CN113489074A - Aircraft and power supply control device for aircraft - Google Patents
Aircraft and power supply control device for aircraft Download PDFInfo
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- CN113489074A CN113489074A CN202110867765.5A CN202110867765A CN113489074A CN 113489074 A CN113489074 A CN 113489074A CN 202110867765 A CN202110867765 A CN 202110867765A CN 113489074 A CN113489074 A CN 113489074A
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- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 claims description 7
- 230000004044 response Effects 0.000 claims description 5
- 230000002035 prolonged effect Effects 0.000 abstract description 5
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
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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
- H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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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
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
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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
- H02J9/002—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which a reserve is maintained in an energy source by disconnecting non-critical loads, e.g. maintaining a reserve of charge in a vehicle battery for starting an engine
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D2221/00—Electric power distribution systems onboard aircraft
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Abstract
The application relates to an aircraft and a power supply control device. The power supply control device comprises a circuit board, a first power supply control circuit and a second power supply control circuit, wherein the first power supply control circuit and the second power supply control circuit are arranged on the circuit board; wherein: the first power supply control circuit comprises a first power supply input end, a first power supply output end, a first switch and a first enabling signal input end, wherein the first power supply output end is used for connecting first-level electric equipment; the second power supply control circuit comprises a second power supply input end, a second power supply output end used for being connected with second-level electric equipment, a second switch electrically connected between the second power supply input end and the second power supply output end, and a second enabling signal input end used for controlling the second switch. According to the embodiment of the application, the different power supply control circuits are used for respectively controlling the electric equipment in the aircraft at different levels, so that the service life of the power supply can be prolonged, and the reliability of system operation is further ensured.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to an aircraft and a power supply control device for the aircraft.
Background
Because the traditional electric aircraft has no manned requirement, the quantity of avionic equipment is small, the function is single, and the power consumption is relatively low. When the aircraft is started, all the avionics equipment can be powered on simultaneously to start working. When the aircraft has manned demand, the aircraft is added with a plurality of devices with different functions, such as lamps, display screens, cabin computers, radio stations and the like. However, when these devices are powered simultaneously, the systems of the aircraft are in the maximum power consumption state, so that the service time of a low-voltage battery in the power supply is shortened, and the power utilization is in short supply. In addition, some devices do not need to operate or may interfere with normal operation under certain conditions, such as lamps that may not operate in relatively bright environments, which also requires that the devices be shut down and rendered inoperative under certain conditions.
Disclosure of Invention
In order to solve or partially solve the problems in the related art, the application provides an aircraft and a power supply control device for the aircraft, which can prolong the service time of a power supply.
The present application provides in a first aspect a power supply control device for an aircraft, comprising:
the power supply control circuit comprises at least one circuit board, a first power supply control circuit and a second power supply control circuit, wherein the first power supply control circuit and the second power supply control circuit are arranged on the at least one circuit board; wherein:
the first power supply control circuit comprises a first power supply input end used for being connected with a power supply, at least one first power supply output end used for being connected with at least one first-level electric device of the aircraft, a first switch electrically connected between the first power supply input end and the at least one first power supply output end, and a first enabling signal input end used for controlling the first switch;
the second power supply control circuit comprises a second power supply input end used for being connected with a power supply, at least one second power supply output end used for being connected with at least one second-level electric device of the aircraft, a second switch electrically connected between the second power supply input end and the at least one second power supply output end, and a second enabling signal input end used for controlling the second switch.
In some embodiments, the power supply control device further comprises a housing, a first power input interface, at least one first power output interface and a first enable signal input interface, which are arranged in the housing, and the first power supply control circuit is arranged in the housing;
the first power input interface is electrically connected with the first power input end, the at least one first power output interface is electrically connected with the at least one first power output end, and the first enable signal input interface is electrically connected with the first enable signal input end.
In some embodiments, the power supply control device further comprises a second power input interface, at least one second power output interface and a second enable signal input interface which are arranged in the housing, and the second power supply control circuit is arranged in the housing; the second power input interface is electrically connected with the second power input end, the at least one second power output interface is electrically connected with the at least one second power output end, and the second enable signal input interface is electrically connected with the second enable signal input end.
