upper end device and a second lower locking module for connecting with the lower end device and capable of being snap-locked with the second upper locking module. The auxiliary locking device is arranged circumferentially around the main locking device.

[0011] Preferably, the movable component includes a movable bracket and a telescopic component connected to the movable bracket, with the telescopic end connected to the first locking module. The telescopic component is used to drive the first locking module to move up and down. The telescopic component includes a plurality of X-shaped rod groups hinged in sequence, a motor, a lead screw, and a slider threadedly connected to the lead screw. The motor drives the lead screw to rotate. The hinge rod at the top of the X-shaped rod group is connected to the slider, and the slider can slide in the direction of the axis of the lead screw.

[0012] Preferably, the movable bracket is rotatably connected to the top end of the telescopic component, and the bottom end of the telescopic component is rotatably connected to the first locking module.

[0013] Preferably, the movable bracket includes a first rotating shaft, a movable block, and a telescopic component mounting block. The top end of the movable block is rotatably connected to the aircraft module through the first rotating shaft. The movable block and the telescopic component mounting block are rotatably connected through a second rotating shaft. The telescopic component is mounted on the telescopic component mounting block. The axes of the first rotating shaft and the second rotating shaft are arranged skew to each other.

[0014] Preferably, the axes of the first rotating shaft and the second rotating shaft are perpendicular to each other.

[0015] Preferably, it further includes a locking structure mounting block, a third rotating shaft and a fourth rotating shaft connected to the upper and lower ends of the locking structure mounting block. The locking structure mounting block is rotatably connected to the lowermost X-shaped rod group through the third rotating shaft. The fourth rotating shaft is rotatably connected to the first locking module. The axes of the third rotating shaft and the fourth rotating shaft are arranged skew to each other.

[0016] Preferably, the axes of the third rotating shaft and the fourth rotating shaft are perpendicular to each other.

[0017] Preferably, it further includes a controller, a first pressure sensor arranged at the position of the mounting surface of the magnetic attraction guiding structure between the first locking module and the first locking module, and a second pressure sensor arranged at the clamping position between the first locking module and the first locking module. When the guiding surface of the first locking module and the magnetic attraction guiding structure of the first locking module are attracted, the controller receives the pressure signal of the first pressure sensor. The controller controls the telescopic component to continue to extend until the first locking module is clamped and locked with the first lower locking module. The controller receives the pressure signal of the second pressure sensor, and the controller controls the telescopic component to contract.

[0018] A flying car, comprising an aircraft module, a payload compartment module, a ground travel module and a docking device, wherein the docking device is the docking device described in any one of the above, and any two of the aircraft module, the payload compartment module and the ground travel module can be connected by the docking device.

[0019] In the above technical solution, the docking device provided by the present invention for a flying car includes a movable component and a locking structure. The movable component is installed below the aircraft module of the flying car and can swing relative to the aircraft module; the locking structure at least includes a first upper locking module, and the first upper locking module is used to be installed at the bottom end of the movable bracket.

[0020] It can be seen from the above description that in the present application, by providing a movable component that can swing relative to the aircraft module, when the upper device and the lower device are docked and locked, the situation that the upper locking module located on the movable component is affected by the inclination of the aircraft module and thus affects the docking is reduced, thereby facilitating the locking structure to lock the docking. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained according to the provided drawings.

[0022] Figure 1 A vertical schematic diagram of the flying car provided by the embodiment of the present invention;

[0023] Figure 2 A three-dimensional schematic diagram of the flying car provided by the embodiment of the present invention in the ground travel mode;

[0024] Figure 3 A three-dimensional schematic diagram of the flying car provided by the embodiment of the present invention in the air flight mode;

[0025] Figure 4 A three-dimensional schematic diagram of the aircraft module provided by the embodiment of the present invention;

[0026] Figure 5 A partially enlarged three-dimensional schematic diagram of the retractable component on the aircraft module provided by the embodiment of the present invention in the retracted state;

[0027] Figure 6 A partially enlarged three-dimensional schematic diagram of the retractable component on the aircraft module provided by the embodiment of the present invention in the extended state;

[0028] Figure 7A three-dimensional structure diagram of the telescopic component in the locking module provided by the embodiment of the present invention in a contracted state;

