CN114290906B - High-voltage control device, control method and aircraft - Google Patents
High-voltage control device, control method and aircraft Download PDFInfo
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- CN114290906B CN114290906B CN202210089252.0A CN202210089252A CN114290906B CN 114290906 B CN114290906 B CN 114290906B CN 202210089252 A CN202210089252 A CN 202210089252A CN 114290906 B CN114290906 B CN 114290906B
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Abstract
The embodiment of the invention provides a high-voltage control device, a control method and an aircraft, wherein the device comprises the following components: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries; the control mechanism is used for controlling the power battery to output the electric energy when detecting that the power battery outputting the electric energy is in an abnormal state. The embodiment of the invention realizes that when the power battery outputting electric energy in the high-voltage control device fails, the other power battery can be adopted to supply power to the driving mechanism in time, so that the normal operation of the driving mechanism is ensured, and the situation that the high-voltage control device cannot continue to normally operate after a single power battery is damaged is avoided.
Description
Technical Field
The invention relates to the technical field of electric energy management, in particular to a high-voltage control device, a corresponding control method and an aircraft.
Background
As shown in fig. 1, the high voltage system architecture on a conventional electric automobile is usually an independent component, and the electric energy is transmitted from a power battery 101 to a BDU102 (Battery Disconnect Unit, battery breaking unit), the BDU102 further to a PDU103 (Power Distribution Unit, energy distribution unit), and finally the PDU103 distributes the electric energy to high voltage loads such as an automobile electric drive 104 and DC/DC. BMS105 (Battery Management System ) manages power battery, VCU106 (Vehicle Control Unit ) manages car electric drive 107, DC/DC controller 108 and VCU106 and BMS105 exchange information through communication network, accomplish the operation of whole vehicle function program jointly. Usually, only one group of control lines and communication lines are provided, if the control lines or the communication lines are disconnected, parts are out of control, and the electric automobile cannot continue to work normally.
Disclosure of Invention
In view of the above, embodiments of the present invention are presented to provide a high voltage control device for an aircraft and a corresponding high voltage control method and aircraft that overcome or at least partially solve the above problems.
In order to solve the above problems, an embodiment of the present invention discloses a high voltage control apparatus including: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries;
the control mechanism is used for controlling the other power batteries to output the electric energy when detecting that the power battery outputting the electric energy is in an abnormal state.
Optionally, the control mechanism is configured to determine a first battery among the plurality of power batteries, and control the first battery to output electric energy to the driving mechanism;
the control mechanism is also used for controlling the switch module to disconnect the electric connection between the first battery and the driving mechanism when the first battery is detected to be in an abnormal state;
the control mechanism is also used for determining a second battery and controlling the switch module to conduct the electrical connection between the second battery and the driving mechanism.
Optionally, the energy control module includes a first energy control unit and a second energy control unit;
the first energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery disconnection module when the first energy control unit is in a normal state;
the second energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery disconnection module when the first energy control unit is in an abnormal state.
Optionally, the switch module includes a plurality of battery breaking units;
one of the battery breaking units is connected with one of the power batteries.
Optionally, the battery breaking unit includes: a positive contactor and a negative contactor connected between the power battery and the energy distribution unit, and a pre-charge branch connected in parallel with the positive contactor; the pre-charging branch circuit comprises a pre-charging resistor and a pre-charging contactor which are connected in series;
the energy control module is used for controlling the opening and closing states of the positive electrode contactor, the negative electrode contactor and the pre-charging contactor; the open-close state includes open or closed.
Optionally, the method further comprises: a discharge contactor; the driving mechanism comprises a plurality of flying electric drives and one or more traveling electric drives;
the discharge contactor is arranged between the energy distribution unit and each positive electrode end of the flying electric drive and between the energy distribution unit and each positive electrode end of the driving electric drive.
Optionally, the dc conversion module includes at least two dc converters;
the energy control module is also used for controlling the output power of the rest DC converters in a normal state when detecting that any DC converter is in an abnormal state.
Optionally, the method further comprises: and an isolation cavity arranged for the direct current converter.