In some embodiments, at least some of the first power input interface, the at least one first power output interface, and the first enable signal input interface are aerial interfaces.
In some embodiments, the at least one circuit board includes a first circuit board and a second circuit board, the first power control circuit is disposed on the first circuit board, and the second power control circuit is disposed on the second circuit board; the first circuit board and the second circuit board are arranged in parallel and are arranged in an overlapping mode at intervals in the thickness direction.
In some embodiments, the first level powered device has a higher security level than the second level powered device.
A second aspect of the present application provides an aircraft having a power supply control device as described in any of the above embodiments.
In some embodiments, the aircraft further comprises an enable signal generation module having a first enable signal output electrically connected to the first enable signal input of the power control device and a second enable signal output electrically connected to the second enable signal input of the power control device; wherein:
the enable signal generation module is configured to cause the first enable signal output terminal and/or the second enable signal output terminal to output a corresponding enable signal in response to a user input.
In one embodiment, the enabling signal generating module comprises a central control touch screen or a switch panel of the aircraft.
In some embodiments, the aircraft is an electric manned aircraft.
The technical scheme provided by the application can comprise the following beneficial effects:
the power supply control device for the aircraft provided by the embodiment of the application controls the electric equipment at different levels in the aircraft through different power supply control circuits respectively, can manage the electric equipment in a grading manner, and selects to turn on or turn off part of the electric equipment according to specific conditions, so that the service life of a power supply is prolonged, and the reliability of system operation is ensured.
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 block schematic diagram of a power control apparatus for an aircraft according to an embodiment of the present disclosure;
fig. 2 is a schematic side view of a power supply control device for an aircraft according to an embodiment of the present application;
FIG. 3 is another schematic structural diagram of a power supply control device for an aircraft according to an embodiment of the present application;
fig. 4 is a circuit schematic diagram of a first power supply control circuit according to an embodiment of the present application.
Reference numerals: the power supply control device 10, the circuit board 110, the first power supply control circuit 120, the first power input interface 121, the first power output interface 122, the first enable signal input interface 123, the second power supply control circuit 130, the second power input interface 131, the second power output interface 132, the second enable signal input interface 133, the first-level electric equipment 140, the second-level electric equipment 150, the shell 160, and the first switch PMOS; a first resistor R1; a power supply 20; the signal generation module 30 is enabled.
Detailed Description
Embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While embodiments of the present application are illustrated in the accompanying 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, "a plurality" means two or more unless specifically limited otherwise.
In the related art, when the traditional unmanned electric aircraft is started, all avionics devices are started to work simultaneously, so that the service time of a battery is shortened, and the power utilization shortage is caused.
In view of the above problems, the embodiment of the application provides an aircraft and a power supply control device for the aircraft, and the service life of a power supply can be prolonged by carrying out hierarchical management on electric equipment of the aircraft.
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 schematic diagram of a power supply control device of an aircraft according to an embodiment of the present application.
Referring to fig. 1, a power supply control device 10 for an aircraft of an embodiment of the present embodiment includes: at least one circuit board 110, and a first power control circuit 120 and a second power control circuit 130 provided to the at least one circuit board 110. Wherein:
the first power supply control circuit 120 comprises a first power supply input for connecting the power supply 20, at least one first power supply output for connecting at least one first level consumer 140 of the aircraft, a first switch electrically connected between the first power supply input and the at least one first power supply output, and a first enable signal input for controlling the first switch. The second power supply control circuit 130 comprises a second power supply input for connecting the power supply 20, at least one second power supply output for connecting at least one second level consumer 150 of the aircraft, a second switch electrically connected between the second power supply input and the at least one second power supply output, and a second enable signal input for controlling the second switch.
