Flying car and docking method of flying car

Abstract

The application discloses a flying car and a docking method of the flying car, and belongs to the technical field of transportation. The flying car comprises a cabin, an aircraft and a plurality of to-be-powered vibrators. The cabin comprises a first docking surface. The aircraft comprises a second docking surface, wherein the first docking surface and the second docking surface move towards each other in a docking direction of the cabin and the aircraft and are docked with each other. A plurality of mounting grooves are arranged on the first docking surface or the second docking surface, and the to-be-powered vibrators are correspondingly arranged in the mounting grooves, wherein the to-be-powered vibrators generate high-frequency vibrations after being powered on, so that a gas layer is formed between the first docking surface and the second docking surface. By adopting the technical scheme, the friction loss of the cabin and the aircraft in the docking process of the flying car can be reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of transportation, in particular to a flying car and a docking method of the flying car. BACKGROUND

[0002] With the rapid development of science and technology, a flying car as a new type of transportation gradually appears in people's vision. The flying car is an air transportation vehicle with land and air dual functions. Using the flying car to travel can greatly shorten the travel time of users, reduce the traffic volume on the road, thereby improving the travel efficiency and safety of people. The split flying car is one of the flying cars, which mainly includes a flight module, a cabin module and a chassis module from top to bottom. Since the cabin module can be combined with the flight module to realize the state of air flight or combined with the chassis module to realize the state of ground driving according to the needs of users, the split flying car not only can realize flexible switching of use modes, but also can reduce energy consumption.

[0003] In related technologies, when the split flying car switches the use mode, the cabin module needs to be docked with the flight module or the chassis module. However, in the docking process, the friction between the parts of different modules is often large, which causes a large friction loss of the structure, not only affects the docking accuracy, but also easily reduces the service life of the flying car. SUMMARY

[0004] Therefore, the embodiments of the present application provide a flying car and a docking method of the flying car, which can reduce the friction loss of the cabin and the aircraft in the docking process.

[0005] In a first aspect, the embodiments of the present application provide a flying car, which includes a cabin, an aircraft and a plurality of to-be-powered vibrators;

[0006] The cabin includes a first docking surface;

[0007] The aircraft includes a second docking surface, wherein the first docking surface and the second docking surface move towards each other in the docking direction of the cabin and the aircraft and are docked with each other;

[0008] A plurality of mounting grooves are arranged on the first docking surface or the second docking surface, and the to-be-powered vibrators are located in the mounting grooves one by one, wherein the to-be-powered vibrators generate high-frequency vibration after being powered on, so as to form a gas layer between the first docking surface and the second docking surface.

[0009] Optionally, the to-be-powered vibrator is a piezoelectric transducer, and the piezoelectric transducer includes a bolt, a piezoelectric component, a connecting piece and a vibrating piece.

[0010] The bottom of the installation groove is provided with an installation hole;

[0011] A part of the bolt penetrates into the installation hole and is connected with the piezoelectric component and the connecting piece in sequence;

[0012] The vibration piece is connected with the connecting piece.

[0013] Optionally, the vibration piece comprises a connecting rod and a vibration plate.

[0014] The two ends of the connecting rod are connected with the connecting piece and the vibration plate respectively, and the area of the vibration plate in orthographic projection on the bottom of the installation groove is greater than the area of the connecting rod in orthographic projection on the bottom of the installation groove.

[0015] Optionally, the plurality of vibration pieces are in a synchronous power-on state, or the plurality of vibration pieces are in an alternating power-on state.

[0016] Optionally, the flying car further comprises a cover body, the cover body closes the slot opening of the installation groove, and the side of the cover body close to the bottom of the installation groove is in abutment with the vibration radiation surface of the vibration piece.

[0017] In a second aspect, the embodiments of the present application further provide a docking method of a flying car, the method is applied to the flying car in any of the above embodiments of the present application, and the method comprises:

[0018] Obtaining a contact state between the first docking surface and the second docking surface;

[0019] When the contact state changes from an uncontacted state to a contacted state, supplying power to the vibration piece, wherein the vibration piece generates high-frequency vibration after being powered on.

