CN112769224A - Aircraft and flight control system's control circuit thereof - Google Patents
Aircraft and flight control system's control circuit thereof Download PDFInfo
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- CN112769224A CN112769224A CN202110196330.2A CN202110196330A CN112769224A CN 112769224 A CN112769224 A CN 112769224A CN 202110196330 A CN202110196330 A CN 202110196330A CN 112769224 A CN112769224 A CN 112769224A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 32
- 238000001514 detection method Methods 0.000 claims description 109
- 230000004044 response Effects 0.000 claims description 18
- 239000003990 capacitor Substances 0.000 claims description 11
- 238000000034 method Methods 0.000 claims description 7
- 230000003044 adaptive effect Effects 0.000 claims description 2
- 230000002159 abnormal effect Effects 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 7
- 230000005669 field effect Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 230000001960 triggered effect Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 2
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0068—Battery or charger load switching, e.g. concurrent charging and load supply
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/007—Regulation of charging or discharging current or voltage
- H02J7/00712—Regulation of charging or discharging current or voltage the cycle being controlled or terminated in response to electric parameters
- H02J7/007182—Regulation of charging or discharging current or voltage the cycle being controlled or terminated in response to electric parameters in response to battery voltage
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/068—Electronic means for switching from one power supply to another power supply, e.g. to avoid parallel connection
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B70/00—Technologies for an efficient end-user side electric power management and consumption
- Y02B70/30—Systems integrating technologies related to power network operation and communication or information technologies for improving the carbon footprint of the management of residential or tertiary loads, i.e. smart grids as climate change mitigation technology in the buildings sector, including also the last stages of power distribution and the control, monitoring or operating management systems at local level
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y04—INFORMATION OR COMMUNICATION TECHNOLOGIES HAVING AN IMPACT ON OTHER TECHNOLOGY AREAS
- Y04S—SYSTEMS INTEGRATING TECHNOLOGIES RELATED TO POWER NETWORK OPERATION, COMMUNICATION OR INFORMATION TECHNOLOGIES FOR IMPROVING THE ELECTRICAL POWER GENERATION, TRANSMISSION, DISTRIBUTION, MANAGEMENT OR USAGE, i.e. SMART GRIDS
- Y04S20/00—Management or operation of end-user stationary applications or the last stages of power distribution; Controlling, monitoring or operating thereof
- Y04S20/20—End-user application control systems
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Power Sources (AREA)
Abstract
This application is about an aircraft and flight control system's control circuit thereof, and this control circuit includes: the power supply device comprises a controller, a first power supply interface used for being connected with a first power supply, a second power supply interface used for being connected with a second power supply, a switch circuit and a power supply selector; the second power supply interface comprises a power supply end and a data transmission end connected with the controller; the switch circuit comprises a first switch connected between the first power supply interface and the controller and a second switch connected between the power supply end of the second power supply interface and the controller; the power supply selector is configured to select a current power supply interface according to a preset rule and output a corresponding switch control signal to the switch circuit. According to the embodiment of the application, under the condition that the power supply of the battery is abnormal, a standby power supply can be provided for the controller, and backup of flight control data is achieved.
Description
Technical Field
The application relates to the field of aircrafts, in particular to a control circuit of an aircraft flight control system.
Background
The flight control system of the manned aircraft executes the starting, execution and control of all flight instructions in a flight task, whether the flight control system is safe or not is directly related to the safety of the aircraft, and the power supply safety of the controller in the flight control system is the premise of ensuring the safety of the flight control system. When the power supply of the controller of the flight control system fails, the aircraft loses control. In order to ensure the safety of the aircraft, the power supply of the flight control system controller must be ensured.
Disclosure of Invention
In order to overcome the problems in the related art, the application provides a control circuit of a flight control system, which can provide a standby power supply for a controller under the condition of abnormal power supply of a battery.
One aspect of the present application provides a control circuit of a flight control system, including:
a controller;
the first power supply interface is used for connecting a first power supply;
the second power supply interface is used for connecting a second power supply and comprises a power supply end and a data transmission end connected with the controller;
the switch circuit comprises a first switch connected between the first power supply interface and the controller and a second switch connected between a power supply end of the second power supply interface and the controller;
and the power supply selector is configured to select the current power supply interface according to a preset rule and output a corresponding switch control signal to the switch circuit.
In some embodiments, the power supply selector is configured to output a switch control signal for closing the second switch and opening the first switch when the second power supply interface is selected as the current power supply interface according to a preset priority order of the power supply interfaces and detection signals of the first power supply and the second power supply; the controller is configured to respond to a signal that the second power supply interface is connected with the second power supply, and send flight control data to a data transmission terminal of the second power supply interface according to a preset data transmission instruction or periodically.
In some embodiments, the second power supply interface is a USB interface.
In some embodiments, the power supply further comprises a third power supply interface for connecting a third power supply, and the switch circuit further comprises a third switch connected between the third power supply interface and the controller;
the first power supply and the third power supply are battery power supplies, and the second power supply interface is a data transmission interface adaptive to the intelligent computing equipment.
In some embodiments, the selecting the current power supply interface according to the preset rule includes:
and selecting one of the first power supply interface and the third power supply interface as a current power supply interface according to a preset priority order of the power supply interfaces and detection signals of the first power supply to the third power supply.
In some embodiments, the selecting one of the first power supply interface to the third power supply interface as the current power supply interface according to a preset priority order of the power supply interfaces and respective detection signals of the first power supply to the third power supply includes:
according to the priority sequence of the three power supply interfaces from the first power supply interface to the third power supply interface, executing the following steps: judging whether a power supply corresponding to the power supply interface at the current level is connected with the control circuit and meets a preset power supply condition, if the power supply corresponding to the power supply interface at the current level meets the preset power supply condition, determining the power supply interface at the current level as the current power supply interface, if the power supply corresponding to the power supply interface at the current level is not connected with the control circuit or does not meet the preset power supply condition, taking the power supply interface at the next priority order as the power supply interface at the current level, and returning to the step of judging whether the power supply corresponding to the power supply interface at the current level is connected with the control circuit and meets the; alternatively, the first and second electrodes may be,
and obtaining respective detection signals of the first power supply to the third power supply, judging whether the first power supply interface to the third power supply interface are respectively connected with the power supply and whether the connected power supply meets a preset power supply condition according to the obtained detection signals, and determining the current power supply interface according to the preset priority sequence of the three power supply interfaces of the first power supply interface to the third power supply interface under the condition that at least two connected power supplies meet the preset power supply condition.