[0029] Figure 8 A three-dimensional structure diagram of the telescopic component in the locking module provided by the embodiment of the present invention in a contracted state from another perspective;

[0030] Figure 9 A three-dimensional structure diagram of the telescopic component in the locking module provided by the embodiment of the present invention in an extended state;

[0031] Figure 10 A partially enlarged three-dimensional structure diagram of the telescopic component in the aircraft module provided by the embodiment of the present invention in an extended state;

[0032] Figure 11 A three-dimensional schematic diagram of the action process of the telescopic component when the aircraft module approaches the payload module in the aircraft provided by the embodiment of the present invention;

[0033] Figure 12 A partially enlarged three-dimensional schematic diagram of the action process of the telescopic component when the aircraft module approaches the payload module in the aircraft;

[0034] Figure 13 A three-dimensional schematic diagram of the action process after the telescopic component is engaged with the payload compartment provided by the embodiment of the present invention;

[0035] Figure 14 A three-dimensional schematic diagram of the corresponding clamping of the aircraft module and the payload compartment provided by the embodiment of the present invention;

[0036] Figure 15 A three-dimensional schematic diagram of the corresponding clamping of the aircraft module and the payload compartment from another perspective provided by the embodiment of the present invention;

[0037] Figure 16 A three-dimensional schematic diagram of the payload compartment module disengaging from the ground travel module after the aircraft module and the payload compartment module of the present invention are successfully docked;

[0038] Figure 17 A three-dimensional schematic diagram of the payload compartment module disengaging from the ground travel module after the aircraft module and the payload compartment module of the present invention are successfully docked from another perspective;

[0039] Figure 18 A three-dimensional schematic diagram of the aircraft module swaying due to wind disturbance when the aircraft module approaches the payload module provided by the embodiment of the present invention;

[0040] Figure 19 A three-dimensional schematic diagram of the aircraft module swaying due to wind disturbance when the aircraft module approaches the payload module from another perspective provided by the embodiment of the present invention;

[0041] Figure 20 Schematic three-dimensional diagram after docking is completed when the aircraft module is affected by wind disturbance provided by an embodiment of the present invention;

[0042] Figure 21 Schematic structural diagram of the lower locking module provided by an embodiment of the present invention.

[0043] Wherein Figure 1-21 In:

[0044] 1. Aircraft module; 1-1. Aircraft head; 1-2. Aircraft body; 1-3. Aircraft support;

[0045] 2. Payload module; 3. Ground travel module;

[0046] 4. Top locking assembly; 4-1. Movable assembly; 4-1-1. Fourth rotating shaft;

[0047] 4-1-2. Locking structure mounting block; 4-1-2-1. Locking structure mounting leg;

[0048] 4-1-3. Third rotating shaft; 4-1-4. Second rotating shaft; 4-1-5. X-shaped rod group; 4-1-6. Lead screw; 4-1-7. Slide block;

[0049] 4-1-8. Movable block; 4-1-8-1. Telescopic assembly mounting leg;

[0050] 4-1-9. First rotating shaft; 4-1-10. Motor; 4-1-11. Telescopic assembly mounting block;

[0051] 4-2. First upper locking module; 4-2-1. First locking hook; 4-2-2. First mating inclined surface; 4-2-3. First magnetic member; 4-2-4. First groove portion; 4-2-5. Connecting portion; 4-2-6. First guiding inclined surface;

[0052] 4-3. Second upper locking module;

[0053] 5. Bottom locking assembly;

[0054] 5-1. Second magnetic member; 5-2. First lower locking module; 5-3. Second lower locking module. Specific embodiments

[0055] The core of the present invention is to provide a docking device to facilitate the docking of the locking structure of a flying car. Another core of the present invention is to provide a flying car including the above docking device.

[0056] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the drawings and embodiments.

[0057] Please refer to Figures 1 to 21 .

[0058] In a specific embodiment, the docking device provided by the specific embodiment of the present invention for a flying car includes a movable component 4-1 and a locking structure. The movable component 4-1 is installed below the aircraft module 1 of the flying car and can swing relative to the aircraft module 1; the locking structure at least includes a first upper locking module 4-2, and the first upper locking module 4-2 is used to be installed at the bottom end of the movable bracket.