[0020] Optionally, the method further comprises:

[0021] In response to the first docking surface and the second docking surface being in the contacted state, obtaining the weight of the flying vehicle;

[0022] According to the weight of the flying vehicle, determining a target number of the vibration pieces to be powered, wherein the target number is positively correlated with the weight of the flying vehicle;

[0023] Supplying power to the target number of the vibration pieces to be powered.

[0024] Optionally, the plurality of vibration pieces comprise a first group of vibration pieces and a second group of vibration pieces, and the method further comprises:

[0025] When the contact state is changed from the non-contact state to the contact state, the first group of vibrators and the second group of vibrators are powered alternately, and the power-on duration of the first group of vibrators is the same as the power-on duration of the second group of vibrators.

[0026] Optionally, the method further comprises:

[0027] In response to the first docking surface and the second docking surface being in the contact state, the weight of the aircraft is acquired.

[0028] According to the weight of the aircraft, a target voltage value is determined, and the target voltage value is positively correlated with the weight of the aircraft.

[0029] The AC power corresponding to the target voltage value is provided to the to-be-powered vibrator.

[0030] Optionally, the method further comprises:

[0031] In response to the first docking surface and the second docking surface being in the contact state, the weight of the aircraft is acquired.

[0032] According to the weight of the aircraft, a target voltage frequency is determined, and the difference between the resonance frequency of the to-be-powered vibrator and the target voltage frequency is negatively correlated with the weight of the aircraft.

[0033] The AC power corresponding to the target voltage frequency is provided to the to-be-powered vibrator.

[0034] The flying car provided by the embodiment of the application comprises a cabin, an aircraft, and a plurality of to-be-powered vibrators. The cabin comprises a first docking surface, the aircraft comprises a second docking surface, the first docking surface and the second docking surface can move towards each other in the docking direction of the cabin and the aircraft and mutually dock, so that the cabin and the aircraft can be relatively fixed together. The first docking surface or the second docking surface is provided with a plurality of mounting grooves, and the to-be-powered vibrators are located in the mounting grooves one by one. Since the to-be-powered vibrators can generate high-frequency vibrations after being powered, a gas layer is formed between the first docking surface and the second docking surface, so that the friction generated between the first docking surface and the second docking surface during docking can be reduced, the friction loss of the first docking surface and the second docking surface is reduced, and the service life of the flying car is improved. BRIEF DESCRIPTION OF DRAWINGS

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative effort.

[0036] Figure 1 is a structural schematic diagram of a flying car provided by an embodiment of the present application;

[0037] Figure 2 is a schematic diagram of a flying car provided by an embodiment of the present application, in which a gas layer is formed between the first and second docking surfaces;

[0038] Figure 3 is Figure 1 is a sectional schematic diagram of a flying car provided by an embodiment of the present application at A-A;

[0039] Figure 4 is a structural schematic diagram of a vibrator to be powered in a flying car provided by an embodiment of the present application;

[0040] Figure 5 is a structural schematic diagram of a flying vehicle in a flying car provided by an embodiment of the present application;

[0041] Figure 6 is a schematic diagram of a flying car provided by an embodiment of the present application, in which the first and second docking surfaces are in a non-contact state;

[0042] Figure 7 is a schematic diagram of a flying car provided by an embodiment of the present application, in which the first and second docking surfaces are in a contact state and are moved to a docking position;

[0043] Figure 8 is a flowchart of a docking method of a flying car provided by an embodiment of the present application;

[0044] Figure 9 is a flowchart of a docking method of a flying car provided by an embodiment of the present application;

[0045] Figure 10 is a block diagram of each part of a flying car provided by an embodiment of the present application.