Further, in one embodiment, the first power control circuit 120 and the second power control circuit 130 are respectively connected to the power source 20. In one embodiment, the power source 20 may be a low voltage battery, and the first and second level consumers are low voltage consumers that may have a supply voltage of, for example, 16 volts or less. The first power input terminal is electrically connected to the power supply 20, and when the first switch is turned off, the power supply 20 supplies power to the first class consumer 150 through the first power supply control circuit 120. Furthermore, the two ends of the first switch are respectively and correspondingly electrically connected with the first power input end and the first power output end, when the first-level electric equipment 140 needs to be powered on, the first enable signal is input at the first enable signal input end, so that the first switch is closed in response to the first enable signal, the first power input end and the first power output end are switched on, and the power supply supplies power to the first-level electric equipment 140. Similarly, the operation principle of the second power supply control circuit 130 may be the same as that of the first power supply control circuit 120, and is not described herein again. It is understood that in other embodiments, the first power control circuit 120 and the second power control circuit 130 may be connected to different power sources, respectively.
In summary, the power supply control device 10 for an aircraft provided in this embodiment controls whether the first-level power-consuming equipment 140 is connected to a power supply to obtain power for operation through the first power supply control circuit 120, and controls whether the second power supply control circuit 130 is connected to the power supply to obtain power for operation through the second power supply control circuit 130, that is, different power supply control circuits respectively control power-consuming equipment at different levels in the aircraft, so that the power-consuming equipment can be managed in a hierarchical manner, and a part of the power-consuming equipment is selectively turned on or off according to specific conditions, thereby prolonging the service life of the power supply and ensuring the reliability of system operation.
It is understood that an aircraft comprises a plurality of electrical devices with different functions, such as flight controls, display screens, various types of lights for lighting or decoration, cabin computers, radio stations, etc. In one embodiment, the powered devices may be classified according to a security level. It can be understood that the safety level is set according to the criticality of the electric equipment, for example, the electric equipment (such as a flight controller, a sensor for flight control, etc.) directly influencing flight safety corresponds to one safety level; in addition, the electrical consumers (e.g., display screens, indicator lights, etc.) that do not affect flight safety correspond to another safety class. In one embodiment, the security level of the first level powered device 140 is different (e.g., higher) than the security level of the second level powered device 150. It will be appreciated that in further embodiments, the division into two levels may not be limited, for example, the low voltage electrical equipment of the aircraft may also be divided into 3 or more levels. The power supply of the electric equipment with different safety levels is controlled by adopting different power supply control circuits, so that the electric equipment with different safety levels can be flexibly supplied, and the service life of the power supply is prolonged; on the other hand, the same power supply control circuit is adopted to uniformly control the power supply of the electric equipment with the same safety level, so that the complexity of the control of the electric equipment can be reduced. In other embodiments, the electric devices may be classified based on other factors, that is, not only the classification according to the safety class, but also the classification according to the supply voltage of the electric devices with different or greatly different supply voltages, or the classification according to whether the electric devices are simultaneously operated, may be performed.
Further, referring to fig. 1 to 3, in an embodiment, the power supply control device includes a first circuit board and a second circuit board, the first power supply control circuit 120 is disposed on the first circuit board, and the second power supply control circuit 130 is disposed on the second circuit board; the power supply control device 10 further includes a housing 160, a first power input interface 121 disposed on the housing 160, at least one first power output interface 122, and a first enable signal input interface 123, wherein the first circuit board and the first power supply control circuit 120 are disposed in the housing 160; the first power input interface 121 is electrically connected to the first power input terminal, the at least one first power output interface 122 is electrically connected to the at least one first power output terminal, and the first enable signal input interface 123 is electrically connected to the first enable signal input terminal. The number of the first power output interfaces 122 may be plural to connect to a plurality of first-level consumers 140.
The first power control circuit 120 may have a single first power output terminal to which the plurality of first power output interfaces 122 are connected, so that the same output voltage can be supplied to the plurality of first-level electric devices 140; alternatively, the first power supply control circuit 120 may have at least two first power output terminals for outputting different voltages, so that the plurality of first power output interfaces 122 may be respectively connected to the corresponding first power output terminals according to the input voltage of each first-level electric device 140.
