CN211468095U

CN211468095U - Flying automobile

Info

Publication number: CN211468095U
Application number: CN201922306109.9U
Authority: CN
Inventors: 孙博; 徐彬; 甄鹏飞; 邢志强
Original assignee: Cool High Technology Beijing Co ltd
Current assignee: Cool High Technology Beijing Co ltd
Priority date: 2019-12-19
Filing date: 2019-12-19
Publication date: 2020-09-11
Anticipated expiration: 2029-12-19

Abstract

The utility model relates to a flying automobile, including the delivery storehouse, have the aircraft of electric drive mode to and have the electric drive mode and at the chassis of traveling that land traveles, the delivery storehouse can with the aircraft with arbitrary one butt joint in the chassis of traveling or dock simultaneously with both, still be provided with power supply unit on the delivery storehouse, power supply unit be used for to with the delivery storehouse butt joint just has the power demand the aircraft and/or the chassis power supply of traveling. The utility model discloses a flying car to cheap cost makes the aircraft and the chassis of traveling obtain reliable and stable power supply and guarantees, has effectively improved flying car's carrying capacity.

Description

Flying automobile

Technical Field

The utility model relates to a hovercar design and production technical field, in particular to hovercar.

Background

With the development of urban three-dimensional traffic technology and the progress of low-airspace traffic control level, aircrafts or flying automobiles with manned and cargo carrying functions are in operation, and in view of the important significance of ecological protection which is generally concerned about in the world, electric power is a main mode of energy supply of the flying automobiles in the future.

The utility model discloses the hovercar that relates to especially indicates disconnect-type hovercar, so-called disconnect-type hovercar is including delivery storehouse, chassis and aircraft of traveling usually, and the chassis of traveling is used for traveling on ground road, and the delivery storehouse can combine or combine together with the aircraft with the chassis of traveling as required to realize the ground transportation or the air transportation in delivery storehouse.

However, the limitation of the carrying range of the electric aerocar is a technical problem which always besets the technicians in the field, so that the power supply device or the power supply method of the aerocar is the direction of important research of various enterprises.

At present, a spare battery is additionally arranged on an aircraft or a running chassis or the capacity of the battery is increased, but due to the energy density of the battery, the increasing effect on the driving range of the flying automobile is very limited only by increasing the battery or increasing the capacity of the battery;

in addition, the other method is that a plurality of parking platforms are arranged in each ground driving area of a city, the charging piles are arranged on the parking platforms, and the flying automobile can select nearby charging piles to charge in the flying or driving process so as to increase the endurance mileage.

Therefore, how to conveniently and effectively improve the endurance mileage and the flight time of the hovercar is a technical problem which needs to be solved urgently in the industry at present.

SUMMERY OF THE UTILITY MODEL

The utility model provides a hovercar to can make things convenient for effectual improvement hovercar's continuation of the journey mileage and flight time, and then guarantee hovercar's carrying capacity.

In order to achieve the above object, the utility model provides a flying car, including the delivery storehouse that has carrying function, the aircraft that has the electric drive mode to and the chassis of traveling that has the electric drive mode, the delivery storehouse can with the aircraft with arbitrary one in the chassis of traveling docks or docks simultaneously with both, still be provided with power supply unit on the delivery storehouse, power supply unit be used for to the aircraft and/or the chassis of traveling provides the electric energy.

Preferably, the power supply device is a power generation device, and the power generation device is used for providing electric energy for the aircraft and/or the running chassis which are in butt joint with the carrying cabin and have the power taking requirement.

Preferably, a first docking mechanism is arranged on the aircraft, a first energy storage device used for storing electric energy in the aircraft is electrically connected with the first docking mechanism, a second docking mechanism matched with the first docking mechanism is arranged on the carrying bin, the power supply device is electrically connected with the second docking mechanism, and when the first docking mechanism is docked with the second docking mechanism, the first docking mechanism is electrically connected with the second docking mechanism.

