CN113162188B - Electric manned aircraft charging control method, device and system - Google Patents

Electric manned aircraft charging control method, device and system Download PDF

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Publication number
CN113162188B
CN113162188B CN202110493568.1A CN202110493568A CN113162188B CN 113162188 B CN113162188 B CN 113162188B CN 202110493568 A CN202110493568 A CN 202110493568A CN 113162188 B CN113162188 B CN 113162188B
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China
Prior art keywords
charging
relay
charging current
preset threshold
rechargeable battery
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Active
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CN202110493568.1A
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Chinese (zh)
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CN113162188A (en
Inventor
赵德力
全洪飞
谢东武
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Guangdong Huitian Aerospace Technology Co Ltd
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Guangdong Huitian Aerospace Technology Co Ltd
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Priority to CN202110493568.1A priority Critical patent/CN113162188B/en
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Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/007—Regulation of charging or discharging current or voltage
    • H02J7/00712—Regulation of charging or discharging current or voltage the cycle being controlled or terminated in response to electric parameters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
    • B60L53/10—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by the energy transfer between the charging station and the vehicle
    • B60L53/14—Conductive energy transfer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
    • B60L53/60—Monitoring or controlling charging stations
    • B60L53/62—Monitoring or controlling charging stations in response to charging parameters, e.g. current, voltage or electrical charge
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H7/00—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions
    • H02H7/22—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systems; for switching devices
    • H02H7/222—Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for distribution gear, e.g. bus-bar systems; for switching devices for switches
    • 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
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H02J7/0031—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits using battery or load disconnect circuits
    • 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
    • H02J7/0047—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with monitoring or indicating devices or circuits
    • H02J7/0048—Detection of remaining charge capacity or state of charge [SOC]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2200/00—Type of vehicles
    • B60L2200/10—Air crafts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/70—Energy storage systems for electromobility, e.g. batteries
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/10—Technologies relating to charging of electric vehicles
    • Y02T90/12—Electric charging stations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02T90/10—Technologies relating to charging of electric vehicles
    • Y02T90/14—Plug-in electric vehicles

Abstract

The application relates to a method, a device and a system for controlling charging of an electric manned aircraft. The electric manned aircraft charging control method comprises the following steps: detecting a charging current of the charging device; and when the charging current of the charging equipment is detected to meet the preset condition, performing operation on a relay, wherein the relay is used for switching on or switching off the connection between the charging equipment and a rechargeable battery of the electric manned aircraft. According to the scheme, the relay contact ageing and failure problems can be reduced, the service life of the relay is prolonged, and the charging safety performance of the electric manned aircraft is improved.

Description

Electric manned aircraft charging control method, device and system
Technical Field
The application relates to the technical field of manned aircraft, in particular to a charging control method, device and system of an electric manned aircraft.
Background
With the development of technology, manned aircraft technology is also continuously developed.
In the related art, a relay is generally provided in a charging circuit of an electric manned aircraft to control connection and disconnection between a rechargeable battery and a charging seat. In a high-voltage high-current system, if the voltages at two ends of the relay are greatly different, the relay generates a spark phenomenon between contacts due to the fact that gaps become smaller in the closing process of the relay; in the process of switching off the relay, if the current is large, the coil of the relay is an inductive device, and the current of the coil needs to be maintained unchanged, so that an arc discharge phenomenon can occur.
In the related art, the charging circuit of the electric manned aircraft is not protected by the relay, so that the relay contact in the charging circuit is easy to age and fail, and the charging safety performance of the electric manned aircraft is affected.
Disclosure of Invention
In order to solve or partially solve the problems existing in the related art, the application provides a charging control method, device and system for an electric manned aircraft, which can reduce the ageing and failure problems of relay contacts, prolong the service life of a relay and improve the charging safety performance of the electric manned aircraft.
A first aspect of the present application provides a method for controlling charging of an electric manned aircraft, including:
detecting a charging current of the charging device;
and when the charging current of the charging equipment is detected to meet the preset condition, performing operation on a relay, wherein the relay is used for switching on or switching off the connection between the charging equipment and a rechargeable battery of the electric manned aircraft.