The embodiment of the invention also discloses a control method which is applied to the high-voltage control device, and the high-voltage control device comprises: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries; the method comprises the following steps:
the control mechanism controls the other power battery to output the electric energy when detecting that the power battery outputting the electric energy is in an abnormal state.
The embodiment of the invention also discloses an aircraft, which comprises the high-voltage control device.
The embodiment of the invention has the following advantages:
the control mechanism can detect whether each power battery is in an abnormal state, and when detecting that the power battery outputting electric energy to the driving mechanism is in the abnormal state, the control mechanism is switched to the power battery outputting electric energy in the normal state in the energy supply mechanism, so that when the power battery outputting electric energy in the high-voltage control device fails, the control mechanism can be powered by the other power battery in time, the normal operation of the driving mechanism is ensured, and the situation that the high-voltage control device cannot continue to normally operate after the single power battery is damaged is avoided.
Drawings
Fig. 1 is a schematic structural diagram of a high-voltage system architecture on a conventional electric vehicle in the prior art;
FIG. 2 is a block diagram of a high voltage control apparatus according to the present invention;
FIG. 3 is a schematic diagram of a switching flow of an energy controller according to the present invention;
fig. 4 is a flow chart of steps of an embodiment of a control method of the present invention.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
One of the core ideas of the embodiment of the invention is that a plurality of devices in the high-voltage control device are provided with redundancy backup, so that when any device fails, a normal device which is redundant backup with the failed device can be adopted to replace the failed device, thereby maintaining the normal operation of the high-voltage control device.
Referring to fig. 2, a block diagram of a high voltage control apparatus according to the present invention is shown; the method specifically comprises the following steps: a control mechanism 210, an energy supply mechanism 220 and a driving mechanism 230 connected with the control mechanism 210; the control mechanism 210 includes an energy control module 211, a switching module 212 connected to the energy control module 211, a dc conversion module 213, and an energy distribution unit 214; one end of the switch module 212 is connected with the energy supply mechanism 220, and the other end is connected with the direct current conversion module 213 and the driving mechanism 230 through the energy distribution unit 214; the power supply mechanism 220 includes a plurality of power cells 221;
the control mechanism 210 is configured to control the output of electric power by the other power cell 221 when it is detected that the power cell 221 currently outputting electric power is in an abnormal state.
The embodiment of the invention can be applied to a mobile body, for example: vehicles, aircraft, etc. Further, the present invention may be applied to an aircraft that includes at least two moving modes of land and flying (moving by one of land and flying at any time), and when the driving mechanism 230 is operated, power required for moving the aircraft can be provided, for example: providing the power for the aircraft to control movement (flight).
The energy control module 211 is connected with the switch module 212, the direct current conversion module 213, the energy supply mechanism 220 and the driving mechanism 230 through electrical connection wires, wherein the electrical connection wires comprise control wires and communication wires, so that the energy control module 211 can send messages to the switch module 212, the direct current conversion module 213, the energy supply mechanism 220 and the driving mechanism 230 and perform corresponding control.
The switch module 212 can switch on or off the connection between the power battery 221 and the energy distribution unit 214, so that when any power battery 221 is switched on with the energy distribution unit 214, the power battery 221 can output electric energy to the driving mechanism 230, and the driving mechanism 230 can perform corresponding operation.
The control mechanism 210 is configured to control the output of electric power by the other power cell 221 when it is detected that the power cell 221 currently outputting electric power is in an abnormal state.
In the embodiment of the present invention, the control mechanism 210 can detect whether each power battery is in an abnormal state, and when detecting that the power battery 221 outputting electric energy to the driving mechanism is in an abnormal state, switch to outputting electric energy by another power battery 221 in a normal state in the energy supply mechanism 220, so that when the power battery 221 outputting electric energy in the high-voltage control device fails, the other power battery 221 can be adopted to supply power to the driving mechanism 230 in time, thereby ensuring the normal operation of the driving mechanism 230, and avoiding that the high-voltage control device cannot continue to normally operate after the single power battery 221 is damaged.