Preferably, a fourth docking mechanism is disposed on the traveling chassis, a second energy storage device for storing electric energy in the traveling chassis is electrically connected to the fourth docking mechanism, a third docking mechanism matched with the fourth docking mechanism is disposed on the carrying bin, the power supply device is electrically connected to the third docking mechanism, and when the third docking mechanism and the fourth docking mechanism are docked, the third docking mechanism and the fourth docking mechanism are electrically connected.

Preferably, the flight electric drive device in the aircraft is electrically connected with the first docking mechanism.

Preferably, a chassis electric drive device in the running chassis is electrically connected with the fourth docking mechanism.

Preferably, a third energy storage device is further arranged in the carrying bin, and the third energy storage device is used for providing electric energy for electric appliances of the carrying bin.

Preferably, the first energy storage device is a storage battery and/or a super capacitor, the second energy storage device is a storage battery and/or a super capacitor, and the third energy storage device is a storage battery and/or a super capacitor.

Preferably, the first docking mechanism, the second docking mechanism, the third docking mechanism and the fourth docking mechanism are electromagnetic docking mechanisms or mechanical clamping structures which are matched with each other.

Preferably, the power supply device is a generator, a fuel cell or a photovoltaic module.

Preferably, still be provided with in the aircraft and be used for monitoring residual capacity's aircraft energy early warning module in the aircraft, still be provided with in the chassis of traveling and be used for monitoring residual capacity's chassis energy early warning module in the chassis of traveling, the aircraft or still be provided with in the delivery storehouse and be used for control power supply unit to the aircraft provides the first local control module of electric energy, the chassis of traveling or still be provided with in the delivery storehouse and be used for control power supply unit to the chassis of traveling provides the second local control module of electric energy, aircraft energy early warning module with first local control module communication connection, chassis energy early warning module with second local control module communication connection.

According to the technical scheme provided by the utility model, in the disclosed hovercar, power supply unit has been set up in the delivery storehouse, when the aircraft or the chassis butt joint of traveling on the delivery storehouse and when having the demand of getting the electricity, power supply unit can be to the aircraft with the chassis power supply of traveling, this just provides a reliable and stable energy guarantee at the in-process of carrying out the transportation task for hovercar, compare in the mode that increases the battery in aircraft or the chassis of traveling at present, this scheme can promote hovercar's continuation of the journey mileage at the bigger degree, and compare in the mode of constructing ground charging pile, this scheme is showing the cost of getting the electricity that has reduced aircraft and chassis of traveling.

Therefore, the utility model discloses a hovercar makes the aircraft and the chassis of traveling obtain reliable and stable power supply with low cost and guarantees, has effectively improved hovercar's carrying capacity.

Drawings

Fig. 1 is a schematic overall structural view of a flying car disclosed in an embodiment of the present invention;

fig. 2 is a schematic view of the overall structure of the aircraft disclosed in the embodiment of the present invention;

FIG. 3 is a schematic structural view of a first energy storage device and a first docking mechanism of the aircraft shown in FIG. 2;

fig. 4 is a schematic view of the overall structure of the carrying bin disclosed in the embodiment of the present invention;

fig. 5 is a schematic structural diagram of the power generation device on the carrier bin shown in fig. 4 and the second docking mechanism and the third docking mechanism;

fig. 6 is a schematic view of the overall structure of the driving chassis disclosed in the embodiment of the present invention;

fig. 7 is a schematic structural view of the second energy storage device and the fourth docking mechanism of the running chassis shown in fig. 6.

The system comprises an aircraft 1, a carrying cabin 2, a running chassis 3, a first docking mechanism 11, a first energy storage device 12, a second docking mechanism 21, a power generation device 22, a third docking mechanism 23, a power supply line 24, a first charging connector 25, a fourth docking mechanism 31, a second charging connector 32 and a second energy storage device 33.

Detailed Description

The core of the utility model is to provide a hovercar to can make things convenient for effectual improvement hovercar's continuation of the journey mileage and flight time, and then guarantee hovercar's carrying capacity.

