Aerocar power system, control method and electronic equipment

Abstract

The invention provides an aerocar power system, a control method and electronic equipment. The aerocar power system comprises a power battery, a first motor, a second motor, a first disconnecting device and a second disconnecting device. The power battery is electrically connected with the first motor and the second motor and used for providing a power source for the first motor and the second motor; the first motor is connected with a driving wheel of the hovercar through the first disconnecting device and used for providing driving power for the driving wheel. The second motor is connected with a first flying rotor wing of the flying car through a second disconnecting device and is used for providing driving power for the first flying rotor wing; the first motor is electrically connected with the second motor and is used for providing extra power for driving wheels of the hovercar when the first disconnecting device is in the combined state and the second disconnecting device is in the disconnected state; when the first disconnecting device is in the disconnected state and the second disconnecting device is in the combined state, additional power is provided for the first flying rotor wing of the flying car.

Description

[0001] This application claims priority to application number 2025107232775, invention name “A flying car power system, control method and electronic equipment”, and application date May 30, 2025. Technical Field

[0002] The present application relates to the intersection of electric aviation technology and electric vehicle technology, and more specifically, to a flying car power system, control method, and electronic equipment. Background Art

[0003] Current electric vehicles use electric motors as their powertrain, while helicopters and aircraft use fuel engines. Flying cars, which can both operate on public roads and remain airborne, are an emerging form of transportation. Their powertrain and control strategies are crucial, and no commercially available flying car powertrain exists. Summary of the Invention

[0004] The purpose of the embodiments of the present application is to provide a flying car power system, control method and electronic equipment, which are used to improve the problem that there are no flying car power systems on the market.

[0005] The present invention provides a flying car power system, comprising: a power battery, a first motor, a second motor, a first disconnect device, and a second disconnect device. The power battery is electrically connected to the first motor and the second motor to provide a power source for the first motor and the second motor. The first motor is connected to the driving wheels of the flying car via the first disconnect device to provide driving power to the driving wheels. The second motor is connected to the first rotor of the flying car via the second disconnect device to provide driving power to the first rotor. The first motor and the second motor are electrically connected to provide additional power to the driving wheels of the flying car when the first disconnect device is engaged and the second disconnect device is disconnected, or to provide additional power to the first rotor of the flying car when the first disconnect device is disconnected and the second disconnect device is engaged. In the implementation of the above solution, the first motor and the second motor in the flying car power system are electrically connected, so that when the first disconnect device is engaged and the second disconnect device is disconnected, the second motor can provide additional power to the wheels through the electrical connection. Even if the first motor fails, the second motor can still drive the wheels. When the second disconnect device is engaged and the first disconnect device is disconnected, the first motor can assist the second motor in driving the rotor. Therefore, when any disconnect device is engaged (land driving mode or air flight mode), the first motor and / or the second motor can provide power to the actuator (wheels or rotors), thereby improving flight thrust while enhancing power redundancy, thereby effectively providing a flying car power system with both power redundancy and safety.

[0006] Optionally, in this embodiment of the present application, the system further includes: a first transmission mechanism and a second transmission mechanism; one end of the first transmission mechanism is connected to the first motor, and the other end of the first transmission mechanism is connected to a first disconnect device, for transmitting the power generated by the first motor to the driving wheels of the flying car via the first disconnect device; one end of the second transmission mechanism is connected to the second motor, and the other end of the second transmission mechanism is connected to the second disconnect device, for transmitting the power generated by the second motor to the first flying rotor via the second disconnect device; the first and second motors are interconnected via the first and second transmission mechanisms, so that the first and second motors jointly provide power output to the driving wheels of the flying car or the first flying rotor. In the implementation of the above solution, the first and second motors are physically connected via the first and second transmission mechanisms, and combined with the switching logic of the disconnect device, the two motors can not only directly cooperate through electrical power but also achieve power sharing through a mechanical transmission path. For example, when the first disconnect device is engaged (wheel drive mode), the second motor can provide auxiliary power to the wheels via the transmission mechanism; conversely, when the second disconnect device is engaged (flight mode), the first motor can also provide support to the rotor via the transmission mechanism. This design not only allows the two motors to work together directly through electricity, but also enables power sharing through a mechanical transmission path. This electric + mechanical dual redundancy strategy breaks through the limitations of traditional pure electric or pure mechanical systems. When one motor fails or requires additional power support, the other motor can provide compensatory power through a mechanical transmission mechanism, thereby enhancing the reliability and redundancy of the entire system, and significantly improving the survivability and mission reliability of the flying car under extreme working conditions.

[0007] Optionally, in this embodiment of the present application, the vehicle further includes a vehicle differential connected to the first disconnect device and the driving wheels of the flying car; the vehicle differential is configured to provide different rotational speeds between the left and right driving wheels of the flying car. In implementing the above solution, the introduction of the vehicle differential allows the left and right driving wheels of the flying car to rotate at different speeds, thereby improving the tire slip and unstable handling caused by turning in traditional flying cars on the ground. Furthermore, the differential can dynamically distribute power based on the turning radius and road conditions, accelerating the outer wheels and decelerating the inner wheels, thereby achieving smooth turns in a pure rolling state. This overcomes the limitations of ground-based driving performance of flying cars. In particular, on complex road conditions (such as wet, muddy, or uneven roads), the differential can reduce the risk of tire slip through power redistribution, thereby improving vehicle maneuverability and driving safety.

