CN214755586U - Aircraft and flight control system's power control circuit thereof - Google Patents
Aircraft and flight control system's power control circuit thereof Download PDFInfo
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- CN214755586U CN214755586U CN202120393088.3U CN202120393088U CN214755586U CN 214755586 U CN214755586 U CN 214755586U CN 202120393088 U CN202120393088 U CN 202120393088U CN 214755586 U CN214755586 U CN 214755586U
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Abstract
The application relates to aircraft and flight control system's power control circuit thereof, this power control circuit includes: the aircraft power module power supply control system comprises a first charging interface and a first power supply interface which are used for being connected with a first power supply of the flight control system, a second power supply interface which is used for being connected with an aircraft power module power supply, a controller which is connected with the first power supply interface, a first charging detection circuit which is used for detecting the first power supply, a first switch which is connected between the second power supply interface and the first charging interface, and a charging controller which is connected with the first switch and the first charging detection circuit. The embodiment of the application can guarantee the power supply electric quantity of the flight control system controller in the flight process of the aircraft, so that the flight safety is guaranteed.
Description
Technical Field
The application relates to the field of aircrafts, in particular to a power supply 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 to be sufficient in electric quantity.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems existing in the related technology, the power supply control circuit of the flight control system is provided, and the electric quantity of a power supply of a flight control system controller can be ensured.
This application provides a flight control system's power control circuit in one aspect, includes:
the first charging interface and the first power supply interface are used for connecting a first power supply of the flight control system;
the second power supply interface is used for connecting a power supply of the aircraft power module;
the controller is connected with the first power supply interface;
a first charge detection circuit for detecting the first power supply;
the first switch is connected between the second power supply interface and the first charging interface; and
and the charging controller is connected with the first switch and the first charging detection circuit.
In some embodiments, the charge controller is configured to output a switch control signal to close the first 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 first 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 first 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 first 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 switch control information that closes the first switch in response to a signal that the first power source is supplying power to the controller and that the amount of power of the first power source does not meet a preset condition.
In some embodiments, further comprising:
the second charging interface and the third power supply interface are used for connecting a second power supply of the flight control system;
a second charge detection circuit for detecting the second power supply;
the fourth power supply interface is used for connecting the power module power supply;
the second switch is connected between the fourth power supply interface and the second charging interface, and the charging controller is respectively connected with the second switch and the second charging detection circuit;
the switch circuit comprises a third switch connected between the first power supply interface and the controller and a fourth switch connected between the third power supply interface and the controller; and
a power supply selector for outputting a switching control signal to the switching 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 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 detecting that the 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.
In some embodiments, further comprising:
the fifth power supply interface is used for being connected with a third power supply of the flight control system and comprises a power supply end and a data transmission end connected with the controller;
the switch circuit further comprises a fifth switch connected between a power supply end of the fifth power supply interface and the controller.
In some embodiments, further comprising a first detection circuit connected between the first power interface and the power selector, a second detection circuit connected between the third power interface and the power selector, and a third detection circuit connected between a power supply terminal of the fifth power interface and the power selector;
at least one of the first detection circuit to the third detection circuit is connected with the power selector through at least three signal lines, and the at least three signal lines comprise a power voltage detection signal line, an overvoltage detection signal line and an undervoltage detection signal line.
In some embodiments, the power supply selector is configured to output, to the switching circuit, switching control signals of the third to fifth switches in response to detection signals of the first to third power supplies, the switching control signals corresponding to a current power supply interface selected in accordance with a preset power supply interface priority order and the detection signals of the first to third power supplies.
In some embodiments, the first and second power sources are battery power sources and the third power source is a smart computing device.
Another aspect of the present application provides an aircraft having the power control circuit of the flight control system as described above.
In the embodiment of the application, the battery power supply is connected with the charging interface, the power supply interface for connecting the aircraft power module power supply is connected with the charging interface through the switch, the charging detection circuit detects the voltage of the battery power supply, and controls the on-off state through the charging controller, so that the aircraft power module power supply charges or does not charge the battery power supply, the battery power supply charges through the battery power supply for the flight control system, the power supply electric quantity of the flight control system controller can be ensured in the flight process of the aircraft, and the 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.