In an alternative embodiment of the present invention, the control mechanism 210 is configured to determine a first battery among the plurality of power batteries 221, and control the first battery to output electric power to the driving mechanism 230;
the control mechanism 210 is further configured to control the switch module 212 to disconnect the electrical connection between the first battery and the driving mechanism 230 when the first battery is detected to be in an abnormal state;
the control mechanism 210 is also configured to determine a second battery and control the switch module 212 to conduct an electrical connection between the second battery and the drive mechanism 230.
The energy control module 211 can determine a first battery among the plurality of power batteries 221 and control the switching module 212 to conduct an electrical connection of the first battery with the energy distribution unit 214 so that the first battery can output electrical energy to the driving mechanism 230. At this time, the connection between the other power cells 221 and the energy distribution unit 214 is in a disconnected state.
The energy control module 211 can also detect whether the first battery is in an abnormal state, and when detecting that the first battery is in an abnormal state, the control switch module 212 disconnects the first battery from the energy distribution unit 214, and the control switch module 212 turns on the connection between the second battery in a normal state and the energy distribution unit 214, so that the second battery is used to output electric energy to the driving mechanism 230.
Switching from the first battery to the second battery to power the driving mechanism 230 is not avoided in a specific implementation, resulting in a temporary power failure of the driving mechanism 230, in a specific implementation the energy control module 211 first controls the switch module 212 to conduct the connection between the second spot battery and the energy distribution unit 214, and then controls the switch module 212 to disconnect the connection between the first spot battery and the energy distribution unit 214.
In one example, the energy control module 211 is capable of obtaining an operating state of the first battery, where the operating state may include one or more of an operating time, a current output value, a voltage output value, and a temperature, setting a corresponding limit for the operating state, and comparing the operating state with the limit to determine whether the first battery is in an abnormal state. In a specific implementation, whether the first battery is in an abnormal state or not may also be determined by other manners, and the method for determining the abnormal state of the first battery does not affect implementation of the embodiment of the present invention.
In a specific implementation, the first battery and the second battery may be determined according to characteristic information (such as temperature, capacity, and remaining capacity) of each power battery 221, or may be determined according to a preset rule (such as setting corresponding priorities for a plurality of power batteries 221).
The control mechanism 210 determines a first battery among the plurality of power batteries 221 and controls the first battery to output electric power to the driving mechanism 230; upon detecting that the first battery is in an abnormal state, controlling the switch module 212 to disconnect the electrical connection between the first battery and the driving mechanism 230; determining the second battery and controlling the switch module 212 to conduct the electrical connection between the second battery and the driving mechanism 230, so that when any power battery 221 in the high-voltage control device fails, another power battery 221 can be timely adopted to supply power to the driving mechanism 230, normal operation of the driving mechanism 230 is ensured, and the situation that the high-voltage control device cannot continue to normally operate after a single power battery 221 is damaged is avoided.
In an alternative embodiment of the present invention, the energy control module 211 includes a first energy control unit 2111 and a second energy control unit 2112;
the first energy control unit 2111 is used for controlling the energy supply mechanism 220, the driving mechanism 230 and the battery disconnection module when the first energy control unit is in a normal state;
the second energy control unit 2112 is configured to control the energy supply mechanism 220, the driving mechanism 230, and the battery disconnection module when the first energy control unit 2111 is in an abnormal state.
The energy control module 211 includes at least two energy control units, one energy control unit may be predetermined to be a first energy control unit 2111, and one of the other energy control units is a second energy control unit 2112, where when the first energy control unit 2111 and the second energy control unit 2112 are in a normal state, the first energy control unit 2111 controls the energy supply mechanism 220, the driving mechanism 230, the battery disconnection module, and the dc conversion module 213. When the second energy control unit 2112 detects that the first energy control unit 2111 is in an abnormal state, the control is switched to the control of the energy supply mechanism 220, the driving mechanism 230, the battery disconnection module and the direct current conversion module 213 by the second energy control unit 2112, and the first energy control unit 2111 stops controlling the energy supply mechanism 220, the driving mechanism 230, the battery disconnection module and the direct current conversion module 213, so that when any energy control unit of the energy control module 211 is abnormal, the redundant energy control unit can be adopted to correspondingly control other modules and mechanisms, and the control device and the safety of the aircraft are improved.
