CN110884311A - Power supply control system and three-dimensional traffic operation system of hovercar - Google Patents
Power supply control system and three-dimensional traffic operation system of hovercar Download PDFInfo
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- CN110884311A CN110884311A CN201911315288.0A CN201911315288A CN110884311A CN 110884311 A CN110884311 A CN 110884311A CN 201911315288 A CN201911315288 A CN 201911315288A CN 110884311 A CN110884311 A CN 110884311A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
- B60L53/60—Monitoring or controlling charging stations
- B60L53/66—Data transfer between charging stations and vehicles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/70—Energy storage systems for electromobility, e.g. batteries
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/10—Technologies relating to charging of electric vehicles
- Y02T90/12—Electric charging stations
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/10—Technologies relating to charging of electric vehicles
- Y02T90/16—Information or communication technologies improving the operation of electric vehicles
Abstract
The invention relates to a power supply control system of a flying automobile, the flying automobile comprises a carrying cabin, an aircraft and a running chassis, the carrying cabin can be in butt joint with any one of the aircraft and the running chassis or can be in butt joint with the aircraft and the running chassis at the same time, a power supply device is also arranged on the carrying cabin, and the power supply control system comprises: the aircraft electric energy early warning module is arranged in the aircraft and used for sending out a first power taking demand; the first local control module controls the power supply device to supply power to the aircraft after receiving the first power taking requirement; the chassis electric energy early warning module is arranged in the running chassis and used for sending a second power taking demand; and the second local control module controls the power supply device to supply power to the running chassis after receiving the second power taking requirement. The scheme can effectively improve the endurance mileage of the hovercar and obviously reduce the electricity taking cost of the aircraft and the running chassis. The invention also discloses a three-dimensional traffic operation system.
Description
Technical Field
The invention relates to the technical field of design and production of flying automobiles, in particular to a power supply control system and a three-dimensional traffic operation system of a flying automobile.
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 invention relates to a flying automobile, in particular to a separated flying automobile, wherein the separated flying automobile generally comprises a carrying cabin, a running chassis and an aircraft, the running chassis is used for running on a ground road, and the carrying cabin can be combined with the running chassis or the aircraft according to requirements so as to realize ground transportation or air transportation of the carrying cabin.
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.
Disclosure of Invention
One of the objectives of the present invention is to provide a power supply control system for an hovercar, so as to conveniently and effectively improve the endurance mileage and flight time of the hovercar, thereby ensuring the carrying capacity of the hovercar.
Another objective of the present invention is to provide a three-dimensional traffic operation system including the above power supply control system.
In order to achieve the above object, the present invention provides a power supply control system for a flying vehicle, wherein the flying vehicle includes a carrying cabin having a carrying function, an aircraft having an electric drive mode, and a traveling chassis having an electric drive mode, the carrying cabin can be docked with either one of the aircraft and the traveling chassis or both of them, the carrying cabin is further provided with a power supply device, the power supply device is configured to supply electric energy to the aircraft and/or the traveling chassis, and the power supply control system includes:
the aircraft electric energy early warning module is arranged in the aircraft and sends a first power taking demand under a first early warning condition;
the first local control module is arranged in the aircraft or the carrying bin, and after the first power taking requirement is received, if the aircraft and the carrying bin are in a butt joint state, the power supply device is controlled to supply power to the aircraft;
the chassis electric energy early warning module is arranged in the running chassis and sends a second power taking requirement under a second early warning condition;
and the second local control module is arranged in the running chassis or the carrying cabin, and controls the power supply device to supply power to the running chassis if the running chassis and the carrying cabin are in a butt joint state after the second power taking requirement is received.
Preferably, the first warning condition is:
the remaining charge in the aircraft reaches a safety threshold, or the remaining charge in the aircraft is insufficient to continue the aircraft to a target location.
Preferably, the second warning condition is:
the remaining capacity of the chassis reaches a safety threshold, or the remaining capacity of the chassis is insufficient to continue the chassis to a target position.