Furthermore, the control circuit is provided with a fifth power supply interface used for being connected with a third power supply, the fifth power supply interface is provided with a power supply end and a data transmission end, the data transmission end is connected with the controller, a fifth switch is arranged between the power supply end and the controller, and the power supply selector can control whether the third power supply interface is selected to work or not by outputting a switch control signal. Through the configuration, the third 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 and the power supply of the second power supply are abnormal, the flight control data obtained by the controller can be transmitted outwards through the data transmission end of the fifth power supply interface, and backup of the flight control data is achieved. On the other hand, whether the fifth power supply interface supplies power or not is managed through the power supply selector, so that the situation that the normal power supply of other power supplies is interfered when the third power supply is connected to the control circuit can be avoided.
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 power control circuit of an flight control system according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a power control circuit of an aircraft flight control system according to another embodiment of the present application;
FIG. 3 is a schematic diagram of a power control circuit of an aircraft flight control system according to another embodiment of the present application;
fig. 4 is a schematic structural diagram of a resistance voltage division detection circuit according to an 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 shows a configuration diagram of a power supply control circuit 100 of an flight control system according to an embodiment of the present application.
Referring to fig. 1, a power control circuit 100 of the flight control system of the present embodiment includes: the aircraft power module control system comprises a controller 20, a first power supply 30 of the flight control system, a first power supply interface 31, a first charging interface 32, a second power supply interface 33, a charging controller 70, a first charging detection circuit 71 and an aircraft power module power supply 80.
The first power supply interface 31 is used for connecting a first power supply 30; the first power supply 30 may be a battery power supply having a capacity less than the aircraft power module power supply to power the weak current flight control system of the aircraft. The first power supply interface 31 is connected to the first power supply 30, and may be connected to the first power supply 30 directly or to a converted power supply obtained by boosting or stepping down the first power supply 30.
The first charging interface 32 is connected to the first power source 30, and the second power supply interface 33 is connected to the aircraft power module power source 80. The aircraft power module power supply 80 is used to charge the first power supply 30. 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 switch connected between the second power supply interface 33 and the first charging interface 32 is connected to the charging controller 70. In one implementation, the first switch may be implemented by a field effect transistor, but the application is not limited thereto.
The first charge detection circuit 71 is connected to the first power supply 30 and detects the first power supply 30. In one 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 supply 30 by detecting the voltage of the first power supply. 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 first switch. In one implementation, the charge controller 70 may include a charge control chip configured to output a corresponding switch control signal to the first switch in response to whether the amount of power of the first power supply 30 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.
The controller 20 is used for flight control.
In the embodiment of the application, the battery power supply of the flight control system is connected with the charging interface, the power supply interface for connecting the power supply of the aircraft power module is connected with the charging interface through the switch, the charging detection circuit detects the battery power supply, the charging controller controls the state of the switch, the aircraft power module power supply charges or does not charge the battery power supply, the battery power supply for the flight control system is charged, the power supply electric quantity of the flight control system controller can be ensured in the flight process of the aircraft, and therefore flight safety is ensured.
Fig. 2 shows a structure diagram of a power control circuit 200 of an flight control system according to another embodiment of the present application. Referring to fig. 2, the power control circuit 200 of the flight control system of the present embodiment includes: the flight control system comprises a controller 20, a first power supply 30 of the flight control system, a first power supply interface 31, a first charging interface 32, a second power supply interface 33, a charging controller 70, a first charging detection circuit 71, an aircraft power module power supply 80, a second power supply 90 of the flight control system, a third power supply interface 91, a second charging interface 92, a fourth power supply interface 93, a second charging detection circuit 72, a switch circuit 40 and a power supply selector 50.
The first power supply interface 31 is used for connecting the first power supply 30, and the third power supply interface 91 is used for connecting the second power supply 90; the first power source 30 and the second power source 90 may be battery power sources, the first power supply interface 31 may be connected to the first power source 30, and may be connected to the first power source 30 directly or after the first power source 30 is boosted or reduced in voltage, and the third power supply interface 91 may be connected to the second power source 90.
The first charging interface 32 is connected with the first power supply 30, the second charging interface 92 is connected with the second power supply 90, and the second power supply interface 33 and the fourth power supply interface 93 are connected with the aircraft power module power supply 80. The aircraft power module power supply 80 is used to charge the first power supply 30 and the second power supply 90. 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.
The first switch is connected between the second power supply interface 33 and the first charging interface 32, the second switch is connected between the fourth power supply interface 93 and the second charging interface 92, and both the first switch and the second switch are connected with the charging controller 70. 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 charge detection circuit 71 is connected to the first power supply 30 for detecting the first power supply 30, and the second charge detection circuit 72 is connected to the second power supply 90 for detecting the second power supply 90. It is to be understood that the first charge detection circuit 71 and the second charge detection circuit 72 may adopt the same or different circuits. The first charge detection circuit 71 and/or the second charge detection circuit 72 can be implemented in the manner described in the previous embodiments, and are not described in detail.