[0046] Reference signs:

[0047] 100, cabin; 110, first docking surface; 120, magnetic attraction element; 111, mounting groove; 112, groove bottom; 114, groove opening;

[0048] 200, flying vehicle; 210, second docking surface; 220, electromagnetic chuck;

[0049] 300, vibrator to be powered; 310, bolt; 320, piezoelectric component; 330, connecting element; 340, vibrating element; 350, vibrating radiation surface; 321, conductive sheet; 322, piezoelectric ceramic; 341, connecting rod; 342, vibrating plate;

[0050] 400. Gas layer;

[0051] 500. Cover;

[0052] 600. Controller;

[0053] 700, Power Module;

[0054] 800. Pressure sensor;

[0055] 900. Image Recognizer.

[0056] The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to particular embodiments. Detailed Implementation

[0057] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. 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.

[0058] Unless otherwise defined, all technical terms used in the embodiments of this application have the same meaning as commonly understood by those skilled in the art.

[0059] To make the technical solutions and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0060] Firstly, combining Figure 1 and Figure 2 As shown in the figure, this application embodiment provides a flying car, which includes a cockpit 100, an aircraft 200, and multiple vibrators 300 to be powered. It should be noted that the flying car generally also includes a chassis (not shown in the figure). The cockpit 100 refers to the space providing space for carrying people and goods. When the cockpit 100 is combined with the aircraft 200, the flying car can fly. When the cockpit 100 is combined with the chassis, the flying car can travel on land. This allows the flying car to have both air and land driving functions, while also avoiding excessive load on the cockpit 100 due to simultaneous combination with the chassis and aircraft 200, thus achieving energy-saving effects.

[0061] The cabin 100 comprises a first docking surface 110. The aircraft 200 comprises a second docking surface 210, wherein the first docking surface 110 and the second docking surface 210 are moved towards each other in the docking direction of the cabin 100 and the aircraft 200 and are docked with each other, so that the cabin 100 and the aircraft 200 can be relatively fixed together. It should be noted that the cabin 100 and the aircraft 200 can be attracted by a magnetic mechanism to realize docking connection, or realize docking connection by a clamping mechanism. During the docking process of the cabin 100 and the aircraft 200, the first docking surface 110 and the second docking surface 210 are separated from each other, until they are close to each other and then move towards each other to the docking position, so as to realize docking.

[0062] A plurality of mounting grooves 111 are arranged on the first docking surface 110 or the second docking surface 210, and the to-be-powered vibrator 300 is correspondingly arranged in the mounting groove 111. When the to-be-powered vibrator 300 is powered, high-frequency vibration is generated, so as to form a gas layer 400 between the first docking surface 110 and the second docking surface 210. It should be noted that the gas layer 400 can reduce the friction generated between the first docking surface 110 and the second docking surface 210 during the docking process of moving towards each other after being close to each other, that is, the gas layer 400 can reduce the friction, thereby reducing the friction loss of the first docking surface 110 and the second docking surface 210 and prolonging the service life of the flying car. It should be noted that the drawings of the present application only take the case of arranging the mounting grooves 111 on the first docking surface 110 as an example, and the principle of arranging the mounting grooves 111 on the second docking surface 210 is the same as that of arranging the mounting grooves 111 on the first docking surface 110. In some embodiments, the mounting grooves 111 are uniformly distributed on the first docking surface 110, so that the vibration is more uniform and the friction reduction effect is improved. Figure 1 As shown, seven mounting grooves 111 are arranged, one of which is arranged at the center of the first docking surface 110, and the other mounting grooves 111 are symmetrically distributed about the center mounting groove 111.

[0063] The drawings of the present application will be described below. Figures 1 to 7 The various component structures and functions of the flying car provided by the embodiments of the present application will be described in more detail.