[0059] When the flying car needs to work in the air flight mode, the aircraft module 1 flies above the ground driving module 3 carrying the load cabin module 2 (the ground driving module 3 carrying the load cabin module 2 is as Figure 2 shown), precisely hovers at a fixed point, docks and locks with the load cabin module 2 through the docking device, unlocks the ground driving module 3 and the load cabin module 2, and the aircraft module 1 hangs the load cabin module 2 and takes off vertically, as Figure 3 shown, to complete the automatic flight mission in an unmanned manner.

[0060] When the flying car needs to work in the ground driving mode, the aircraft module 1 (as Figure 3 shown) hangs the load cabin module 2 and flies above the ground driving module 3, precisely hovers at a fixed point, automatically places the load cabin module 2 on the ground driving module 3, unlocks the aircraft module 1 and the load cabin module 2, the aircraft module 1 automatically takes off vertically and flies away from the load cabin module 2, the ground driving module 3 and the load cabin module 2 are automatically docked and locked, and the ground driving module 3 carries the load cabin module 2 and drives to the target destination in an autonomous driving manner to complete the ground driving mission.

[0061] It can be seen from the above description that in the present application, by setting the movable component 4-1 that can swing relative to the aircraft module 1, when the upper device and the lower device are docked and locked, the situation that the upper locking module located on the movable component 4-1 is affected by the inclination of the aircraft module and thus affects the docking is reduced, which facilitates the locking structure to lock and dock.

[0062] Of course, in order to avoid docking errors, preferably, a magnetic member is provided between the first upper locking module 4-2 and the first lower locking module 5-2, and no magnetic member is provided between the second upper locking module 4-3 and the second lower locking module 5-3.

[0063] In a specific embodiment, the main locking device further includes a first lower locking module 5-2 for connecting with the lower device and capable of being clamped and locked with the first upper locking module 4-2, and the first upper locking module 4-2 and the first lower locking module 5-2 are provided with a magnetic attraction guiding structure capable of mutually attracting each other.

[0064] Specifically, the first upper locking module 4-2 is a first upper locking hook, and the first lower locking module 5-2 is a first lower locking hook. A first magnetic member 4-2-3 is installed at the lowermost end of the first upper locking hook. Correspondingly, a locking structure capable of cooperating with the first upper locking hook is provided at the top of the first lower locking hook, and a second magnetic member 5-1 is installed at the locking structure. Preferably, both the first magnetic member 4-2-3 and the second magnetic member 5-1 are electromagnets, that is, the first magnetic member 4-2-3 is a first electromagnet, and the second magnetic member 5-1 is a second electromagnet.

[0065] During operation, after the first electromagnet and the second electromagnet are powered on, the magnetic fields of the two electromagnets are opposite. When the X-shaped rod group installed on the aircraft body extends to a certain position, the first electromagnet of the first locking hook and the second electromagnet at the top of the payload module 2 attract each other, and the magnetic fields interact with each other, causing the first upper locking hook and the locking structure to be attracted and engaged with each other.

[0066] To improve the connection stability, preferably, the docking device further includes an auxiliary locking device. The auxiliary locking device includes a second upper locking module 4-3 for connecting with the upper device and a second lower locking module 5-3 for connecting with the lower device and capable of being snap-locked with the second upper locking module 4-3. The auxiliary locking device is arranged circumferentially around the main locking device. Specifically, there are multiple auxiliary locking devices, and the auxiliary locking devices are symmetrically distributed on opposite sides of the main locking device.

[0067] Or a plurality of auxiliary locking devices are circumferentially and evenly distributed around the main locking device.

[0068] Or a plurality of the auxiliary locking devices are symmetrically distributed on opposite sides of the main locking device, and an auxiliary setting device is distributed in front of the main locking device.