And a charge controller 70 for outputting a switching control signal to the first switch and the second switch. In one implementation, the charge controller 70 may include a charge control chip configured to output corresponding switch control signals to the first switch and the second switch in response to whether the amount of power of the first power supply 30 and/or the second power supply 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 charge controller 70 may be a common controller as shown in the figure, or in other embodiments, may be two separate controllers, one of which is connected to the first charge detection circuit and the first switch, and the other of which is connected to the second charge detection circuit and the second switch.
In one implementation, the charge controller 70 is configured to output a switch control signal that closes the first switch to cause the aircraft motion module power supply 80 to charge the first power supply 31 in response to the voltage of the first power supply 30 being less than a first preset threshold, and to output a switch control signal that opens the first switch to cause the aircraft motion module power supply 80 to stop charging the first power supply 31 in response to the voltage of the first power supply 30 being greater than a second preset threshold. The charge controller 70 may perform charge control of the second power supply 90 in a similar manner.
In an embodiment, taking charging control of the first power supply as an example, when the first charging detection circuit 71 detects that the voltage of the first power supply 30 is smaller than a first preset threshold, the charging controller 70 outputs a switch control signal to close the first switch, the aircraft power module power supply 80 charges the first power supply 30 through the second power supply interface 33 and the first charging interface 32, and when the first charging detection circuit 71 detects that the voltage of the first power supply 30 reaches a second preset threshold, the charging controller 70 outputs a switch control signal to open the first switch, and the aircraft power module power supply 80 stops charging the first power supply 30. For example, in one specific example, for a single-chip battery, when the charge detection circuit detects that the voltage of the battery is less than 3.8V, the battery starts to be charged, and when the voltage of the battery reaches 4.2V, the charging is stopped; as another example, the first power supply 30 is configured as a 3-cell battery, and the aircraft power module power supply begins charging the first power supply 30 when the first charge detection circuit 31 detects that the voltage of the first power supply 30 is less than 11.4V, and stops charging the first power supply 30 when the voltage of the first power supply 30 reaches 12.5V. The charging control of the second power supply can be similar to this, and is not described in detail.
The switch circuit 40 includes a third switch connected between the first power supply interface 31 and the controller 20, and a fourth switch connected between the third power supply interface 91 and the controller 20. In one implementation, the third switch and the fourth switch may be implemented by field effect transistors, but the application is not limited thereto.
The power supply selector 50 may include a power supply control chip configured to select one of the first power supply interface 31 and the third power supply interface 91 as a current power supply interface according to a preset rule, and output a corresponding switch control signal to the switch circuit 40. For example, the power supply selector 50 may select the current power supply interface according to a preset power supply interface priority order, and output a corresponding switch control signal to the switch circuit 40. For another example, the power supply selector 50 is configured to select the current power supply interface according to a preset power supply interface priority order, and the detection signal of the first power supply and the 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 supply interface 31 is higher than the priority of the third power supply interface 32. If the first power supply interface 31 has a battery power supply connection 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 close the third switch and open the fourth switch; if the first power supply interface 31 has no battery power supply connected or the battery power supply does not meet the preset power supply condition although the first power supply interface 31 is connected, and the third power supply interface 32 has battery power supply connected 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 close the fourth switch and open the third 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 and the third power supply interface is the current power supply interface, and is configured to output a corresponding switch control signal when detecting that 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 one embodiment, taking the first power supply 30 as the current power supply interface as an example, when the first power supply 30 supplies power to the flight control system and the first charging detection circuit 71 detects that the voltage of the first power supply 30 is less than 11.4V, the charging controller 70 outputs a switch control signal for closing the first switch, and the aircraft power module power supply 80 charges the first power supply 30 through the second power supply interface 33 and the first charging interface 32, and simultaneously the first power supply 30 discharges to supply power to the controller 20.
The controller 20 is used for flight control.
In the embodiment of the application, the battery power supply is connected with the charging interface, the power supply interface for connecting the aircraft power module power supply is connected with the charging interface through the switch, the charging detection circuit detects the voltage of the battery power supply, and controls the on-off state through the charging controller, so that the aircraft power module power supply charges or does not charge the battery power supply, the battery power supply charges through the battery power supply for the flight control system, the power supply electric quantity of the flight control system controller can be ensured in the flight process of the aircraft, and the flight safety is ensured. On the other hand, when the battery power supply of the current power supply interface 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 corresponding 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 is realized, and the power supply safety of the flight control system is ensured.