[0008] Optionally, in an embodiment of the present application, the flying car power system further includes: a third motor, a fourth motor, a third disconnect device, and a fourth disconnect device; a power battery electrically connected to the third and fourth motors to provide a power source for the third and fourth motors; the third motor is connected to the driving wheels of the flying car via the third disconnect device to provide driving power to the driving wheels; the fourth motor is connected to the second flight rotor of the flying car via the fourth disconnect device to provide driving power to the second flight rotor; and the third motor is electrically connected to the fourth motor to provide additional power to the driving wheels of the flying car when the third disconnect device is engaged and the fourth disconnect device is disengaged, or to provide additional power to the second flight rotor of the flying car when the third disconnect device is disengaged and the fourth disconnect device is engaged. In the implementation of the above solution, by introducing the third and fourth motors and combining the intelligent switching of the third and fourth disconnect devices, a dual redundant power architecture for both ground and flight modes is constructed. If a motor or disconnect fails, another set of motors can directly take over power output through the power connection (for example, if the third motor fails during ground driving, the fourth motor can provide auxiliary power to the wheels; if the fourth motor fails during flight, the third motor can support the rotors). Even if multiple motors / disconnects fail simultaneously, cross-power supply logic can still maintain minimal operation. This design breaks through the limitations of "single-mode redundancy" (flight-only or ground-only) in traditional flying car power systems and achieves cross-mode, multi-level fault tolerance for the first time, significantly improving the survivability and mission reliability of flying cars in extreme operating conditions such as simultaneous multi-motor failures or complex airspace environments.

[0009] Optionally, in an embodiment of the present application, the flying car power system further includes: a fifth motor, a sixth motor, a fifth disconnecting device, and a sixth disconnecting device; the power battery is electrically connected to the fifth motor and the sixth motor, for providing a source of power for the fifth motor and the sixth motor; the fifth motor is connected to the driving wheels of the flying car through the fifth disconnecting device, for providing driving power for the driving wheels; the sixth motor is connected to the third flight rotor of the flying car through the sixth disconnecting device, for providing driving power for the third flight rotor; the fifth motor is electrically connected to the sixth motor, for providing additional power to the driving wheels of the flying car when the fifth disconnecting device is engaged and the sixth disconnecting device is disconnected, or, when the fifth disconnecting device is disconnected and the sixth disconnecting device is engaged, for providing additional power to the third flight rotor of the flying car. Providing additional power; the flying car power system also includes: a seventh motor, an eighth motor, a seventh disconnect device, and an eighth disconnect device; a power battery electrically connected to the seventh motor and the eighth motor to provide a power source for the seventh motor and the eighth motor; the seventh motor is connected to the driving wheels of the flying car via the seventh disconnect device to provide driving power to the driving wheels; the eighth motor is connected to the fourth flight rotor of the flying car via the eighth disconnect device to provide driving power to the fourth flight rotor; the seventh motor is electrically connected to the eighth motor to provide additional power to the driving wheels of the flying car when the seventh disconnect device is engaged and the eighth disconnect device is disconnected, or to provide additional power to the fourth flight rotor of the flying car when the seventh disconnect device is disconnected and the eighth disconnect device is engaged. In the implementation of the above solution, by introducing the fifth to eighth motors and their corresponding disconnect devices, a quad-redundant power architecture is constructed, which enables the flying car to have cross-mode and multi-level fault tolerance capabilities in both ground driving and flight modes. For example, if the fifth motor driving the wheels fails, the sixth motor (originally powering the third rotor) can reverse power the wheels through an electrical connection. Similarly, if the fourth motor of the rotor fails, the seventh motor (originally powering the wheels) can take over its power output. This multi-motor cross-powering logic transcends the limitations of traditional redundancy designs, which rely on "single-mode redundancy" (flight-only or ground-only). It achieves full-system cascade redundancy for the first time. This means that even when multiple motors or disconnect devices fail simultaneously (e.g., two wheel motors and one rotor motor fail), minimal operation can still be maintained by dynamically reconfiguring the power path. This solution significantly improves the flying car's survivability in extreme airspace environments (such as electromagnetic interference, sudden obstacles) or complex ground conditions (such as heavy rain and tire blowouts). It significantly enhances the flying car's survivability and mission reliability in extreme operating conditions such as simultaneous multiple motor failures or complex airspace environments.

[0010] The present application also provides a control method, comprising: determining whether the flying car power system described above meets in-flight flight mode switching conditions, wherein the in-flight flight mode switching conditions include: the flying car power system receiving a flight mode button control command, the remaining state of charge (SOC) of the flying car's power battery being greater than a preset charge threshold, and the flying car's second disconnect device, first flight rotor, power battery, first motor, and second motor being all fault-free; if so, setting the flying car's first disconnect device to a disconnected state and the flying car's second disconnect device to an engaged state. In implementing the above scheme, before switching to in-flight mode, the system not only verifies the power battery's energy availability but also monitors the fault status of key components such as the second disconnect device, first flight rotor, and first / second motors in real time to ensure that all power chain nodes are operational. More importantly, when the switch is successful, the first disconnect device actively disconnects the ground power chain, while the second disconnect device integrates with the flight power chain, forming a physically isolated redundant protection mechanism. Even if a ground power system failure occurs during flight, flight stability will not be affected. This significantly improves the safety of mode switching compared to traditional flying cars that rely solely on single commands or simple electronic control switching.