In some embodiments, further comprising: a first detection circuit connected between the first power supply interface and the power supply selector, a second detection circuit connected between a power supply terminal of the second power supply interface and the power supply selector, and a third detection circuit connected between the third power supply interface and the power supply selector;
at least one of the first detection circuit to the third detection circuit is connected with the power supply selector through at least three signal lines, and the at least three signal lines comprise a power supply voltage detection signal line, an overvoltage detection signal line and an undervoltage detection signal line.
In some embodiments, the first and third power interfaces have a higher priority than the second power interface;
the priority of the first power supply interface is higher than the priority of the third power supply interface.
In some embodiments, the power supply selector is further configured to determine a next power supply interface according to a preset rule and perform power supply interface switching through the switching circuit, if the current power supply interface does not meet a preset power supply condition; wherein, carrying out power supply interface switching through the switch circuit includes: and after the next power supply interface is firstly connected with the controller, the current power supply interface is disconnected with the controller.
In some embodiments, the control circuit further comprises a first capacitor connected between the first power interface and ground, a second capacitor connected between a power supply terminal of the second power interface and ground, and a third capacitor connected between the third power interface and ground.
In some embodiments, the power selector is further configured to obtain power management data according to the detection signals of the first to third detection circuits, and send the power management data to the controller;
the controller is further configured to make flight decisions based at least on the power management data and preset decision rules, including:
the method comprises the steps of periodically obtaining the residual power of a power supply, and sending an alarm to prompt a user or enabling an aircraft to automatically execute preset safeguard measures when the residual power of the power supply reaches a preset alarm threshold value; or
Periodically obtaining the residual power of a power supply, determining a corresponding alarm level according to the residual power of the power supply, and making a flight decision according to the determined alarm level; or
Performing flight decision according to flight state information of the aircraft, the power supply residual capacity and a preset decision rule; or
And performing flight decision according to the flight state information, the flight mission, the power supply residual capacity and a preset decision rule of the aircraft.
In some embodiments, the system further comprises a first charging interface for connecting the first power supply, a fourth power supply interface for connecting an aircraft power module power supply, a first charging detection circuit for detecting the first power supply, a fourth switch connected between the fourth power supply interface and the first charging interface, and a charging controller connected with the fourth switch and the first charging detection circuit.
In some embodiments, the charge controller is configured to output a switch control signal to close the fourth switch in response to a signal that the charge level of the first power source does not meet a preset condition, and to output a switch control signal to open the fourth switch in response to the signal that the charge level of the first power source meets the preset condition.
In some embodiments, the charge controller is configured to output a switch control signal to close the fourth switch in response to a signal that the voltage of the first power source is less than a first preset threshold, and to output a switch control signal to open the fourth switch in response to a signal that the voltage of the first power source is greater than a second preset threshold.
In some embodiments, the charging controller is configured to output the switch control information to close the fourth switch in response to the first power source supplying power to the controller and the power of the first power source not meeting a preset condition.
In some embodiments, further comprising: the first charging interface is used for being connected with the first power supply, the fourth power supply interface is used for being connected with an aircraft power module power supply, the first charging detection circuit is used for detecting the first power supply, the fourth switch is connected between the second power supply interface and the first charging interface, the second charging interface is used for being connected with the third power supply, the second charging detection circuit is used for detecting the third power supply, the fifth power supply interface is used for being connected with the power module power supply, and the fifth switch is connected between the fifth power supply interface and the second charging interface; and the charging controller is connected with the fourth switch, the fifth switch, the first charging detection circuit and the second charging detection circuit.
In some embodiments, the charging controller is connected to the power supply selector, and acquires a signal indicating which of the first power supply interface, the second power supply interface, and the third power supply interface is a current power supply interface;
the charging controller is configured to output a corresponding switch control signal when one of the first power supply interface and the third power supply interface is a current power supply interface and a power supply connected with the current power supply interface does not meet a preset condition, so that the aircraft power module power supply charges the power supply connected with the current power supply interface.
Another aspect of the present application provides an aircraft having the control circuit of the flight control system as described above.
In this embodiment, the control circuit is configured with a second power supply interface for connecting to a second power supply, the second power supply interface has a power supply end and a data transmission end, the data transmission end is connected to the controller, a second switch is disposed between the power supply end and the controller, and the power supply selector can control whether to select the second power supply interface to operate by outputting a switch control signal. Through the configuration, the second power supply can be selected to provide a standby power supply for the controller under the condition that the power supply of the first power supply is abnormal, and the flight control data obtained by the controller can be transmitted outwards through the data transmission end of the second power supply interface, so that the backup of the flight control data is realized. On the other hand, whether the second power supply interface supplies power or not is managed through the power supply selector, so that the interference of the normal power supply of other power supplies when the second power supply is connected to the control circuit can be avoided.
Further, in some embodiments, after the next power supply interface is connected to the controller, the current power supply interface is disconnected from the controller, so that seamless switching of the power supply can be realized, and continuous power supply of the controller is ensured.
Furthermore, through the charge and discharge capacitors of the equipment between each power supply interface and the ground, the power supply of the current power supply can be continuously supplied to the controller through the corresponding capacitors under the conditions that the power supply fails or the electric quantity is insufficient and the switching is not performed, so that the power failure of the controller is avoided, and the continuous power supply of the controller is ensured.
Furthermore, a battery power supply is connected with a charging interface, a power supply interface used for being connected with an aircraft power module power supply is connected with the charging interface through a switch, a charging detection circuit detects the voltage of the battery power supply, the state of the switch is controlled through a charging controller, the aircraft power module power supply charges or does not charge the battery power supply, the battery power supply of the flight control system is charged, the electric quantity of the power supply of the flight control system controller can be ensured in the flight process of the aircraft, and therefore flight safety is ensured. On the other hand, when the battery power supply supplies power to the controller and the electric quantity of the battery power supply does not accord with the preset voltage, the charging controller controls the switch between the power supply interface connected with the aircraft power module power supply and the charging interface to be closed, so that the aircraft power module power supply charges the battery power supply, the electric quantity of the power supply battery power supply is ensured, the real-time charging and discharging of the power supply of the flight control system are realized, and the power supply safety of the flight control system is ensured.
