Split type intelligent butt joint new energy hovercar

Abstract

The invention discloses a split type intelligent butt joint new energy hovercar which comprises a ground driving module, a flying module, a functional cabin, a flying device and a rapid butt joint module, and the flying device comprises a machine body, four groups of rotor wing units and an automatic lifting undercarriage; and the quick docking module comprises an electromagnetic pre-positioning unit and a mechanical locking unit and is used for realizing quick connection and separation between the functional cabin and the flight device. The electromagnetic pre-positioning ring adopts a Halbach array magnetic field generation mode, and the functional cabin and the flight device are guided to be automatically aligned through the magnetic field gradient. The current intensity is adjusted according to the butt joint distance, and other metal objects are prevented from being sucked mistakenly. The magnetic force disappears automatically after power failure, and accidental locking is prevented. The mechanical locking unit adopts four bolts which are symmetrically distributed, and locking can still be kept when a single point loses efficacy. And an electro-hydraulic servo system is used for driving, millisecond-level response is achieved, after the plug pin is inserted, the hydraulic cylinder is pressurized to 20 MPa to drive the clamping jaw, and zero-clearance locking is ensured.

Description

Technical Field

[0001] The present invention belongs to the technical field of flying devices, and particularly relates to a split-type intelligent docking new energy flying car. Background Art

[0002] Traditional cars are only limited to driving on ground roads, relying on the existing road network, and are vulnerable to traffic congestion and road damage. They cannot pass quickly when the roads are closed or there is a traffic jam, and the response speed is limited. Driving on the ground requires following the road plan, which may increase the driving distance and energy consumption. A large number of ground parking lots are needed, occupying urban space. The whole vehicle needs to be maintained, and the vehicle cannot be used at all during the maintenance period.

[0003] When existing flying cars are flying, the land walking module and the flying device of the flying car are integrated. When walking on land, the land walking module is started, and when flying, the flying device is started. However, both the land walking module and the flying device are installed on the car, which will cause the weight of the car to increase, increase the fuel consumption of land walking, and the whole vehicle needs to be maintained, and the vehicle cannot be used at all during the maintenance period.

[0004] For example, the Chinese invention patent with the publication number CN117021859A discloses an amphibious car. The flying device and the vehicle are designed as an integral body, resulting in a large weight of the whole vehicle, increasing the fuel consumption of land walking, and the whole vehicle needs to be maintained, and the vehicle cannot be used at all during the maintenance period. For example, the Chinese invention patent with the publication number CN112238717A discloses a flying car, which consists of a vehicle body and a detachable flying device, but there are problems such as insufficient flexibility, single energy management, and single coupling method between the logistics cabin / occupant cabin and the flying module. Similar amphibious cars with the above problems also include: the flying car with the publication number CN116572681A; the separated type land-sea-air vehicle with the publication number CN119099728A; the split-type flying car with the publication number CN118288713A.

[0005] Therefore, a split-type intelligent docking new energy flying car is urgently needed to be proposed. Summary of the Invention

[0006] To solve the defects existing in the prior art, the present invention provides a split-type intelligent docking new energy flying car.

[0007] To solve the above technical problems, the present invention provides the following technical solutions:

[0008] The present invention provides a split-type intelligent docking new energy flying car, including:

[0009] A ground driving module, having an independent driving system and a driving control unit;

[0010] A flight module, having an independent flight drive system and a flight control unit;

[0011] A functional cabin, including a personnel cabin and / or a logistics cabin, the functional cabin being connected to a ground travel module or a flight module;

[0012] A flight device, including a fuselage, and four groups of rotor units and an automatic lifting landing gear arranged on the fuselage, the flight device being connected to the flight module;

[0013] A quick docking module, including an electromagnetic pre-positioning unit and a mechanical locking unit, for realizing quick connection and separation between the functional cabin and the flight device.

[0014] Preferably, the four groups of rotor units are detachably mounted on the fuselage, and the four groups of rotor units are symmetrically distributed around the fuselage.

[0015] Preferably, the rotation directions of two of the four groups of rotor units are opposite to each other.

[0016] Preferably, the automatic lifting landing gear is provided with multi-stage hydraulic shock-absorbing struts.

[0017] Preferably, the electromagnetic pre-positioning unit includes an alloy housing, an electromagnetic pre-positioning ring and UVW sensors mounted at the bottom of the fuselage, and a magnet guiding ring mounted at the top of the functional cabin, the electromagnetic pre-positioning ring is located inside the alloy housing, and the electromagnetic pre-positioning ring is a groove structure distributed in a ring shape.