[0011] Optionally, in an embodiment of the present application, the method further includes determining whether the flying car's power system meets a land driving mode switching condition, where the land driving mode switching condition includes: the flying car's power system receives a land mode button control command, and the rotational speed of the flying car's first flight rotor is less than a preset speed threshold; if so, setting the flying car's first disconnect device to an engaged state and the flying car's second disconnect device to a disconnected state. In implementing the above scheme, by introducing a rotor speed threshold determination mechanism, the limitations of traditional flying car mode switching, namely static command triggering, are overcome, achieving dynamic safety verification based on real-time motion status. Specifically, the flying car's power system not only relies on the user's input of the land mode button command, but also monitors whether the rotational speed of the first flight rotor is less than a preset threshold to ensure that the flight rotor has entered a safe braking state, thereby avoiding mechanical interference or power conflicts caused by the rotor not being fully stopped. When the conditions are met, the first disconnect device restores power transmission to the drive wheels, and the second disconnect device isolates the power supply to the flight rotor, forming a physical cross-mode isolation. Compared to traditional split-body flying cars that rely solely on mechanical locking and command switching, this significantly improves the safety of mode switching.

[0012] An embodiment of the present application further provides an electronic device, including: a processor and a memory, wherein the memory stores machine-readable instructions executable by the processor, and the machine-readable instructions execute the method described above when executed by the processor.

[0013] An embodiment of the present application further provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the method described above is executed.

[0014] An embodiment of the present application further provides a computer program product, including: a computer program or computer instructions, which executes the method described above when the computer program or computer instructions are executed by a processor. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments of the present application. It should be understood that the following drawings only illustrate certain embodiments of the embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 A first structural schematic diagram of a flying car power system provided by an embodiment of the present application is shown; Figure 2 A second structural schematic diagram of the flying car power system provided by an embodiment of the present application is shown; Figure 3 A third structural schematic diagram of the flying car power system provided by an embodiment of the present application is shown; Figure 4 A fourth structural schematic diagram of the flying car power system provided by an embodiment of the present application is shown; Figure 5 A flow chart of a control method provided in an embodiment of the present application is shown.

[0017] Icons: 100 - flying car power system; 110 - power battery; 120 - motor; 121 - first motor; 122 - second motor; 123 - third motor; 124 - fourth motor; 125 - fifth motor; 126 - sixth motor; 127 - seventh motor; 128 - eighth motor; 130 - disconnect device; 131 - first disconnect device; 132 - second disconnect device; 133 - third disconnect device; 134 - fourth disconnect device; 135 - fifth disconnect device; 136 - sixth Disconnecting device; 137-seventh disconnecting device; 138-eighth disconnecting device; 140-transmission mechanism; 141-first transmission mechanism; 142-second transmission mechanism; 180-vehicle differential; 200-drive wheels; 210-first drive wheels; 220-second drive wheels; 230-third drive wheels; 240-fourth drive wheels; 300-flight rotor; 310-first flight rotor; 320-second flight rotor; 330-third flight rotor; 340-fourth flight rotor. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. It should be understood that the drawings in the embodiments of the present application only serve the purpose of illustration and description and are not intended to limit the scope of protection of the embodiments of the present application. In addition, it should be understood that the schematic drawings are not drawn to scale. The flowcharts used in the embodiments of the present application illustrate the operations implemented according to some embodiments of the embodiments of the present application. It should be understood that the operations of the flowcharts can be implemented out of sequence, and steps without logical context can be reversed in order or implemented simultaneously. In addition, those skilled in the art, guided by the contents of the embodiments of the present application, can add one or more other operations to the flowcharts, or remove one or more operations from the flowcharts.

[0019] In addition, the described embodiments are only a portion of the embodiments of the present application, rather than all embodiments. The components of the embodiments of the present application generally described and shown in the accompanying drawings can be arranged and designed in a variety of different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the claimed embodiments of the present application, but rather merely represents selected embodiments of the embodiments of the present application.

[0020] It is understandable that the "first" and "second" in the embodiments of the present application are used to distinguish similar objects. Those skilled in the art will understand that words such as "first" and "second" do not limit the quantity and execution order, and words such as "first" and "second" do not necessarily limit differences. In the description of the embodiments of the present application, the term "and / or" is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the previous and subsequent associated objects are in an "or" relationship. The term "multiple" refers to more than two (including two). Similarly, "multiple groups" refers to more than two (including two).

[0021] The following describes the application scenarios for this flying car power system. This flying car power system can be applied to flying cars, enabling them to drive both on roads and in the air. Flying cars, which can function both as vehicles on public roads and in the air, are an emerging form of transportation. Their power systems and control strategies are crucial, and currently, no commercially available flying car power systems exist.

