Air-ground integrated electric appliance framework of hovercar

Abstract

The invention discloses an air-ground integrated electric appliance framework of a hovercar, which comprises a flight cabin domain and a chassis domain, and the flight cabin domain and the chassis domain are connected through a 5G cellular network. The flight cabin domain and the chassis domain are connected through the 5G cellular network, seamless switching between an air flight mode and a ground running mode of the hovercar is achieved, the flight cabin domain is responsible for storing separation and butt joint pressure threshold values, a switching instruction is sent through a human-computer interaction interface, equipment in a cabin is controlled, and the flight cabin domain and the chassis domain are connected through the 5G cellular network. The chassis domain is responsible for managing the ground driving and structure connection process, integrates the functions of environment perception, positioning navigation, energy management, communication, power control and the like, and ensures safe and efficient operation of the hovercar. Through key components such as a flight cabin ECU, an environment sensing system, a pose sensing system, a driving system, a communication system, a chassis ECU, a sensing system, a positioning navigation system and an energy management system, the system has the characteristics of timely communication, quick response, small interference and the like.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of flying cars, in particular to an air-ground integrated electrical appliance architecture of a flying car. BACKGROUND

[0002] A flying car is a new type of transportation tool combining traditional ground driving capability and air flight capability, aiming to improve urban traffic efficiency and relieve ground congestion through multi-mode operation, and is usually composed of a separable flight cabin and a chassis, capable of switching between air flight and ground driving to realize "air-ground integration" travel experience.

[0003] The working principle of the electrical appliance architecture of the traditional flying car mainly depends on independent control modules and communication networks. In the flight mode, the flight control system is responsible for receiving instructions from the pilot or the automatic driving system, and after processing by the flight control computer, the attitude adjustment, power distribution and the like of the aircraft are controlled to ensure flight safety. In the ground driving mode, the vehicle control system is responsible for managing power output, steering control, brake system and the like to realize smooth driving of the vehicle.

[0004] However, the traditional flying car electrical appliance architecture adopts a discrete design, that is, the flight system and the ground driving system each have independent control units and communication networks, and there is a lack of efficient interaction and cooperation mechanism between the two, which often needs manual intervention or complex preset programs when switching modes, thereby limiting the function integration and performance optimization of the flying car to a certain extent, and it is difficult to meet the requirements of efficient, safe and flexible travel of future intelligent traffic. SUMMARY

[0005] The application aims to provide an air-ground integrated electrical appliance architecture of a flying car, which has the advantages of efficient and seamless switching, and solves the problem that the traditional flying car electrical appliance architecture adopts a discrete design, that is, the flight system and the ground driving system each have independent control units and communication networks, and there is a lack of efficient interaction and cooperation mechanism between the two, which often needs manual intervention or complex preset programs when switching modes, thereby limiting the function integration and performance optimization of the flying car to a certain extent, and it is difficult to meet the requirements of efficient, safe and flexible travel of future intelligent traffic.

[0006] In order to achieve the above object, the present application provides the following technical scheme: An air-ground integrated electrical architecture of a flying car, comprising a flight cabin domain and a chassis domain, the flight cabin domain and the chassis domain are connected through a 5G cellular network, the flight cabin domain comprises a flight cabin ECU, a flight cabin environment perception system, a flight pose perception system, a flight driving system, a docking camera, a PWM controller, a flight inertial / satellite integrated navigation system, a flight cabin communication system, a flight cabin power supply system, a flight cabin docking system, a flight cabin lighting system, a flight cabin air conditioning system, a sound, a human-computer interaction interface and a flight cabin data transmission module, the chassis domain comprises a chassis ECU, a chassis perception system, a chassis positioning navigation system, a chassis energy management system, a chassis communication system, a chassis data transmission module, a chassis power supply system, a chassis docking unit, a chassis power system and a chassis fault warning system.

[0007] Preferably, the flight cabin communication system is connected with the flight cabin ECU through an Ethernet, the flight cabin communication system is connected with the flight cabin environment perception system, the flight pose perception system and the docking camera through a USB interface, the flight ECU is connected with the PWM controller through a USB interface, the flight cabin lighting system and the flight cabin air conditioning system are connected with the flight cabin ECU through a LIN bus respectively, the sound and the human-computer interaction interface are connected with the flight cabin ECU through an HDMI respectively, and the flight cabin power supply system is connected with the cabin communication system, the cabin docking system, the cabin lighting system, the cabin air conditioning system, the sound, the human-computer interaction page, the cabin ECU and the cabin environment perception system.