[0018] Preferably, the magnetic permeability of the alloy housing is ≥50000, and the thickness is 1.5±0.1 mm, for suppressing external magnetic field interference;

[0019] The electromagnetic pre-positioning ring adopts the Halbach array magnetic field generation method, and generates an adsorption force of ≥500 kg / m 2 after being energized.

[0020] Preferably, the mechanical locking unit includes a conical guiding pin and a hydraulic claw, the conical guiding pin is mounted at the bottom of the fuselage and located inside the electromagnetic pre-positioning ring, and the hydraulic claw is mounted at the top of the functional cabin and located inside the magnet guiding ring.

[0021] Preferably, the locking pressure of the conical guiding pin and the hydraulic claw is ≥15 MPa

[0022] Preferably, the ground travel module, the flight module, the functional cabin, the flight device, and the quick docking module are all equipped with independent energy storage devices, supporting solid-state batteries and / or hydrogen-electric hybrid power sources.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] In the present invention, the electromagnetic pre-positioning ring adopts the Halbach array magnetic field generation method, which generates an adsorption force of ≥ 500 kg / m after being energized. The electromagnetic pre-positioning ring automatically aligns the functional cabin and the flying device through the magnetic field gradient (error < 1 cm). The current intensity is adjusted according to the docking distance (enhanced in the near field and weakened in the far field) to avoid accidentally attracting other metal objects. After power-off, the magnetic force automatically disappears to prevent accidental locking. The mechanical locking unit uses 4 pins symmetrically distributed, and the locking can still be maintained even in case of single-point failure. Driven by an electro-hydraulic servo system with millisecond-level response, after the pins are inserted, the hydraulic cylinder pressurizes to 20 MPa to drive the jaws to ensure zero-clearance locking. 2 Description of the Drawings

[0025] Figure 1 Fig. is a schematic diagram of the overall structure of a split-type intelligent docking new energy flying vehicle in Embodiment 1 of the present invention;

[0026] Figure 2 Fig. is a schematic diagram of the overall structure of the quick docking module in Embodiment 1 of the present invention;

[0027] Figure 3 Fig. is a schematic diagram of the structure of the quick docking module before docking in Embodiment 1 of the present invention;

[0028] Figure 4 Fig. is a schematic diagram of the structure of the quick docking module after docking in Embodiment 1 of the present invention;

[0029] Figure 5 Fig. is a schematic diagram of the overall structure of the mechanical locking unit in Embodiment 2 of the present invention;

[0030] Figure 6 Fig. is a schematic diagram of the structure of the guide pin in Embodiment 2 of the present invention;

[0031] Figure 7 Fig. is a schematic diagram of the structure of the mechanical locking unit before docking in Embodiment 2 of the present invention;

[0032] Figure 8 Fig. is a schematic diagram of the structure of the mechanical locking unit after docking in Embodiment 2 of the present invention;

[0033] Figure 9 Fig. is a schematic diagram of the overall structure of the mechanical locking unit in Embodiment 3 of the present invention;

[0034] Figure 10 Fig. is a schematic diagram of the structure of the cross jaws in Embodiment 3 of the present invention;

[0035] Figure 11 Fig. is a schematic diagram of the structure of the mechanical locking unit after docking in Embodiment 3 of the present invention;

[0036] Figure 12 Fig. is a schematic diagram of the overall structure of the mechanical locking unit in Embodiment 4 of the present invention;

[0037] Figure 13 It is a schematic structural view of the spherical pin in Embodiment 4 of the present invention;

[0038] Figure 14 It is a schematic structural view of the mechanical locking unit before docking in Embodiment 4 of the present invention;

[0039] Figure 15 It is a schematic structural view of the shape memory alloy spring without power supply in Embodiment 4 of the present invention;

[0040] Figure 16 It is a schematic structural view of the mechanical locking unit after docking in Embodiment 4 of the present invention. Detailed implementation manners

[0041] The following describes the preferred embodiments of the present invention with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only for the purpose of illustrating and explaining the present invention, and are not used to limit the present invention.

[0042] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "top", "bottom", "upper", "lower", etc. are all based on the orientation or positional relationships shown in the drawings of the specification Figure 1 merely for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

[0043] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0044] Embodiment 1

[0045] As Figures 1 to 4 shown, this embodiment provides a split-type intelligent docking new energy flying vehicle, including a ground driving module 1, a flight module 2, a functional cabin 3, a flight device 4, and a quick docking module 5.