[0022] For the above questions, please see Figure 1The first structural schematic diagram of the flying car power system 100 provided in an embodiment of the present application is shown. The flying car power system 100 may include: a power battery 110, a first motor 121, a second motor 122, a first disconnect device 131 and a second disconnect device 132. The connection relationship between the power battery 110, the first motor 121, the second motor 122, the first disconnect device 131 and the second disconnect device 132 is shown in the structure in the figure. The connection relationship between the various components is described in detail below.

[0023] The power battery 110 is connected to the motor 120 . Specifically, the power battery 110 is electrically connected to the first motor 121 and the second motor 122 , respectively, to provide a power source for the first motor 121 and the second motor 122 .

[0024] The first motor 121 is connected to the driving wheels 200 of the flying car through the first disconnecting device 131 to provide driving power for the driving wheels 200.

[0025] The second motor 122 is connected to the first flying rotor 310 of the flying car through the second disconnecting device 132 , and is used to provide driving power for the first flying rotor 310 .

[0026] The first motor 121 is electrically connected to the second motor 122, and is used to provide additional power to the flying car's drive wheels 200 when the first disconnecting device 131 is engaged and the second disconnecting device 132 is disconnected. Alternatively, the first motor 121 is used to provide additional power to the flying car's first rotor 310 when the first disconnecting device 131 is disconnected and the second disconnecting device 132 is engaged. Because the two motors 120 are electrically connected, the system can intelligently allocate the output power of the two motors 120 according to different operating conditions (such as acceleration, climbing, takeoff, and hovering). For example, during ground travel, if greater driving force is required, the second motor 122 can provide additional power to the drive wheels 200 without affecting flight performance. This dynamic allocation mechanism can also be reversed during flight. This dynamic allocation mechanism not only improves energy efficiency, but also reduces the load on individual motors 120, extending their service life, while avoiding over-reliance on high-power-density batteries.

[0027] As can be understood, this solution, through the electrical connection design between the first motor 121 and the second motor 122, enables the other motor 120 to provide additional power support when a disconnect device 130 is disconnected and the corresponding actuator (wheel or rotor) loses direct power input, thereby achieving power redundancy in the power system. This design overcomes the limitations of traditional mechanical transmission that relies on a single power path. Even if one motor 120 or disconnect device 130 fails in flight mode or ground driving mode, basic operation can still be maintained through the other motor 120, significantly improving the safety and mission reliability of the flying car.

[0028] In the implementation of the above-described solution, the first motor 121 and the second motor 122 in the flying car power system 100 are electrically connected. This allows the second motor 122 to provide additional power to the wheels when the first disconnecting device 131 is engaged and the second disconnecting device 132 is disconnected. Even if the first motor 121 fails, the second motor 122 can still drive the wheels 200. If the second disconnecting device 132 is engaged and the first disconnecting device 131 is disconnected, the first motor 121 can assist the second motor 122 in driving the rotors. This allows the flying car to share the same power system 100 for both land and air travel, effectively balancing both power and economic efficiency. Therefore, when either disconnecting device 130 is engaged (land travel mode or air travel mode), the first motor 121 and / or the second motor 122 can both power the actuators (wheels or rotors), improving flight thrust while also enhancing power redundancy. This effectively provides a flying car power system 100 that combines both power redundancy and safety.

[0029] See Figure 2 A second structural schematic diagram of the flying car power system 100 provided in an embodiment of the present application is shown; as an optional implementation of the above-mentioned flying car power system 100, it may also include: a first transmission mechanism 141 and a second transmission mechanism 142.

[0030] One end of the first transmission mechanism 141 is connected to the first motor 121, and the other end of the first transmission mechanism 141 is connected to the first disconnecting device 131. The first disconnecting device 131 is connected to the driving wheels 200 of the flying car. The function of the first transmission mechanism 141 here is to transmit the power generated by the first motor 121 to the driving wheels 200 of the flying car through the first disconnecting device 131.

[0031] One end of the second transmission mechanism 142 is connected to the second motor 122, and the other end of the second transmission mechanism 142 is connected to the second disconnecting device 132. The second disconnecting device 132 is connected to the first flying rotor 310 of the flying car. The function of the second transmission mechanism 142 here is to transmit the power generated by the second motor 122 to the first flying rotor 310 through the second disconnecting device 132.

[0032] The first motor 121 and the second motor 122 are interconnected via the first transmission mechanism 141 and the second transmission mechanism 142, so that the first motor 121 and the second motor 122 jointly provide power output for the flying car's drive wheels 200 or the first flying rotor 310. Specifically, the second transmission mechanism 142 can be connected to the first disconnecting device 131 via a gear of the first transmission mechanism 141, or the first transmission mechanism 141 can be connected to the second disconnecting device 132 via a gear of the second transmission mechanism 142.

[0033] As an optional embodiment of the aforementioned flying car power system 100, the aforementioned flying car power system 100 may further include a vehicle differential 180, which is connected to the first disconnect device 131 and the flying car's drive wheels 200, respectively. In other words, the first disconnect device 131 is directly connected to the vehicle differential 180, which is then connected to the flying car's drive wheels 200. In the presence of the vehicle differential 180, it can be understood that the first disconnect device 131 is indirectly connected to the flying car's drive wheels via the vehicle differential 180.

[0034] The vehicle differential 180 is used to provide different rotation speeds between the left drive wheel and the right drive wheel of the flying car.