[0064] The drawings of the present application will be described below. Figure 3 And Figure 4As shown in the figure, in some embodiments, the to-be-powered vibrator 300 is a piezoelectric transducer, which includes a bolt 310, a piezoelectric component 320, a connecting piece 330, and a vibrating piece 340. The groove bottom 112 of the mounting groove 111 is provided with a mounting hole. A part of the bolt 310 penetrates into the mounting hole and is sequentially connected with the piezoelectric component 320 and the connecting piece 330. The vibrating piece 340 is connected with the connecting piece 330. It should be noted that the working principle of the piezoelectric transducer is that after alternating current is provided to the piezoelectric component 320, the piezoelectric component 320 generates ultrasonic vibration due to the piezoelectric effect. The ultrasonic vibration is amplified in sequence through the connecting piece 330 and the vibrating piece 340. In some embodiments, the connecting piece 330 is conical, thereby being more conducive to realizing the transmission of vibration. The side of the vibrating piece 340 away from the groove bottom 112 of the mounting groove 111 can abut against the second abutting surface 210, and the gas layer 400 is formed between the first abutting surface 110 and the second abutting surface 210 due to the ultrasonic near-field effect, which can reduce the friction between the first abutting surface 110 and the second abutting surface 210, that is, has a certain friction-reducing effect. In this way, not only the wear degree of the first abutting surface 110 and the second abutting surface 210 is reduced, but also the wear degree between the planes where the first abutting surface 110 and the second abutting surface 210 are located and the related components used for abutting therebetween is reduced, thereby prolonging the service life of the flying car and improving the abutting precision.

[0065] As shown in the figure, Figure 3 In some embodiments, the flying car further includes a cover 500, which encloses the slot opening 114 of the mounting groove 111, and the side of the cover 500 close to the groove bottom 112 of the mounting groove 111 abuts against the vibration radiation surface 350 of the to-be-powered vibrator 300. It should be noted that by arranging the cover 500, impurities can be prevented from entering the mounting groove 111 and affecting the normal work of the to-be-powered vibrator 300, that is, the to-be-powered vibrator 300 is better protected, and the service life of the flying car is further prolonged. Moreover, since the area of the cover 500 is large, when vibration is transmitted to the cover 500, the vibration can be made more uniform, and the friction-reducing effect is improved. In some embodiments, the groove top of the mounting groove 111 can be flush with the cover 500 or flush with the end of the to-be-powered vibrator 300 away from the groove bottom 112, thereby ensuring the effectiveness of vibration propagation.

[0066] As shown in the figure, Figure 3As shown, in some embodiments, the piezoelectric assembly 320 includes a plurality of conductive sheets 321 and a plurality of piezoelectric ceramics 322, wherein the number of the conductive sheets 321 and the piezoelectric ceramics 322 can be the same. The conductive sheets 321 and the piezoelectric ceramics 322 can each be annular. The bolt 310 includes a nut and a screw rod, the nut abuts the outer side of the slot bottom 112 of the mounting slot 111, and the screw rod penetrates into the mounting slot 111 from the mounting hole. The piezoelectric ceramics 322 and the conductive sheets 321 are alternately stacked in sequence and sleeved on the screw rod. The screw rod is connected with the piezoelectric ceramics 322 and the conductive sheets 321 through threads. It should be noted that a part of the conductive sheets 321 is adapted to be in communication with alternating current, and another part of the conductive sheets 321 is adapted to be grounded, for example, the conductive sheets 321 are connected with the shell of the cabin 100 to achieve the grounding effect. Figure 3 As shown, the piezoelectric transducer includes four conductive sheets 321 and four piezoelectric ceramics 322, wherein two conductive sheets 321 are adapted to be in communication with a power supply providing alternating current, and the other two conductive sheets 321 are adapted to be grounded. When the conductive sheets 321 are powered on, the piezoelectric ceramics 322 will generate longitudinal vibration of ultrasonic waves in accordance with the piezoelectric effect, the ultrasonic vibration is transmitted to the connecting piece 330, and then amplified by the vibrating piece 340, so that the gas layer 400 can be formed between the first mating surface 110 and the second mating surface 210.

[0067] In combination Figure 3 and Figure 4 As shown, in some embodiments, the vibrating piece 340 includes a connecting rod 341 and a vibrating plate 342. The two ends of the connecting rod 341 are respectively connected with the connecting piece 330 and the vibrating plate 342, and the area of the vibrating plate 342 in the orthogonal projection on the slot bottom 112 of the mounting slot 111 is greater than the area of the connecting rod 341 in the orthogonal projection on the slot bottom 112 of the mounting slot 111. In this way, the effect of amplifying the ultrasonic vibration generated by the piezoelectric assembly 320 can be better achieved.