In one embodiment, the performing the operation of the relay when detecting that the charging current of the charging device satisfies a preset condition includes:
and when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing the relay to conduct connection between the charging equipment and the rechargeable battery.
In one embodiment, before detecting the charging current of the charging device, the method further includes:
and when judging that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, indicating the charging equipment to reduce the charging current to the first preset threshold value.
In one embodiment, the performing the operation of the relay when detecting that the charging current of the charging device satisfies a preset condition includes:
and when detecting that the charging current of the charging equipment is smaller than or equal to a second preset threshold value, disconnecting the relay so as to disconnect the charging equipment from the rechargeable battery.
In one embodiment, before detecting that the charging current of the charging device is less than or equal to a second preset threshold, the method further includes:
and after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to the second preset threshold value.
In one embodiment, the method further comprises:
and after the charging battery is detected to be not fully charged, continuing to charge.
A second aspect of the present application provides an electric manned aircraft charge control device, comprising:
the detection module is used for detecting the charging current of the charging equipment;
and the control module is used for executing the operation of the relay when the detection module detects that the charging current of the charging equipment meets the preset condition, wherein the relay is used for connecting or disconnecting the charging equipment and the charging battery of the electric manned aircraft.
In one embodiment, the control module includes:
and the first control submodule is used for closing the relay when the detection module detects that the charging current of the charging equipment is smaller than or equal to a first preset threshold value so as to conduct connection between the charging equipment and the rechargeable battery.
In one embodiment, the apparatus further comprises:
and the first indication module is used for indicating the charging equipment to reduce the charging current to the first preset threshold value when judging that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft.
In one embodiment, the control module includes:
and the second control submodule is used for disconnecting the relay when the detection module detects that the charging current of the charging equipment is smaller than or equal to a second preset threshold value so as to disconnect the charging equipment from the rechargeable battery.
In one embodiment, the apparatus further comprises:
and the second indication module is used for indicating the charging equipment to reduce the charging current to the second preset threshold value after the detection module detects that the rechargeable battery is fully charged.
A third aspect of the present application provides an electric manned aircraft charge control system comprising: charging equipment, rechargeable battery of electric manned aircraft and electric manned aircraft charge control device as above.
A fourth aspect of the present application provides a non-transitory machine-readable storage medium having stored thereon executable code, which when executed by a processor of an electronic device, causes the processor to perform the method described above.
The technical scheme that this application provided can include following beneficial effect:
according to the scheme provided by the embodiment of the application, the charging current of the charging equipment is detected, and when the charging current of the charging equipment is detected to meet the preset condition, the operation of the relay is executed. Therefore, before the operation of the relay is executed, the charging current is limited, the ignition phenomenon or the arcing phenomenon generated by directly closing or opening the relay under the current charging current condition in the related technology is avoided, a protection measure is provided for the relay, the ageing and failure problems of the relay contact can be reduced, the service life of the relay is prolonged, the reliability of the relay is improved, and the charging safety performance of the electric manned aircraft is improved.
Further, the solution provided by the embodiment of the present application may close the relay when detecting that the charging current of the charging device is less than or equal to a first preset threshold, so as to conduct connection between the charging device and the rechargeable battery; or when the charging current of the charging equipment is detected to be smaller than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging equipment from the rechargeable battery, so that a protective measure is provided for the relay by limiting the charging current.
Further, in the solution provided in the embodiment of the present application, when it is determined that charging needs to be performed on a rechargeable battery of the electric manned aircraft, the charging device may be instructed to reduce the charging current to the first preset threshold; or after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to the second preset threshold value; therefore, the charging current can be limited through the control instruction, a relay on the charging circuit is protected, and damage to the relay is reduced.
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 flow chart of a method for controlling the charge of an electric manned aircraft according to one embodiment of the present application;
FIG. 2 is a flow chart of an electric manned aircraft charge control method according to another embodiment of the present application;
FIG. 3 is a flow chart of an electric manned aircraft charge control method according to another embodiment of the present application;
fig. 4 is a schematic structural view of an electric manned aircraft charge control device according to an embodiment of the present application;
fig. 5 is a schematic structural view of an electric manned aircraft charge control device according to another embodiment of the present application;
fig. 6 is a schematic structural view of an electric manned aircraft charge control system according to another embodiment of the present application.