In some embodiments, the control circuit is configured with a second power supply interface for connecting the first battery, a third power supply interface for connecting the second battery, and a second power supply interface for connecting the smart computing device, the second power supply interface may be a USB interface having a power end and a data transmission end, the data transmission end is connected to the controller, a second switch is disposed between the power end and the controller, and the power selector may control whether to select the second power supply interface to operate by outputting a switch control signal. Through the configuration, double-battery power supply backup power supply can be provided for the controller, the intelligent computing equipment is selected to provide the backup power supply for the controller under the abnormal condition that the first battery and the second battery cannot normally supply power, the flight control data obtained by the controller can be transmitted to the intelligent computing equipment through the data transmission end of the USB interface, and backup of the flight control data is achieved.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.
Drawings
The foregoing and other objects, features and advantages of the application will be apparent from the following more particular descriptions of exemplary embodiments of the application, as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the application.
Fig. 1 is a schematic structural diagram illustrating a control circuit of an flight control system according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a control circuit of an aircraft control system according to another embodiment of the present application;
fig. 3 is a schematic structural diagram of a resistance voltage division detection circuit according to an embodiment of the present application;
fig. 4 is a schematic structural diagram of a control circuit of an flight control system according to another embodiment of the present application.
Detailed Description
Preferred embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present application are shown in the drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this application and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It should be understood that although the terms "first," "second," "third," etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "at least one" means one or more than one, and "a plurality" means two or more than two unless specifically limited otherwise.
Unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly and can include, for example, direct connection, indirect connection through an intermediary, communication between two elements, or an interaction between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.
Fig. 1 is a block diagram showing a control circuit 100 of an flight control system according to an embodiment of the present invention.
Referring to fig. 1, a control circuit 100 of the flight control system of the present embodiment includes: controller 20, first power supply interface 30, second power supply interface 32, switching circuit 40, and power supply selector 50.
The first power supply interface 30 is used for connecting a first power supply; the first power source may be a battery power source, and the connection of the first power source to the first power supply interface 30 includes a direct connection with the first power source and a connection with a converted power source after voltage boosting or voltage reducing processing is performed on the first power source.
The second power interface 32 is for connecting a second power source and includes a power terminal 36 and a data transfer terminal 38 connected to the controller 20. In this embodiment of the application, the second power supply may be an intelligent computing device, for example, an operating device (e.g., a tablet pc console) and an intelligent mobile terminal (e.g., a smart phone) that are installed in an aircraft, and the second power supply interface 32 is a data transmission interface adapted to the intelligent computing device, for example, a Universal Serial Bus (english: USB for short) interface, a Lightning interface, and the like may be used, and the USB interface may include various types of USB interfaces such as Type a, Type B, Micro a, Micro B, Mini a, Mini B, and Type C.
The switching circuit 40 includes a first switch connected between the first power interface 30 and the controller 20, and a second switch connected between the power terminal 36 of the second power interface 32 and the controller 20. In one implementation, the first switch and the second switch may be implemented by field effect transistors, but the application is not limited thereto.
The power supply selector 50 outputs a switching control signal to the switching circuit 40. In one implementation, the power selector 50 may include a power control chip configured to select the current power supply interface according to a preset rule and output a corresponding switch control signal to the switch circuit 40, for example, when the second power supply interface 50 is selected as the current power supply interface according to a preset priority order of the power supply interfaces and the detection signals of the first power supply and the second power supply, a switch control signal for turning on the second switch and turning off the first switch is output. It is to be understood that the power selector 50 in the present application may also be a switch driving circuit composed of discrete components.
The controller 20 is configured to perform flight control, and in this embodiment, is further configured to send flight control data to the data transmission terminal 38 of the second power supply interface 32 according to a preset data transmission instruction or periodically in response to a signal that the second power supply interface 32 is connected to the second power supply. It is understood that the sending of the flight control data by the controller 20 to the second power source through the data transmission terminal 38 of the second power supply interface 32 and the supplying of the power to the controller 20 by the second power source may or may not be performed simultaneously.
In this embodiment, the control circuit is configured with a second power supply interface for connecting to a second power supply, the second power supply interface has a power supply end and a data transmission end, the data transmission end is connected to the controller, a second switch is disposed between the power supply end and the controller, and the power supply selector can control whether to select the second power supply interface to operate by outputting a switch control signal. Through the configuration, the second power supply can be selected to provide a standby power supply for the controller under the condition that the power supply of the first power supply is abnormal, and the flight control data obtained by the controller can be transmitted outwards through the data transmission end of the second power supply interface, so that the backup of the flight control data is realized. On the other hand, whether the second power supply interface supplies power or not is managed through the power supply selector, so that the interference of the normal power supply of other power supplies when the second power supply is connected to the control circuit can be avoided.
Fig. 2 shows a block diagram of a control circuit 200 of an flight control system according to another embodiment of the present application. Referring to fig. 2, the control circuit 200 of the flight control system of the present embodiment includes: the flight control system includes a controller 20, a first power supply interface 30, a second power supply interface 32, a first detection circuit 60, a second detection circuit 62, a switch circuit 40, and a power supply selector 50.
The first power supply interface 30 is used for connecting a first power supply; the first power source may be a battery power source, and the connection of the first power source to the first power supply interface 30 includes a direct connection with the first power source and a connection with a converted power source after voltage boosting or voltage reducing processing is performed on the first power source.
The second power interface 32 is for connecting a second power source and includes a power terminal 36 and a data transfer terminal 38 connected to the controller 20. In an embodiment of the present application, the second power source may be an intelligent computing device.
The switching circuit 40 includes a first switch connected between the first power interface 30 and the controller 20, and a second switch connected between the power terminal 36 of the second power interface 32 and the controller 20. In one implementation, the first switch and the second switch may be implemented by field effect transistors, but the application is not limited thereto.