In order to make the technical field better understand the solution of the present invention, the following detailed description of the present invention is provided with reference to the accompanying drawings and the detailed description.

Referring to fig. 1 to 7, the flying car disclosed in the present embodiment includes a carrying cabin 2, an aircraft 1 and a traveling chassis 3, wherein the purpose of the carrier cabin 2 is to carry cargo, or to carry passengers, or to carry cargo and simultaneously to carry passengers, the aircraft 1 can fly in the air, and the electric drive mode is at least one drive mode of the aircraft 1, the running chassis 3 being intended for running on land, and the electric driving mode is at least one driving mode of the running chassis 3, the carrying cabin 2 can be butted with either one of the aircraft 1 and the running chassis 3 or both the aircraft 1 and the running chassis 3, and the carrying cabin 2 is also provided with a power supply device, the power supply device is used for supplying power to the aircraft 1 and/or the running chassis 3 which are in butt joint with the carrying cabin 2 and have power taking requirements.

It should be noted that, the power supply device disposed in the carrying cabin includes, but is not limited to, a battery with an electric power storage function, a super capacitor, and the like, and when the power supply device is a battery or a super capacitor, the function of the carrying cabin is similar to that of a charger for charging a mobile device at present; in addition, the power supply unit also includes a power generation unit 22 that can convert other forms of energy into electrical energy.

As an optimal mode, the utility model provides a power supply unit is power generation facility 22, when

aircraft

1 or 3 docks on the chassis of traveling are on delivery storehouse 2 and have the electricity demand of getting, power generation facility 22 can be to

aircraft

1 and 3 powers supplies power on the chassis of traveling, this just provides a reliable and stable energy guarantee at the in-process of carrying out the transportation task for hovercar, compare in the mode that increases the battery in aircraft 1 or chassis of traveling 3 at present, this scheme can promote hovercar's continuation of the journey mileage at the bigger degree, and compare in the mode of constructing ground charging pile, this scheme is showing the electricity cost of getting that has reduced aircraft 1 and chassis of traveling 3.

Therefore, the flying vehicle disclosed in the above embodiment can ensure stable and reliable power supply to the aircraft 1 and the chassis 3 at low cost, and effectively improve the carrying capacity of the flying vehicle.

The embodiment of the utility model provides an in the disclosed hovercar, all can realize automatic butt joint (of course, also can be manual or semi-automatic butt joint) between aircraft 1 and the delivery storehouse 2 and between chassis 3 and the delivery storehouse 2 of traveling, through aircraft 1's flight control system to combine difference GPS, vision positioning system to realize accurate butt joint, this kind of butt joint technique has been widely used in this field, consequently does not carry out detailed description to this kind of butt joint technique again in this embodiment.

It is understood that, in both the aircraft 1 and the traveling chassis 3, after the docking with the carrying cabin 2, the electrical connection between the aircraft 1 and the carrying cabin 2 and between the traveling chassis 3 and the carrying cabin 2 can be realized by additionally providing a charging plug, but such charging plug is usually exposed outside the combination of the aircraft 1 and the carrying cabin 2 and the combination of the traveling chassis 3 and the carrying cabin 2, which not only affects the appearance, but also is prone to cause accidents due to interference of lines and obstacles, for further optimization, in the flying automobile disclosed in this embodiment, the aircraft 1 is provided with the first docking mechanism 11, the first energy storage device 12 for storing electric energy in the aircraft 1 is electrically connected with the first docking mechanism 11, the first energy storage device 12 is used for providing electric power for the flying electric power driving device in the aircraft 1, the carrying cabin 2 is provided with the second docking mechanism 21 cooperating with the first docking mechanism 11, the power generation device 22 is electrically connected to the second docking mechanism 21, and when the first docking mechanism 11 and the second docking mechanism 21 are docked, an electrical connection is formed between the first docking mechanism 11 and the second docking mechanism 21.