Preferably, the system also comprises a remote control center, a first remote signal transceiver module and a second remote signal transceiver module, wherein,
when the remote control center receives a power supply request sent by the first remote signal transceiver module, if the aircraft is in a butt joint state with the carrying bin, the remote control center controls the power supply device to supply power to the aircraft; when the remote control center receives a power supply request sent by the second remote signal transceiver module, if the running chassis is in a butt joint state with the carrying cabin, the remote control center controls the power supply device to supply power to the running chassis;
the first remote signal transceiver module is arranged in the aircraft or the carrying bin and sends a power supply request to the remote control center after receiving the first power taking requirement;
the second remote signal transceiver module is arranged in the running chassis or the carrying cabin and sends a power supply request to the remote control center after receiving the second power taking requirement.
Preferably, the aircraft is provided with a flight electric drive device and a first energy storage device for storing electric energy, and the mode of supplying power to the aircraft by the power supply device comprises: supplying power only to the first energy storage device; supplying power only to the flight power drive; or the flight power drive device is powered simultaneously with the first energy storage device.
Preferably, a chassis electric drive device and a second energy storage device for storing electric energy are arranged in the traveling chassis, and the mode of supplying power to the traveling chassis by the power supply device includes: supplying power only to the second energy storage device; supplying power only to the chassis power drive; or the second energy storage device is powered at the same time as the chassis electric drive device.
The three-dimensional traffic operation system disclosed by the invention comprises any one of the power supply control systems disclosed in the above, and in addition, the three-dimensional traffic operation system further comprises an operation center and a plurality of flying vehicles, wherein each flying vehicle comprises a carrying cabin with a carrying function, an aircraft with an electric drive mode and a running chassis with an electric drive mode, the aircraft is internally provided with a flying electric drive device and a first energy storage device for storing electric energy, the running chassis is internally provided with a chassis electric drive device and a second energy storage device for storing electric energy, the carrying cabin can be butted with any one of the aircraft and the running chassis or butted with both of the aircraft and the running chassis, the carrying cabin is also provided with a power supply device for supplying electric energy to the aircraft and/or the running chassis, and the operation center is at least used for carrying out state monitoring and fault diagnosis on the flying vehicle, the aircraft, the running chassis and the carrying cabin are all internally provided with a first communication module which is used for being in communication connection with the operation center.
Preferably, the operation center at least comprises a center communication module, a center logic processing module, a center display module and a center control terminal, wherein,
the central communication module is in real-time communication with the first communication module and acquires state information of the aircraft, the running chassis and the carrying bin;
the central logic processing module judges whether the aircraft, the running chassis and the carrying cabin run normally according to the state information acquired by the central communication module; when the aircraft electric energy early warning module sends out a first power taking demand, the central logic processing module obtains an optimal mode for the power supply device to supply power to the aircraft according to the state information of the aircraft; when the chassis electric energy early warning module sends out a second power taking demand, the central logic processing module obtains an optimal power supply mode from the power supply device to the running chassis according to the state information of the running chassis;
the central display module is used for displaying the processing result of the central logic processing module;
and the central control terminal is used for an operator to send a control instruction to the aircraft, the running chassis and the carrying cabin.
Preferably, the remote control center comprises a second communication module, the first communication module, the second communication module and the center communication module are all in real-time communication connection, and the operation center is further used for scheduling the hovercar and regulating and controlling the power supply control system.
Preferably, the remote control center and the operation center adopt a wired or wireless communication mode.
According to the technical scheme, in the power supply control system of the flying automobile disclosed by the invention, the power supply device is arranged in the carrying bin of the targeted flying automobile, and when the aircraft is butted on the carrying bin and the aircraft electric energy early warning module sends out a first power taking demand, the first local control module can control the power supply device to supply power to the aircraft; when the running chassis is in butt joint with the carrying bin and the chassis electric energy early warning module sends out a second power taking demand, the second local control module can control the power supply device to supply power to the running chassis, so that a stable and reliable energy guarantee is provided for the flying automobile in the process of executing a transportation task, compared with the mode of adding a storage battery in the aircraft or the running chassis at present, the scheme can improve the endurance mileage of the flying automobile to a greater extent, and compared with the mode of constructing a ground charging pile, the scheme remarkably reduces the power taking cost of the aircraft and the running chassis.
