CN114290906A - High-voltage control device, control method and aircraft - Google Patents
High-voltage control device, control method and aircraft Download PDFInfo
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- CN114290906A CN114290906A CN202210089252.0A CN202210089252A CN114290906A CN 114290906 A CN114290906 A CN 114290906A CN 202210089252 A CN202210089252 A CN 202210089252A CN 114290906 A CN114290906 A CN 114290906A
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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 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 which outputs the electric energy at present to output the electric energy by another power battery when the power battery is detected to be in an abnormal state. The embodiment of the invention can adopt another power battery to supply power to the driving mechanism in time when the power battery outputting the electric energy in the high-voltage control device fails, thereby ensuring the normal work of the driving mechanism and avoiding the problem that the high-voltage control device cannot continue to work normally after the single power battery is damaged.
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 of a conventional electric vehicle is generally independent components, and Power is distributed from a Power Battery 101 to a BDU102(Battery disconnection Unit), the BDU102 to a PDU103(Power Distribution Unit), and finally the PDU103 distributes the Power to high-voltage loads such as a vehicle electric driver 104 and DC/DC. The BMS105(Battery Management System) manages a power Battery, the VCU106(Vehicle Control Unit) manages a Vehicle electric driver 107, and the DC/DC controller 108, the VCU106 and the BMS105 exchange information through a communication network to collectively complete the operation of a Vehicle function program. Usually, only one set of control line and communication line is provided, and if the control line or the communication line is disconnected, the parts will be 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 proposed in order to provide a high-voltage control device of an aircraft and a corresponding high-voltage control method and aircraft that overcome or at least partially solve the above-mentioned problems.
In order to solve the above problem, 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 battery to output electric energy when the power battery which outputs the electric energy at present is detected to be 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 further 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 further used for determining a second battery and controlling the switch module to conduct the electric connection between the second battery and the driving mechanism.
Optionally, 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.
Optionally, the switch module comprises a plurality of battery disconnect units;
one of the battery disconnection units is connected with one of the power batteries.
Optionally, the battery disconnection unit includes: the positive contactor and the negative contactor are connected between the power battery and the energy distribution unit, and the pre-charging branch is connected with the positive contactor in parallel; the pre-charging branch 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 contactor, the negative contactor and the pre-charging contactor; the open-close state comprises open or close.
Optionally, the method further comprises: a discharge contactor; the driving mechanism comprises a plurality of flight electric drives and one or more traveling electric drives;
the discharge contactor sets up in energy distribution unit and each between the positive terminal that the flight electricity drove, and set up in energy distribution unit and each between the positive terminal that the driving electricity drove.
Optionally, the dc conversion module comprises at least two dc converters;
and the energy control module is also used for controlling the output power of the rest direct current converters in the normal state when any direct current converter is detected to be in the abnormal state.
Optionally, the method further comprises: an isolation cavity is provided for the DC converter.
The embodiment of the invention also discloses a control method, which is applied to a high-voltage control device, wherein the high-voltage control 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 method comprises the following steps:
the control mechanism controls the output of electric energy by the other power battery when detecting that the power battery that currently outputs 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 or not, and when the power battery outputting the electric energy to the driving mechanism is detected to be in the abnormal state, the power battery is switched to the power battery outputting the electric energy in a normal state in the energy supply mechanism, so that when the power battery outputting the electric energy in the high-voltage control device breaks down, the driving mechanism can be powered by the other power battery in time, the normal work of the driving mechanism is ensured, and the problem that the high-voltage control device cannot continue to work normally after the single power battery is damaged is avoided.
Drawings
FIG. 1 is a schematic 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 the switching process of the energy controller provided by the present invention;
FIG. 4 is a flow chart of the steps of an embodiment of a control method of the present invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
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 backups, 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 so as to maintain 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 comprises an energy control module 211, a switch module 212 connected with the energy control module 211, a direct current conversion module 213 and an energy distribution unit 214; one end of the switch module 212 is connected to the energy supply mechanism 220, and the other end is connected to the dc conversion module 213 and the driving mechanism 230 through the energy distribution unit 214; the energy supply mechanism 220 includes a plurality of power batteries 221;
the control mechanism 210 is configured to control the output of electric energy from the other power battery 221 when the power battery 221 that is currently outputting electric energy is detected to be in an abnormal state.
The embodiment of the invention can be applied to a moving body, for example: vehicles, aircraft, and the like. Further, it can be applied to an aircraft that includes at least two movement modes of land and flight (moving at any time by using one of land and flight), and when the driving mechanism 230 is operated, the driving mechanism can provide the power for the aircraft to move, for example: provides the power for controlling the movement (flying) of the aircraft.