According to the scheme, the docking mechanism and the electric connection mechanism between the aircraft 1 and the carrying bin 2 are ingeniously combined into one, when the first docking mechanism 11 is docked with the second docking mechanism 21, the aircraft 1 is electrically connected with the carrying bin 2, the second docking mechanism 21 is electrically connected with the power generation device 22, the first docking mechanism 11 is electrically connected with the first energy storage device 12 in the aircraft 1, the first docking mechanism 11 and the second docking mechanism 21 are electrically connected, meanwhile, the power generation device 22 in the carrying bin 2 is electrically connected with the first energy storage device 12 in the aircraft 1, and when the aircraft 1 has a power taking requirement, the power generation device 22 can charge the first energy storage device 12.

In order to further optimize the technical solution in the above embodiment, the flying power driving device in the aircraft 1 in this embodiment is electrically connected to the first docking mechanism 11, and the flying power driving device in the aircraft 1 is usually a motor, and this design enables the power generation device 22 to be electrically connected to the first energy storage device 12 and the flying power driving device at the same time after the first docking mechanism 11 and the second docking mechanism 21 are docked, so that the power generation device 22 can charge the first energy storage device 12 as needed, and can also directly supply power to the flying power driving device to operate, and can also directly supply power to the flying power driving device while charging the first energy storage device 12, so as to increase the endurance mileage of the aircraft 1.

Referring to the docking manner of the aircraft 1 and the carrying cabin 2, a fourth docking mechanism 31 is arranged on the running chassis 3, a second energy storage device 33 for storing electric energy in the running chassis 3 is electrically connected with the fourth docking mechanism 31, as shown in fig. 6 and 7, a third docking mechanism 23 matched with the fourth docking mechanism 31 is arranged on the carrying cabin 2, the power generation device 22 is simultaneously electrically connected with the third docking mechanism 23, and when the third docking mechanism 23 is docked with the fourth docking mechanism 31, the third docking mechanism and the fourth docking mechanism 31 are also electrically connected.

The scheme also skillfully combines the docking mechanism and the electric connection mechanism between the running chassis 3 and the carrying bin 2 into a whole, the third docking mechanism 23 is docked with the fourth docking mechanism 31, the running chassis 3 is electrically connected with the carrying bin 2, the third docking mechanism 23 is electrically connected with the power generation device 22, the fourth docking mechanism 31 is electrically connected with the second energy storage device 33 in the running chassis 3, the power generation device 22 in the carrying bin 2 is electrically connected with the second energy storage device 33 in the running chassis 3 when the third docking mechanism 23 and the fourth docking mechanism 31 form electric connection, and the power generation device 22 can charge the second energy storage device 33 when the running chassis 3 has the power taking requirement.

In order to further optimize the technical solution in the above embodiment, the chassis power driving device in the driving chassis 3 in this embodiment is electrically connected to the fourth docking mechanism 31, and the chassis power driving device in the driving chassis 3 is also usually a motor, and this design makes the power generation device 22 be electrically connected to the second energy storage device 33 and the chassis power driving device at the same time after the third docking mechanism 23 and the fourth docking mechanism 31 are docked, and the power generation device 22 may charge the second energy storage device 33, may also directly supply power to the chassis power driving device to make it work, and may also directly supply power to the chassis power driving device while charging the second energy storage device 33, so as to increase the cruising range of the driving chassis 3.

Referring to fig. 2 to 7, in order to realize the electrical connection, a first charging connector 25 may be disposed in one of the first docking mechanism 11 and the second docking mechanism 21, and a first charging socket corresponding to the first charging connector 25 may be disposed on the other one of the first docking mechanism 11 and the second docking mechanism 21, as shown in fig. 5, the first charging connector 25 is disposed on the second docking mechanism 21, and accordingly, the first charging socket should be disposed on the first docking mechanism 11; one of the third docking mechanism 23 and the fourth docking mechanism 31 is provided with a second charging connector 32, and the other is provided with a second charging socket corresponding to the second charging connector 32, as shown in fig. 6 and 7, the fourth docking mechanism 31 is provided with the second charging connector 32, and correspondingly, the third docking mechanism 23 should be provided with the second charging socket.