The first detection circuit 60 is connected between the first power supply interface 30 and the power supply selector 50, and the second detection circuit 62 is connected between the power supply terminals 36 of the second power supply interface 32 and the power supply selector 50. It will be appreciated that the same or different detection circuits may be used for the first detection circuit 60 and the second detection circuit 62.
In one implementation, the first detection circuit 60 and the second detection circuit 62 each include a voltage detection circuit, which may be implemented by a voltage division circuit, such as a resistance division detection circuit 66, that outputs a detection signal of the first power supply and a detection signal of the second power supply to the power supply selector 50.
As shown in fig. 3, in a specific implementation, the resistance voltage division detecting circuit 66 includes a first resistor R1, a second resistor R2, and a third resistor R3 connected in series between the corresponding power supply interface and the ground in sequence, wherein one end of the first resistor R1 connected to the corresponding power supply interface, one end of the first resistor R1 connected to the second resistor R2, and one end of the second resistor R2 connected to the third resistor R3 are connected to the power selector 50 through a power supply voltage detecting signal line T1, an overvoltage detecting signal line T2, and an undervoltage detecting signal line T3, respectively, so as to output a power supply voltage detecting signal, an overvoltage detecting signal, and an undervoltage detecting signal to the power selector 50. The power selector 50 may determine whether a power supply is connected to the corresponding power supply interface and whether the connected power supply meets a preset power supply condition, such as whether the power supply circuit is normal, whether the power supply is within a power supply range between a preset high voltage threshold and a preset low voltage threshold, or the like, according to the power supply voltage detection signal, the overvoltage detection signal, and the undervoltage detection signal.
It will be appreciated that in other embodiments, other suitable detection circuits may be used to detect the power supply, such as current detection circuits. The detection signal of the power supply output from the detection circuit to the power supply selector 50 may be a part of the power supply voltage detection signal, the overvoltage detection signal, and the undervoltage detection signal, or may be another detection signal.
The power supply selector 50 may include a power supply control chip configured to select a current power supply interface according to a preset power supply interface priority order, and a detection signal of the first power supply and a detection signal of the second power supply, and output a corresponding switch control signal to the switch circuit 40. It is to be understood that in another embodiment, the power selector 50 may also be composed of discrete components.
In one implementation, the priority of the first power interface 30 is higher than the priority of the second power interface 32. If the first power supply interface 30 has a battery power supply connected thereto and the battery power supply meets the preset power supply condition, the power supply selector 50 outputs a switch control signal to the switch circuit 40 to turn on the first switch and turn off the second switch; if the first power supply interface 30 has no battery power connected or the battery power does not meet the preset power supply condition although the first power supply interface is connected, and the second power supply interface 32 has the intelligent computing device connected and the power provided by the intelligent computing device meets the preset power supply condition, the power supply selector 50 outputs a switch control signal for turning on the second switch and turning off the first switch to the switch circuit 40.
The controller 20 is configured to perform flight control, and in this embodiment, is further configured to send flight control data to the data transmission terminal 38 of the second power supply interface 32 when the second power supply interface 32 is the current power supply interface. In one implementation, the controller 20 is connected to the power supply selector 50, and configured to send the flight control data to the data transmission terminal 38 of the second power supply interface 32 in response to the indication signal sent by the power supply selector 50 that the second power supply interface 32 is the current power supply interface, and transmit the flight control data to the smart computing device via the second power supply interface 32 for data backup. The flight control data includes, for example, flight control data, attitude data, control data, and the like.
In this embodiment, the method further includes: a first charging interface 93 for connecting first power source 91, a fourth power supply interface 95 for connecting aircraft power module power source 80, a first charging detection circuit 71 for detecting first power source 91, a fourth switch connected between fourth power supply interface 95 and first charging interface 93, and a charging controller 70 connected with fourth switch and first charging detection circuit 71.
The aircraft power module power supply 80 is used to charge the first power supply 91. In one implementation, the aircraft power module power supply may be a large power supply internal to the aircraft, such as a cabin battery or the like. In this application, the aircraft can be electronic manned aircraft, and aircraft power module power can locate manned aircraft's passenger cabin top, for the power supply of a plurality of power modules of aircraft. The power module may include, for example, an electric motor, a propeller, etc.
The first charge detection circuit 71 is connected to the first power supply 91, and detects the first power supply 91. In one specific implementation, the first charge detection circuit may be a voltage detection circuit, for example, a resistance division detection circuit, which detects the power amount of the first power source 91 by detecting the voltage of the first power source. It is to be understood that the first charge detection circuit may also be a current detection circuit.
And a charge controller 70 for outputting a switching control signal to the fourth switch. In one implementation, the charge controller 70 may include a charge control chip configured to output a corresponding switch control signal to the fourth switch in response to whether the amount of power of the first power source 91 meets a preset condition. It is to be understood that the charge controller 70 in the present application may also be a switch driving circuit composed of discrete components.
In one implementation, the charge controller 70 is configured to output a switch control signal to close the fourth switch to cause the aircraft motion module power supply 80 to charge the first power supply 91 in response to the voltage of the first power supply 91 being less than a first preset threshold, and to output a switch control signal to open the fourth switch to cause the aircraft motion module power supply 80 to stop charging the first power supply 91 in response to the voltage of the first power supply 91 being greater than a second preset threshold.
In one implementation, the charging controller 70 is configured to output the switch control information for switching the fourth switch on and off in response to the first power source 91 supplying power to the controller 20 and the power of the first power source 91 not meeting the preset condition.
In this embodiment, the control circuit is configured with a second power supply interface for connecting to a second power supply, the second power supply interface has a power supply end and a data transmission end, the data transmission end is connected to the controller, a second switch is disposed between the power supply end and the controller, and the power supply selector can control whether to select the second power supply interface to operate by outputting a switch control signal. Through the configuration, the second power supply can be selected to provide a standby power supply for the controller under the condition that the power supply of the first power supply is abnormal, and the flight control data obtained by the controller can be transmitted outwards through the data transmission end of the second power supply interface, so that the backup of the flight control data is realized. On the other hand, whether the second power supply interface supplies power or not is managed through the power supply selector, so that the interference of the normal power supply of other power supplies when the second power supply is connected to the control circuit can be avoided.