[0069] Such as Figure 7 and Figure 8As shown, in a specific embodiment, the movable component 4-1 includes a movable bracket and a telescopic component connected to the movable bracket, and the telescopic end is connected to the first locking module 4-2. The telescopic component is used to drive the first locking module 4-2 to move up and down. The telescopic component includes a plurality of X-shaped rod groups 4-1-5, a motor 4-1-10, a lead screw 4-1-6, and a slider 4-1-7 threadedly connected to the lead screw 4-1-6, which are sequentially hinged. The motor 4-1-10 drives the lead screw 4-1-6 to rotate. The hinge rod at the top of the X-shaped rod group 4-1-5 is connected to the slider 4-1-7. Specifically, the hinge rod is fixedly connected to the slider 4-1-7, and the hinge rod is hinged to the X-shaped rod body of the X-shaped rod group 4-1-5. The slider 4-1-7 can slide in the axial direction of the lead screw 4-1-6. Among them, the motor 4-1-10 drives the slider 4-1-7 to slide on the lead screw 4-1-6, thereby sequentially driving the opening and closing movement of the X-shaped rod group 4-1-5. This opening and closing movement realizes the elongation and contraction of the telescopic component, so that the first locking hook moves downward to approach the load compartment module 2. When the telescopic component is arranged below the load compartment module 2, the motor 4-1-10 drives the slider 4-1-7 to slide on the lead screw 4-1-6, thereby sequentially driving the opening and closing movement of the X-shaped rod group 4-1-5. This opening and closing movement realizes the elongation and contraction of the telescopic component, so that the first locking hook moves downward to approach the ground driving module 3.

[0070] In a specific embodiment, when there is a magnetic part between the first upper locking module 4-2 and the first lower locking module 5-2, and there is no magnetic part between the second upper locking module 4-3 and the second lower locking module 5-3, during specific docking, due to the magnetic adsorption effect, the first upper locking module 4-2 and the first lower locking module 5-2 first align their positions, and then are driven by the telescopic component (specifically, the X-shaped rod group 4-1-5) to complete the docking first. Then, the telescopic component drives the second upper locking module 4-3 to move downward, and the second upper locking module 4-3 and the second lower locking module 5-3 approach each other to complete the docking.

[0071] When not working, the telescopic component is in a contracted and folded state, which is convenient for flight.

[0072] Preferably, the movable bracket is rotatably connected to the top end of the telescopic component, and the bottom end of the telescopic component is rotatably connected to the first locking module 4-2.

[0073] Specifically, the movable bracket includes a first rotating shaft 4-1-9, a movable block 4-1-8, and a telescopic component mounting block 4-1-11. The top end of the movable block 4-1-8 is rotatably connected to the aircraft module 1 through the first rotating shaft 4-1-9. The movable block 4-1-8 and the telescopic component mounting block 4-1-11 are rotatably connected through a second rotating shaft 4-1-4. The telescopic component is mounted on the telescopic component mounting block 4-1-11. The axes of the first rotating shaft 4-1-9 and the second rotating shaft 4-1-4 are arranged skew to each other.

[0074] Preferably, the axis of the first rotating shaft 4-1-9 and the axis of the second rotating shaft 4-1-4 are arranged perpendicular to each other. As Figure 5 and Figure 6 shown, the telescopic assembly is connected to the bottom of the aircraft body of the aircraft module 1 through a movable bracket. The movable bracket is embedded inside the aircraft body 1-2. The lower end of the telescopic assembly is connected to the first locking hook. The upper part of the movable bracket is provided with the first rotating shaft 4-1-9 in the front-back direction, and its lower part is provided with the second rotating shaft 4-1-4 in the left-right direction. The upper end of the telescopic assembly is movably connected to the lower end of the movable bracket. The telescopic assembly can rotate relative to the movable bracket around the front-back direction and the left-right direction respectively through the first rotating shaft 4-1-9 and the second rotating shaft 4-1-4.

[0075] To facilitate the installation of the second rotating shaft 4-1-4, two telescopic assembly mounting legs 4-1-8-1 are provided at the bottom end of the movable block 4-1-8. The two telescopic assembly mounting legs 4-1-8-1 are located on the opposite sides of the telescopic assembly mounting block 4-1-11, and each telescopic assembly mounting leg 4-1-8-1 is respectively provided with a second rotating shaft 4-1-4.