Besides, a person skilled in the art can also convert the charging plug and the charging socket into other electrical connection forms, for example, the charging plug and the charging socket include a plurality of charging plugs and charging sockets, and the charging plugs and the charging sockets are uniformly distributed at the edge of the docking mechanism, or the charging plug and the charging socket are converted into a mutually-matched fastening mechanism to achieve the purpose of electrical connection, which is not limited herein, as long as it is ensured that the aircraft 1 and the traveling chassis 3 can be electrically connected after being docked with the carrying bin 2.

Normally, a third energy storage device electrically connected to the power generation device 22 is further disposed in the carrying cabin 2, and the third energy storage device obtains electric energy from the power generation device 22 and is a power-consuming device in the carrying cabin 2, such as: seats, glass, air conditioners, display screens, various sensors and various automatic switches, etc. provide power supplies.

It should be understood that the types of the first energy storage device 12, the second energy storage device 33, and the third energy storage device are not limited to one type, as long as the purpose of storing electric energy can be achieved, and the types of the three energy storage devices may be all consistent, partially consistent, or completely inconsistent.

The utility model discloses well first docking mechanism 11, second docking mechanism 21, third docking mechanism 23 and fourth docking mechanism 31's concrete form does not do the restriction, as long as can reach the butt joint function and guarantee the stability and the reliability of connecting can, possible docking mechanism includes but not limited to electromagnetism docking mechanism and buckle formula machinery latch mechanism.

The specific form of the power generation device 22 disposed in the carrier cabin 2 may be various, such as a conventional generator, which is usually driven by an internal combustion engine to generate power, so that a fuel tank of the internal combustion engine is also disposed in the carrier cabin 2; or the power generation device 22 may be a fuel cell to convert energy of high energy density into electric energy; of course, efficient photovoltaic modules can also be used to generate electricity.

In addition, the utility model also discloses a power supply method of the flying automobile, which at least comprises the power supply of the aircraft and the power supply of the running chassis, wherein,

the aircraft is powered as follows: when the first docking mechanism 11 and the second docking mechanism 21 are in a docking state, if a first power-taking requirement of the aircraft 1 is received, controlling a power supply device to supply power to the aircraft 1;

the running chassis supplies power as follows: when the third docking mechanism 23 and the fourth docking mechanism 31 are in a docking state, if a second power supply requirement of the running chassis 3 is received, the power supply device is controlled to supply power to the running chassis 3.

The power supply mode enables the carrying cabin to supply power for the flying aircraft and the running chassis in the running state, and meanwhile, when the flying aircraft and the running chassis are both in the stopping state and are both connected with the carrying cabin, the flying aircraft and the running chassis can be charged simultaneously.

More specifically, be provided with first local control module in aircraft 1 or the delivery storehouse 2, including local automatic power mode in the aircraft power supply at least, local automatic power mode can control power generation facility 22 at least and supply power to aircraft 1 with three kinds of different modes, and these three kinds of modes are respectively:

the first mode is as follows: the first local control module controls the power generation device 22 to charge the first energy storage device 12 only, and the flight electric drive device obtains electric energy from the first energy storage device 12; the second way is: the first local control module controls the power generation device 22 to supply power only to the flight power driving device, and the flight power driving device directly obtains electric energy from the power generation device 22 to maintain the flight of the aircraft 1; the third mode is as follows: the first local control module controls the power generation device 22 to supply power to the flight power drive while charging the first energy storage device 12.