Therefore, the power supply control system of the flying automobile disclosed by the invention ensures that the aircraft and the running chassis obtain stable and reliable power supply with low cost, and effectively improves the carrying capacity of the flying automobile.
The three-dimensional traffic operation system disclosed by the invention has the corresponding technical advantages of the power supply control system due to the adoption of the power supply control system, and the description is omitted;
meanwhile, the three-dimensional traffic operation system can also monitor and diagnose the operation state, the energy condition, the position information, the conditions of various auxiliary electronic devices on each flying automobile and the like, so that the ground and air traffic system consisting of the flying automobiles, the power supply control system and the operation center can normally and orderly operate.
Drawings
Fig. 1 is a schematic view of a communication principle related to an aircraft in a three-dimensional traffic operation system disclosed in an embodiment of the invention;
FIG. 2 is a schematic view of the communication principle related to the chassis in the three-dimensional transportation operation system disclosed in the embodiment of the invention;
FIG. 3 is a schematic view of the overall structure of the flying automobile disclosed in the embodiment of the invention;
FIG. 4 is a schematic overall structure view of the aircraft disclosed in the embodiment of the invention;
FIG. 5 is a schematic structural view of a first energy storage device and a first docking mechanism of the aircraft shown in FIG. 2;
FIG. 6 is a schematic view of the overall structure of the disclosed carrier magazine;
fig. 7 is a schematic structural view of the power generation device on the carrier bin shown in fig. 5 and the second docking mechanism and the third docking mechanism;
FIG. 8 is a schematic overall view of a land vehicle chassis disclosed in an embodiment of the present invention;
fig. 9 is a schematic structural view of the second energy storage device and the fourth docking mechanism of the running chassis shown in fig. 8.
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
One of the cores of the invention is to provide a power supply control system of the flying automobile, so that the endurance mileage and the flight time of the flying automobile can be conveniently and effectively improved, and the carrying capacity of the flying automobile is further ensured.
Another objective of the present invention is to provide a three-dimensional traffic operation system including the above power supply control system.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Before describing the power supply system of the hovercar disclosed in the present application, it is necessary to describe the hovercar to which the power supply system is directed.
Referring to fig. 3 to 9, 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 2 includes, but is not limited to, a battery with a power storage function, a super capacitor, and the like, and when the power supply device is the battery or the super capacitor, the function of the carrying cabin is similar to that of a charger currently charging the mobile device; in addition, the power supply device may include a power generation device 22 that can convert another type of energy into electric energy, and as a preferable embodiment, the power supply device in the present invention is the power generation device 22.
The power supply control system disclosed by the invention is based on the hovercar and also comprises an aircraft electric energy early warning module, a first local control module, a chassis electric energy early warning module and a second local control module, wherein under a first early warning condition, the aircraft electric energy early warning module sends out a first power taking requirement, the first local control module is arranged in the aircraft 1 or the carrying bin 2, and after receiving the first power taking requirement, if the aircraft 1 and the carrying bin 2 are in a butt joint state, the first local control module controls a power supply device to supply power to the aircraft;
under a second early warning condition, the chassis electric energy early warning module sends out a second power-taking requirement, and after the second power-taking requirement is received, if the running chassis 3 and the carrying cabin 2 are in a butt joint state, the second local control module controls the power supply device to supply power to the running chassis.