[0068] In some embodiments, a plurality of to-be-powered vibrators 300 are in a synchronous power-on state, or a plurality of to-be-powered vibrators 300 are in an alternating power-on state. It should be noted that in the alternating power-on state, sufficient vibration amplitude can be ensured, energy consumption can be saved, the to-be-powered vibrator 300 can be prevented from being in a continuous working state for a long time, and thus the service life of the to-be-powered vibrator 300 can be prolonged, thereby further prolonging the service life of the flying car.

[0069] In combination Figure 1 and Figure 5As shown, in some embodiments, the aircraft 200 comprises an electromagnetic chuck 220, which is installed on the side of the aircraft 200 facing the cabin 100, and the first docking surface 110 is the magnetic conductive surface of the electromagnetic chuck 220 facing the cabin 100. It should be noted that the shape of the electromagnetic chuck 220 can be set according to requirements, such as a rectangle, a square or a circle, etc. Figure 5 As shown, the electromagnetic chuck 220 is circular. The cabin 100 comprises a magnetic attraction member 120, which is installed on the side of the cabin 100 facing the aircraft 200. At this time, the second docking surface 210 is the surface of the magnetic attraction member 120 facing the aircraft 200. The shape of the magnetic attraction member 120 matches the shape of the electromagnetic chuck 220, such as Figure 1 As shown, the magnetic attraction member 120 is circular. It should be noted that when the electromagnetic chuck 220 is powered, the magnetic conductive surface can be adsorbed together with the magnetic attraction member 120, so as to combine the cabin 100 and the aircraft 200 together. It should be noted that since the to-be-powered vibrator 300 in the embodiment of the present application is a piezoelectric transducer, and the piezoelectric transducer generates ultrasonic vibration, the vibration process of the piezoelectric transducer will not interfere with the magnetic field between the electromagnetic chuck 200 and the magnetic attraction member 120, so as to ensure the stability of the to-be-powered vibrator 300 and the stability of the adsorption of the electromagnetic chuck 200 and the magnetic attraction member 120.

[0070] The process of docking the aircraft 200 and the cabin 100 in the flying car provided by the embodiment of the present application can be: first, control the aircraft 200 to gradually land until the first docking surface 110 and the second docking surface 210 are attached, that is, the state shown in Figure 6 is changed to the state shown in Figure 2 , and the electromagnetic chuck 220 is powered. Under the action of the magnetic field, the aircraft 200 and the cabin 100 are firmly attached together. Then, the to-be-powered vibrator 300 is powered, and based on the above principle, the gas layer 400 is formed between the first docking surface 110 and the second docking surface 210, that is, as shown in Figure 2 , so as to reduce the friction between the first docking surface 110 and the second docking surface 210. Then, the first docking surface 110 can move relative to the second docking surface 210 in the docking direction, and at this time, the aircraft 200 and the cabin 100 can realize low-friction relative motion without being separated from each other, until the positions of the first docking surface 110 and the second docking surface 210 reach the specified docking position, such as Figure 7The first pair of abutting surfaces 110 and the second pair of abutting surfaces 210 are abutted together, and then the position of the cabin 100 and the aircraft 200 is locked and fixedly connected by the abutting mechanism to complete the abutting process. It should be noted that the abutting mechanism can be a structure that can fix the aircraft 200 and the cabin 100 together, for example, a clamping structure, and the like, and the specific composition of the abutting mechanism is not limited in the embodiments of the present application.

[0071] As can be seen from the above, the flying car provided in the embodiments of the present application can realize the precise abutting process of the aircraft 200 and the cabin 100 under low friction, thereby prolonging the service life of the flying car.

[0072] In a second aspect, as Figure 8 The embodiments of the present application also provide an abutting method of a flying car, which is applied to any one of the flying cars provided in the embodiments of the present application. It should be noted that the flying car generally comprises a controller 600, and the method can be executed by the controller 600. In combination with Figure 6 The abutting method provided in the embodiments of the present application comprises steps 101 to 102.