If the flight in-process delivery storehouse 2 interior personnel take, then can also adopt the manual power-taking mode to realize delivery storehouse 2 to the power supply of aircraft 1, it is concrete, still be provided with manual power-taking switch and charge suggestion device (for example suggestion devices such as sound, light, electricity) in the delivery storehouse 2, include local manual power-taking mode at least in the aircraft power supply, local manual power-taking mode is: after receiving first power demand, the suggestion device that charges carries out the suggestion of charging, and operating personnel controls manual power switch closure so that power generation facility 22 supplies power to aircraft 1 with three kinds of different modes at least, and these three kinds of modes are respectively:

the first mode is as follows: power generation device 22 charges only first energy storage device 12; the second way is: the power generation device 22 supplies power only to the flight power drive device; the third mode is as follows: the power generation device 22 supplies power to the flight power driving device and simultaneously charges the first energy storage device 12, and the three modes can be manually selected by an operator or automatically matched and selected according to system judgment.

If flight in-process delivery storehouse 2 interior unmanned aerial vehicle takes, and local automatic get the electricity mode can't get into or when the local automatic electricity mode breaks down, can also design long-range automatic electricity mode of getting, specific still is provided with first remote signal transceiver module in delivery storehouse 2 or the aircraft 1, and long-range automatic electricity mode of getting is: after receiving first power demand, first remote signal transceiver module sends the power supply request to remote control center, and remote control center controls power generation facility 2 according to this power supply request at least with the power supply to the aircraft in three kinds of different modes, these three kinds of modes are respectively:

the first mode is as follows: power generation device 22 charges only first energy storage device 12; the second way is: the power generation device 22 supplies power only to the flight power drive device; the third mode is as follows: the power generation device 22 charges the first energy storage device 12 while supplying power to the flight power drive. The three modes can be manually selected by an operator or automatically matched and selected according to system judgment.

Under the ordinary condition, an aircraft electric energy early warning module is arranged in the aircraft 1, the first docking mechanism 11 and the second docking mechanism 21 are in a docking state, and when the aircraft electric energy early warning module meets a first early warning condition, the local automatic power taking mode, the local manual power taking mode and the remote automatic power taking mode are entered, the three power taking modes can set priorities according to requirements, the priority of the automatic power taking mode is the highest under the ordinary condition, the priority of the local manual power taking mode is the lowest, and the priority of the remote automatic power taking mode is the lowest.

First early warning condition can set up as required, the embodiment of the utility model provides an in first early warning condition be: the remaining charge in the first energy storage device 12 reaches a safety threshold (e.g., 10% of the remaining charge), or the remaining charge in the first energy storage device 12 is insufficient to continue the aircraft 1 to the target position.

Furthermore, a first display output module is further arranged in the aircraft 1 or the carrying cabin 2, a first display device is arranged in the carrying cabin 2, and the remaining electric quantity of the first energy storage device 12 can be converted into a first endurance mileage to be displayed on the first display device in real time so as to be referred by passengers and/or operators in the carrying cabin 2.

Referring to the implementation mode of the aircraft 1 during power taking, the running chassis 3 also has a local automatic power taking mode, a local manual power taking mode and a remote automatic power taking mode.

Specifically, still be provided with second control module in chassis 3 or the delivery storehouse 2 traveles, including local automatic electricity mode of getting in the chassis power supply that traveles at least, local automatic electricity mode of getting can control power generation facility 22 at least and supply power to chassis 3 that traveles with three kinds of different modes, these three kinds of modes are respectively:

the first mode is as follows: the second local control module controls the power generation device 22 to charge the second energy storage device 33 only, and the chassis electric drive device obtains electric energy from the second energy storage device 33; the second way is: the second local control module controls the power generation device 22 to supply power only to the chassis power driving device, and the chassis power driving device directly obtains electric energy from the power generation device 22 to maintain the running chassis 3 to run; the third mode is as follows: the second local control module controls the power generation means 22 to supply power to the chassis electric drive means while charging the second energy storage means 33.