In the power supply control system for the hovercar disclosed in the above embodiment, the hovercar to which the power supply device is directed is provided in the carrying cabin, and when the aircraft 1 is docked on the carrying cabin 2 and the aircraft electric energy early warning module sends out the first power taking demand, the first local control module can control the power supply device to supply power to the aircraft 1; when the running chassis 3 is butted on the carrying bin 2 and the chassis electric energy early warning module sends out a second power taking demand, the second local control module can control the power supply device to supply power to the running chassis 3, under the control of the first local control module and the second local control module, the aircraft 1 and the running chassis 3 realize a local automatic power taking process, a stable and reliable energy guarantee is provided for the flying automobile in the process of executing a transportation task, compared with the mode of increasing the storage battery in the aircraft 1 or the running chassis 3 at present, the scheme can increase the endurance mileage of the flying automobile to a greater extent, and compared with the mode of constructing a ground charging pile, the scheme remarkably reduces the power taking cost of the aircraft 1 and the running chassis 3.
Therefore, the power supply control system for the hovercar 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 hovercar.
In the power supply control system disclosed in the embodiment of the present invention, automatic docking (of course, manual or semi-automatic docking) can be achieved between the aircraft 1 and the delivery cabin 2 and between the driving chassis 3 and the delivery cabin 2, and accurate docking is achieved by the flight control system of the aircraft 1 in combination with the differential GPS and the visual positioning system, which is widely used in the field (for example, the automatic docking technology in the air is disclosed in chinese patents with publication numbers CN109334968A, CN109533341A, and CN 106772514A), so the docking technology in this embodiment is not described in detail.
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 makes the power generation device 22 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 according to the requirement, or directly supply power to the flying power driving device to make it work, or directly supply power to the flying power driving device while charging the first energy storage device 12 to increase the endurance mileage of the aircraft 1, and the above three charging modes can be manually switched freely by adding a change-over switch, and of course, can also be automatically switched by a control program, when the automatic switching is performed, the switching condition can be set in a user-defined mode, for example, the switching condition can be set according to the electricity-taking requirement, the electric quantity residual condition of an aircraft or a running chassis and the like.
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. 8 and 9, 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. 4 to 9, 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 of the first docking mechanism 11 and the second docking mechanism 21, as shown in fig. 7, 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. 8 and 9, 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 specific forms of the first docking mechanism 11, the second docking mechanism 21, the third docking mechanism 23 and the fourth docking mechanism 31 in the present invention are not limited as long as the docking function can be achieved and the stability and reliability of the connection can be ensured, and possible docking mechanisms include, but are not limited to, an electromagnetic docking mechanism and a snap-in mechanical latching 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.
It should be noted that the power supply control system disclosed in the above embodiment enables the carrier pod to supply power to both the flying aircraft 1 and the running chassis 3, and also to charge both the flying aircraft and the form chassis when both the flying aircraft 1 and the form chassis 3 are in a stopped state and are engaged with the carrier pod 2.
In the local automatic electricity taking process, the power generation device 22 can supply power to the aircraft 1 in at least three different ways, which are:
the first mode is as follows: the power generation device 22 only charges the first energy storage device 12, and the flight power driving device obtains electric energy from the first energy storage device 12; the second way is: the power generation device 22 only supplies power to the flight power drive device, and the flight power drive device directly obtains electric energy from the power generation device 22 to maintain the aircraft 1 to fly; 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.
If the flight in-process delivery storehouse 2 interior personnel take, then can also adopt manual power-taking mode to realize delivery storehouse 2 to aircraft 1's power supply, 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, among the above-mentioned power supply control system, power supply unit can also include local manual power-taking mode to the power supply mode of aircraft, and 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 no person sits in the carrying bin 2 in the flying process, and the local automatic power-taking mode cannot enter or the local automatic power-taking mode fails, a remote automatic power-taking mode can be designed, the power supply control system under the situation is further improved on the basis of the above embodiment, please refer to fig. 1 and 2, the power supply control system further comprises a remote control center, a first remote signal transceiving module and a second remote signal transceiving module, and when the remote control center receives a power supply request sent by the first remote signal transceiving module, if the aircraft 1 and the carrying bin 2 are in a butt joint state, the first remote control center controls a power supply device to supply power to the aircraft 1;
when the remote control center receives the power supply request sent by the second remote signal transceiver module, if the running chassis 3 and the carrying cabin 2 are in a butt joint state, the second remote control center controls the power supply device to supply power to the running chassis 3.