[0073] In step 101, the controller 600 acquires the contact state between the first pair of abutting surfaces 110 and the second pair of abutting surfaces 210.

[0074] It should be noted that a sensor for detecting the contact state can be arranged on the aircraft 200 and / or the cabin 100, for example, a pressure sensor 800. The sensor is generally electrically connected with the controller 600, and the controller 600 and the sensor can transmit signals to each other. The controller 600 determines the contact state between the first pair of abutting surfaces 110 and the second pair of abutting surfaces 210 based on the detection signal of the sensor. For example, when the controller 600 determines that the current pressure value detected by the pressure sensor 800 is greater than the preset pressure value, it is determined that the first pair of abutting surfaces 110 and the second pair of abutting surfaces 210 are in the contacted state. When the controller 600 determines that the current pressure value detected by the pressure sensor 800 is less than the preset pressure value, it is determined that the first pair of abutting surfaces 110 and the second pair of abutting surfaces 210 are in the uncontacted state.

[0075] In step 102, when the contact state changes from the uncontacted state to the contacted state, the controller 600 supplies power to the to-be-powered vibrator 300.

[0076] The to-be-powered vibrator 300 generates high-frequency vibration after being powered. It should be noted that the controller 600 is generally electrically connected with the power module 700, and when the contact state changes to the contacted state, the controller 600 can control the power module 700 to output alternating current to the to-be-powered vibrator 300, so that the to-be-powered vibrator 300 can generate high-frequency vibration after being powered. Further, the gas layer 400 is formed between the first docking surface 110 and the second docking surface 210 to reduce the friction between the first docking surface 110 and the second docking surface 210 during the docking process, to realize the relative movement under low friction, to reduce the wear degree between the first docking surface 110 and the second docking surface 210, to not only improve the docking accuracy, but also prolong the service life of the flying car.

[0077] In combination with Figures 8 to 10 As shown in FIG. 1, the embodiment of the present application also provides a docking method of a flying car. The method is applied to any one of the flying cars provided by the embodiments of the present application. It should be noted that the flying car generally includes a controller 600, and the method can be executed by the controller 600. In combination with Figure 7 As shown in FIG. 1, the docking method provided by the embodiment of the present application includes steps 201 to 204.

[0078] In step 201, the controller 600 acquires the contact state between the first docking surface 110 and the second docking surface 210.

[0079] It should be noted that step 201 is the same as step 101, and the embodiment of the present application will not be repeated here.

[0080] In step 202, the controller 600 acquires the weight of the aircraft 200 in response to the first docking surface 110 and the second docking surface 210 being in the contacted state.

[0081] In some embodiments, the cabin 100 can also be provided with a pressure sensor 800 or an image recognizer 900. The controller 600 is arranged in the cabin 100. The controller 600 is electrically connected with the pressure sensor 800. The controller 600 determines the weight of the aircraft 200 based on the pressure signal detected by the pressure sensor 800. Alternatively, the controller 600 is electrically connected with the image recognizer 900, and the controller 600 determines the model of the aircraft 200 matched with the image information based on the image information detected by the image recognizer 900, and determines the weight of the aircraft 200 according to the corresponding relationship between the model of the aircraft 200 and the weight of the aircraft 200.

[0082] In step 203, the controller 600 determines the target number of to-be-powered vibrators 300 to be powered according to the weight of the aircraft 200.

[0083] The target number is positively correlated with the weight of the aircraft 200. It should be noted that the more the number of the to-be-powered vibrators 300 is powered on, the greater the amplitude is.

[0084] In step 204, the controller 600 powers the target number of to-be-powered vibrators 300.

[0085] The to-be-powered vibrator 300 generates high-frequency vibration after being powered on, and thus the gas layer 400 can be formed between the first docking surface 110 and the second docking surface 210. This can ensure that the to-be-powered vibrator 300 can generate sufficient amplitude to form the gas layer 400 between the first docking surface 110 and the second docking surface 210, so as to achieve the friction reduction effect between the first docking surface 110 and the second docking surface 210, and avoid unnecessary power supply to too many to-be-powered vibrators 300, thereby achieving the energy-saving effect.