[0035] See Figure 3 The third structural schematic diagram of the flying car power system 100 provided in an embodiment of the present application is shown; as an optional implementation of the above-mentioned flying car power system 100, the flying car power system 100 includes: a power battery 110, a first motor 121, a second motor 122, a first disconnecting device 131, a second disconnecting device 132, a third motor 123, a fourth motor 124, a third disconnecting device 133 and a fourth disconnecting device 134.

[0036] The power battery 110 is electrically connected to the first motor 121 and the second motor 122 , respectively, and is used to provide a power source for the first motor 121 and the second motor 122 .

[0037] The first motor 121 is connected to the driving wheels 200 of the flying car through the first disconnecting device 131 to provide driving power for the driving wheels 200.

[0038] The second motor 122 is connected to the first flying rotor 310 of the flying car through the second disconnecting device 132 , and is used to provide driving power for the first flying rotor 310 .

[0039] The first motor 121 is electrically connected to the second motor 122 and is used to provide additional power to the driving wheels 200 of the flying car when the first disconnecting device 131 is in the engaged state and the second disconnecting device 132 is in the disconnected state, or to provide additional power to the first flying rotor 310 of the flying car when the first disconnecting device 131 is in the disconnected state and the second disconnecting device 132 is in the engaged state.

[0040] The power battery 110 is electrically connected to the third motor 123 and the fourth motor 124 , respectively, and is used to provide a power source for the third motor 123 and the fourth motor 124 .

[0041] The third motor 123 is connected to the driving wheels 200 of the flying car through the third disconnecting device 133 to provide driving power for the driving wheels 200.

[0042] The fourth motor 124 is connected to the second flying rotor 320 of the flying car through the fourth disconnecting device 134 , and is used to provide driving power for the second flying rotor 320 .

[0043] The third motor 123 is electrically connected to the fourth motor 124 and is used to provide additional power to the driving wheels 200 of the flying car when the third disconnecting device 133 is engaged and the fourth disconnecting device 134 is disconnected, or to provide additional power to the second flying rotor 320 of the flying car when the third disconnecting device 133 is disconnected and the fourth disconnecting device 134 is engaged.

[0044] See Figure 4 FIG4 shows a fourth structural schematic diagram of a flying car power system 100 provided in an embodiment of the present application. As an optional embodiment of the above-mentioned flying car power system 100, the flying car power system 100 includes: a power battery 110, a first motor 121, a second motor 122, a first disconnecting device 131, a second disconnecting device 132, a third motor 123, a fourth motor 124, a third disconnecting device 133, a fourth disconnecting device 134, a fifth motor 125, a sixth motor 126, a fifth disconnecting device 135, a sixth disconnecting device 136, a seventh motor 127, an eighth motor 128, a seventh disconnecting device 137, and an eighth disconnecting device 138. The power battery 110 is electrically connected to the first motor 121 and the second motor 122, respectively, to provide a source of power for the first motor 121 and the second motor 122. The first motor 121 is connected to the first drive wheel 210 of the flying vehicle via a first disconnect device 131 to provide driving power to the first drive wheel 210. The second motor 122 is connected to the first flight rotor 310 of the flying vehicle via a second disconnect device 132 to provide driving power to the first flight rotor 310. The first motor 121 and the second motor 122 are electrically connected to provide additional power to the driving wheel 200 of the flying vehicle when the first disconnect device 131 is engaged and the second disconnect device 132 is disconnected, or to provide additional power to the first flight rotor 310 of the flying vehicle when the first disconnect device 131 is disconnected and the second disconnect device 132 is engaged.

[0045] The power battery 110 is electrically connected to the third motor 123 and the fourth motor 124, respectively, to provide power for the third motor 123 and the fourth motor 124. The third motor 123 is connected to the second drive wheel 220 of the flying vehicle via the third disconnect device 133 to provide driving power to the second drive wheel 220. The fourth motor 124 is connected to the second flight rotor 320 of the flying vehicle via the fourth disconnect device 134 to provide driving power to the second flight rotor 320. The third motor 123 and the fourth motor 124 are electrically connected to provide additional power to the drive wheel 200 of the flying vehicle when the third disconnect device 133 is engaged and the fourth disconnect device 134 is disconnected, or to provide additional power to the second flight rotor 320 of the flying vehicle when the third disconnect device 133 is disconnected and the fourth disconnect device 134 is engaged.

[0046] The power battery 110 is electrically connected to the fifth motor 125 and the sixth motor 126, respectively, for providing a source of electricity for the fifth motor 125 and the sixth motor 126; the fifth motor 125 is connected to the third drive wheel 230 of the flying car via a fifth disconnecting device 135, for providing driving power for the third drive wheel 230; the sixth motor 126 is connected to the third flight rotor 330 of the flying car via a sixth disconnecting device 136, for providing driving power for the third flight rotor 330; the fifth motor 125 and the sixth motor 126 are electrically connected to provide additional power to the drive wheel 200 of the flying car when the fifth disconnecting device 135 is engaged and the sixth disconnecting device 136 is disconnected, or to provide additional power to the third flight rotor 330 of the flying car when the fifth disconnecting device 135 is disconnected and the sixth disconnecting device 136 is engaged.