Each first power output interface 122 may be electrically connected to the corresponding first level powered device 140 through a connection line. In an embodiment, the number of the first power output interfaces 122 may be greater than the number of the first level consumers 140, so as to reserve the first power output interfaces 122 as a spare. In an embodiment, the number of the first enabling signal input interface 123 may be plural, that is, enough first enabling signal input interface 123 may be provided to connect to a plurality of enabling signal generating modules according to actual equipment conditions on the aircraft. In an embodiment, at least a portion of or all of the first power input interface 121, the at least one first power output interface 122, and the first enable signal input interface 123 are aerial interfaces. Accordingly, the connection may be made using a connection wire with an aviation plug.
In an embodiment, the power supply control device 10 further includes a second power input interface 131, at least one second power output interface 132 and a second enable signal input interface 133 disposed in the housing 160, and the second circuit board and the second power supply control circuit 130 are disposed in the housing 160. Different power supply control circuits for controlling different grades of electric equipment are respectively arranged on different circuit boards, so that modular configuration can be realized, convenience is brought to expansion, and cost reduction is facilitated. It is understood that in another embodiment, the first power control circuit 120 and the second power control circuit 130 may be disposed on the same circuit board.
The second power input interface 131 is electrically connected to the second power input terminal, the at least one second power output interface 132 is electrically connected to the at least one second power output terminal, and the second enable signal input interface 133 is electrically connected to the second enable signal input terminal. That is, the second power supply control circuit 130 and the first power supply control circuit 120 are disposed in the same housing 160, so that the installation space can be saved. Similarly, the specific configurations of the second power input interface 131, the second power output interface 132 and the second enable signal input interface 133 are similar to the first power input interface 121, the first power output interface 122 and the first enable signal input interface 123, and are not described herein again. In one embodiment, at least some of the second power input interface 131, the at least one second power output interface 132, and the second enable signal input interface 133 are air-plug interfaces. In one embodiment, the number of the second power output interfaces 132 may be the same as or different from the first power output interfaces 122; the number of the second enable signal input interfaces 133 may be the same as or different from the first enable signal input interfaces 123, i.e., may be set according to the actual size of the housing 160 or the number of the electric devices of the corresponding level. In this embodiment, the first power supply control circuit 120 and the second power supply control circuit 130 are integrated in the same case 160, so that the integration level of the power supply control device can be increased, the production cost can be reduced, and the assembly efficiency can be improved.
In an embodiment, as shown in fig. 2 and 3, the housing 160 may be a rectangular parallelepiped structure, and the first circuit board 110 and the second circuit board 110 are disposed in parallel and overlapped at intervals in the thickness direction in the housing 160. The input interface and the output interface may be arranged on the same side or different sides of the housing 160 according to actual conditions. The housing may be divided into a plurality of regions, and each of the first power output interfaces 122 and each of the second power output interfaces 132 may be respectively and collectively disposed in different regions, for example, as shown in fig. 2 and 3, each of the first power output interfaces 122 is disposed in an upper end region of a side surface of the housing, and each of the second power output interfaces 132 is disposed in a lower end region of the side surface of the housing. By means of the partition arrangement, the possibility of errors when the power output interfaces are connected with the corresponding electric equipment can be reduced.
Furthermore, the first circuit board can be arranged above the second circuit board in the shell, the first power input interface, the first power output interface and the first enabling signal input interface which are connected with the first power supply control circuit are arranged in the upper end area of the side face of the shell, and the second power input interface, the second power output interface and the second enabling signal input interface which are connected with the second power supply control circuit are arranged in the lower end area of the side face of the shell, so that the using amount of connecting wires can be saved, the cost is reduced, and the possibility of interconnection faults of the power supply control device can be reduced.
It is understood that in other embodiments, the number of the housings 160 of the power supply control device is not limited to one, and for example, the first circuit board and the second circuit board may be disposed in different housings.
It is understood that, in an embodiment, the power supply control device 10 for an aircraft of the present application may further include more power supply control circuits, such as a third power supply control circuit, a fourth power supply control circuit, and so on, to meet the power supply requirement of more levels or numbers of electrical devices of the aircraft. The power supply control circuits may be commonly disposed on the same circuit board or different circuit boards of the same housing 160, for example, a third power supply control circuit and a fourth power supply control circuit are separately disposed on the third circuit board and the fourth circuit board; or each power supply control circuit is respectively arranged on the corresponding circuit boards in different shells.