[0008] Preferably, the flight cabin environment perception system comprises a flight cabin front camera, a flight cabin rear camera, a landing camera and a flight cabin laser radar, and the flight cabin docking system comprises a flight cabin pressure sensor, a docking control unit and a driving docking actuator.

[0009] Preferably, the flight pose perception system comprises an air speed pipe, a radar altimeter, an attack angle and sideslip angle sensor and a magnetic heading meter, and the flight driving system comprises six electronic governors and six corresponding motors.

[0010] Preferably, the flight power supply system comprises a high-voltage power supply unit for supplying power to the flight cabin driving system, and a low-voltage power supply unit for supplying power to the flight ECU, the flight pose perception system, the flight communication system, the flight lighting system, the flight inertial / satellite integrated navigation system and the flight data transmission module.

[0011] Preferably, the chassis environment perception system comprises a chassis millimeter wave radar, a chassis laser radar and a chassis vision sensor, and the chassis positioning navigation system comprises a chassis GPS / BD, a chassis RTK and a chassis IMU.

[0012] Preferably, the chassis power supply system comprises a battery pack and a corresponding DC-DC converter, the chassis docking unit system comprises telescopic mechanisms at the front and rear of the vehicle, four locking mechanisms, a horizontal measurement unit, a hydraulic control mechanism and four hydraulic support rods, and the chassis power system comprises four motor controllers, four hub motors and four hydraulic brakes.

[0013] Compared with the prior art, the application has the following advantages:

[0014] The application connects the flight cabin domain and the chassis domain through a 5G cellular network, realizes seamless switching between the flight mode and the ground driving mode of the flying car, the flight cabin domain is responsible for storing the separation and docking pressure threshold, sending switching instructions through a human-machine interface, and controlling the equipment in the cabin such as lights, air conditioners and sound, the chassis domain is responsible for managing the ground driving and structural connection process, integrating environmental perception, positioning and navigation, energy management, communication and power control functions, and ensuring the safe and efficient operation of the flying car, the architecture also includes the flight cabin ECU, the environmental perception system, the pose perception system, the driving system, the communication system and the chassis ECU, the perception system, the positioning and navigation system, the energy management system and other key components, has the characteristics of timely communication, rapid response, safe and stable flight and driving, small interference and the like, and can be widely applied to the field of transportation. BRIEF DESCRIPTION OF DRAWINGS

[0015] Fig. 1 It is a schematic diagram of the overall structure of the application;

[0016] Fig. 2 It is a schematic diagram of the composition structure of the flight cabin information system of the application;

[0017] Fig. 3 It is a schematic diagram of the composition structure of the chassis information system of the application. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, not all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the application.

[0019] Embodiment 1

[0020] As Figs. 1-3As shown, it is the first embodiment of the application, which provides an air-ground integrated electrical architecture of a flying car, including a flight cabin domain and a chassis domain, the flight cabin domain and the chassis domain are connected through a 5G cellular network, the flight cabin domain includes a flight cabin ECU, a flight cabin environment perception system, a flight pose perception system, a flight driving system, a docking camera, a PWM controller, a flight inertial / satellite integrated navigation system, a flight cabin communication system, a flight cabin power supply system, a flight cabin docking system, a flight cabin lighting system, a flight cabin air conditioning system, a sound, a human-computer interaction interface and a flight cabin data transmission module, the chassis domain includes a chassis ECU, a chassis perception system, a chassis positioning navigation system, a chassis energy management system, a chassis communication system, a chassis data transmission module, a chassis power supply system, a chassis docking unit, a chassis power system and a chassis fault warning system.