[0047] The power battery 110 is electrically connected to the seventh motor 127 and the eighth motor 128, respectively, for providing a source of electricity for the seventh motor 127 and the eighth motor 128; the seventh motor 127 is connected to the fourth drive wheel 240 of the flying car via the seventh disconnecting device 137, for providing driving power for the fourth drive wheel 240; the eighth motor 128 is connected to the fourth flight rotor 340 of the flying car via the eighth disconnecting device 138, for providing driving power for the fourth flight rotor 340; the seventh motor 127 is electrically connected to the eighth motor 128, for providing additional power to the driving wheel 200 of the flying car when the seventh disconnecting device 137 is engaged and the eighth disconnecting device 138 is disconnected, or for providing additional power to the fourth flight rotor 340 of the flying car when the seventh disconnecting device 137 is disconnected and the eighth disconnecting device 138 is engaged.

[0048] See Figure 5 The flowchart of the control method provided by the embodiment of the present application is shown. The embodiment of the present application also provides a control method for a flying car power system. The above-mentioned flying car power system includes two modes: land driving mode and air flight mode. The control method for switching from land driving mode to air flight mode is first described below. The implementation of this control method may include: Step S301: Determine whether the flying car power system meets the in-flight flight mode switching conditions. The in-flight flight mode switching conditions include: the flying car power system receives a flight mode button control command, the remaining state of charge (SOC) of the flying car's power battery is greater than a preset charge threshold, and the flying car's second disconnect device, first flight rotor, power battery, first motor, and second motor are all in good condition.

[0049] For example, regarding the implementation of step S301 above, it is understood that after the flying car is powered on by the power battery, it defaults to operating in land driving mode. Therefore, if the flying car is to be switched from land driving mode to air flight mode, it is necessary to first determine whether the flying car's power system meets the air flight mode switching conditions. The air flight mode switching conditions include: the flying car's power system receiving a flight mode button control command, the remaining state of charge (SOC) of the flying car's power battery being greater than a preset charge threshold, and the flying car's first disconnect device, second disconnect device, first flight rotor, power battery, first motor, and second motor being all fault-free. The preset charge threshold can be set based on specific circumstances, for example, to 50% or 60% of a fully charged power battery.

[0050] Step S302: If the flying car power system meets the flying mode switching condition, the first disconnecting device of the flying car is set to the disconnected state, and the second disconnecting device of the flying car is set to the engaged state.

[0051] In implementing the above solution, before switching flight modes, the system not only verifies the battery's energy level (to prevent mid-flight power loss), but also ensures that all power chain nodes are operational by monitoring the fault status of key components such as the second disconnect device, the first flight rotor, and the first and second motors in real time. More importantly, once the switch is successful, the first disconnect device actively disconnects the ground power chain, while the second disconnect device integrates with the flight power chain, creating a physically isolated redundant protection mechanism. Even if a sudden failure of the ground power system occurs during flight, flight stability is not affected. Compared to traditional flying cars that rely solely on a single command or simple electronic control switching, this significantly improves the atomicity and safety of mode switching (i.e., the switching process is irreversible and the failure cannot spread). This provides a fundamental guarantee for the high-frequency, high-density operation of flying cars in complex airspace environments, thereby enhancing the safety of mode switching.

[0052] As an optional implementation of the control method for the above-mentioned flying car power system, the control method for switching from the land driving mode to the air flight mode has been described above. The control method for switching from the air flight mode to the land driving mode will be described below. The implementation of this control method may also include: Step S303: Determine whether the flying car power system meets the land driving mode switching conditions. The land driving mode switching conditions include: the flying car power system receives a land mode button control command, and the rotation speed of the first flight rotor of the flying car is less than a preset speed threshold.

[0053] For example, in step S303, after a period of flight, a flying car may need to switch from flight mode to land mode. The pilot of the flying car can press a land mode button. In response to the pilot pressing the land mode button, the flying car's power system can first determine whether the flying car's power system meets the land mode switching conditions. The land mode switching conditions include: the flying car's power system receiving a control command from the land mode button, and the rotational speed of the flying car's first rotor being less than a preset speed threshold. The preset speed threshold can be set based on specific circumstances, for example, 1000 revolutions per second or 800 revolutions per second.

[0054] Step S304: If the power system of the flying car meets the land driving mode switching condition, the first disconnecting device of the flying car is set to the engaged state, and the second disconnecting device of the flying car is set to the disconnected state.

[0055] For example, in step S304, if the flying car's power system meets the conditions for switching to land driving mode, the flying car's first disconnecting device can be set to an engaged state, and the flying car's second disconnecting device can be set to a disconnected state, thereby switching the flying car from airborne mode to land driving mode. It is understood that in land driving mode, the first motor can also be used to drive the flying car alone, and the flying car can use it to recover braking energy into the power battery during driving. In this case, the second motor neither drives the flying car nor participates in brake energy recovery, but serves as a backup motor to ensure high availability. This approach allows for both driving and energy recovery using only one motor, effectively improving the actual utilization efficiency of the motors. Since the flying car's second disconnecting device is set to the disconnected state, the flying rotor is inoperative, thereby reducing the drag of the flying rotor and improving the flying car's efficiency during land driving.