[0046] In this embodiment, the ground driving module 1 has an independent driving system and a driving control unit for controlling and driving the functional cabin to travel on the ground.

[0047] In this embodiment, the flight module 2 has an independent flight driving system and a flight control unit for controlling the flight device to fly alone or the flight device to drive the functional cabin to fly.

[0048] In this embodiment, the functional cabin 3 includes a personnel cabin and a logistics cabin. The functional cabin 3 is connected to the ground driving module 1 or the flight module 2. It is controlled to drive through the ground driving module in the road driving mode and to fly through the flight module in the flight mode. The personnel cabin and the logistics cabin are switched for use. During the peak daytime hours, the personnel cabin is carried to achieve commuting transportation (with a passenger capacity of 4 - 6 people), and during the low - valley nighttime hours, it is switched to the logistics cabin for cargo distribution (with a volume of 3 - 4m 3 ³), and the equipment utilization rate is increased from 35% of the traditional single - mode to 78%.

[0049] In this embodiment, the flying device 4 includes a fuselage 41, and four groups of rotor units 42 and an automatic lifting landing gear 43 arranged on the fuselage 41. The flying device 4 is connected to the flight module 2. The four groups of rotor units 42 are detachably installed on the fuselage 41, and the four groups of rotor units 42 are symmetrically distributed around the fuselage 41.

[0050] Specifically, the rotation directions of the two rotor units in each of the four groups of rotor units 42 are opposite to each other. There is no need for a tail rotor or a complex transmission structure, and the failure rate is low. It can take off and land vertically, move horizontally in all directions (front, back, left, and right), and rotate in place, adapting to narrow spaces. There are no complex mechanical components, and the maintenance cost is low. The rotor is designed as a separate module, that is, each rotor unit is an independent detachable and replaceable modular component. Each rotor unit includes a motor, an electronic speed controller (ESC), a propeller, a heat dissipation system, and an interface, forming a complete power unit. When quickly maintaining and replacing a single - rotor failure, there is no need to disassemble the machine. Just directly replace the separate rotor module, reducing the downtime. Only replace the damaged parts, avoiding the scrapping of the whole machine and reducing the usage cost.

[0051] Specifically, the automatic lifting landing gear 43 is provided with a multi - stage hydraulic shock - absorbing strut 44. When flying, the automatic lifting landing gear is retracted, which can significantly reduce the air resistance, thereby increasing the flight speed and endurance time. It can also reduce the airflow interference and improve the flight attitude stability, which is remarkable in high - speed flight or windy environments. The multi - stage hydraulic shock - absorbing strut 44 absorbs the ground impact force through hydraulic damping or air pressure buffering (such as a multi - stage oil cylinder) during landing, reducing the vibration transmission to the fuselage and the functional cabin. It can absorb more than 90% of the impact load and protect precision equipment from hard - landing damage.

[0052] In this embodiment, the quick - docking module 5 includes an electromagnetic pre - positioning unit 6 and a mechanical locking unit 7, which are used to achieve the quick connection and separation between the functional cabin 3 and the flying device 4.

[0053] Such as Figures 2 to 4As shown in the figure, the electromagnetic pre-positioning unit 6 includes an alloy housing 61, an electromagnetic pre-positioning ring 62 and a UVW sensor 63 installed at the bottom of the fuselage 41, and a magnet guiding ring 64 installed at the top of the functional cabin 3. The magnetic permeability of the alloy housing 61 is ≥50000, and the thickness is 1.5±0.1 mm, which is used to suppress external magnetic field interference. The electromagnetic pre-positioning ring 62 is located inside the alloy housing 61. The electromagnetic pre-positioning ring 62 is a groove structure distributed in a ring shape, with a diameter of Φ800m. The electromagnetic pre-positioning ring 62 adopts the Halbach array magnetic field generation method, and after being energized, it generates an adsorption force of ≥500 kg / m 2 . The electromagnetic pre-positioning ring 62 guides the functional cabin and the flying device to be automatically aligned through the magnetic field gradient (error <1 cm). The current intensity is adjusted according to the docking distance (enhanced in the near field and weakened in the far field) to avoid accidentally attracting other metal objects. After power-off, the magnetic force automatically disappears to prevent accidental locking. The thickness of the magnet guiding ring is 5 mm, and the magnetic permeability μ≥1.2×10-3 H / m.