Detailed Description
Preferred embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present application are shown in the drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
The terminology used in the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the present 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 or 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 by these terms. These terms are only used to distinguish one type of information from another. For example, a first message may also be referred to as a second message, and similarly, a second message may also be referred to as a first message, without departing from the scope of the present application. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the related art, a relay contact in a charging circuit is easy to age and lose efficacy, and the charging safety performance of the electric manned aircraft is affected. Aiming at the problems, the embodiment of the application provides a charging control method for an electric manned aircraft, which can reduce the problems of aging and failure of contacts of a relay, prolong the service life of the relay and improve the charging safety performance of the electric manned aircraft.
The following describes the technical scheme of the embodiments of the present application in detail with reference to the accompanying drawings.
Fig. 1 is a schematic flow chart of a method for controlling charging of an electric manned aircraft according to an embodiment of the present application.
Referring to fig. 1, the method includes:
step S101, detecting a charging current of the charging device.
In this step, the charging current of the charging device may be detected by using different detection methods in the related art, which is not limited in the embodiment of the present application.
Step S102, when it is detected that the charging current of the charging device satisfies a preset condition, performing an operation on a relay for turning on or off a connection between the charging device and a rechargeable battery of the electric manned aircraft.
Wherein, can include: when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing a relay to conduct connection between the charging equipment and the rechargeable battery; or when detecting that the charging current of the charging device is less than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging device from the rechargeable battery. By this processing, the magnitude of the charging current can be restricted before the operation of the relay is performed.
The first predetermined threshold described therein may be, for example, 0-3A (amperes), and the second predetermined threshold may be, for example, 0-0.5A (amperes), but is not limited thereto.
As can be seen from this embodiment, in the scheme provided in the embodiment of the present application, the charging current of the charging device is detected first, and when it is detected that the charging current of the charging device meets the preset condition, the operation on the relay is performed. Therefore, before the operation of the relay is executed, the charging current is limited, the ignition phenomenon or the arcing phenomenon generated by directly closing or opening the relay under the current charging current condition in the related technology is avoided, a protection measure is provided for the relay, the ageing and failure problems of the relay contact can be reduced, the service life of the relay is prolonged, the reliability of the relay is improved, and the charging safety performance of the electric manned aircraft is improved.
Fig. 2 is a schematic flow chart of a method for controlling charging of an electric manned aircraft according to another embodiment of the present application. Fig. 2 illustrates the technical solution of the embodiment of the present application in more detail with respect to fig. 1.
Referring to fig. 2, the method includes:
step S201, when it is judged that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, the charging equipment is instructed to reduce the charging current to a first preset threshold value.
The charging circuit of the electric manned aircraft is generally provided with a relay for controlling the connection and disconnection between the rechargeable battery and the charging seat. The method comprises the steps of firstly judging whether a relay needs to be closed to charge a rechargeable battery of the electric manned aircraft, and if so, indicating the charging equipment to reduce the charging current to a first preset threshold value, so as to limit the charging current and protect the accessed relay.
The relay can be judged whether to be closed or not in various modes to charge the rechargeable battery of the electric manned aircraft. For example, when the charging interface of the rechargeable battery of the electric manned aircraft is plugged into the charging device, after the charging function is started in a code scanning or card swiping mode, the relay can be considered to be closed to charge the rechargeable battery of the electric manned aircraft. At this time, the charging device acquires a charging start signal.
Step S202, detecting a charging current of the charging device.
In this step, the charging current of the charging device may be detected by using different detection methods in the related art, which is not limited in the embodiment of the present application.
Step S203, when detecting that the charging current of the charging device is less than or equal to the first preset threshold, closing the relay to conduct the connection between the charging device and the rechargeable battery.
When the charging current of the charging device is detected to be smaller than or equal to a first preset threshold value, the charging current is limited, and at the moment, the relay is closed again to conduct connection between the charging device and the rechargeable battery for charging. The first preset threshold may be, for example, 0-3A (amperes).
Step S204, after detecting that the rechargeable battery is fully charged, the charging device is instructed to reduce the charging current to a second preset threshold.
And continuously detecting the charging current of the charging equipment, and after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to a second preset threshold value. The second preset threshold may be, for example, 0-0.5A (amperes).