[0056] In the land driving mode, the flying car can also be driven simultaneously by the first motor and the second motor. For example, the driving torque demand is determined according to the driver's accelerator pedal opening. When the driving torque demand is greater than the maximum torque capacity of the first motor, the first motor and the second motor can be controlled to drive the flying car simultaneously. Correspondingly, when the driving torque demand is less than or equal to the maximum torque capacity of the first motor, the flying car can be driven solely by the first motor.

[0057] In addition, when braking an electric vehicle in land driving mode, the braking demand torque and braking demand deceleration can also be determined according to the braking master cylinder pressure. When the braking demand deceleration is greater than the preset deceleration threshold (for example, 5M / S 2 ), it is usually considered an emergency brake. In order to ensure the safety of emergency braking, the first motor and the second motor can be controlled not to participate in the braking energy recovery, and the braking is performed by the mechanical hydraulic system, thereby improving the safety of the electric vehicle in the emergency braking state. If the braking demand deceleration is less than the preset deceleration threshold (for example, 5M / S 2 ), and the braking recovery torque requirement is less than or equal to the maximum generating torque capacity of the first motor, it can be considered normal braking. At this time, the first motor is controlled to participate in the braking energy recovery, and the second motor does not participate in the braking energy recovery. It can be understood that if the braking demand deceleration is less than the preset deceleration threshold (for example, 5M / S 2 ), and the braking recovery torque demand is greater than the maximum generating torque of the first motor, which can be considered as normal braking. At this time, the first motor is controlled to use the maximum torque to recover braking energy, and the second motor recovers the remaining braking energy, that is, the second motor is used to meet the remaining braking recovery torque demand.

[0058] It can be understood that the description of the first motor and the second motor in the above control method can also be replaced by the description of the third motor and the fourth motor, or replaced by the description of the fifth motor and the sixth motor, or replaced by the description of the seventh motor and the eighth motor. The technical principles and implementation methods of these motors in the control method are similar, so they will not be repeated.

[0059] The implementation of this solution overcomes the limitations of traditional "static command triggering" in flying car mode switching by introducing a rotor speed threshold determination mechanism, achieving dynamic safety verification based on real-time motion status. Specifically, the flying car's power system not only relies on user-inputted land mode button commands but also monitors whether the rotational speed of the first flying rotor falls below a preset threshold (such as a complete stop or near-stop) to ensure the rotor has entered a safe braking state, thereby avoiding mechanical interference or power conflicts caused by an incomplete rotor stop. When the conditions are met, the first disconnect device engages the ground power chain (restoring power to the drive wheels), while the second disconnect device disconnects the flight power chain (isolating power supply to the flying rotor), creating physical cross-mode isolation. This significantly improves mode switching safety compared to traditional split-body flying cars that rely solely on mechanical locking and command switching.

[0060] It should be understood that the device corresponds to the aforementioned control method embodiment and is capable of executing each of the steps involved in the aforementioned method embodiment. The specific functions of the device can be found in the description above, and a detailed description is omitted here. The device includes at least one software functional module that can be stored in a memory in the form of software or firmware or embedded in the device's operating system (OS).

[0061] An electronic device provided by an embodiment of the present application includes: a processor and a memory, the memory storing machine-readable instructions executable by the processor, and the above method being executed when the machine-readable instructions are executed by the processor.

[0062] The embodiment of the present application also provides a computer-readable storage medium having a computer program stored thereon, and the computer program is executed by a processor to execute the above method. The computer-readable storage medium can be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic memory, flash memory, magnetic disk or optical disk.

[0063] An embodiment of the present application further provides a computer program product, including: a computer program or computer instructions, which executes the method described above when the computer program or computer instructions are executed by a processor.

[0064] It should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similarities between the various embodiments can be referred to in conjunction with each other. For system-related embodiments, since they are generally similar to method-related embodiments, their description is relatively simple. For relevant details, refer to the description of the method-related embodiments.

[0065] In the several embodiments provided in the embodiments of the present application, it should be understood that the disclosed devices and methods can also be implemented in other ways. The device embodiments described above are only schematic. For example, the flowcharts and block diagrams in the accompanying drawings show the possible implementation architectures, functions and operations of the devices, methods and computer program products according to the multiple embodiments of the embodiments of the present application. In this regard, each box in the flowchart or block diagram can represent a module, a program segment or a part of a code, and a module, a program segment or a part of a code contains one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also be different from the order of occurrence marked in the accompanying drawings. For example, two consecutive boxes can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, which is mainly based on the functions involved.

[0066] In addition, the functional modules of each embodiment in the embodiments of the present application can be integrated together to form an independent part, or each module can exist separately, or two or more modules can be integrated to form an independent part. In addition, in the description of this specification, the descriptions with reference to the terms "one embodiment", "some embodiments", "example", "specific example", "some examples", etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiments of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in an appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples, without contradiction.

[0067] The above description is only an optional implementation method of the embodiment of the present application, but the protection scope of the embodiment of the present application is not limited to this. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed in the embodiment of the present application, and they should all be covered by the protection scope of the embodiment of the present application.