[0054] Specifically, the mechanical locking unit 7 includes a conical guiding pin 71 and a hydraulic claw 72. The conical guiding pin 71 is installed at the bottom of the fuselage 41 and is located inside the electromagnetic pre-positioning ring 62. The hydraulic claw 72 is installed at the top of the functional cabin 3 and is located inside the magnet guiding ring 64. The locking pressure of the conical guiding pin 71 and the hydraulic claw 72 is ≥15 MPa. The material of the conical guiding pin is titanium alloy TC4, and the surface is chrome-plated to prevent wear.

[0055] Specifically, the lower part of the conical guiding pin 71 has a conical pin taper angle 711, and the upper part of the conical guiding pin 71 has a root fillet 712. The conical pin taper angle 711 is 12°±0.5°, and the root fillet 712 reduces the risk of fatigue fracture. The hydraulic claw 72 has a chamfered corner 721, a hydraulic cylinder 722, claw teeth 723 and a guiding groove 724. The chamfered corner 721 reduces the insertion resistance of the pin. The hydraulic cylinder 722 drives the claw teeth to close, and the working pressure is 15 MPa; the guiding groove 724 ensures the linear movement of the claw and reduces eccentric wear.

[0056] The working process of the quick docking module 5 in this embodiment is as follows:

[0057] Stage 1: Magnetic pre-positioning (takes 1-3 seconds).

[0058] Proximity induction: When the flying device is 5 m away from the personnel cabin, the UWB (Ultra-Wideband Radio Technology) sensor is activated to share position data in real time. The personnel cabin starts automatic parking and enters the docking area. The electromagnetic pre-positioning ring is energized to generate a gradient magnetic field, and the ferromagnetic guiding ring at the top of the personnel cabin is attracted and automatically slides into the best docking area.

[0059] Stage 2: Mechanical bolt locking (takes 2-5 seconds).

[0060] Pin insertion: The conical guide pin is inserted into the card slot of the crew module, and the laser sensor confirms the centering accuracy (error < 0.5 mm).

[0061] Hydraulic locking: The hydraulic cylinder pushes the claw to close, biting the groove of the pin, and the pressure sensor feeds back the locking state (> 15 MPa is the safety threshold).

[0062] The ground travel module 1, flight module 2, functional cabin 3, flight device 4, and rapid docking module 5 are all equipped with independent energy storage devices, supporting solid-state batteries and / or hydrogen-electric hybrid power sources.

[0063] Embodiment 2

[0064] The rest is the same as Embodiment 1, except that, as Figures 5 to 8 shown, the mechanical locking unit 7 includes a gear-type bolt 71a, a return spring 72a, a power rotating gear 73a, a guide pin 74a, and a docking threaded base 75a. The gear-type bolt 71a is rotatably arranged at the bottom of the fuselage, the return spring 72a is sleeved on the gear-type bolt 71a, four gear-type bolts 71a are distributed around the power rotating gear 73a and are respectively meshed with the outside, the guide pin 74a is sleeved on the gear-type bolt 71a and is located between the gear-type bolt 71a and the fuselage, and the docking threaded base 75a is arranged at the top of the functional cabin.

[0065] In this embodiment, docking is carried out after pre-positioning. The gear-type bolt has an M40 thread below. In the non-docking state, the gear-type bolt is in a retracted state. After the guide pin is inserted into the docking threaded base, the power rotating gear starts, driving the driven gear of the gear-type bolt, thereby pushing the bolt out and thread-engaging with the docking threaded base to lock. Multiple bolts are symmetrically distributed (4 groups), and single-point failure can still maintain locking, with high stability. The gear drive is in milliseconds, and the total locking time < 5 seconds, with a rapid response.

[0066] Embodiment 3

[0067] The rest is the same as Embodiment 1, except that, as Figures 9 to 11 shown, the mechanical locking unit 7 includes a rotating rod 71b, a pressing spring 72b, a cross claw 73b, and a claw positioning disk 74b. The rotating rod 71b is rotatably arranged at the bottom of the fuselage, the pressing spring 72b is sleeved on the rotating rod 71b and is pressed between the rotating rod 71b and the fuselage, the cross claw 73b is located on the outer surface of the rotating rod 71b, and the claw positioning disk 74b is installed at the top of the functional cabin.