The first remote signal transceiver module is arranged in the aircraft 1 or the carrying bin 2, and the first remote signal transceiver module sends a power supply request to the remote control center after receiving a first power taking demand; the second remote signal transceiver module is arranged in the running chassis 3 or the carrying bin 2, and the second remote signal transceiver module sends a power supply request to the remote control center after receiving the second power taking requirement.
Similarly, under the control of the remote control centre, the power generation means 22 also supply power to the aircraft in at least three different ways:
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.
The power supply system comprises a local automatic power supply mode, a local manual power supply mode and a remote automatic power supply mode, wherein the three power supply modes can be set with priorities according to requirements, the priority of the local automatic power supply mode is the highest in a normal condition, the priority of the local manual power supply mode is the next highest, and the priority of the remote automatic power supply mode is the lowest.
The first early warning condition may be set as required, and in the embodiment of the present invention, the first early warning condition is: 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, in the process of local automatic power supply, the power generation device 22 can supply power to the running chassis 3 in at least three different modes, which are respectively:
the first mode is as follows: the power generation device 22 only charges the second energy storage device 33, and the chassis electric drive device obtains electric energy from the second energy storage device 33; the second way is: the generator 22 only supplies power to the chassis power drive, which directly draws power from the generator 22 to maintain the running chassis 3 running; 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.
If the personnel take in the in-process of flying delivery storehouse 2, then can also adopt local 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, among the above-mentioned power supply control system, power supply unit can also include local manual power-taking mode to the mode of chassis power supply that traveles, and 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 no person takes in the carrying cabin 2 in the flight process, and the local automatic power-taking mode cannot enter or the local automatic power-taking mode fails, a remote automatic power-taking mode can be designed, under the control of a remote control center, the power generation device 22 supplies power to the running chassis 3 in at least three different modes, and the three modes are respectively:
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.
The power supply system comprises a local automatic power supply mode, a local manual power supply mode and a remote automatic power supply mode, wherein the three power supply modes can be set with priorities according to requirements, the priority of the automatic power supply mode is the highest under a common condition, and the priority of the local manual power supply mode is the next lowest and the priority of the remote automatic power supply mode is the lowest.
The second early warning condition may be set as required, and in the embodiment of the present invention, the second early warning condition is: 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. 3, 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 an actual application process, the first local control module, the second local 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 a desired control function, and the first display device and the second display device may be the same display screen.
In addition, the invention also discloses a three-dimensional traffic operation system, which comprises an operation center, a power supply control system disclosed in the embodiment and a plurality of flying cars disclosed in the embodiment, wherein a first communication module for communication connection with the operation center is arranged in each of the aircraft 1, the running chassis 3 and the carrying cabin 2, a second communication module for communication connection with the operation center is arranged in the remote control center, and the first communication module, the second communication module and the center communication module or any two of the first communication module, the second communication module and the center communication module can be in real-time communication, and it needs to be explained that the aircraft electric energy early warning module, the first local control module and the first remote signal transceiver module are arranged on the aircraft 1 or the carrying cabin 2, so that the components can be in communication connection with the operation center through the first communication module arranged on the aircraft 1 and the carrying cabin 2 (the signal connection joints are not shown in fig. 1) Is (ii); the chassis electric energy early warning module, the second local control module and the second remote signal transceiver module are all arranged on the traveling chassis 3 or the carrying cabin 2, so that the components can be in communication connection with an operation center through the first communication modules arranged on the traveling chassis 3 and the carrying cabin 2 (the signal connection relation is not shown in fig. 1); the operation center can monitor and diagnose the running state, energy condition, position information, condition of various auxiliary electronic devices on each flying automobile, and the like; and the three-dimensional traffic operation system can also monitor the operation state, diagnose faults and regulate and control parameters of all modules and devices in the power supply control system, so that the ground and air traffic system consisting of the aerocar, the power supply control system and the operation center can operate normally and orderly.