Claims

1. A flying car power system, characterized in that: include: A power battery, a first motor, a second motor, a first disconnecting device and a second disconnecting device; The power battery is electrically connected to the first motor and the second motor, and is used to provide a power source for the first motor and the second motor; The first motor is connected to the driving wheels of the flying car through the first disconnecting device, and is used to provide driving power for the driving wheels; The second motor is connected to the first flight rotor of the flying car through the second disconnecting device, and is used to provide driving power for the first flight rotor; The first motor is connected to the second motor and is used to provide additional power to the driving wheels of the flying car when the first disconnecting device is in an engaged state and the second disconnecting device is in a disconnected state, or to provide additional power to the first flying rotor when the first disconnecting device is in a disconnected state and the second disconnecting device is in an engaged state.

2. The system according to claim 1, wherein: Also includes: a first transmission mechanism and a second transmission mechanism; One end of the first transmission mechanism is connected to the first motor, and the other end of the first transmission mechanism is connected to the first disconnecting device, so as to transmit the power generated by the first motor to the driving wheels of the flying car through the first disconnecting device; One end of the second transmission mechanism is connected to the second motor, and the other end of the second transmission mechanism is connected to the second disconnecting device, for transmitting the power generated by the second motor to the first flight rotor through the second disconnecting device; The first motor and the second motor are connected to each other through the first transmission mechanism and the second transmission mechanism, so that the first motor and the second motor can jointly provide power output for the driving wheels of the flying car or the first flying rotor.

3. The system according to claim 2, characterized in that Also includes: a vehicle differential connected to the first disconnect device and the driving wheels of the flying car; The vehicle differential is used to provide different rotation speeds between the left drive wheel and the right drive wheel of the flying car.

4. The system according to claim 1, wherein: The flying car power system further includes: a third motor, a fourth motor, a third disconnecting device, and a fourth disconnecting device; The power battery is electrically connected to the third motor and the fourth motor, and is used to provide a power source for the third motor and the fourth motor; The third motor is connected to the driving wheels of the flying car through the third disconnecting device, and is used to provide driving power for the driving wheels; The fourth motor is connected to the second flight rotor of the flying car through the fourth disconnecting device, and is used to provide driving power for the second flight rotor; The third motor is electrically connected to the fourth motor, and is used to provide additional power to the driving wheels of the flying car when the third disconnecting device is engaged and the fourth disconnecting device is disconnected, or to provide additional power to the second flight rotor of the flying car when the third disconnecting device is disconnected and the fourth disconnecting device is engaged.

5. The system according to claim 4, characterized in that The flying car power system further includes: a fifth motor, a sixth motor, a fifth disconnect device, and a sixth disconnect device; the power battery is electrically connected to the fifth motor and the sixth motor to provide a power source for the fifth motor and the sixth motor; the fifth motor is connected to the driving wheels of the flying car via the fifth disconnect device to provide driving power for the driving wheels; the sixth motor is connected to the third flight rotor of the flying car via the sixth disconnect device to provide driving power for the third flight rotor; the fifth motor is electrically connected to the sixth motor to provide additional power to the driving wheels of the flying car when the fifth disconnect device is engaged and the sixth disconnect device is disconnected, or to provide additional power to the third flight rotor of the flying car when the fifth disconnect device is disconnected and the sixth disconnect device is engaged; The flying car power system also includes: a seventh motor, an eighth motor, a seventh disconnect device, and an eighth disconnect device; the power battery is electrically connected to the seventh motor and the eighth motor to provide a source of electricity for the seventh motor and the eighth motor; the seventh motor is connected to the driving wheels of the flying car through the seventh disconnect device to provide driving power for the driving wheels; the eighth motor is connected to the fourth flight rotor of the flying car through the eighth disconnect device to provide driving power for the fourth flight rotor; the seventh motor is electrically connected to the eighth motor to provide additional power to the driving wheels of the flying car when the seventh disconnect device is engaged and the eighth disconnect device is disconnected, or to provide additional power to the fourth flight rotor of the flying car when the seventh disconnect device is disconnected and the eighth disconnect device is engaged.

6. A control method, characterized in that: include: determining whether the flying car power system according to any one of claims 1 to 5 satisfies an in-flight flight mode switching condition, the in-flight flight mode switching condition comprising: the flying car power system receiving a flight mode button control command, the remaining state of charge (SOC) of the power battery of the flying car being greater than a preset charge threshold, and the second disconnecting device, the first flight rotor, the power battery, the first motor, and the second motor of the flying car being all in good condition; If so, the first disconnecting device of the flying car is set to a disconnected state, and the second disconnecting device of the flying car is set to a connected state.

7. The method according to claim 6, characterized in that Also includes: determining whether the flying car power system satisfies a land driving mode switching condition, the land driving mode switching condition comprising: the flying car power system receiving a land mode button control command, and a rotation speed of the first flight rotor of the flying car being less than a preset speed threshold; If so, the first disconnecting device of the flying car is set to an engaged state, and the second disconnecting device of the flying car is set to a disconnected state.

8. An electronic device, characterized in that: include: A processor and a memory, wherein the memory stores machine-readable instructions executable by the processor, and the machine-readable instructions are executed by the processor to perform the method according to any one of claims 6 to 7.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method according to any one of claims 6 to 7 is executed.

10. A computer program product, characterized in that include: A computer program or computer instruction, wherein the computer program or the computer instruction is executed by a processor to perform the method according to any one of claims 6 to 7.

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