Fig. 4 shows a block diagram of a control circuit 400 of an flight control system according to another embodiment of the present application. Referring to fig. 4, the control circuit 400 of the flight control system of the present embodiment includes: controller 20, first power supply interface 30, second power supply interface 32, third power supply interface 34, first detection circuit 60, second detection circuit 62, third detection circuit 64, switching circuit 40, and power supply selector 50.
The first power supply interface 30 is used for connecting a first power supply, and the third power supply interface 34 is used for connecting a third power supply; the first power source and the third power source may be battery power sources, the first power supply interface 30 may be connected to the first power source, and may be connected to the first power source directly or after the first power source is boosted or reduced, and the third power supply interface 34 may be connected to the third power source.
The second power interface 32 is for connecting a second power source and includes a power terminal 36 and a data transfer terminal 38 connected to the controller 20. In an embodiment of the present application, the second power source may be an intelligent computing device.
The switching circuit 40 includes a first switch connected between the first power interface 30 and the controller 20, a second switch connected between the power terminal 36 of the second power interface 32 and the controller 20, and a third switch connected between the power terminal 36 of the third power interface 34 and the controller 20. In one implementation, the first to third switches may be implemented by field effect transistors, but the present application is not limited thereto.
The first detection circuit 60 is connected between the first power supply interface 30 and the power supply selector 50, the second detection circuit 62 is connected between the power supply terminal 36 of the second power supply interface 32 and the power supply selector 50, and the third detection circuit 64 is connected between the power supply terminal 36 of the third power supply interface 34 and the power supply selector 50. It will be appreciated that the same or different circuits may be used for the first sensing circuit 60, the second sensing circuit 62 and the third sensing circuit 64.
In one implementation, the first to third detection circuits 60 to 64 respectively include a voltage detection circuit 66, which may be implemented by a voltage division circuit, such as a resistance voltage division detection circuit, and outputs detection signals of the first to third power supplies to the power supply selector 50.
It will be appreciated that in other embodiments, other suitable sensing circuits may be used to sense the power supply, such as current sensing circuits. The detection signal of the power supply output from the detection circuit to the power supply selector 50 may be a part of the power supply voltage detection signal, the overvoltage detection signal, and the undervoltage detection signal, or may be another detection signal.
The power supply selector 50 may include a power supply control chip configured to select one of the first power supply interface 30 to the third power supply interface 34 as a current power supply interface according to a preset power supply interface priority order and detection signals of the first power supply to the third power supply, and output a corresponding switch control signal to the switch circuit 40.
In one implementation, the first power interface 30 and the third power interface 34 have a higher priority than the second power interface 32, and the first power interface 30 has a higher priority than the third power interface 34.
In one implementation, selecting one of the first power interface 30 to the third power interface 34 as the current power interface according to a preset priority order of the power interfaces and the detection signals of the first power supply to the third power supply includes:
in order of priority of the first power supply interface 30 to the third power supply interface 34, the following steps are performed: judging whether a power supply corresponding to the power supply interface at the current level is connected with the control circuit and accords with preset power supply conditions, if so, determining that the power supply interface at the current level is the current power supply interface, if not, taking the power supply interface at the next priority order as the power supply interface at the current level, and returning to the step of judging whether the power supply corresponding to the power supply interface at the current level is connected with the control circuit and accords with the preset power supply conditions.
In another implementation manner, selecting one of the first power supply interface 30 to the third power supply interface 34 as the current power supply interface according to a preset priority order of the first power supply interface 30 to the third power supply interface 34 and respective detection signals of the first power supply to the third power supply includes:
the method comprises the steps of obtaining respective detection signals of the first power supply to the third power supply, judging whether the first power supply interface 30 to the third power supply interface 34 are respectively connected with the power supply and whether the connected power supply meets preset power supply conditions according to the obtained detection signals, and determining the current power supply interface according to the preset priority sequence of the first power supply interface 30 to the third power supply interface 34 under the condition that at least two connected power supplies meet the preset power supply conditions. For example, in a specific example, only the first power supply interface 30 of the three power supply interfaces is connected with a power supply, and neither the second power supply interface 32 nor the third power supply interface 34 is connected with a power supply, and at this time, the second power supply interface 32 and the third power supply interface 34 are equivalent to being grounded, the power supply selector 50 may consider that the power supplies of the second power supply and the third power supply are both abnormal, determine that the first power supply interface 30 is the current power supply interface, and output a switch control signal for closing the first switch and opening the second switch and the third switch, so that the first power supply supplies power; for another example, the first power supply interface 30 and the third power supply interface of the three power supply interfaces are both connected to a battery power supply, and both of them meet preset power supply conditions, the power supply selector 50 determines that the first power supply interface 30 is the current power supply interface according to the priority order of the three power supply interfaces, outputs a switch control signal for turning on the first switch, turning off the second switch, and turning off the third switch, and when the first power supply does not meet the preset power supply conditions, for example, no output voltage or a voltage lower than a preset threshold value, the power supply selector 50 switches the third power supply interface 34 to the current power supply interface, and outputs a switch control signal for turning on the third switch, turning off the first switch, and turning off the second switch, so that the third power supply supplies power.
In one implementation, when switching the power supply interfaces, after the third power supply interface 34 is connected to the controller 20, the first power supply interface 30 is disconnected from the controller 20, so as to implement seamless switching of the power supply and ensure continuous power supply of the controller 20.
In some embodiments, the control circuit further comprises a first capacitor connected between the first power interface 30 and ground, a second capacitor connected between the power supply terminal 36 of the second power interface 32 and ground, and a third capacitor connected between the third power interface 34 and ground. Through setting up first electric capacity to third electric capacity, can be in the power failure (for example battery connecting wire is not hard up, power supply interface is not hard up, the battery explodes etc.) or the electric quantity not enough and not switching yet the condition under, continue to supply power for the controller through corresponding electric capacity, avoid the controller outage.