[0076] Specifically, the docking device further includes a locking structure mounting block 4-1-2, a third rotating shaft 4-1-3 and a fourth rotating shaft 4-1-1 connected to the upper and lower ends of the locking structure mounting block 4-1-2. The locking structure mounting block 4-1-2 is rotatably connected to the lowermost X-shaped rod group 4-1-5 through the third rotating shaft 4-1-3. The fourth rotating shaft 4-1-1 is rotatably connected to the first locking module 4-2. The axis of the third rotating shaft 4-1-3 and the axis of the fourth rotating shaft 4-1-1 are arranged skew to each other.

[0077] Preferably, the axis of the third rotating shaft 4-1-3 and the axis of the fourth rotating shaft 4-1-1 are arranged perpendicular to each other. The third rotating shaft 4-1-3 is arranged in the front-back direction on the X-shaped rod group 4-1-5 at the lowermost part of the telescopic assembly, and the fourth rotating shaft 4-1-1 is arranged in the left-right direction. The upper end of the first locking hook is movably connected to the lower end of the X-shaped rod group. The first locking hook can rotate relative to the X-shaped rod group 4-1-5 around the front-back direction and the left-right direction respectively through the third rotating shaft 4-1-3 and the fourth rotating shaft 4-1-1.

[0078] To facilitate the installation of the fourth rotating shaft 4-1-1, the locking structure mounting block 4-1-2 is provided with two locking structure mounting legs 4-1-2-1. The two locking structure mounting legs 4-1-2-1 are located on the opposite sides of the locking structure mounting block 4-1-2, and each locking structure mounting leg 4-1-2-1 is respectively provided with a fourth rotating shaft 4-1-1.

[0079] As Figure 18 and Figure 19As shown in the figure, when the aircraft module 1 in flight state approaches the payload module 2, a three-dimensional schematic diagram of the aircraft module 1 swaying due to wind disturbance. Through the first rotating shaft 4-1-9, the second rotating shaft 4-1-4, the third rotating shaft 4-1-3 and the fourth rotating shaft 4-1-1, the first locking hook can flexibly adjust its attitude in two directions at the upper and lower ends of the telescopic assembly, so as to accurately dock with the locking structure of the lower payload module 2.

[0080] The first upper locking module 4-2 includes a first locking hook 4-2-1. The first locking hook 4-2-1 includes a connecting portion 4-2-5, a first groove portion 4-2-4 and a first guiding portion with a gradually decreasing outer dimension from top to bottom. The bottom end of the first guiding portion is provided with a first guiding inclined surface 4-2-6 and first mating inclined surfaces 4-2-2 arranged on opposite sides of the first guiding inclined surface 4-2-6 and with edges connected to the first guiding inclined surface 4-2-6. The connecting portion 4-2-5 is movably connected to the telescopic assembly. The first groove portion 4-2-4 has a groove provided on the side surface. The lowermost end of the first guiding portion forms a tip. In this embodiment, the tip is in the shape of a frustum of a cone, including a first guiding inclined surface 4-2-6 and three first mating inclined surfaces 4-2-2. The first guiding inclined surface 4-2-6 and the groove of the first groove portion 4-2-4 are on the same side of the first upper locking module 4-2.

[0081] As an implementable way, the first upper locking module 4-2 and the second upper locking module 4-3 are locking hooks with the same structure. The first lower locking module 5-2 and the second lower locking module 5-3 are locking hooks with the same structure. The second upper locking module 4-3 can specifically be a second locking hook. The second lower locking module 5-3 is a second lower locking hook. The second locking hook is rotatably connected to the top of the payload module 2. Electromagnets are provided on the second locking hook, and electromagnets are also provided on the second lower locking hook. The electromagnets attract each other after being energized. The mutual attraction of the electromagnets has a guiding effect on the first upper locking module 4-2 and the second upper locking module 4-3, so that the first upper locking module 4-2 and the second upper locking module 4-3 can enter the opening of the locking groove of the corresponding locking structure under the suction force until the first upper locking module 4-2 and the second upper locking module 4-3 completely fall into the corresponding locking groove and are fully engaged and clamped with the first lower locking module 5-2 and the second lower locking module 5-3.

[0082] Specifically, the movable assembly 4-1, the first upper locking module 4-2 and the second upper locking module 4-3 are installed as the top locking assembly 4 at the bottom end of the aircraft module 1 and the bottom end of the payload module 2. The first lower locking module 5-2 and the second lower locking module 5-3 are installed as the bottom locking assembly 5 at the top end of the payload module 2 and the top end of the ground driving module 3.