In a specific implementation, the first energy control unit 2111 and the second energy control unit 2112 are switched through a flow as shown in fig. 2, and the specific flow is as follows:
the EMU1 (first energy control unit 2111) is set as a master manager, and the EMU2 (second energy control unit 2112) is set as a slave manager. Normally, only the master EMU1 manages the energy supply mechanism 220, the driving mechanism 230, and the battery disconnection module, the slave EMU2 does not participate in the management, and the master EMU2 receives the status message from the master EMU1 and monitors the messages sent by the master EMU1 to each component. When the slave manager EMU2 receives the status message from the master manager EMU1 as an error code, or monitors that the message sent by the master manager EMU1 to the rest of the components is abnormal (including no message or message error), the slave manager EMU2 automatically changes to the master manager, taking over the management of the other components (the power supply mechanism 220, the driving mechanism 230, the battery disconnection module).
In an alternative embodiment of the present invention, the switch module 212 includes a plurality of battery break units 2121;
one of the battery break units 2121 is connected to one of the power cells 221.
In an alternative embodiment of the present invention, the battery breaking unit 2121 includes: a positive contactor 21211 and a negative contactor 21212 connected between the power cell 221 and the energy distribution unit 214, and a pre-charge branch connected in parallel with the positive contactor 21211; the precharge branch includes a precharge resistor 21213 and a precharge contactor 21214 in series;
the energy control module 211 is configured to control the open and close states of the positive contactor 21211, the negative contactor 21212, and the pre-charge contactor 21214; the open-close state includes open or closed.
When the control device is powered up, the control device may be pre-charged by closing the pre-charge contactor 21214 and the negative contactor 21212, and when the pre-charging is completed, the positive contactor 21211 may be closed and the pre-charge contactor 21214 may be opened to complete the high voltage power up of the control device. By arranging the pre-charging branch, the control device can be pre-charged, and the problem that the electric device is damaged due to instant high-voltage impact caused by directly carrying out high-voltage charging on the control device by adopting the power battery 221 is avoided.
In an alternative embodiment of the present invention, further comprising: a discharge contactor 240; the drive mechanism 230 includes a plurality of flight drives 231 and one or more crane drives 232; for an amphibious aircraft, the flight electric drive 231 can drive the rotor to enable the aircraft to fly in the air, and the drive electric drive 232 is used for providing power for the aircraft to travel on land.
The discharging contactor 240 is disposed between the energy distribution unit 214 and the positive electrode terminal of each flying electric drive, and between the energy distribution unit 214 and the positive electrode terminal of each driving electric drive.
Specifically, the energy distribution unit 214 includes a positive electrode connector 2141 and a negative electrode connector 2142; the positive connection 2141 connects 21211 with each of the positive contactors and with the positive terminal of each of the flying electric drives 231; the negative electrode connector 2142 is connected to each of the negative electrode connectors and to the 231 negative end of each of the flying electric drives.
The discharging contactor 240 is disposed between the positive electrode connector 2141 and the positive electrode end of each flying electric drive, and between the positive electrode connector 2141 and the positive electrode end of each driving electric drive.
In one example, the positive and negative connectors 2141, 2142 are copper bars.
The first energy control unit 2111 and the second energy control unit 2112 each include: comprises BMS (Battery Management System ), VCU (Vehicle Control Unit, vehicle control unit), FCU (Flight Control Unit ). The BMS is used for controlling the power battery 221, the VCU is used for controlling the driving electric drive, and the FCU is used for controlling the flying electric drive.
The energy control module 211 is further configured to disconnect the discharge contactor 240 connected to the failed electric power drive when the failure of the electric power drive is detected. By providing the discharge contactor 240, the circuit may be disconnected in the event of an uncontrollable failure of the electric drive (the crane electric drive and/or the flight electric drive), further improving the reliability of the aircraft. In addition, a fuse may be provided between the discharge contactor 240 and the positive electrode connection 2141 to further improve the safety of the control device.