The controller 20 is configured to perform flight control, and in this embodiment, is further configured to send flight control data to the data transmission terminal 38 of the second power supply interface 32 when the second power supply interface 32 is the current power supply interface. In one implementation, the controller 20 is connected to the power supply selector 50, and configured to send the flight control data to the data transmission terminal 38 of the second power supply interface 32 in response to the indication signal sent by the power supply selector 50 that the second power supply interface 32 is the current power supply interface, and transmit the flight control data to the smart computing device via the second power supply interface 32 for data backup. The flight control data includes, for example, flight control data, attitude data, control data, and the like.
In the embodiment of the present application, the power selector 50 may obtain power management data according to the detection signals of the first to third detection circuits 60 to 64, and send the power management data to the controller 20, where the power management data includes a current power supply interface, state information of a battery, and the like, and the battery state information includes, for example, a battery voltage value, a remaining power value, an output current value, and the like.
After obtaining the power management data, the controller 20 may make a flight decision according to the power management data, the flight status information, and a preset decision rule. The flight status information may include, for example, altitude, speed, location, etc.
In one embodiment, the controller 20 is configured to make flight decisions based on flight status information of the aircraft, power supply remaining capacity, and preset decision rules; the flight decision data may include whether to alarm or not, whether to force the aircraft to automatically return or land, and the like. For example, in one embodiment, whether the aircraft can safely land is determined according to the flying height of the aircraft, the remaining power of the power supply and a preset decision rule, if the aircraft can safely land but the remaining power of the battery is lower than a preset threshold, an alarm is triggered to prompt a user or force the aircraft to automatically land, and if the aircraft cannot safely land, a higher-level safeguard measure is triggered.
In another embodiment, the controller 20 is configured to make flight decisions based on flight status information of the aircraft, flight mission, power supply remaining capacity, and preset decision rules. For example, in a specific example, whether the power supply remaining capacity can complete the flight mission is determined according to the flight altitude, the flight speed, the flight mission, the power supply remaining capacity and a preset decision rule of the aircraft, if the power supply remaining capacity can complete the flight mission, no alarm is given, and if the power supply remaining capacity cannot complete, an alarm is triggered to prompt a user or force the aircraft to automatically land or return.
In another embodiment, the controller 20 is configured to periodically obtain the power supply remaining capacity, and obtain flight decision data based on the power supply remaining capacity. For example, in one embodiment, the controller 20 periodically obtains the remaining power of the power source, and sends an alarm to prompt the user or make the aircraft automatically perform a predetermined safeguard, such as automatic return or landing, when the remaining power of the power source reaches a predetermined alarm threshold.
In another embodiment, the controller 20 is configured to periodically obtain the power supply remaining capacity, determine a corresponding alert level according to the power supply remaining capacity, and make flight decisions according to the determined alert level. For example, in one embodiment, the lower the power supply remaining capacity, the higher the warning level, and when the warning level determined from the power supply remaining capacity is the highest level, the aircraft is forced to automatically land or return.
In this embodiment, the method further includes: the first charging interface 93 is used for connecting the first power supply 91, the fourth power supply interface 95 is used for connecting the aircraft power module power supply 80, the first charging detection circuit 71 is used for detecting the first power supply 91, the fourth switch is connected between the fourth power supply interface 95 and the first charging interface 93, the second charging interface 92 is used for connecting the third power supply 90, the second charging detection circuit 72 is used for detecting the third power supply 90, the fifth power supply interface 94 is used for connecting the power module power supply 80, the fifth switch is connected between the fifth power supply interface 94 and the second charging interface 92, and the charging controller 70 is connected with the fourth switch, the fifth switch, the first charging detection circuit 71 and the second charging detection circuit 72.
And a charge controller 70 for outputting switching control signals to the fourth switch and the fifth switch. In one implementation, the charge controller 70 may include a charge control chip configured to output corresponding switch control signals to the fourth switch and the fifth switch in response to whether the amount of power of the first power source 91 and/or the third power source 90 meets a preset condition. It is to be understood that the charge controller 70 in the present application may also be a switch driving circuit composed of discrete components. It is understood that the charging controller 70 may be a common controller as shown in the figure, or in other embodiments, may be two independent controllers, one of which is connected to the first charging detection circuit and the fourth switch, and the other of which is connected to the second charging detection circuit and the fifth switch.
In one implementation, the charging controller 70 is connected to the power selector 50, obtains a signal indicating which of the first power supply interface 30 to the third power supply interface 34 is a current power supply interface, and is configured to output a corresponding switch control signal when one of the first power supply interface 30 and the third power supply interface 34 is the current power supply interface and the power supply connected to the current power supply interface does not meet a preset condition, so that the aircraft power module power supply 80 charges the power supply connected to the current power supply interface.
In this embodiment, the control circuit is configured with a second power supply interface for connecting the first battery, a third power supply interface for connecting the second battery, and a second power supply interface for connecting the intelligent computing device, where the second power supply interface may be a USB interface having a power source end and a data transmission end, the data transmission end is connected to the controller, a second switch is disposed between the power source end and the controller, and the power source selector may control whether to select the second power supply interface to operate by outputting a switch control signal. Through the configuration, double-battery power supply backup power supply can be provided for the controller, the intelligent computing equipment is selected to provide the backup power supply for the controller under the abnormal condition that the first battery and the second battery cannot normally supply power, the flight control data obtained by the controller can be transmitted to the intelligent computing equipment through the data transmission end of the USB interface, and backup of the flight control data is achieved. On the other hand, whether the second power supply interface supplies power or not is managed through the power supply selector, so that the interference of the normal power supply of other power supplies when the second power supply is connected to the control circuit can be avoided.
The present application also provides an aircraft, which may be, for example, an electric manned aircraft, including a control circuit as described above.
The aspects of the present application have been described in detail hereinabove with reference to the accompanying drawings. In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments. Those skilled in the art should also appreciate that the acts and modules referred to in the specification are not necessarily required in the present application. In addition, it can be understood that the steps in the method of the embodiment of the present application may be sequentially adjusted, combined, and deleted according to actual needs, and the modules in the device of the embodiment of the present application may be combined, divided, and deleted according to actual needs.
Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the spirit of scope of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
Claims (18)
1. A control circuit of a flight control system, comprising:
a controller;
the first power supply interface is used for connecting a first power supply;
the second power supply interface is used for connecting a second power supply and comprises a power supply end and a data transmission end connected with the controller;
the switch circuit comprises a first switch connected between the first power supply interface and the controller and a second switch connected between a power supply end of the second power supply interface and the controller;
and the power supply selector is configured to select the current power supply interface according to a preset rule and output a corresponding switch control signal to the switch circuit.