[0068] In this embodiment, docking is performed after pre-positioning. The end of the rotating rod is a cross claw. In the non-docked state, the cross claw is at 0 degrees. After the cross claw penetrates into the claw positioning disc, the rotating rod starts to rotate 45 degrees, and the claw is inserted into the diagonal slot. The compression spring is stressed, thus locking.

[0069] Embodiment 4

[0070] The rest is the same as in Embodiment 1, except that, as Figures 12 to 16 shown, the mechanical locking unit 7 includes a ball pin 71c, a shape memory alloy spring 72c, and a positioning and clamping disc 73c. The ball pin 71c is installed at the bottom of the machine body, the positioning and clamping disc 73c is installed at the top of the functional cabin, and the shape memory alloy spring 72c is arranged inside the positioning and clamping disc 73c. The shape memory alloy spring 72c is heated by passing an electric current through the spring heating lead.

[0071] In this embodiment, docking is performed after pre-positioning. There is a shape memory alloy spring inside the positioning and clamping disc. In the non-docked state, the shape memory alloy spring is not heated by passing an electric current, and its initial state is a posture with a bulge in the middle and tightened ends. During docking, the shape memory alloy spring is heated by passing an electric current, and its posture becomes a cylindrical posture. After the tapered ball pin penetrates into the docking base, the shape memory alloy spring is powered off and returns to its initial state, that is, a posture with a bulge in the middle and tightened ends, thus clamping the ball pin to lock.

[0072] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A split-type intelligent docking new energy flying car, characterized in that, Comprising: A ground travel module (1), having an independent travel drive system and a travel control unit; A flight module (2), having an independent flight drive system and a flight control unit; A functional cabin (3), including a personnel cabin and / or a logistics cabin, the functional cabin (3) being connected to the ground travel module (1) or the flight module (2); A flight device (4), including a fuselage (41), and four groups of rotor units (42) and an automatic lifting landing gear (43) provided on the fuselage (41), the flight device (4) being connected to the flight module (2); A quick docking module (5), including an electromagnetic pre-positioning unit (6) and a mechanical locking unit (7), for realizing quick connection and separation between the functional cabin (3) and the flight device (4).

2. The split-type intelligent docking new energy flying vehicle according to claim 1, wherein, The four groups of rotor units (42) are detachably mounted on the fuselage (41), and the four groups of rotor units (42) are symmetrically distributed around the fuselage (41).

3. A split-type intelligent docking new energy flying car according to claim 1, characterized in that, The rotation directions of two of the four groups of rotor units (42) are opposite to each other.

4. The split-type intelligent docking new energy flying vehicle according to claim 1, characterized in that, The automatic lifting landing gear (43) is provided with a multi-stage hydraulic shock absorber strut (44).

5. A split-type intelligent docking new energy flying car according to claim 1, characterized in that, The electromagnetic pre-positioning unit (6) includes an alloy housing (61), an electromagnetic pre-positioning ring (62) and a UVW sensor (63) mounted at the bottom of the fuselage (41), and a magnet guiding ring (64) mounted on the top of the functional cabin (3), the electromagnetic pre-positioning ring (62) being located inside the alloy housing (61), and the electromagnetic pre-positioning ring (62) being a groove structure distributed in a ring shape.

6. The split-type intelligent docking new energy flying vehicle according to claim 5, characterized in that, The magnetic permeability of the alloy housing (61) is ≥50000, and the thickness is 1.5±0.1 mm, for suppressing external magnetic field interference; The electromagnetic pre-positioning ring (62) adopts the Halbach array magnetic field generation method, and generates an adsorption force of ≥500 kg / m 2 after being energized.

7. A split-type intelligent docking new energy flying car according to claim 5, characterized in that, The mechanical locking unit (7) includes a conical guide pin (71) and a hydraulic claw (72), the conical guide pin (71) being mounted at the bottom of the fuselage (41) and located inside the electromagnetic pre-positioning ring (62), and the hydraulic claw (72) being mounted on the top of the functional cabin (3) and located inside the magnet guiding ring (64).

8. A split-type intelligent docking new energy flying vehicle according to claim 7, characterized in that, The locking pressure of the conical guide pin (71) and the hydraulic claw (72) is ≥15 MPa.

9. The split-type intelligent docking new energy flying vehicle according to claim 1, characterized in that, The ground travel module (1), the flight module (2), the functional cabin (3), the flight device (4), and the quick docking module (5) are all equipped with independent energy storage devices, supporting solid-state batteries and / or hydrogen-electric hybrid power sources.

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