[0021] As Figs. 1-3As shown, through the flight cabin ECU, when the flight cabin needs to be separated or docked with the chassis, according to the flight cabin data, the information sent by the flight cabin data transmission module that the flight cabin reaches the separation or docking position, the switching instruction for executing ground driving or air flight is sent to the flight cabin docking system and the flight cabin data transmission module, and the driving switching state information and the flight cabin environment information are sent to the human-computer interaction interface, the flight cabin environment perception system is used for sending the measured flight cabin real-time environment information to the flight cabin communication system, the flight pose perception system is used for sending the measured flight vehicle real-time pose information to the flight communication system, the flight driving system is used for controlling the corresponding motor and the corresponding electronic governor according to the 6 PWM signals sent by the PWM controller, and 6 sets of propellers are respectively output by 6 motors to drive the flight cabin to reach the first docking position, the docking camera is used for detecting whether the flight cabin is successfully docked with the chassis, and the docking result is sent to the flight cabin ECU, the PWM controller is used for generating 6 PWM signals according to the flight driving control instruction sent by the flight cabin ECU, and sending the 6 PWM signals to the flight driving system, the flight inertial / satellite integrated navigation system is used for sending the flight cabin real-time position to the flight communication system and providing navigation for the flight cabin, the flight cabin communication system is used for forwarding the flight cabin real-time pose information sent by the flight pose perception system, the flight cabin real-time environment information sent by the flight environment perception system, the flight cabin real-time position sent by the flight inertial / satellite integrated navigation system and the chassis real-time position sent by the chassis domain to the flight cabin ECU, and is also used for forwarding the flight cabin real-time position to the chassis domain, the flight cabin power supply system is used for powering the ECU, the flight pose perception system, the flight communication system, the flight driving system, the flight cabin lighting system, the flight inertial / satellite integrated navigation system, the flight cabin data transmission module, the flight cabin docking system, the flight cabin air conditioning system, the audio and the human-computer interaction interface, the flight cabin docking system is used for pre-storing the separation pressure threshold and the docking pressure threshold, and when the flight cabin needs to be separated or docked with the chassis, the separation or docking operation is performed according to the air flight switching instruction sent by the flight cabin ECU, the flight cabin lighting system is used for turning on or off the light in and outside the cabin according to the light on or light off control signal sent by the flight cabin ECU, the flight cabin air conditioning system is used for turning on or off the air conditioner in the cabin according to the air conditioner on or off control signal sent by the flight cabin ECU, the audio is used for playing or turning off the music according to the music on or off control signal sent by the flight cabin ECU, and the human-computer interaction interface is used for displaying the flight switching state information or the ground switching state information and the flight cabin environment information, receiving the air flight switching instruction or the ground driving switching instruction of the person in the cabin, and forwarding the air flight switching instruction or the ground driving switching instruction to the cabin data transmission module.The flight cabin data transmission module is used for corresponding forwarding of air flight switching instructions or ground travel switching instructions from a human-computer interaction interface to a flight cabin domain or a chassis domain by the cloud, the chassis perception system is used for sending collected information of the surrounding environment and obstacles to the chassis communication system, the chassis positioning and navigation system is used for receiving information sent by the chassis perception system, fusing the information with self-positioning data, and sending accurate position and speed information of the vehicle to the chassis communication system, and providing navigation and path planning functions for the chassis, the chassis energy management system is used for optimizing four-wheel torque distribution and electro-hydraulic brake distribution of the vehicle, and sending the distribution results to the chassis communication system, the chassis communication system is used for sending information from the chassis perception system, the chassis positioning and navigation system and the chassis energy management system to the chassis ECU, the chassis data transmission module is used for receiving ground-air switching instructions sent by the flight cabin data transmission module and control commands for vehicle travel through a 5G cellular network, and forwarding them to the chassis ECU, the chassis power supply system is used for supplying power for the chassis ECU, the chassis perception system, the chassis positioning and navigation system, the chassis energy management system, the chassis communication system, the chassis data transmission module, the chassis docking unit, the chassis power system and the chassis fault warning system, through the chassis docking unit, after receiving the low-altitude switching instructions sent by the chassis ECU, the information sent by the chassis perception system and the flight cabin perception system is fused, the flight cabin is lifted upward or downward to ensure the horizontal position of the flight cabin and the chassis, and the docking or separation operation of the chassis and the flight cabin is realized, the chassis power system is used for providing power required for vehicle travel according to the vehicle travel control signal sent by the chassis ECU, and completing driving, braking and steering of the vehicle, and the chassis fault warning system is used for monitoring the running state of the chassis system in real time, predicting and diagnosing potential faults, and sending the potential faults to the flight cabin data transmission module through the chassis data transmission module.

[0022] Embodiment 2

[0023] Reference Fig. 2 For the second embodiment of the application, the embodiment is based on the previous embodiment.