Step S205, when detecting that the charging current of the charging device is less than or equal to the second preset threshold, turns off the relay to disconnect the connection between the charging device and the rechargeable battery.
And continuously detecting the charging current of the charging equipment, and when the charging current of the charging equipment is detected to be smaller than or equal to a second preset threshold value, indicating that the charging current is limited in size, at the moment, disconnecting the relay to disconnect the charging equipment from the rechargeable battery, and ending the charging.
As can be seen from the embodiment, the scheme provided by the embodiment of the application can close the relay to conduct the connection between the charging device and the charging battery when detecting that the charging current of the charging device is smaller than or equal to the first preset threshold value; or when the charging current of the charging equipment is detected to be smaller than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging equipment from the rechargeable battery, so that a protective measure is provided for the relay by limiting the magnitude of the charging current.
Fig. 3 is a schematic flow chart of a method for controlling charging of an electric manned aircraft according to another embodiment of the present application. Fig. 3 illustrates the technical solution of the embodiment of the present application in more detail with respect to fig. 2.
Referring to fig. 3, the method includes:
step S301, determining whether the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, if yes, proceeding to step S302, if no, proceeding to step S305.
In this step, if it is determined that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, the process proceeds to step S302, and if it is determined that the relay does not need to be closed to charge the rechargeable battery of the electric manned aircraft, the process proceeds to step S305.
In this embodiment of the application, the charging control circuit may determine whether the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, that is, determine whether the relay needs to be closed to conduct a circuit between the rechargeable battery and the charging device. The charging device may be, for example, a charging stand, a charging pile, or the like, but is not limited thereto.
The relay can be judged whether to be closed or not in various modes to charge the rechargeable battery of the electric manned aircraft. For example, when the charging interface of the rechargeable battery of the electric manned aircraft is plugged into the charging device, after the charging function is started in a code scanning or card swiping mode, the relay can be considered to be closed to charge the rechargeable battery of the electric manned aircraft. At this time, the charging device acquires a charging start signal. It should be noted that this is by way of example only and is not limiting.
Step S302, instructs the charging device to reduce the charging current to a first preset threshold.
If the relay is judged to be closed to charge the rechargeable battery of the electric manned aircraft, an instruction for reducing the charging current to a first preset threshold value is sent to the charging equipment, and the charging equipment is instructed to reduce the charging current to the first preset threshold value.
The first predetermined threshold described therein may be, for example, but not limited to, 0-3A (amperes). For example, if the first preset threshold is 2A, an instruction to decrease the charging current to 2A is sent to the charging device so that after the charging current is decreased to 2A or below 2A, the relay is closed again so that the relay is incorporated in the charging circuit. If the first preset threshold is 1A, an instruction to decrease the charging current to 1A is sent to the charging device so that after the charging current is decreased to 1A or below 1A, the relay is closed again so that the relay is incorporated in the charging circuit.
Step S303, detecting a charging current of the charging device.
In this step, the charging current of the charging device may be detected by using different detection methods in the related art, which is not limited in the embodiment of the present application. In addition, the charging current of the charging device may be detected at all times, or at a specified stage.
Step S304, when detecting that the charging current of the charging device is less than or equal to the first preset threshold, closing the relay to conduct the connection between the charging device and the rechargeable battery.
The step can detect the charging current of the charging equipment in real time, and when the charging current is detected to be smaller than or equal to a first preset threshold value, the charging current is limited, and at the moment, the relay is closed again so as to conduct the connection between the charging equipment and the rechargeable battery, so that the charging equipment charges the rechargeable battery.
Step S305, it is determined whether the rechargeable battery is fully charged, and if yes, step S307 is entered, and if no, step S306 is entered.
In the step, the voltage and the electric quantity of the rechargeable battery can be detected in real time to detect whether the rechargeable battery is fully charged. The full charge described herein may be a residual charge up to 100%.
Step S306, the charging is continued, and the process returns to step S305.
If the rechargeable battery is detected to be not fully charged, the rechargeable battery is continuously charged until the residual charge of the rechargeable battery is 100%
Step S307 instructs the charging device to reduce the charging current to a second preset threshold.