The energy control module 211 is connected to the switch module 212, the dc conversion module 213, the energy supply mechanism 220, and the driving mechanism 230 through electrical connection lines, where the electrical connection lines include control lines and communication lines, so that the energy control module 211 can send messages to the switch module 212, the dc conversion module 213, the energy supply mechanism 220, and the driving mechanism 230 and perform corresponding control.
The switch module 212 can turn on or off the connection between the power battery 221 and the energy distribution unit 214, so that when any power battery 221 is turned 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 work accordingly.
The control mechanism 210 is configured to control the output of electric energy from the other power battery 221 when the power battery 221 that is currently outputting electric energy is detected to be 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 the electric energy to the driving mechanism is in the abnormal state, switch to the power battery 221 outputting the electric energy from the other power battery 221 in the normal state in the energy supply mechanism 220, so that when the power battery 221 outputting the electric energy in the high voltage control device fails, the other power battery 221 can be used to supply the electric energy to the driving mechanism 230 in time, thereby ensuring the normal operation of the driving mechanism 230, and avoiding the situation that the high voltage control device cannot continue to operate normally 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 energy 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 further configured to determine a second battery and control the switch module 212 to conduct an electrical connection between the second battery and the driving mechanism 230.
The energy control module 211 can determine a first battery among the plurality of power batteries 221 and control the switch module 212 to electrically connect the first battery with the energy distribution unit 214, so that the first battery can output electric energy to the driving mechanism 230. At this time, the connection between the other power battery 221 and the energy distribution unit 214 is in a disconnected state.
The power control module 211 can also detect whether the first battery is in an abnormal state, and when the first battery is detected to be in the abnormal state, the control switch module 212 disconnects the first battery from the power distribution unit 214, and the control switch module 212 conducts the connection between the second battery in a normal state and the power distribution unit 214, so that the second battery is used to output power to the driving mechanism 230.
In a specific implementation, it is not avoided that the driving mechanism 230 is powered by switching from the first battery to the second battery, which results in a temporary power failure of the driving mechanism 230, and in a specific implementation, the energy control module 211 controls the switch module 212 to first turn on the connection between the second point battery and the energy distribution unit 214, and then controls the switch module 212 to turn off the connection between the first point battery and the energy distribution unit 214.
In one example, the energy control module 211 can obtain 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, set a corresponding limit value for the operating state, and compare the operating state with the limit to determine whether the first battery is in an abnormal state. In specific implementation, whether the first battery is in the abnormal state or not can be judged in other ways, and the judgment method for the abnormal state of the first battery does not influence the implementation of the embodiment of the invention.
In a specific implementation, the first battery and the second battery may be determined according to characteristic information (e.g., temperature, capacity, remaining capacity) of each power battery 221, or may be determined according to a preset rule (e.g., corresponding priorities are set 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 energy to the driving mechanism 230; when the first battery is detected to be in an abnormal state, the switch module 212 is controlled to disconnect the electrical connection between the first battery and the driving mechanism 230; the second battery is determined and the switch module 212 is controlled 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 adopted to supply power to the driving mechanism 230 in time, the normal operation of the driving mechanism 230 is ensured, and the problem that the high-voltage control device cannot continue to operate normally after a single power battery 221 is damaged is avoided.
In an alternative embodiment of the invention, the energy control module 211 comprises 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 of the energy control units may be a first energy control unit 2111, and one of the other energy control units is a second energy control unit 2112, and when the first energy control unit 2111 and the second energy control unit 2112 are both in a normal state, the first energy control unit 2111 controls the power 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 second energy control unit 2112 controls the energy supply mechanism 220, the driving mechanism 230, the battery disconnection module and the direct current conversion module 213, 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 units can be adopted to correspondingly control other modules and mechanisms, and the safety of the control device and the aircraft is improved.
In a specific implementation, the first energy control unit 2111 and the second energy control unit 2112 are switched through a process shown in fig. 2, where the specific process is as follows:
the EMU1 (first energy control unit 2111) is set as the master manager and the EMU2 (second energy control unit 2112) is set as the slave manager. Under normal conditions, only the master manager EMU1 manages the energy supply mechanism 220, the driving mechanism 230 and the battery disconnection module, the slave manager EMU2 does not participate in management, and the manager EMU2 receives the status messages from the master manager EMU1 and monitors the messages sent by each component by the master manager EMU 1. When receiving the status message from master EMU1 as an error code from manager EMU2, or monitoring that the message sent by master EMU1 from the rest of the components is abnormal (including no message or message error), slave EMU2 automatically changes to the master manager and takes over the management of the other components (power supply mechanism 220, drive mechanism 230, battery disconnect module).