[0083] The docking device further includes a controller, a first pressure sensor disposed at the mounting surface position of the magnetic attraction guiding structure between the first upper locking module 4-2 and the first upper locking module 4-2, and a second pressure sensor disposed at the clamping position between the first upper locking module 4-2 and the first lower locking module 5-2. When the guiding surface of the first upper locking module 4-2 and the magnetic attraction guiding structure of the first upper locking module 4-2 are attracted, the controller receives the pressure signal of the first pressure sensor, and the controller controls the telescopic assembly to continue to extend until the first upper locking module 4-2 is clamped and locked with the first lower locking module 5-2. The controller receives the pressure signal of the second pressure sensor, that is, the controller receives the docking completion signal, and the controller controls the telescopic assembly to contract. Of course, a second pressure sensor can also be disposed at the locking position between the second upper locking module 4-3 and the second lower locking module 5-3. When the controller receives the pressure signals of all the second pressure sensors, it determines that the locking is completed, and the controller controls the telescopic assembly to contract until the telescopic assembly contracts to the minimum size.

[0084] Specifically, the controller controls the motor 4-1-10 to rotate forward and backward, driving the slider 4-1-7 to reciprocate, thereby realizing the extension and contraction of the X-shaped rod group 4-1-5.

[0085] By setting the first pressure sensor, the situation of clamping under the condition of incorrect docking of the docking device is avoided, and the telescopic assembly contracts after the docking device is locked through the second pressure sensor, improving the connection stability of the docking device.

[0086] When the aircraft module 1 needs to dock with the payload module 2 in the ground driving state and switch to the flight mode, the aircraft first finds the allocated ground driving module 3 (i.e., the unmanned vehicle) carrying the payload module 2 (cockpit) according to the scheduling information of the control system, and hovers at a certain height above the cockpit that is in a safe area and stationary. This height is within the reachable range after the telescopic assembly extends. At this time, the aircraft module 1 establishes communication with the payload module 2 and starts the docking procedure. The motor 4-1-10 drives the slider 4-1-7 to slide on the lead screw. In this embodiment, the motor 4-1-10 drives the lead screw to drive the slider 4-1-7 to move backward, pushing the X-shaped rod group to gradually unfold and gradually extend vertically towards the cockpit to achieve subsequent docking.

[0087] After the aircraft module 1 and the payload module 2 complete docking, the payload module 2 detaches from the ground driving module 3 and switches to the air flight mode. Specifically, the attitude of the aircraft module 1 can be controlled by adjusting the rotation speeds of the ducted thrusters or open rotors symmetrically distributed front and back, left and right on the aircraft module 1, changing the lift of different ducts or rotors.

[0088] A flying car provided by the present application includes an aircraft module 1, a payload module 2, a ground driving module 3 and a docking device, and the docking device is any of the above docking devices. The specific structure of the docking device has been described above. The present application includes the above docking device and also has the above technical effects. Specifically, the aircraft module 1 is a vertical takeoff and landing aircraft driven by multi-ducts or multi-rotors in a distributed manner, the payload module 2 can be divided into a passenger or cargo cabin, and the ground driving module 3 is a wheeled driverless chassis.

[0089] Among them, any two of the aircraft module 1, the payload module 2, and the ground driving module 3 can be connected through the docking device. Specifically, the movable component 4-1 can be installed below the aircraft module 1, and the movable component 4-1 can also be installed below the payload module 2. That is, a docking device is installed between the aircraft module 1 and the payload module 2, and a docking device is installed between the payload module 2 and the ground driving module 3.

[0090] Specifically, the aircraft module 1 includes an aircraft head 1-1, an aircraft body 1-2, and an aircraft support 1-3 provided at the bottom end of the aircraft body. When the aircraft module 1 lands on the ground, it is supported by the aircraft support 1-3.

[0091] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other.