Fig. 3 shows a structure diagram of a power control circuit 300 of an flight control system according to another embodiment of the present application. Referring to fig. 3, the power control circuit 300 of the flight control system of the present embodiment includes: the flight control system comprises a controller 20, a first power supply 30 of the flight control system, a first power supply interface 31, a first charging interface 32, a second power supply interface 33, a charging controller 70, a first charging detection circuit 71, an aircraft power module power supply 80, a second power supply 90 of the flight control system, a third power supply interface 91, a second charging interface 92, a fourth power supply interface 93, a second charging detection circuit 72, a fifth power supply interface 35, a first detection circuit 60, a second detection circuit 62, a third detection circuit 64, a switch circuit 40 and a power supply selector 50.
The first power supply interface 31 is used for connecting the first power supply 30, and the third power supply interface 91 is used for connecting the second power supply 90; the first power source 30 and the second power source 90 may be battery power sources, the first power supply interface 31 may be connected to the first power source 30, and may be connected to the first power source 30 directly or after the first power source 30 is boosted or reduced in voltage, and the third power supply interface 91 may be connected to the second power source 90.
The first charging interface 32 is connected with the first power supply 30, the second charging interface 92 is connected with the second power supply 90, and the second power supply interface 33 and the fourth power supply interface 93 are connected with the aircraft power module power supply 80. The aircraft power module power supply 80 is used to charge the first power supply 30 and the second power supply 90. 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.
The first switch is connected between the second power supply interface 33 and the first charging interface 32, the second switch is connected between the fourth power supply interface 93 and the second charging interface 92, and both the first switch and the second switch are connected with the charging controller 70. 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 charge detection circuit 71 is connected to the first power supply 30 for detecting the first power supply 30, and the second charge detection circuit 72 is connected to the second power supply 90 for detecting the second power supply 90. It is to be understood that the first charge detection circuit 71 and the second charge detection circuit 72 may adopt the same or different circuits. The first charge detection circuit 71 and/or the second charge detection circuit 72 can be implemented in the manner described in the previous embodiments, and are not described in detail.
And a charge controller 70 for outputting a switching control signal to the first switch and the second switch. In one implementation, the charge controller 70 may include a charge control chip configured to output corresponding switch control signals to the first switch and the second switch in response to whether the amount of power of the first power supply 30 and/or the second power supply 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 charge controller 70 may be a common controller as shown in the figure, or in other embodiments, may be two separate controllers, one of which is connected to the first charge detection circuit and the first switch, and the other of which is connected to the second charge detection circuit and the second switch.
In one implementation, the charge controller 70 is configured to output a switch control signal that closes the first switch to cause the aircraft motion module power supply 80 to charge the first power supply 31 in response to the voltage of the first power supply 30 being less than a first preset threshold, and to output a switch control signal that opens the first switch to cause the aircraft motion module power supply 80 to stop charging the first power supply 31 in response to the voltage of the first power supply 30 being greater than a second preset threshold. The charge controller 70 may perform charge control of the second power supply 90 in a similar manner.
The fifth power supply interface 35 is used for connecting a third power supply of the flight control system, and the fifth power supply interface 35 includes a power supply end 36 and a data transmission end 38 connected with the controller 20. In this embodiment of the application, the third power source of the flight control system may be an intelligent computing device, for example, an operating device (e.g., a tablet personal computer console) and an intelligent mobile terminal (e.g., a smart phone) that are arranged in the aircraft, and the fifth power supply interface 35 is a data transmission interface adapted to the intelligent computing device, and may be, for example, a Universal Serial Bus (english: USB) interface, a Lightning interface, and the like, 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 switch circuit 40 includes a third switch connected between the first power supply interface 31 and the controller 20, a fourth switch connected between the third power supply interface 91 and the controller 20, and a fifth switch connected between the power source terminal 36 of the fifth power supply interface 35 and the controller 20. In one implementation, the third to fifth 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 31 and the power supply selector 50, the second detection circuit 62 is connected between the third power supply interface and the power supply selector 50, and the third detection circuit 64 is connected between the power supply terminal 36 of the fifth power supply interface 35 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.