In an alternative embodiment of the present invention, the switch module 212 includes a plurality of battery disconnect units 2121;
one of the battery disconnection units 2121 is connected to one of the power batteries 221.
In an alternative embodiment of the present invention, the battery disconnection unit 2121 includes: a positive contactor 21211 and a negative contactor 21212 connected between the power battery 221 and the energy distribution unit 214, and a pre-charging branch connected in parallel with the positive contactor 21211; the pre-charging branch comprises a pre-charging resistor 21213 and a pre-charging contactor 21214 which are connected in series;
the energy control module 211 is configured to control the open/close states of the positive contactor 21211, the negative contactor 21212, and the precharge contactor 21214; the open-close state comprises open or close.
The control device may be pre-charged by closing the pre-charge contactor 21214 and the negative contactor 21212 when the control device is powered up, and the positive contactor 21211 may be closed and the pre-charge contactor 21214 may be opened when the pre-charge is completed to complete the high voltage power up of the control device. Through setting up the pre-charge branch road, can carry out the pre-charge to controlling means, avoid adopting power battery 221 directly to carry out the high voltage to the controlling means and lead to the consumer receive the high voltage impact in the twinkling of an eye and lead to damaging.
In an optional embodiment of the present invention, further comprising: a discharge contactor 240; the drive mechanism 230 includes a plurality of flight electric drives 231 and one or more flight electric drives 232; for an air-ground amphibious aircraft, flight electric drives 231 can drive rotors to enable the aircraft to fly in the air, and travel electric drives 232 are used for providing power for the aircraft to travel on the land.
The discharging contactor 240 is disposed between the energy distribution unit 214 and the positive terminal of each flight electric drive, and between the energy distribution unit 214 and the positive terminal of each flight electric drive.
Specifically, the energy distribution unit 214 includes a positive electrode connector 2141 and a negative electrode connector 2142; the positive connection 2141 is connected 21211 to each of the positive contactors and to the positive terminal of each of the flight electric drives 231; the negative connector 2142 is connected to each of the negative connectors and to the 231 negative terminal of each of the flying electric drives.
The discharging contactor 240 is arranged between the positive terminal of the flying electric drive and the positive terminal of the flying electric drive, and between the positive terminal of the flying electric drive and the positive terminal of the flying 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: the System comprises a BMS (Battery Management System), a VCU (Vehicle Control Unit), and an FCU (Flight Control Unit). BMS is used to control power battery 221, VCU is used to control the driving electric drives, and FCU is used to control the flying electric drives.
The energy control module 211 is also configured to open the discharge contactor 240 connected to the failed flight electric drive upon detection of a failure of the flight electric drive. By providing the discharging contactor 240, the circuit can be opened when an uncontrollable fault occurs in the electric drives (the traveling electric drive and/or the flying electric drive), further improving the reliability of the aircraft. In addition, a fuse may be further provided between the discharge contactor 240 and the positive connection member 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 the normal state when detecting that any dc converter 2131 is in the abnormal state.
The first energy control unit 2111 and the second energy control unit 2112 each further include: and a dc conversion control unit configured to control the dc converter 2131.
In one example, different dc converters 2131 may be connected to the same power-consuming accessories, the energy control module 211 may control one or more dc converters 2131 to supply power to the power-consuming accessories, and when an abnormality (including, but not limited to, high temperature, low output power, etc.) of any one of the dc converters 2131 is detected, output power of the remaining dc converters 2131 in a normal state is adjusted, and when some of the dc converters 2131 are abnormal, output power of the remaining dc converters 2131 may meet the demand of the power-consuming accessories, thereby ensuring normal operation of the control device.
In an optional embodiment of the present invention, further comprising: an isolation cavity is provided for the dc converter 2131.
When any direct current converter 2131 is in fault and fire, the isolation cavity ensures that the faulty direct current converter 2131 does not affect other devices.
In the embodiment of the invention, the aircraft control device is provided with the mutually redundant power battery 221, the mutually redundant direct current converter 2131, the mutually redundant flight electric driver 321 and the mutually redundant energy control unit, so that when any one of the mutually redundant devices fails, the redundant device can be called to ensure the control device to further ensure the normal operation of the aircraft, and the safety and the reliability of the aircraft are improved.
Referring to fig. 4, a flow chart of steps of an embodiment of a control method of the present invention is shown, applied to a high voltage control device 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 method specifically comprises the following steps:
in step 401, the control mechanism controls the output of electric energy by another power battery when detecting that the power battery which currently outputs electric energy is in an abnormal state.