2. The control circuit of claim 1, wherein:
the power supply selector is configured to output a switch control signal for closing the second switch and opening the first switch when the second power supply interface is selected as the current power supply interface according to a preset priority order of the power supply interfaces and detection signals of the first power supply and the second power supply;
the controller is configured to respond to a signal that the second power supply interface is connected with the second power supply, and send flight control data to a data transmission terminal of the second power supply interface according to a preset data transmission instruction or periodically.
3. The control circuit of claim 1 or 2, wherein the second power supply interface is a USB interface.
4. The control circuit of claim 1 or 2,
the switch circuit further comprises a third power supply interface used for being connected with a third power supply, and a third switch connected between the third power supply interface and the controller;
the first power supply and the third power supply are battery power supplies, and the second power supply interface is a data transmission interface adaptive to the intelligent computing equipment.
5. The control circuit of claim 4, wherein said selecting a current power interface according to a predetermined rule comprises:
and selecting one of the first power supply interface and the third power supply interface as a current power supply interface according to a preset priority order of the power supply interfaces and detection signals of the first power supply to the third power supply.
6. The control circuit of claim 5, wherein the selecting one of the first to third power interfaces as a current power interface according to a predetermined priority order of the power interfaces and the respective detection signals of the first to third power sources comprises:
according to the priority sequence of the three power supply interfaces from the first power supply interface to the third power supply interface, executing the following steps: judging whether a power supply corresponding to the power supply interface at the current level is connected with the control circuit and meets a preset power supply condition, if the power supply corresponding to the power supply interface at the current level meets the preset power supply condition, determining the power supply interface at the current level as the current power supply interface, if the power supply corresponding to the power supply interface at the current level is not connected with the control circuit or does not meet the preset power supply condition, taking the power supply interface at the next priority order as the power supply interface at the current level, and returning to the step of judging whether the power supply corresponding to the power supply interface at the current level is connected with the control circuit and meets the; alternatively, the first and second electrodes may be,
and obtaining respective detection signals of the first power supply to the third power supply, judging whether the first power supply interface to the third power supply interface are respectively connected with the power supply and whether the connected power supply meets a preset power supply condition according to the obtained detection signals, and determining the current power supply interface according to the preset priority sequence of the three power supply interfaces of the first power supply interface to the third power supply interface under the condition that at least two connected power supplies meet the preset power supply condition.
7. The control circuit of claim 5, further comprising:
a first detection circuit connected between the first power supply interface and the power supply selector, a second detection circuit connected between a power supply terminal of the second power supply interface and the power supply selector, and a third detection circuit connected between the third power supply interface and the power supply selector;
at least one of the first detection circuit to the third detection circuit is connected with the power supply selector through at least three signal lines, and the at least three signal lines comprise a power supply voltage detection signal line, an overvoltage detection signal line and an undervoltage detection signal line.
8. The control circuit of claim 5,
the priority of the first power supply interface and the priority of the third power supply interface are higher than the priority of the second power supply interface;
the priority of the first power supply interface is higher than the priority of the third power supply interface.
9. The control circuit of claim 5, wherein:
the power supply selector is further configured to determine a next power supply interface according to a preset rule and perform power supply interface switching through the switching circuit when the current power supply interface does not meet a preset power supply condition; wherein, carrying out power supply interface switching through the switch circuit includes: and after the next power supply interface is firstly connected with the controller, the current power supply interface is disconnected with the controller.
10. The control circuit of claim 9, wherein:
the control circuit further comprises a first capacitor connected between the first power supply interface and ground, a second capacitor connected between a power supply end of the second power supply interface and ground, and a third capacitor connected between the third power supply interface and ground.
11. The control circuit of claim 4, wherein:
the power supply selector is further configured to obtain power supply management data according to detection signals of the first detection circuit to the third detection circuit, and send the power supply management data to the controller;
the controller is further configured to make flight decisions based at least on the power management data and preset decision rules, including:
the method comprises the steps of periodically obtaining the residual power of a power supply, and sending an alarm to prompt a user or enabling an aircraft to automatically execute preset safeguard measures when the residual power of the power supply reaches a preset alarm threshold value; or
Periodically obtaining the residual power of a power supply, determining a corresponding alarm level according to the residual power of the power supply, and making a flight decision according to the determined alarm level; or
Performing flight decision according to flight state information of the aircraft, the power supply residual capacity and a preset decision rule; or
And performing flight decision according to the flight state information, the flight mission, the power supply residual capacity and a preset decision rule of the aircraft.
12. The control circuit of claim 1, further comprising:
the first charging interface is used for connecting the first power supply;
a fourth power supply interface for connecting an aircraft power module power supply;
a first charge detection circuit for detecting the first power supply;
the fourth switch is connected between the fourth power supply interface and the first charging interface; and
and the charging controller is connected with the fourth switch and the first charging detection circuit.
13. The power control circuit of claim 12, wherein:
the charge controller is configured to output a switch control signal to close the fourth switch in response to a signal that the amount of power of the first power supply does not meet a preset condition, and to output a switch control signal to open the fourth switch in response to a signal that the amount of power of the first power supply meets the preset condition.
14. The power control circuit of claim 12, wherein:
the charge controller is configured to output a switch control signal to close the fourth switch in response to a signal that the voltage of the first power source is less than a first preset threshold, and to output a switch control signal to open the fourth switch in response to a signal that the voltage of the first power source is greater than a second preset threshold.
15. The control circuit of claim 12, wherein:
the charging controller is configured to output switch control information for switching the fourth switch on and off in response to a signal that the first power supply is supplying power to the controller and that the power of the first power supply does not meet a preset condition.
16. The control circuit of claim 4, further comprising:
the first charging interface is used for connecting the first power supply;
a fourth power supply interface for connecting an aircraft power module power supply;
a first charge detection circuit for detecting the first power supply;
the fourth switch is connected between the second power supply interface and the first charging interface;
the second charging interface is used for connecting the third power supply;
a second charge detection circuit for detecting the third power supply;
the fifth power supply interface is used for connecting the power module power supply;
the fifth switch is connected between the fifth power supply interface and the second charging interface; and
and the charging controller is connected with the fourth switch, the fifth switch, the first charging detection circuit and the second charging detection circuit.