If the rechargeable battery is judged to be fully charged, namely, the residual electric quantity reaches 100%, an instruction for reducing the charging current to a second preset threshold value is sent to the charging equipment, and the charging equipment is instructed to reduce the charging current to the second preset threshold value. It should be noted that, after determining that the electric quantity of the rechargeable battery is full to the set electric quantity, for example, the remaining electric quantity reaches 95%, an instruction for reducing the charging current to the second preset threshold may be sent to the charging device.
The second preset threshold described therein may be, for example, but not limited to, 0-0.5A (amperes). The range of values of the second preset threshold may be smaller than the range of values of the first preset threshold. For example, if the first preset threshold is 0A, an instruction to decrease the charging current to 0A is sent to the charging device so that the relay is turned off after the charging current is decreased to 0A. If the first preset threshold is 0.1A, an instruction to decrease the charging current to 0.1A is sent to the charging device so that the relay is turned off after the charging current is decreased to 0.1A or below 0.1A.
Step S308, when detecting that the charging current of the charging device is less than or equal to the second preset threshold, the relay is opened to disconnect the charging device from the rechargeable battery.
The step can detect the charging current of the charging equipment in real time, and when the charging current is detected to be smaller than or equal to a second preset threshold value, the relay is disconnected, and the charging is finished.
The relay according to the embodiment of the present application may be, for example, an electromagnetic relay, but is not limited thereto. The relays typically used in control circuits are mostly electromagnetic relays. Common electromagnetic relays may include current relays, voltage relays, intermediate relays, various small-sized general-purpose relays, and the like. The electromagnetic relay has a structure and a working principle similar to those of a contactor and mainly comprises an electromagnetic mechanism and contacts.
According to the scheme provided by the embodiment of the application, when the relay is judged to be closed to charge the rechargeable battery of the electric manned aircraft, the charging equipment is instructed to reduce the charging current to the first preset threshold value; or after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to a second preset threshold value; then when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing a relay to conduct connection between the charging equipment and the rechargeable battery; or when detecting that the charging current of the charging device is less than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging device from the rechargeable battery. Through the processing, the protection measures can be provided for the relay by limiting the charging current, the arcing phenomenon or the arcing phenomenon occurring during grid-connected charging in the related technology is avoided, the problems of aging and failure of the relay contact are reduced, the service life of the relay is prolonged, the reliability of the relay is improved, and the charging safety performance of the electric manned aircraft is improved.
The foregoing describes in detail the method for controlling the charging of the electric manned aircraft shown in the embodiment of the present application, and correspondingly, the embodiment of the present application further provides a corresponding device, a corresponding system and a corresponding device for controlling the charging of the electric manned aircraft.
Fig. 4 is a schematic structural view of an electric manned aircraft charge control device according to an embodiment of the present application.
Referring to fig. 4, an electric manned aircraft charge control device 40 of an embodiment of the present application includes: a detection module 41 and a control module 42.
The detection module 41 is configured to detect a charging current of the charging device. The detection module 41 may detect the charging current of the charging device by using different detection methods in the related art, which is not limited in the embodiment of the present application.
And a control module 42 for performing an operation of a relay for turning on or off a connection between the charging device and a rechargeable battery of the electric manned aircraft when the detection module 41 detects that the charging current of the charging device satisfies a preset condition.
The control module 42 may close the relay to conduct the connection between the charging device and the rechargeable battery when detecting that the charging current of the charging device is less than or equal to the first preset threshold; or when detecting that the charging current of the charging device is less than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging device from the rechargeable battery. The first predetermined threshold described therein may be, for example, 0-3A (amperes), and the second predetermined threshold may be, for example, 0-0.5A (amperes), but is not limited thereto.
As can be seen from this embodiment, the electric manned vehicle charging control device 40 provided in the embodiment of the present application detects the charging current of the charging device first, and executes the operation of the relay when detecting that the charging current of the charging device meets the preset condition. Therefore, before the operation of the relay is executed, the charging current is limited, the ignition phenomenon or the arcing phenomenon generated by directly closing or opening the relay under the current charging current condition in the related technology is avoided, a protection measure is provided for the relay, the ageing and failure problems of the relay contact can be reduced, the service life of the relay is prolonged, the reliability of the relay is improved, and the charging safety performance of the electric manned aircraft is improved.