If the flight in-process delivery storehouse 2 in someone take, then can also adopt manual power-taking mode to realize delivery storehouse 2 to the power supply of chassis 3 that traveles, it is concrete, still be provided with manual power-taking switch and charge suggestion device (for example suggestion devices such as sound, light, electricity) in the delivery storehouse 2, including local manual power-taking mode at least in the chassis power supply that traveles, local manual power-taking mode is: after receiving the second power-taking requirement, the charging prompting device carries out charging prompting, and an operator controls the manual power-taking switch to be closed so as to enable the power generation device 22 to supply power to the running chassis 3 in at least three different modes, wherein the three modes are respectively as follows:

the first mode is as follows: the power generation device 22 charges only the second energy storage device 33; the second way is: the power generation device 22 supplies power only to the chassis electric drive device; the third mode is as follows: the power generation device 22 supplies power to the chassis electric driving device and simultaneously charges the second energy storage device 33, and the three modes can be manually selected by an operator or automatically matched and selected according to system judgment.

If flight in-process delivery storehouse 2 interior unmanned aerial vehicle takes, and local automatic get the electricity mode can't get into or when the local automatic electricity mode breaks down, can also design long-range automatic electricity mode of getting, specific, still be provided with second remote signal transceiver module in delivery storehouse 2 or the chassis 3 that traveles, long-range automatic electricity mode of getting is: after receiving the second power-taking requirement, the second remote signal transceiver module sends a power supply request to the remote control center, and the remote control center controls the power generation device 2 to supply power to the running chassis in at least three different modes according to the power supply request, wherein the three modes are respectively as follows:

the first mode is as follows: the power generation device 22 charges only the second energy storage device 33; the second way is: the power generation device 22 supplies power only to the chassis electric drive device; the third mode is as follows: the power generation means 22 supplies power to the chassis electric drive means while charging the second energy storage means 33. The three modes can be manually selected by an operator or automatically matched and selected according to system judgment.

Under the ordinary condition, be provided with chassis electric energy early warning module in the chassis 3 that traveles, be in the butt joint state at third docking mechanism 23 and fourth docking mechanism 31 to chassis electric energy early warning module accords with the second early warning condition, gets into above-mentioned local automatic power mode, local manual power mode and long-range automatic power mode, and above-mentioned three kinds of power modes can set up the priority according to the demand, and the priority of automatic power mode is the highest under the ordinary condition, and the priority of local manual power mode is the second, and the priority of long-range automatic power mode is the lowest.

The second early warning condition can set up as required, the embodiment of the utility model provides an in the second early warning condition be: the remaining charge in the second energy store 33 reaches a safety threshold (for example 10% of the remaining charge), or the remaining charge in the second energy store 33 is not sufficient to continue the travel chassis 3 to the target position.

Furthermore, a second display output module is further arranged in the running chassis 3 or the carrying cabin 2, a second display device is arranged in the carrying cabin 2, and the remaining electric quantity of the second energy storage device 33 can be converted into a second endurance mileage to be displayed on the second display device in real time so as to be referenced by passengers and/or control personnel in the carrying cabin 2.

When the whole flying automobile is in a stopped state, the aircraft 1 and the running chassis 3 are both butted on the carrying cabin 2, as shown in fig. 1, at this time, the aircraft 1 and the running chassis 3 can obtain electric quantity supplement from a power grid or can supplement the electric quantity of the aircraft 1 and the running chassis 3 through the carrying cabin 2; the docking mechanisms in the figures are all arranged at the upper part and the lower part of the aircraft 1, the carrying cabin 2 and the running chassis 3, and the position of each docking mechanism can be changed by a person skilled in the art according to the shapes of the aircraft 1, the carrying cabin 2 and the running chassis 3.

It should be noted that, in the practical application process, the first control module, the second control module, the first display module, the second display module, and the like may not appear as independent devices, these different modules may be integrated in the same controller to achieve the desired control function, and the first display device and the second display device may be the same display screen.