[0086] It should be noted that steps 202 to 204 are a way in which the controller 600 powers the to-be-powered vibrator 300 when the contact state changes from the non-contact state to the contacted state.

[0087] In some embodiments, the plurality of to-be-powered vibrators 300 includes a first group of vibrators and a second group of vibrators, and the method further includes: when the contact state changes from the non-contact state to the contacted state, alternately powering the first group of vibrators and the second group of vibrators, wherein the power-on duration of the first group of vibrators is the same as the power-on duration of the second group of vibrators. It should be noted that the power-on duration can refer to the single power-on duration, or the total duration of multiple power-ons. By alternately powering, the working duration of each to-be-powered vibrator 300 can be reduced, and the performance of the to-be-powered vibrator 300 can be prevented from being affected due to being in a long-term working state all the time, thereby prolonging the service life of the to-be-powered vibrator 300 and the service life of the flying car.

[0088] In some embodiments, the first group of vibrators includes a plurality of to-be-powered vibrators 300, and the second group of vibrators includes a plurality of to-be-powered vibrators 300, and the to-be-powered vibrators 300 in the first group of vibrators are distributed apart from the to-be-powered vibrators 300 in the second group of vibrators. Thus, when the first group of vibrators or the second group of vibrators is powered, a more uniform gas layer 400 can be formed between the first docking surface 110 and the second docking surface 210, and the friction reduction effect is better.

[0089] In some embodiments, the method further comprises: in response to the first interface 110 and the second interface 210 being in the contacted state, obtaining the weight of the aircraft 200. According to the weight of the aircraft 200, a target voltage value is determined, wherein the target voltage value is positively correlated with the weight of the aircraft 200. The to-be-powered vibrator 300 is provided with alternating current corresponding to the target voltage value. It can be understood that the greater the voltage value, the greater the amplitude generated by the to-be-powered vibrator 300 after being powered, the thicker the air layer, and the greater the degree of friction reduction between the first interface 110 and the second interface 210. The method can accurately provide the target voltage value according to the weight of the aircraft 200, which can not only ensure that the to-be-powered vibrator 300 generates a suitable amplitude to separate the first interface 110 and the second interface 210, but also ensure that the first interface 110 and the second interface 210 achieve a good friction reduction effect.

[0090] In some embodiments, the method further comprises: in response to the first interface 110 and the second interface 210 being in the contacted state, obtaining the weight of the aircraft 200. According to the weight of the aircraft 200, a target voltage value is determined, wherein the target voltage value is positively correlated with the weight of the aircraft 200. The to-be-powered vibrator 300 is provided with alternating current corresponding to the target voltage value. It can be understood that the greater the voltage value, the greater the amplitude generated by the to-be-powered vibrator 300 after being powered, the thicker the air layer, and the greater the degree of friction reduction between the first interface 110 and the second interface 210. The method can accurately provide the target voltage value according to the weight of the aircraft 200, which can not only ensure that the to-be-powered vibrator 300 generates a suitable amplitude to separate the first interface 110 and the second interface 210, but also ensure that the first interface 110 and the second interface 210 achieve a good friction reduction effect.

[0091] In the present application, the terms "first" and "second" are only for descriptive purposes and cannot be understood or implied to indicate or suggest relative importance. The term "a plurality of" refers to two or more, unless otherwise explicitly limited.

[0092] Other embodiments of the present application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. The present application is intended to cover any variations, uses or adaptive changes of the application following the general principles thereof and including those expressly mentioned or implied herein. The specification and examples are to be regarded as illustrative only.

[0093] It is to be understood that the application is not limited to the precise construction already described above and shown in the drawings, and that various modifications and changes can be made by those skilled in the art without departing from the scope of the application. The scope of the application should only be limited by the claims appended hereto.