[0092] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A docking device for a flying car, characterized in that, Comprising: An active component (4-1) installed below the aircraft module (1) of the flying car and capable of swinging relative to the aircraft module (1); A main locking device, at least including a first upper locking module (4-2), and the first upper locking module is installed at the bottom end of the active component (4-1); The main locking device further includes a first lower locking module (5-2) connected to the lower end device and capable of being snap-locked with the first upper locking module (4-2). The first upper locking module (4-2) and the first lower locking module (5-2) are provided with a magnetic attraction guiding structure capable of attracting each other; The active component (4-1) includes an active bracket and a telescopic component connected to the active bracket, and the telescopic end of the telescopic component is connected to the first upper locking module (4-2). The telescopic component is used to drive the first upper locking module (4-2) to move up and down. The telescopic component includes a plurality of X-shaped rod groups (4-1-5) hinged in sequence, a motor (4-1-10), a lead screw (4-1-6), and a slider (4-1-7) threadedly connected to the lead screw (4-1-6). The motor (4-1-10) drives the lead screw (4-1-6) to rotate. The hinge rod at the top of the X-shaped rod group (4-1-5) is connected to the slider (4-1-7), and the slider (4-1-7) can slide in the axial direction of the lead screw (4-1-6); The active bracket is rotatably connected to the top end of the telescopic component, and the bottom end of the telescopic component is rotatably connected to the first upper locking module (4-2).

2. The docking device according to claim 1, characterized in that, It further includes an auxiliary locking device. The auxiliary locking device includes a second upper locking module (4-3) connected to the upper end device and a second lower locking module (5-3) used for connecting to the lower end device and capable of being snap-locked with the second upper locking module (4-3). The auxiliary locking device is arranged circumferentially around the main locking device.

3. The docking device according to claim 1, characterized in that, The active bracket includes a first rotating shaft (4-1-9), an active block (4-1-8), and a telescopic component mounting block (4-1-11). The top end of the active block (4-1-8) is rotatably connected to the aircraft module (1) through the first rotating shaft (4-1-9). The active block (4-1-8) and the telescopic component mounting block (4-1-11) are rotatably connected through a second rotating shaft (4-1-4). The telescopic component is installed on the telescopic component mounting block (4-1-11). The axes of the first rotating shaft (4-1-9) and the second rotating shaft (4-1-4) are arranged in a skew manner.

4. The docking device according to claim 3, characterized in that, The axes of the first rotating shaft (4-1-9) and the second rotating shaft (4-1-4) are perpendicular to each other.

5. The docking device according to claim 3, characterized in that, It further includes a locking structure mounting block (4-1-2), a third rotating shaft (4-1-3) and a fourth rotating shaft (4-1-1) connected to the upper and lower ends of the locking structure mounting block (4-1-2). The locking structure mounting block (4-1-2) is rotatably connected to the lowermost X-shaped rod group (4-1-5) through the third rotating shaft (4-1-3). The fourth rotating shaft (4-1-1) is rotatably connected to the first upper locking module (4-2). The axis of the third rotating shaft (4-1-3) and the axis of the fourth rotating shaft (4-1-1) are arranged skew.

6. The docking device according to claim 5, characterized in that, The axis of the third rotating shaft (4-1-3) and the axis of the fourth rotating shaft (4-1-1) are arranged perpendicular to each other.

7. The docking device according to claim 1, characterized in that, It further includes a controller, a first pressure sensor arranged at the mounting surface position of the magnetic attraction guiding structure between the first upper locking module (4-2) and the first upper locking module (4-2), and a second pressure sensor arranged at the clamping position between the first upper locking module (4-2) and the first upper locking module (4-2). When the guiding surface of the first upper locking module (4-2) and the magnetic attraction guiding structure of the first upper locking module (4-2) are attracted, the controller receives the pressure signal of the first pressure sensor, and the controller controls the telescopic assembly to continue to extend until the first upper locking module (4-2) is clamped and locked with the first lower locking module (5-2). The controller receives the pressure signal of the second pressure sensor, and the controller controls the telescopic assembly to contract.

8. A flying car, characterized in that, It includes an aircraft module (1), a payload cabin module (2), a ground travel module (3) and a docking device. The docking device is the docking device according to any one of claims 1-7. Any two of the aircraft module (1), the payload cabin module (2) and the ground travel module (3) can be connected through the docking device.

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