The utility model discloses a technical scheme through set up power generation facility 22 on delivery storehouse 2, turns into the electric energy with high energy density's energy medium, then realizes supplementing the electric quantity of aircraft 1 and chassis 3 that traveles through the mode of butt joint, and the global design is exquisite, has effectively increased hovercar's continuation of the journey mileage under low-cost prerequisite.

It is right above the utility model provides a hovercar has carried out detailed introduction. The principles and embodiments of the present invention have been explained herein using specific examples, and the above descriptions of the embodiments are only used to help understand the method and its core ideas of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.

Claims

1. The flying automobile is characterized by comprising a carrying cabin (2) with a carrying function, an aircraft (1) with an electric driving mode and a running chassis (3) with the electric driving mode, wherein the carrying cabin (2) can be in butt joint with the aircraft (1) or the running chassis (3) or in butt joint with the aircraft (1) or the running chassis (3) at the same time, and a power supply device is further arranged on the carrying cabin (2) and is used for supplying electric energy to the aircraft (1) and/or the running chassis (3).

2. The flying automobile according to claim 1, characterized in that the power supply device is a power generation device (22), and the power generation device (22) is used for providing electric energy for the aircraft (1) which is docked with the carrying cabin (2) and has a power taking requirement and/or the running chassis (3).

3. The hovercar as claimed in claim 1, characterized in that a first docking mechanism (11) is arranged on the aircraft (1), a first energy storage device (12) for storing electric energy in the aircraft (1) is electrically connected with the first docking mechanism (11), a second docking mechanism (21) matched with the first docking mechanism (11) is arranged on the carrying cabin (2), the power supply device is electrically connected with the second docking mechanism (21), and when the first docking mechanism (11) and the second docking mechanism (21) are docked, the first docking mechanism (11) and the second docking mechanism (21) are electrically connected.

4. The hovercar as claimed in claim 3, characterized in that a fourth docking mechanism (31) is arranged on the chassis (3), a second energy storage device (33) for storing electric energy in the chassis (3) is electrically connected with the fourth docking mechanism (31), a third docking mechanism (23) matched with the fourth docking mechanism (31) is arranged on the carrying cabin (2), the power supply device is electrically connected with the third docking mechanism (23), and when the third docking mechanism (23) and the fourth docking mechanism (31) are docked, the third docking mechanism (23) and the fourth docking mechanism (31) are electrically connected.

5. A flying automobile according to claim 4, characterised in that the flying electric drive in the aircraft (1) is electrically connected to the first docking mechanism (11).

6. A flying automobile according to claim 5, characterised in that the chassis electrical drive in the running chassis (3) is electrically connected to the fourth docking mechanism (31).

7. A flying automobile according to any one of claims 4-6, characterized in that a third energy storage device is arranged in the carrying cabin (2) and is used for providing electric energy for the electric appliances of the carrying cabin (2) itself.

8. A flying automobile according to claim 7, wherein the first energy storage device is a battery and/or a supercapacitor, the second energy storage device is a battery and/or a supercapacitor and the third energy storage device is a battery and/or a supercapacitor.

9. The hovercar of claim 4, wherein the first docking mechanism (11), the second docking mechanism (21), the third docking mechanism (23) and the fourth docking mechanism (31) are mutually matched electromagnetic docking mechanisms or mechanical clamping structures.

10. A flying automobile according to any one of claims 2 to 6 and 8 to 9, wherein the power supply means is a generator, a fuel cell or a photovoltaic module.

11. The flying automobile of claim 1, wherein an aircraft energy source early warning module for monitoring the remaining amount of electricity in the aircraft is further arranged in the aircraft, a chassis energy source early warning module for monitoring the remaining amount of electricity in the running chassis is further arranged in the running chassis, a first local control module for controlling the power supply device to supply the electricity to the aircraft is further arranged in the aircraft or the carrying cabin, a second local control module for controlling the power supply device to supply the electricity to the running chassis is further arranged in the running chassis or the carrying cabin, the aircraft energy source early warning module is in communication connection with the first local control module, and the chassis energy source early warning module is in communication connection with the second local control module.