As shown in fig. 4, in a specific implementation, the resistance voltage division detection 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 detection signal line T1, an overvoltage detection signal line T2, and an undervoltage detection signal line T3, respectively, so as to output a power supply voltage detection signal, an overvoltage detection signal, and an undervoltage detection 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 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 31, the third power supply interface 91, and the fifth power supply interface 35 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 priority of the first power supply interface 31 and the third power supply interface 91 is higher than the priority of the fifth power supply interface 35, and the priority of the first power supply interface 31 is higher than the priority of the third power supply interface 91.
In one implementation, selecting one of the first power supply interface 31, the third power supply interface 91, and the fifth power supply interface 35 as the current power supply interface according to a preset power supply interface priority order and a detection signal from the first power supply to the third power supply includes:
in order of priority of the first power supply interface 31, the third power supply interface 91, and the fifth power supply interface 35, 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 31, the third power supply interface 91, and the fifth power supply interface 35 as a current power supply interface according to a preset priority order of the first power supply interface 31, the third power supply interface 91, and the fifth power supply interface 35 and a detection signal of the third power supply from the first power supply to the flight control system includes:
the respective detection signals of the first power supply to the third power supply are obtained, whether the first power supply interface 31, the third power supply interface 91 and the fifth power supply interface 35 are connected with the power supply and whether the connected power supply meets the preset power supply condition or not are judged according to the obtained detection signals, and under the condition that at least two connected power supplies meet the preset power supply condition, the current power supply interface is determined according to the preset priority sequence of the first power supply interface 31, the third power supply interface 91 and the fifth power supply interface 35. For example, in a specific example, only the first power supply interface 31 of the three power supply interfaces is connected with a power supply, neither the third power supply interface 91 nor the fifth power supply interface 35 is connected with a power supply, and at this time, both the third power supply interface 91 and the fifth power supply interface 35 are equivalently grounded, the power supply selector 50 may regard that the power supplies of the second power supply and the third power supply are abnormal, determine that the first power supply interface 31 is the current power supply interface, and output a switch control signal for closing the third switch and opening the fourth switch and the fifth switch, so as to supply power to the first power supply; for another example, the first power supply interface 31 and the third power supply interface 91 of the three power supply interfaces are both connected to a battery power supply, and both of them meet the preset power supply condition, the power supply selector 50 determines that the first power supply interface 31 is the current power supply interface according to the priority order of the three power supply interfaces, and outputs a switch control signal for turning on the third switch and turning off the fourth switch and the fifth switch, when the first power supply 30 does not meet the preset power supply condition, 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 91 to the current power supply interface, and outputs a switch control signal for turning on the fourth switch and turning off the third switch and the fifth switch, so that the second power supply 90 supplies power.
In one implementation, when switching the power supply interfaces, after the third power supply interface 91 is connected to the controller 20, the first power supply interface 31 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 31 and ground, a second capacitor connected between the third power interface 91 and ground, and a third capacitor connected between the power supply terminal 36 of the fifth power interface 35 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.
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, the third power supply interface, and the fifth power supply interface is the current power supply interface, and is configured to output a corresponding switch control signal when one of the first power supply interface and the third power supply interface 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.
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 fifth power supply interface 35 when the fifth power supply interface 35 is the current power supply interface. In one implementation, the controller 20 is connected to the power supply selector 50, and configured to respond to the signal sent by the power supply selector 50 that the fifth power supply interface 35 is connected to the third power supply, send the flight control data to the data transmission terminal 38 of the fifth power supply interface 35 according to a preset data transmission instruction or periodically, and transmit the flight control data to the smart computing device via the fifth power supply interface 35 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.
It is to be understood that, in the present application, the first detection circuit may be a detection circuit provided in addition to the first charge detection circuit, or may be used as the first detection circuit at the same time, in which case, the detection signal of the first detection circuit may be provided to the charge controller and the power supply selector at the same time. The second detection circuit can be understood as such and is not described in detail.
In the embodiment of the application, the battery power supply of the flight control system is connected with the charging interface, the power supply interface for connecting the aircraft power module power supply is connected with the charging interface through the switch, the charging detection circuit detects the voltage of the battery power supply, and controls the on-off state through the charging controller, so that the aircraft power module power supply charges or does not charge the battery power supply, the battery power supply for the flight control system is charged, the power supply electric quantity of the flight control system controller can be ensured in the flight process of the aircraft, and the flight safety is ensured. On the other hand, when the battery power supply is supplying power for 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 and the charging interface which are connected with the aircraft power module power supply to be closed, so that the aircraft power module power supply charges the battery power supply, and the electric quantity of the power supply battery power supply is ensured.