In some embodiments, the first switch and/or the second switch may be MOS transistors. Fig. 4 shows an embodiment of the first power control circuit 120, in which the PMOS transistor is the first switch. The first power supply control circuit 120 further includes a first resistor R1, a second resistor R2, and a third resistor R3, the first resistor R1 and the second resistor R2 are connected in series between the first power input terminal and the first enable signal input terminal, the third resistor R3 is connected in parallel with the second resistor R2, a connection point of the first resistor R1 and the second resistor R2 is connected to a gate of a PMOS transistor, a source of the PMOS transistor is connected to the first power input terminal, and a drain of the PMOS transistor is connected to the first power output terminal. The first power input terminal is for connection to a power supply 20; a first enable signal input for connection to an enable signal generation module 30 in the aircraft; the first power output end is used for connecting the first power output interface. In an embodiment, the second power control circuit 130 may be the same as the first power control circuit 120, and is not described herein again. It is understood that the second power supply control circuit 130 may also be different from the first power supply control circuit 120, and the first power supply control circuit 120 and the second power supply control circuit 130 may also be configured as other types of switching circuits.
In an embodiment, the enable signal generating module 30 has a first enable signal output terminal and a second enable signal output terminal, the first enable signal input terminal is electrically connected to the first enable signal input terminal of the power supply control device 10, and the second enable signal output terminal is electrically connected to the second enable signal input terminal of the power supply control device 10; wherein: the enable signal generation module 30 is configured to cause the first enable signal output terminal and/or the second enable signal output terminal to output the corresponding enable signal in response to a user input. In one embodiment, the enable signal generating module 30 comprises a central touch screen, or a switch panel, of the aircraft. The user can control the central control touch screen or the switch panel to input instructions so as to control the power-on work of the electric equipment at the corresponding level or stop the power supply of the electric equipment. It is understood that, in another embodiment, the enabling signal generating module 30 may be, for example, a flight controller, and may generate a corresponding enabling signal according to a user input or automatically generate a corresponding enabling signal according to a preset strategy to control the power supply control device.
The above embodiment describes the power supply control circuit provided in the embodiment of the present application, and accordingly, the present application further provides an embodiment of an aircraft, where the aircraft provided in this embodiment includes the power supply control device 10 described in any of the above embodiments.
In an embodiment, the aircraft may be an electric manned aircraft, which includes the power supply control device 10 and the enable signal generating module 30 as described in any of the above embodiments, where the enable signal generating module 30 includes a first enable signal output terminal and a second enable signal output terminal, the first enable signal input terminal is electrically connected to the first enable signal input terminal of the power supply control device 10, and the second enable signal output terminal is electrically connected to the second enable signal input terminal of the power supply control device 10. Wherein: the enable signal generation module 30 is configured to cause the first enable signal output terminal and/or the second enable signal output terminal to output the corresponding enable signal in response to a user input. In one embodiment, the enable signal generating module 30 comprises a central touch screen, or a switch panel, of the aircraft. In other embodiments, the enabling signal generating module 30 may be an intermediate signal transmitting module that receives a central control touch screen, a switch panel, or the like and can generate a control signal, so as to collect various control signals in a centralized manner, and transmit the control signals to a corresponding power supply control circuit as corresponding enabling signals.
When power supply control is performed on electric equipment in an aircraft, taking the working power consumption of the first-level electric equipment 140 as an example, when the first-level electric equipment 140 needs to be powered on to work, the enabling signal generating module 30 generates a first preset signal, and when the first-level electric equipment 140 does not need to work, the enabling signal generating module 30 generates a second preset signal; the first preset signal or the second preset signal may be transmitted to the first enable signal input terminal of the power supply control device 10 through the first enable signal output terminal. I.e. the first enable signal comprises a first preset signal and a second preset signal. When the first power supply control circuit is configured as the circuit shown in fig. 4, the first preset signal is a low level signal, and at this time, the voltage difference between the source and the gate of the PMOS transistor of the first power supply control circuit 120 makes the PMOS transistor (i.e., the first switch) conduct, and at this time, the first power supply control circuit 120 connects the power supply 20 to the first-level electric device 140. The second preset signal is a high level signal, which makes the PMOS transistor cut off, so as to disconnect the first power supply control circuit 120, and then disconnect the power supply 20 and the first-level electric equipment 140, so that the first-level electric equipment 140 stops using electricity, thereby saving the electric quantity of the power supply 20 and prolonging the service life of the power supply 20.