In an alternative embodiment of the present invention, the dc conversion module 213 includes at least two dc converters 2131;
the energy control module 211 is further configured to control the output power of the remaining dc converters 2131 in a normal state when detecting that any dc converter 2131 is in an abnormal state.
The first energy control unit 2111 and the second energy control unit 2112 each further include: a dc conversion control unit for controlling the dc converter 2131.
In one example, the same power consuming component may be connected to different dc converters 2131, and the energy control module 211 may be capable of controlling one or more dc converters 2131 to supply power to the power consuming component, and when any dc converter 2131 is detected to be abnormal (including but not limited to, high temperature, excessively low output power, etc.), adjusting the output power of the remaining dc converters 2131 in a normal state, and when some dc converters 2131 are abnormal, the output power of the remaining dc converters 2131 may meet the power consuming component requirement, so as to ensure the normal operation of the control device.
In an alternative embodiment of the present invention, further comprising: an isolation cavity provided for the dc converter 2131.
When any of the dc converters 2131 fails and fires, the isolation cavity ensures that the failed dc converter 2131 does not affect the remaining devices.
In the embodiment of the invention, the control device of the aircraft is provided with the power battery 221, the direct current converter 2131, the flying electric drive 321 and the energy control unit, so that when any one of the devices with mutual redundancy fails, the redundant device can be invoked to ensure the control device, thereby ensuring the normal operation of the aircraft and improving the safety and reliability of the aircraft.
Referring to fig. 4, a flowchart illustrating steps of an embodiment of a control method of the present invention is applied to a high voltage control apparatus, which includes: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries; the method specifically comprises the following steps:
in step 401, the control mechanism controls the other power battery to output electric energy when detecting that the power battery currently outputting electric energy is in an abnormal state.
In an alternative embodiment of the present invention, the step 401 includes:
substep 4011, wherein the control mechanism determines a first battery among the plurality of power batteries, and controls the first battery to output electric power to the driving mechanism;
substep 4012, wherein the control mechanism controls the switch module to disconnect the electrical connection between the first battery and the driving mechanism when detecting that the first battery is in an abnormal state;
substep 4013, wherein the control mechanism determines a second battery and controls the switch module to conduct an electrical connection between the second battery and the drive mechanism.
In an alternative embodiment of the invention, the energy control module comprises a first energy control unit and a second energy control unit;
the first energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery disconnection module when the first energy control unit is in a normal state;
the second energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery disconnection module when the first energy control unit is in an abnormal state.
In an alternative embodiment of the invention, the switch module comprises a plurality of battery disconnect units;
one of the battery breaking units is connected with one of the power batteries.
In an alternative embodiment of the present invention, the battery breaking unit includes: a positive contactor and a negative contactor connected between the power battery and the energy distribution unit, and a pre-charge branch connected in parallel with the positive contactor; the pre-charging branch circuit comprises a pre-charging resistor and a pre-charging contactor which are connected in series; the method further comprises the steps of:
the energy control module controls the opening and closing states of the positive electrode contactor, the negative electrode contactor and the pre-charging contactor; the open-close state includes open or closed.
In an alternative embodiment of the present invention, further comprising: a discharge contactor; the driving mechanism comprises a plurality of flying electric drives and one or more traveling electric drives; the discharge contactor is arranged between the energy distribution unit and the positive electrode end of each flying electric drive and between the energy distribution unit and the positive electrode end of each driving electric drive; the method further comprises the steps of:
and when the energy control module detects that the flying electric drive fails, the discharge controller connected with the failed flying electric drive is disconnected.
In an alternative embodiment of the invention, the dc conversion module comprises at least two dc converters; the method further comprises the steps of:
and when the energy control module detects that any one of the direct current converters is in an abnormal state, the energy control module controls the output power of the other direct current converters in a normal state.
In an alternative embodiment of the invention, an isolation cavity is provided for the dc converter.
For the method embodiments, since they are substantially similar to the apparatus embodiments, the description is relatively simple, and reference is made to the description of the method embodiments in part.
The embodiment of the invention also provides an aircraft, which comprises: the high-voltage control apparatus as described above.