Claims

1. A flying car, characterized by, The flying automobile comprises a cabin (100), an aircraft (200) and a plurality of to-be-powered vibrators (300); The cabin (100) comprises a first docking surface (110); The aircraft (200) comprises a second docking surface (210), wherein the first docking surface (110) and the second docking surface (210) move towards each other in the docking direction of the cabin (100) and the aircraft (200) and are docked with each other; A plurality of mounting grooves (111) are arranged on the first docking surface (110) or the second docking surface (210), and the to-be-powered vibrators (300) are arranged in the mounting grooves (111) one by one, the to-be-powered vibrator (300) is a piezoelectric transducer, and the piezoelectric transducer comprises a bolt (310), a piezoelectric component (320), a connecting piece (330) and a vibrating piece (340); the vibrating piece (340) comprises a connecting rod (341) and a vibrating plate (342); the two ends of the connecting rod (341) are connected with the connecting piece (330) and the vibrating plate (342) respectively, the projection area of the vibrating plate (342) on the groove bottom (112) of the mounting groove (111) is greater than the projection area of the connecting rod (341) on the groove bottom (112) of the mounting groove (111); the groove bottom (112) of the mounting groove (111) is provided with a mounting hole; a part of the bolt (310) penetrates into the mounting hole and is connected with the piezoelectric component (320) and the connecting piece (330) in sequence; the vibrating piece (340) is connected with the connecting piece (330), wherein the to-be-powered vibrator (300) generates high-frequency vibration after being powered on, so as to form a gas layer (400) between the first docking surface (110) and the second docking surface (210).

2. The flying car of claim 1, wherein, A plurality of to-be-powered vibrators (300) are in a synchronous power-on state, or a plurality of to-be-powered vibrators (300) are in an alternating power-on state.

3. The flying car of claim 1, wherein, The flying automobile further comprises a cover body (500), the cover body (500) closes the groove opening (114) of the mounting groove (111), and the side of the cover body (500) close to the groove bottom (112) of the mounting groove (111) is in abutment with the vibration radiation surface (350) of the to-be-powered vibrator (300).

4. A method of docking a flying car, characterized by, The method is applied to the flying automobile of any one of claims 1 to 3, and the method comprises: acquiring a contact state between the first docking surface (110) and the second docking surface (210); when the contact state changes from an uncontacted state to a contacted state, powering the to-be-powered vibrator (300), wherein the to-be-powered vibrator (300) generates high-frequency vibration after being powered on.

5. The method of docking the air car of claim 4, wherein, The method further comprises: in response to the first docking surface (110) and the second docking surface (210) being in a contacted state, acquiring the weight of the aircraft (200); According to the weight of the aircraft (200), a target number of the to-be-powered vibrators (300) to be powered is determined, wherein the target number is positively correlated with the weight of the aircraft (200); Power is supplied to the target number of the to-be-powered vibrators (300).

6. The method of docking a flying car of claim 4, wherein, The plurality of to-be-powered vibrators (300) include a first group of vibrators and a second group of vibrators, and the method further includes: When the contact state changes from the non-contact state to the contacted state, the first group of vibrators and the second group of vibrators are alternately powered, wherein the energization time length of the first group of vibrators is the same as that of the second group of vibrators.

7. The method of docking the air car of claim 4, wherein, The method further includes: In response to the first docking surface (110) and the second docking surface (210) being in the contacted state, the weight of the aircraft (200) is obtained; According to the weight of the aircraft (200), a target voltage value is determined, wherein the target voltage value is positively correlated with the weight of the aircraft (200); The to-be-powered vibrators (300) are provided with alternating current corresponding to the target voltage value.

8. The method of docking a flying car of claim 4, wherein, The method further includes: In response to the first docking surface (110) and the second docking surface (210) being in the contacted state, the weight of the aircraft (200) is obtained; According to the weight of the aircraft (200), a target voltage frequency is determined, wherein the difference between the resonance frequency of the to-be-powered vibrator (300) and the target voltage frequency is negatively correlated with the weight of the aircraft (200); The to-be-powered vibrators (300) are provided with alternating current corresponding to the target voltage frequency.

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