Furthermore, the operation center at least comprises a center communication module, a center logic processing module, a center display module and a center control terminal, wherein,
the central communication module is in real-time communication with the first communication module, and acquires state information of the aircraft 1, the traveling chassis 3 and the carrying bin 2, wherein the state information of the aircraft 1 and the traveling chassis 3 includes but is not limited to running states of various parts, electric quantity conditions of the first energy storage device and the second energy storage device, positions of the aircraft 1 and the traveling chassis 3, destinations and the like;
the central logic processing module judges whether the aircraft 1, the running chassis 3 and the carrying cabin 2 normally run or not according to the state information acquired by the central communication module; when the aircraft electric energy early warning module sends out a first power taking demand, the central logic processing module obtains an optimal mode of supplying power to the aircraft 1 by the power supply device according to the state information of the aircraft 1; when the chassis electric energy early warning module sends out a second power taking demand, the central logic processing module obtains an optimal power supply mode of the power supply device to the running chassis 3 according to the state information of the running chassis 3; it should be noted that the logical operation method for obtaining the optimal power supply mode of the power supply device to the aircraft or the traveling chassis is not limited, and a person skilled in the art may design the logical operation method according to actual needs, for example, in an embodiment, after the aircraft 1 performs the task, the next task needs to be performed immediately, and the optimal power supply mode is to simultaneously supply power to the first energy storage device and the flight power driving device; if the aircraft 1 does not have other tasks after the task is executed and the electric quantity of the first energy storage device is sufficient, the flight electric drive device can be powered only; if the electric quantity of the first energy storage device is insufficient, the first energy storage device can be only powered, and the flying electric driving device can obtain electric power from the first energy storage device; the optimal power supply mode of the running chassis 3 can be designed by referring to the aircraft 1;
the central display module is used for displaying the processing result of the central logic processing module, an operator in the operation center can monitor the processing result of the central logic processing module in real time, and the operator can not intervene the processing result, so that the first local control module, the second local control module and the control center control the power supply device to supply power to the aircraft or the running chassis according to the processing result of the central logic processing module, and the operator can intervene the processing result, so that the first local control module, the second local control module and the control center control the power supply device to supply power to the aircraft 1 or the running chassis 3 according to the control instruction of the operator;
the central control terminal (e.g. a touch screen, a keyboard or a button) is used for the operator to send control commands to the aircraft 1, the chassis 3 and the carrier 2.
In addition, the operation center is also used for scheduling the hovercar and for parameter regulation and control of the power supply control system, for example, the operation center regulates and controls the first early warning condition and the second early warning condition, changes the flight destination of the aircraft 1, and the like.
Referring to fig. 1 and 2, the remote control center is actually a control station disposed on the ground, and the remote control center has a remote logic operation module in addition to the second communication module, and in an embodiment, after receiving the power supply request sent by the first remote signal transceiver module and the second remote signal transceiver module, the remote logic operation module further performs operation processing on the power supply request to determine whether to immediately control the power supply device to supply power to the aircraft 1 or the driving chassis 3.
Taking the aircraft 1 as an example, when the safety threshold of the remaining power in the aircraft 1 under the first early warning condition is set to be 30% of the power of the first energy storage device, and after the operation is performed by combining the destination information of the aircraft, the remote logic operation module obtains that the power is sufficient, the remote logic operation module does not send an instruction of immediate power supply, if the operation is performed by combining the destination information of the aircraft, the remote logic operation module obtains that the power is insufficient, the remote logic operation module sends an instruction of immediate power supply, and the power supply device immediately supplies power to the aircraft 1 at the moment; the logic module determines whether or not immediate power supply to the chassis 3 is required as will be understood with reference to the above description.