[0024] In this embodiment, the flight cabin communication system and the flight cabin ECU are connected through an Ethernet, the flight cabin communication system, the flight cabin environment perception system, the flight pose perception system and the docking camera are connected through a USB interface, the flight ECU and the PWM controller are connected through a USB interface, the flight cabin light system and the flight cabin air conditioning system are respectively connected to the flight cabin ECU through a LIN bus, the sound and the human-computer interaction interface are respectively connected to the flight cabin ECU through an HDMI, and the flight cabin power supply system is connected to the cabin communication system, the cabin docking system, the cabin light system, the cabin air conditioning system, the sound, the human-computer interaction page, the cabin ECU and the cabin environment perception system.

[0025] The flight cabin environment perception system comprises a flight cabin front camera, a flight cabin rear camera, a landing camera and a flight cabin laser radar, the flight cabin docking system comprises a flight cabin pressure sensor, a docking control unit and a driving docking actuator, wherein the flight cabin ECU is further connected to a power supply end of the cabin front camera, a power supply end of the cabin rear camera, a power supply end of the docking camera and a power supply end of the flight cabin laser radar.

[0026] The flight pose perception system comprises an airspeed tube, a radar altimeter, an angle of attack and sideslip angle sensor and a magnetic heading meter, the flight driving system comprises six electronic governors and six corresponding motors, one electronic governor corresponding to one motor, one electronic governor corresponding to one PWM controller to generate one PWM signal, and one motor corresponding to a group of propellers on the aircraft, and additionally four electronic governors and four corresponding motors, one electronic governor corresponding to one motor, one electronic governor corresponding to one PWM controller to generate one PWM signal, and four motors corresponding to four propeller arms of left front, right front, left rear and right rear respectively.

[0027] The flight power supply system comprises a high-voltage power supply unit for supplying power to the flight cabin driving system, and a low-voltage power supply unit for supplying power to the flight ECU, the flight pose perception system, the flight communication system, the flight light system, the flight inertial / satellite integrated navigation system and the flight data transmission module, wherein the high-voltage power supply unit is composed of eighteen groups of parallel battery groups, each battery group is composed of two 48V batteries connected in series; the low-voltage power supply unit is a voltage source outputting 24V voltage.

[0028] As Fig. 2The flight cabin pressure sensor is used to send the measured real-time pressure between the flight cabin and the chassis to the docking control unit; the docking control unit is used to pre-store a pressure threshold; according to the execution of the air flight switching instruction sent by the flight cabin ECU, when the first docking implementation pressure sent by the flight cabin pressure sensor is equal to the pressure threshold, the unlocking signal is sent to the driving docking actuator; according to the execution of the ground driving switching instruction sent by the flight cabin ECU, when the second real-time docking pressure sent by the flight cabin pressure sensor is equal to the second pressure threshold, the locking signal is sent to the driving docking actuator; the docking actuator is used to lock or unlock the chassis according to the locking signal or the unlocking signal sent by the docking control unit, the pitot tube is used to send the measured flight real-time speed to the flight cabin communication system; the radar altimeter is used to send the measured flight cabin real-time height to the flight cabin communication system; the angle of attack and sideslip angle sensor is used to send the measured flight cabin real-time attack angle and flight cabin real-time sideslip angle to the flight cabin communication system; the magnetic heading angle is used to send the measured flight cabin real-time heading to the flight cabin communication system, the electric governor is used to adjust the opening of the electric governor internal electronic switch according to the PWM signal sent by the PWM controller, and the rotation speed control signal is sent to the corresponding motor; the motor controls the corresponding propeller group to operate, and the rotation expansion and rotation folding of the left front, right front, left rear and right rear four propeller arms.

[0029] Embodiment 3

[0030] Reference Fig. 3 For the third embodiment of the present application, this embodiment is based on the previous two embodiments.

[0031] In this embodiment, the chassis environment perception system includes a chassis millimeter wave radar, a chassis laser radar and a chassis vision sensor, the chassis positioning and navigation system includes a chassis GPS / BD, a chassis RTK and a chassis IMU, and the chassis vision sensor includes a front camera and a rear camera.

[0032] The chassis power supply system includes a battery pack and a corresponding DC-DC converter, the chassis docking unit system includes telescopic mechanisms at the front and rear of the vehicle, four locking mechanisms, a horizontal measurement unit, a hydraulic control mechanism and four hydraulic support rods, and the chassis power system includes four motor controllers, four hub motors and four hydraulic brakes.