17. The control circuit of claim 16,
the charging controller is connected with the power supply selector and is used for acquiring a signal of which one of the first power supply interface, the second power supply interface and the third power supply interface is the current power supply interface;
the charging controller is configured to output a corresponding switch control signal when one of the first power supply interface and the third power supply interface is a current power supply interface and a power supply connected with the current power supply interface does not meet a preset condition, so that the aircraft power module power supply charges the power supply connected with the current power supply interface.
18. An aircraft having a control circuit as claimed in any one of claims 1 to 17.
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| CN202110196330.2A CN112769224B (en) | 2021-02-22 | 2021-02-22 | Aircraft and control circuit of flight control system thereof |
| PCT/CN2021/118304 WO2022174580A1 (en) | 2021-02-22 | 2021-09-14 | Aircraft, and control circuit of flight control system thereof |
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| CN202110196330.2A CN112769224B (en) | 2021-02-22 | 2021-02-22 | Aircraft and control circuit of flight control system thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113489074A (en) * | 2021-07-29 | 2021-10-08 | 广东汇天航空航天科技有限公司 | Aircraft and power supply control device for aircraft |
| CN114336935A (en) * | 2021-12-27 | 2022-04-12 | 宁波南方航空油料辅机厂 | Energy supply system for underground water level monitoring |
| WO2022174580A1 (en) * | 2021-02-22 | 2022-08-25 | 广东汇天航空航天科技有限公司 | Aircraft, and control circuit of flight control system thereof |
| CN115440090A (en) * | 2022-08-31 | 2022-12-06 | 亿航智能设备（广州）有限公司 | Fault protection method and equipment for aircraft and computer readable storage medium |
| CN116466637A (en) * | 2023-04-19 | 2023-07-21 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103332296A (en) * | 2013-07-17 | 2013-10-02 | 国家电网公司 | Power supply for unmanned aerial vehicle |
| CN206224184U (en) * | 2016-11-18 | 2017-06-06 | 广州极飞科技有限公司 | Intelligent battery communication interface compatible circuit, intelligent battery and unmanned vehicle |
| WO2017143583A1 (en) * | 2016-02-26 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and power supply system, method and device thereof |
| CN107600390A (en) * | 2017-06-16 | 2018-01-19 | 道通欧洲股份有限公司 | Unmanned plane and its power-supply management system and method for managing power supply |
| CN208369273U (en) * | 2018-06-29 | 2019-01-11 | 深圳市大疆创新科技有限公司 | Charger and unmanned vehicle system |
| CN210225056U (en) * | 2019-08-29 | 2020-03-31 | 深圳市大疆创新科技有限公司 | External expansion device, remote control device of unmanned aerial vehicle and external member |
| CN210807090U (en) * | 2019-11-18 | 2020-06-19 | 东莞市欧派奇电子科技有限公司 | Power adapter with electric energy conversion and data transmission functions |
| US20200338989A1 (en) * | 2018-01-19 | 2020-10-29 | SZ DJI Technology Co., Ltd. | Battery control method, battery control system, unmanned aerial vehicle, and battery |
| CN212137370U (en) * | 2019-12-28 | 2020-12-11 | 西安因诺航空科技有限公司 | Dual-power redundancy flight control system |
-
2021
- 2021-02-22 CN CN202110196330.2A patent/CN112769224B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103332296A (en) * | 2013-07-17 | 2013-10-02 | 国家电网公司 | Power supply for unmanned aerial vehicle |
| WO2017143583A1 (en) * | 2016-02-26 | 2017-08-31 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and power supply system, method and device thereof |
| CN206224184U (en) * | 2016-11-18 | 2017-06-06 | 广州极飞科技有限公司 | Intelligent battery communication interface compatible circuit, intelligent battery and unmanned vehicle |
| CN107600390A (en) * | 2017-06-16 | 2018-01-19 | 道通欧洲股份有限公司 | Unmanned plane and its power-supply management system and method for managing power supply |
| US20200338989A1 (en) * | 2018-01-19 | 2020-10-29 | SZ DJI Technology Co., Ltd. | Battery control method, battery control system, unmanned aerial vehicle, and battery |
| CN208369273U (en) * | 2018-06-29 | 2019-01-11 | 深圳市大疆创新科技有限公司 | Charger and unmanned vehicle system |
| CN210225056U (en) * | 2019-08-29 | 2020-03-31 | 深圳市大疆创新科技有限公司 | External expansion device, remote control device of unmanned aerial vehicle and external member |
| CN210807090U (en) * | 2019-11-18 | 2020-06-19 | 东莞市欧派奇电子科技有限公司 | Power adapter with electric energy conversion and data transmission functions |
| CN212137370U (en) * | 2019-12-28 | 2020-12-11 | 西安因诺航空科技有限公司 | Dual-power redundancy flight control system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022174580A1 (en) * | 2021-02-22 | 2022-08-25 | 广东汇天航空航天科技有限公司 | Aircraft, and control circuit of flight control system thereof |
| CN113489074A (en) * | 2021-07-29 | 2021-10-08 | 广东汇天航空航天科技有限公司 | Aircraft and power supply control device for aircraft |
| CN114336935A (en) * | 2021-12-27 | 2022-04-12 | 宁波南方航空油料辅机厂 | Energy supply system for underground water level monitoring |
| CN115440090A (en) * | 2022-08-31 | 2022-12-06 | 亿航智能设备（广州）有限公司 | Fault protection method and equipment for aircraft and computer readable storage medium |
| CN115440090B (en) * | 2022-08-31 | 2024-05-28 | 亿航智能设备（广州）有限公司 | Method and equipment for protecting faults of aircraft and computer readable storage medium |
| CN116466637A (en) * | 2023-04-19 | 2023-07-21 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
| CN116466637B (en) * | 2023-04-19 | 2024-01-12 | 东方空间技术(山东)有限公司 | Power distribution control system and method of aircraft and flight control computer |
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