Those skilled in the art CAN understand that the hovercar and the remote control center and the operation center should be connected by wireless communication, and the communication components in the aircraft 1, the communication components in the delivery cabin 2 and the communication components in the chassis 3 CAN be connected by wired or wireless communication (i.e. communication), and the remote control center and the operation center are connected by wireless communication, wherein the wired and wireless communication includes but is not limited to serial communication, USB communication, CAN communication, ethernet, bluetooth, mobile communication, LoRa, WIFI, Zigbee, NFC, etc.
The three-dimensional traffic operation system and the power supply control system of the hovercar provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (10)
1. The utility model provides a power supply control system of hovercar, characterized in that, hovercar includes delivery storehouse (2) that has the delivery function, aircraft (1) that has the electric drive mode to and chassis (3) of traveling that has the electric drive mode, delivery storehouse (2) can with aircraft (1) with any one dock in chassis (3) of traveling or dock simultaneously with both, still be provided with power supply unit on delivery storehouse (2), power supply unit is used for to provide the electric energy to aircraft (1) and/or chassis (3) of traveling, power supply control system includes:
the aircraft electric energy early warning module is arranged in the aircraft (1) and sends a first power taking demand under a first early warning condition;
the first local control module is arranged in the aircraft (1) or the carrying bin (2), and after the first power taking requirement is received, if the aircraft (1) and the carrying bin (2) are in a butt joint state, the power supply device is controlled to supply power to the aircraft (1);
the chassis electric energy early warning module is arranged in the running chassis (3) and sends a second power taking requirement under a second early warning condition;
and the second local control module is arranged in the running chassis (3) or the carrying cabin (2), and after the second power taking requirement is received, if the running chassis (3) and the carrying cabin (2) are in a butt joint state, the power supply device is controlled to supply power to the running chassis (3).
2. The power supply control system of claim 1, wherein the first pre-warning condition is:
the remaining charge in the aircraft (1) reaches a safety threshold, or the remaining charge in the aircraft (1) is insufficient to continue the aircraft (1) to a target position.
3. The power supply control system of claim 1, wherein the second pre-warning condition is:
the remaining capacity of the chassis (3) reaches a safety threshold value, or the remaining capacity of the chassis (3) is insufficient to continue the chassis (3) to a target position.
4. The power supply control system of claim 1, further comprising a remote control center, a first remote signal transceiver module, and a second remote signal transceiver module, wherein,
when the remote control center receives a power supply request sent by the first remote signal transceiver module, if the aircraft (1) and the carrying bin (2) are in a butt joint state, the power supply device is controlled to supply power to the aircraft (1); when the remote control center receives a power supply request sent by the second remote signal transceiver module, if the running chassis (3) is in a butt joint state with the carrying cabin (2), the power supply device is controlled to supply power to the running chassis (3);
the first remote signal transceiver module is arranged in the aircraft (1) or the carrying bin (2), and sends a power supply request to the remote control center after receiving the first power taking requirement;
the second remote signal transceiver module is arranged in the running chassis (3) or the carrying cabin (2), and sends a power supply request to the remote control center after receiving the second power taking requirement.
5. The power supply control system according to claim 1 or 4, characterized in that the aircraft (1) is provided with a flight power drive and a first energy storage device for storing electrical energy, and the power supply device supplies power to the aircraft (1) by means of: supplying power only to the first energy storage device; supplying power only to the flight power drive; or the flight power drive device is powered simultaneously with the first energy storage device.
6. The power supply control system according to claim 1 or 4, wherein the traveling chassis (3) is provided therein with a chassis power drive device and a second energy storage device for storing electric energy, and the manner in which the power supply device supplies power to the traveling chassis includes: supplying power only to the second energy storage device; supplying power only to the chassis power drive; or the second energy storage device is powered at the same time as the chassis electric drive device.