[0033] As Fig. 3As shown, chassis millimeter wave radar and chassis laser radar, for sending measured surrounding obstacle information to chassis communication system, chassis vision sensor, for sending measured surrounding environment information to chassis communication system, chassis GPS / BD, for obtaining real-time position of vehicle according to satellite positioning system, and sending to chassis communication system after fusion with data obtained by other devices, chassis RTK, for eliminating common error in satellite signal propagation, obtaining more accurate real-time position of vehicle, and sending to chassis communication system after fusion with data obtained by other devices, chassis IMU, for providing accurate real-time position of vehicle in a short time under GPS / BD signal loss or weak signal environment, and sending to chassis communication system after fusion with data obtained by other devices, through battery pack for powering the entire chassis and charging the flight cabin area, DC-DC converter for converting direct current from one voltage level to another voltage level, through the telescopic mechanism at the front and rear of the vehicle for controlling the telescoping of the front and rear of the vehicle, so that the flight cabin is exposed or wrapped; locking mechanism for locking the chassis and flight cabin, horizontal measurement unit for ensuring that the chassis and flight cabin remain relatively horizontal, hydraulic electric control mechanism for controlling the hydraulic support rod, hydraulic support rod for providing upward or downward lifting force, through the motor controller for sending the generated PWM signal to the corresponding in-wheel motor according to the steering, driving, braking control signal sent by the chassis ECU; in-wheel motor for outputting a certain speed according to the PWM signal sent by the motor controller, completing the steering, driving and braking operation; hydraulic brake for providing hydraulic braking force according to the electro-hydraulic braking distribution generated by the chassis energy management system.

[0034] In use, first, the separation pressure threshold and the docking pressure threshold are stored in the flight cabin domain in advance for judging whether the flight cabin and the chassis meet the conditions of structural separation or docking, when the flight cabin and the chassis need to be structurally separated, the personnel in the cabin sends an air flight switching instruction to the flight cabin domain through the human-computer interaction interface, the flight cabin domain receives the instruction and then forwards the switching instruction to the chassis domain through the cloud communication system, and displays the flight switching state information on the human-computer interaction interface, then the flight cabin fuses the real-time attitude information, the real-time environmental information, the real-time position information of the flight cabin, the real-time position information of the chassis domain and the height information of the lifting platform of the chassis domain according to the received air flight switching instruction, and sends the fused information to the chassis domain, the chassis domain controls the four propeller arms of the flight cabin, such as the left front, the right front, the left rear and the right rear, to rotate and unfold, and controls the start and rotation of the six groups of propellers, so as to perform the structural separation operation between the flight cabin and the chassis, when the flight switching state information displays "flight switching completed", the flight cabin domain receives the air flight switching completion response signal fed back from the chassis domain, and confirms that the structural separation operation is completed, when the flight cabin and the chassis need to be structurally connected, the personnel in the cabin also sends a ground driving switching instruction through the human-computer interaction interface, the flight cabin domain sends the instruction to the chassis domain through the cloud, and displays the driving switching state information on the human-computer interaction interface, at this time, the flight cabin fuses the real-time attitude information, the real-time environmental information, the real-time position information of the flight cabin, the real-time position information of the chassis domain and the height information of the lifting platform of the chassis domain according to the ground driving switching instruction, and sends the fused information to the chassis domain, the chassis domain controls the four propeller arms of the flight cabin to rotate and fold according to the information, and controls the six groups of propellers to stop running, so as to perform the structural connection operation between the flight cabin and the chassis, when the driving switching state information displays "driving switching completed", the flight cabin domain receives the ground driving switching completion response signal from the chassis domain, and confirms that the structural connection operation is completed, in addition, the flight cabin domain is also responsible for controlling the opening or closing of the cabin equipment such as lights, air conditioners and stereos according to the needs of the personnel in the cabin, to improve the riding comfort, at the same time, since the chassis domain can also be used to pre-store the separation pressure threshold and the docking pressure threshold as a basis for performing the structural separation or docking operation between the flight cabin and the chassis, the chassis domain is mainly responsible for the operation management of the flying car when driving on the ground, and the whole process control of the structural connection between the flight cabin and the chassis, through the integration of the chassis domain, the functions of environmental perception, positioning and navigation, energy management, communication and power control are integrated, and then the ground driving switching instruction and the pose information of the flight cabin from the flight cabin domain can be received and fused, so as to regulate and control the driving state of the vehicle, when the chassis ECU receives the flight mode switching instruction, the telescopic mechanism is controlled to extend the front and rear of the vehicle, so that the flight cabin is completely exposed, the chassis docking unit is then lifted upwards, when the separation pressure threshold is reached,The chassis docking unit stops lifting, and the telescopic mechanism retracts the front and rear of the vehicle, completing the separation process. When the chassis ECU receives a command to switch to ground mode, it first controls the telescopic mechanism to extend the front and rear of the vehicle, and then the chassis docking unit lifts downwards. When the docking pressure threshold is reached, the chassis docking unit stops lifting, and the telescopic mechanism retracts the front and rear of the vehicle, completing the docking process. After the flight cockpit and chassis are structurally connected, the chassis domain ensures the safe and efficient operation of the flying car in ground driving mode and feeds back real-time location information to the flight cockpit domain to support the integrated air-ground operation of the flying car. In addition, after the flight cockpit and chassis are structurally connected, the chassis domain can also receive charging commands from the flight cockpit domain and provide power support to the flight cockpit domain, realizing energy collaborative management. Through this structural coupling and separation architecture of the flight cockpit domain and chassis domain, the flying car can seamlessly switch between air flight and ground driving modes, and fully support its integrated air-ground operation through efficient signal communication and functional mode switching mechanisms.