In this embodiment, the control circuit is configured with a first power supply interface for connecting the first battery, a third power supply interface for connecting the second battery, and a fifth power supply interface for connecting the intelligent computing device, where the fifth 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 fifth switch is disposed between the power source end and the controller, and the power source selector may control whether to select the fifth 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 fifth power supply interface supplies power or not is managed through the power supply selector, so that the situation that the third power supply of the flight control system interferes with normal power supply of other power supplies when being 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 (11)
1. A power control circuit of a flight control system is characterized by comprising:
the first charging interface and the first power supply interface are used for connecting a first power supply of the flight control system;
the second power supply interface is used for connecting a power supply of the aircraft power module;
the controller is connected with the first power supply interface;
a first charge detection circuit for detecting the first power supply;
the first switch is connected between the second power supply interface and the first charging interface; and
and the charging controller is connected with the first switch and the first charging detection circuit.
2. The power control circuit of claim 1, wherein:
the charge controller is configured to output a switch control signal to close the first 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 first switch in response to a signal that the amount of power of the first power supply meets the preset condition.
3. The power control circuit of claim 1, wherein:
the charge controller is configured to output a switch control signal to close the first switch in response to a signal that a voltage of the first power source is less than a first preset threshold, and to output a switch control signal to open the first switch in response to a signal that the voltage of the first power source is greater than a second preset threshold.
4. The power control circuit of claim 1, wherein:
the charging controller is configured to output switch control information for closing the first switch 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.
5. The power control circuit of claim 1, further comprising:
the second charging interface and the third power supply interface are used for connecting a second power supply of the flight control system;
a second charge detection circuit for detecting the second power supply;
the fourth power supply interface is used for connecting the power module power supply;
the second switch is connected between the fourth power supply interface and the second charging interface, and the charging controller is respectively connected with the second switch and the second charging detection circuit;
the switch circuit comprises a third switch connected between the first power supply interface and the controller and a fourth switch connected between the third power supply interface and the controller; and
a power supply selector for outputting a switching control signal to the switching circuit.
6. The power control circuit of claim 5, wherein:
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 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 detecting that the 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.
7. The power control circuit of claim 5, further comprising:
the fifth power supply interface is used for being connected with a third power supply of the flight control system and comprises a power supply end and a data transmission end connected with the controller;
the switch circuit further comprises a fifth switch connected between a power supply end of the fifth power supply interface and the controller.
8. The power control circuit of claim 7, wherein:
the power supply selector is connected with the first power supply interface, the second power supply interface is connected with the power supply selector, and the third power supply interface is connected with the power supply selector;
at least one of the first detection circuit to the third detection circuit is connected with the power selector through at least three signal lines, and the at least three signal lines comprise a power voltage detection signal line, an overvoltage detection signal line and an undervoltage detection signal line.
9. The power control circuit of claim 7, wherein:
the power supply selector is configured to output, to the switching circuit, switching control signals of the third to fifth switches in response to detection signals of the first to third power supplies, the switching control signals corresponding to a current power supply interface selected in accordance with a preset power supply interface priority order and the detection signals of the first to third power supplies.
10. The power control circuit of claim 7, wherein:
the first power supply and the second power supply are battery power supplies, and the third power supply is intelligent computing equipment.
11. An aircraft having a power supply control circuit as claimed in any one of claims 1 to 10.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120393088.3U CN214755586U (en) | 2021-02-22 | 2021-02-22 | Aircraft and flight control system's power control circuit thereof |
| PCT/CN2021/118304 WO2022174580A1 (en) | 2021-02-22 | 2021-09-14 | Aircraft, and control circuit of flight control system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120393088.3U CN214755586U (en) | 2021-02-22 | 2021-02-22 | Aircraft and flight control system's power control circuit thereof |
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| Publication Number | Publication Date |
|---|---|
| CN214755586U true CN214755586U (en) | 2021-11-16 |
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| CN202120393088.3U Active CN214755586U (en) | 2021-02-22 | 2021-02-22 | Aircraft and flight control system's power control circuit thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114123442A (en) * | 2021-11-26 | 2022-03-01 | 歌尔科技有限公司 | Aircraft and power supply system, power supply control method and readable storage medium thereof |
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- 2021-02-22 CN CN202120393088.3U patent/CN214755586U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114123442A (en) * | 2021-11-26 | 2022-03-01 | 歌尔科技有限公司 | Aircraft and power supply system, power supply control method and readable storage medium thereof |
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