7. A three-dimensional transportation operation system, comprising the power supply control system, the operation center and a plurality of flying vehicles according to any one of claims 1 to 6, wherein the flying vehicles comprise a carrying cabin (2) with carrying function, an aircraft (1) with electric drive mode, and a driving chassis (3) with electric drive mode, the aircraft (1) is provided with a flying electric drive device and a first energy storage device for storing electric energy, the driving chassis (3) is provided with a chassis electric drive device and a second energy storage device for storing electric energy, the carrying cabin (2) can be butted with any one of the aircraft (1) and the driving chassis (3) or can be butted with both of the aircraft (1) and the driving chassis (3), the carrying cabin (2) is further provided with a power supply device for supplying electric energy to the aircraft (1) and/or the driving chassis (3), the operation center is at least used for carrying out state monitoring and fault diagnosis on the hovercar, and first communication modules used for being in communication connection with the operation center are arranged in the aircraft, the running chassis and the carrying cabin.
8. The stereoscopic transportation operation system according to claim 7, wherein the operation center comprises at least a center communication module, a center logic processing module, a center display module and a center control terminal, wherein,
the central communication module is in real-time communication with the first communication module and acquires state information of the aircraft (1), the running chassis (3) and the carrying bin (2);
the central logic processing module judges whether the aircraft (1), the running chassis (3) and the carrying cabin (2) normally run or not according to the state information acquired by the central communication module; when the aircraft electric energy early warning module sends out a first power taking demand, the central logic processing module obtains the optimal power supply mode of the power supply device for the aircraft (1) according to the state information of the aircraft (1); when the chassis electric energy early warning module sends out a second power taking demand, the central logic processing module obtains an optimal power supply mode of the power supply device to the running chassis (3) according to the state information of the running chassis (3);
the central display module is used for displaying the processing result of the central logic processing module;
the central control terminal is used for an operator to send a control instruction to the aircraft (1), the running chassis (3) and the carrying cabin (2).
9. A three-dimensional transportation operation system, comprising the power supply control system according to claim 4, an operation center and a plurality of flying vehicles, wherein the flying vehicles comprise a carrying cabin (2) with carrying function, an aircraft (1) with electric drive mode, and a running chassis (3) with electric drive mode, the aircraft (1) is provided with a flying electric drive device and a first energy storage device for storing electric energy, the running chassis (3) is provided with a chassis electric drive device and a second energy storage device for storing electric energy, the carrying cabin (2) can be docked with either one of the aircraft (1) and the running chassis (3) or docked with both of them, the carrying cabin (2) is further provided with a power supply device for supplying electric energy to the aircraft (1) and/or the running chassis (3), the operation center is at least used for carrying out state monitoring and fault diagnosis on the hovercar, and first communication modules used for being in communication connection with the operation center are arranged in the aircraft, the running chassis and the carrying cabin;
the operation center at least comprises a center communication module, a center logic processing module, a center display module and a center control terminal, wherein,
the central communication module is in real-time communication with the first communication module and acquires state information of the aircraft (1), the running chassis (3) and the carrying bin (2);
the central logic processing module judges whether the aircraft (1), the running chassis (3) and the carrying cabin (2) normally run or not according to the state information acquired by the central communication module; when the aircraft electric energy early warning module sends out a first power taking demand, the central logic processing module obtains the optimal power supply mode of the power supply device for the aircraft (1) according to the state information of the aircraft (1); when the chassis electric energy early warning module sends out a second power taking demand, the central logic processing module obtains an optimal power supply mode of the power supply device to the running chassis (3) according to the state information of the running chassis (3);
the central display module is used for displaying the processing result of the central logic processing module;
the central control terminal is used for an operator to send a control instruction to the aircraft (1), the running chassis (3) and the carrying cabin (2);
the remote control center comprises a second communication module, the first communication module, the second communication module and the center communication module are all in real-time communication connection, and the operation center is further used for scheduling the hovercar and regulating and controlling the power supply control system.
10. The stereoscopic traffic operation system according to claim 9, wherein the first communication module, the second communication module and the central communication module are in wired or wireless communication.
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