In other embodiments, the aircraft may be an unmanned aerial vehicle. The user can send a corresponding enabling signal to the power supply control device 10 of the aircraft through the remote control so as to perform power supply control on corresponding electric equipment on the aircraft.
The aircraft of this application embodiment, through carrying out the power consumption management in grades to the consumer, prolonged the power in the aircraft like the live time of low-voltage battery, and be convenient for select to open or close corresponding consumer according to actual conditions, improve user experience.
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 scope and spirit 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 (10)
1. An electrical power supply control device for an aircraft, comprising:
the power supply control circuit comprises at least one circuit board, a first power supply control circuit and a second power supply control circuit, wherein the first power supply control circuit and the second power supply control circuit are arranged on the at least one circuit board; wherein:
the first power supply control circuit comprises a first power supply input end used for being connected with a power supply, at least one first power supply output end used for being connected with at least one first-level electric device of the aircraft, a first switch electrically connected between the first power supply input end and the at least one first power supply output end, and a first enabling signal input end used for controlling the first switch;
the second power supply control circuit comprises a second power supply input end used for being connected with a power supply, at least one second power supply output end used for being connected with at least one second-level electric device of the aircraft, a second switch electrically connected between the second power supply input end and the at least one second power supply output end, and a second enabling signal input end used for controlling the second switch.
2. The power supply control device according to claim 1, characterized in that:
the power supply control circuit comprises a shell, a first power input interface, at least one first power output interface and a first enabling signal input interface, wherein the first power input interface, the at least one first power output interface and the first enabling signal input interface are arranged on the shell;
the first power input interface is electrically connected with the first power input end, the at least one first power output interface is electrically connected with the at least one first power output end, and the first enable signal input interface is electrically connected with the first enable signal input end.
3. The power supply control device according to claim 2, characterized in that:
the power supply control circuit also comprises a second power input interface, at least one second power output interface and a second enabling signal input interface which are arranged in the shell, and the second power supply control circuit is arranged in the shell;
the second power input interface is electrically connected with the second power input end, the at least one second power output interface is electrically connected with the at least one second power output end, and the second enable signal input interface is electrically connected with the second enable signal input end.
4. The power supply control device according to claim 2, characterized in that: at least part of the first power input interface, the at least one first power output interface and the first enabling signal input interface is an aerial plug interface.
5. The power supply control device according to any one of claims 1 to 4, characterized in that:
the at least one circuit board comprises a first circuit board and a second circuit board, the first power supply control circuit is arranged on the first circuit board, and the second power supply control circuit is arranged on the second circuit board;
the first circuit board and the second circuit board are arranged in parallel and are arranged in an overlapping mode at intervals in the thickness direction.
6. The aircraft according to any one of claims 1 to 4, characterized in that the safety level of said first level of electrical consumers is higher than the safety level of said second level of electrical consumers.
7. An aircraft, characterized by having a power supply control device as claimed in any one of claims 1 to 6.
8. The aircraft of claim 7, wherein:
the power supply control device also comprises an enabling signal generating module, wherein the enabling signal generating module is provided with a first enabling signal output end and a second enabling signal output end, the first enabling signal input end is electrically connected with the first enabling signal input end of the power supply control device, and the second enabling signal output end is electrically connected with the second enabling signal input end of the power supply control device; wherein:
the enable signal generation module is configured to cause the first enable signal output terminal and/or the second enable signal output terminal to output a corresponding enable signal in response to a user input.
9. The aircraft of claim 7, wherein: the enabling signal generating module comprises a central control touch screen or a switch panel of the aircraft.
10. The aircraft according to any one of claims 7 to 9, characterized in that: the aircraft is an electric manned aircraft.
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