[0035] All standard parts used in this application can be purchased from the market, and can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts and equipment adopt conventional models in the prior art. The control method is automatic control through a controller. The control circuit of the controller can be implemented by simple programming by those skilled in the art and is common knowledge in the field. Since this application is mainly used to protect mechanical devices, the control method and circuit connection will not be explained in detail in this application.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An integrated air-to-ground electrical architecture for a flying car, characterized in that, It includes a flight cockpit domain and a chassis domain, which are connected via a 5G cellular network. The flight cockpit domain includes a flight cockpit ECU, a flight cockpit environmental perception system, a flight attitude perception system, a flight drive system, a docking camera, a PWM controller, a flight inertial / satellite integrated navigation system, a flight cockpit communication system, a flight cockpit power system, a flight cockpit docking system, a flight cockpit lighting system, a flight cockpit air conditioning system, an audio system, a human-machine interface, and a flight cockpit data transmission module. The chassis domain includes a chassis ECU, a chassis perception system, a chassis positioning and navigation system, a chassis energy management system, a chassis communication system, a chassis data transmission module, a chassis power system, a chassis docking unit, a chassis power system, and a chassis fault early warning system.

2. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The flight cockpit communication system is connected to the flight cockpit ECU via Ethernet. The flight cockpit communication system is connected to the flight cockpit environment perception system, flight attitude perception system, and docking camera via USB interface. The flight ECU is connected to the PWM controller via USB interface. The flight cockpit lighting system and flight cockpit air conditioning system are connected to the flight cockpit ECU via LIN bus. The audio system and human-machine interface are connected to the flight cockpit ECU via HDMI. The flight cockpit power system is connected to the cockpit communication system, cockpit docking system, cockpit lighting system, cockpit air conditioning system, audio system, human-machine interface, cockpit ECU, and cockpit environment perception system.

3. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The flight cockpit environment perception system includes a front flight cockpit camera, a rear flight cockpit camera, a landing camera, and a flight cockpit lidar. The flight cockpit docking system includes a flight cockpit pressure sensor, a docking control unit, and a driving docking actuator.

4. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The flight attitude perception system includes: pitot tube, radar altimeter, angle of attack and sideslip angle sensors, and magnetoheading indicator. The flight drive system includes six electronic speed controllers and six corresponding motors.

5. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The flight power system includes a high-voltage power supply unit for powering the flight cockpit drive system, and a low-voltage power supply unit for powering the flight ECU, flight attitude perception system, flight communication system, flight lighting system, flight inertial / satellite integrated navigation system, and flight data transmission module.

6. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The chassis environment perception system includes a chassis millimeter-wave radar, a chassis lidar, and a chassis vision sensor. The chassis positioning and navigation system includes a chassis GPS / BD, a chassis RTK, and a chassis IMU.

7. The air-to-ground integrated electrical architecture of a flying car according to claim 1, characterized in that: The chassis power system includes a battery pack and a corresponding DC-DC converter. The chassis docking unit system includes telescopic mechanisms for the front and rear of the vehicle, four locking mechanisms, a level measuring unit, a hydraulic electronic control mechanism, and four hydraulic support rods. The chassis power system includes four motor controllers, four wheel hub motors, and four hydraulic brakes.

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