In an alternative embodiment of the present invention, the step 401 includes:
a substep 4011, wherein the control mechanism determines a first battery in the plurality of power batteries and controls the first battery to output electric energy to the driving mechanism;
a 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;
and a substep 4013, wherein the control mechanism determines a second battery and controls the switch module to conduct the electrical connection between the second battery and the driving mechanism.
In an optional 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 disconnection units;
one of the battery disconnection units is connected with one of the power batteries.
In an alternative embodiment of the present invention, the battery disconnection unit includes: the positive contactor and the negative contactor are connected between the power battery and the energy distribution unit, and the pre-charging branch is connected with the positive contactor in parallel; the pre-charging branch comprises a pre-charging resistor and a pre-charging contactor which are connected in series; the method further comprises the following steps:
the energy control module controls the opening and closing states of the positive contactor, the negative contactor and the pre-charging contactor; the open-close state comprises open or close.
In an optional embodiment of the present invention, further comprising: a discharge contactor; the driving mechanism comprises a plurality of flight electric drives and one or more traveling electric drives; the discharging contactor is arranged between the energy distribution unit and the positive end of each flight electric driver and between the energy distribution unit and the positive end of each traveling electric driver; the method further comprises the following steps:
and when the energy control module detects that the flight electric drive is in fault, the energy control module disconnects the discharge controller connected with the flight electric drive in fault.
In an alternative embodiment of the invention, the dc conversion module comprises at least two dc converters; the method further comprises the following steps:
and the energy control module controls the output power of the rest direct current converters in the normal state when detecting that any direct current converter is in the abnormal state.
In an optional embodiment of the invention, an isolation cavity is provided for the dc converter.
As for the method embodiment, since it is basically similar to the apparatus embodiment, the description is simple, and the relevant points can be referred to the partial description of the method embodiment.
An embodiment of the present invention further provides an aircraft, including: the high voltage control device as described above.
The embodiments in the present specification are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
As will be appreciated by one skilled in the art, 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 present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) 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 flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams 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 to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal, 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 terminal 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 terminal to cause a series of operational steps to be performed on the computer or other programmable terminal to produce a computer implemented process such that the instructions which execute on the computer or other programmable terminal 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 of these embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the embodiments of the invention.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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 an … …" does not exclude the presence of other like elements in a process, method, article, or terminal that comprises the element.
The high-voltage control device, the control method and the aircraft provided by the invention are described in detail, specific examples are applied in the description to explain the principle and the implementation mode of the invention, and the description of the examples is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (10)
1. A high-pressure control device, 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 control mechanism is used for controlling the other power battery to output electric energy when the power battery which outputs the electric energy at present is detected to be in an abnormal state.
2. The apparatus of claim 1,
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 further 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 further used for determining a second battery and controlling the switch module to conduct the electric connection between the second battery and the driving mechanism.
3. The apparatus of claim 1 or 2, wherein 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.
4. The device of claim 1 or 2, wherein the switch module comprises a plurality of battery disconnect units;
one of the battery disconnection units is connected with one of the power batteries.
5. The apparatus of claim 4, wherein the battery disconnect unit comprises: the positive contactor and the negative contactor are connected between the power battery and the energy distribution unit, and the pre-charging branch is connected with the positive contactor in parallel; the pre-charging branch 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 contactor, the negative contactor and the pre-charging contactor; the open-close state comprises open or close.
6. The apparatus of claim 5, further comprising: a discharge contactor; the driving mechanism comprises a plurality of flight electric drives and one or more traveling electric drives;
the discharge contactor sets up in energy distribution unit and each between the positive terminal that the flight electricity drove, and set up in energy distribution unit and each between the positive terminal that the driving electricity drove.
7. The apparatus of claim 2, wherein the dc conversion module comprises at least two dc converters;
and the energy control module is also used for controlling the output power of the rest direct current converters in the normal state when any direct current converter is detected to be in the abnormal state.
8. The apparatus of claim 7, further comprising: an isolation cavity is provided for the DC converter.
9. A control method, characterized by being applied to 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 method comprises the following steps:
the control mechanism controls the output of electric energy by the other power battery when detecting that the power battery that currently outputs electric energy is in an abnormal state.
10. An aircraft, characterized in that it comprises a high-voltage control device according to any one of claims 1-8.
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| CN115180161A (en) * | 2022-05-18 | 2022-10-14 | 北京锐士装备科技有限公司 | Driving equipment and driving method for unmanned aerial vehicle load device |
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