In this specification, each embodiment is described in a progressive manner, and each embodiment is mainly described by differences from other embodiments, and identical and similar parts between the embodiments are all enough to be referred to each other.
It will be apparent to those skilled in the art that embodiments of the present invention may be provided as a method, apparatus, or computer program product. Accordingly, embodiments of the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the invention may take the form of a computer program product on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) having computer-usable program code embodied therein.
Embodiments of the present invention are described with reference to flowchart illustrations and/or block diagrams of methods, terminal devices (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing terminal device to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal device, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the scope of the embodiments of the invention.
Finally, it is further noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article or terminal device comprising the element.
The high-voltage control device, the control method and the aircraft provided by the invention are described in detail, and specific examples are applied to illustrate the principle and the implementation mode of the invention, and the description of the above examples is only used for helping to understand the method and the core idea of the invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (8)
1. A high voltage control apparatus, comprising: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries; the energy control module comprises a first energy control unit and a second energy control unit; the switch module comprises a plurality of battery breaking units; one of the battery breaking units is connected with one power battery; the driving mechanism comprises a plurality of flying electric drives and one or more traveling electric drives; the direct current conversion module comprises at least two direct current converters;
the control mechanism is used for controlling the other power batteries to output the electric energy when detecting that the power battery outputting the electric energy is in an abnormal state;
the first energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery breaking unit when the first energy control unit is in a normal state;
the second energy control unit is used for controlling the energy supply mechanism, the driving mechanism and the battery breaking unit when the first energy control unit is in an abnormal state.
2. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the control mechanism is used for determining a first battery in the plurality of power batteries and controlling the first battery to output electric energy to the driving mechanism;
the control mechanism is also used for controlling the switch module to disconnect the electric connection between the first battery and the driving mechanism when the first battery is detected to be in an abnormal state;
the control mechanism is also used for determining a second battery and controlling the switch module to conduct the electrical connection between the second battery and the driving mechanism.
3. The apparatus of claim 1, wherein the battery breaking unit comprises: a positive contactor and a negative contactor connected between the power battery and the energy distribution unit, and a pre-charge branch connected in parallel with the positive contactor; the pre-charging branch circuit comprises a pre-charging resistor and a pre-charging contactor which are connected in series;
the energy control module is used for controlling the opening and closing states of the positive electrode contactor, the negative electrode contactor and the pre-charging contactor; the open-close state includes open or closed.
4. A device according to claim 3, further comprising: a discharge contactor;
the discharge contactor is arranged between the energy distribution unit and each positive electrode end of the flying electric drive and between the energy distribution unit and each positive electrode end of the driving electric drive.
5. The apparatus of claim 2, wherein the device comprises a plurality of sensors,
the energy control module is also used for controlling the output power of the rest DC converters in a normal state when detecting that any DC converter is in an abnormal state.
6. The apparatus as recited in claim 5, further comprising: and an isolation cavity arranged for the direct current converter.
7. A control method, characterized by being applied to a high-voltage control apparatus, the high-voltage control apparatus comprising: the control mechanism is connected with the energy supply mechanism and the driving mechanism; the control mechanism comprises an energy control module, a switch module connected with the energy control module, a direct current conversion module and an energy distribution unit; one end of the switch module is connected with the energy supply mechanism, and the other end of the switch module is connected with the direct current conversion module and the driving mechanism through the energy distribution unit; the energy supply mechanism comprises a plurality of power batteries; the energy control module comprises a first energy control unit and a second energy control unit; the switch module comprises a plurality of battery breaking units; one of the battery breaking units is connected with one power battery; the driving mechanism comprises a plurality of flying electric drives and one or more traveling electric drives; the direct current conversion module comprises at least two direct current converters; the method comprises the following steps:
the control mechanism controls the other power batteries to output electric energy when detecting that the power battery outputting electric energy is in an abnormal state;
when the first energy control unit is in a normal state, the energy supply mechanism, the driving mechanism and the battery breaking unit are controlled;
the second energy control unit controls the energy supply mechanism, the driving mechanism and the battery breaking unit when the first energy control unit is in an abnormal state.
8. An aircraft comprising a high voltage control device according to any one of claims 1-6.
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