Fig. 5 is a schematic structural view of an electric manned aircraft charge control device according to another embodiment of the present application.
Referring to fig. 5, an electric manned aircraft charge control device 40 of an embodiment of the present application includes: a detection module 41, a control module 42 and an indication module 43. The function of the detection module 41 and the control module 42 may be seen from the description in fig. 4.
Wherein, the control module 42 may further comprise: a first control sub-module 421, a second control sub-module 422; the indication module 43 may further include: a first indication module 431 and a second indication module 432.
An indication module 43, configured to instruct the charging device to reduce the charging current to a preset threshold.
The first indication module 431 is configured to instruct the charging device to reduce the charging current to a first preset threshold when it is determined that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft. The first indication module 431 sends an instruction to the charging device to decrease the charging current to the first preset threshold value, and instructs the charging device to decrease the charging current to the first preset threshold value. The first predetermined threshold described therein may be, for example, but not limited to, 0-3A (amperes). For example, if the first preset threshold is 1A, an instruction to decrease the charging current to 1A is sent to the charging device so that after the charging current is decreased to 1A or below 1A, the relay is closed again so that the relay is incorporated in the charging circuit.
The first control sub-module 421 is configured to close the relay when the detection module 41 detects that the charging current of the charging device is less than or equal to the first preset threshold, so as to conduct connection between the charging device and the rechargeable battery, and achieve charging of the rechargeable battery by the charging device.
The second indication module 432 is configured to instruct the charging device to reduce the charging current to a second preset threshold after the detection module 41 detects that the rechargeable battery is fully charged. The second instruction module 432 sends an instruction to the charging device to decrease the charging current to the second preset threshold, instructing the charging device to decrease the charging current to the second preset threshold. The second preset threshold described therein may be, for example, but not limited to, 0-0.5A (amperes). For example, if the first preset threshold is 0A, an instruction to decrease the charging current to 0A is sent to the charging device so that the relay is turned off after the charging current is decreased to 0A.
The second control sub-module 422 is configured to disconnect the relay to disconnect the charging device from the rechargeable battery when the detection module 41 detects that the charging current of the charging device is less than or equal to a second preset threshold. At this time, the charging ends.
As can be seen from this embodiment, the electric manned aircraft charging control device 40 provided in the embodiment of the present application may instruct the charging apparatus to reduce the charging current to the first preset threshold when it is determined that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft; or after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to a second preset threshold value; then when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing a relay to conduct connection between the charging equipment and the rechargeable battery; or when detecting that the charging current of the charging device is less than or equal to a second preset threshold value, the relay is disconnected to disconnect the charging device from the rechargeable battery. Through the processing, the protection measures can be provided for the relay by limiting the charging current, the arcing phenomenon or the arcing phenomenon occurring during grid-connected charging in the related technology is avoided, the problems of aging and failure of the relay contact are reduced, the service life of the relay is prolonged, the reliability of the relay is improved, and the charging safety performance of the electric manned aircraft is improved.
Fig. 6 is a schematic structural view of an electric manned aircraft charge control system according to another embodiment of the present application.
Referring to fig. 6, an electric manned aircraft charge control system 60 of an embodiment of the present application includes: a charging device 61, a rechargeable battery 62 of an electric unmanned aerial vehicle, and the electric unmanned aerial vehicle charging control apparatus 40 as described above. The function and structure of the electric manned vehicle charge control device 40 may be described in fig. 4-5, and will not be described again here.
The specific manner in which the respective modules perform the operations in the apparatus of the above embodiments has been described in detail in the embodiments related to the method, and will not be described in detail herein.
Those of skill would further appreciate that the various illustrative logical blocks, modules, circuits, and algorithm steps described in connection with the application herein may be implemented as electronic hardware, computer software, or combinations of both.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems and methods according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
Furthermore, the method according to the present application may also be implemented as a computer program or computer program product comprising computer program code instructions for performing part or all of the steps of the above-described method of the present application.
Alternatively, the present application may also be embodied as a non-transitory machine-readable storage medium (or computer-readable storage medium, or machine-readable storage medium) having stored thereon executable code (or a computer program, or computer instruction code) that, when executed by a processor of an electronic device (or electronic device, server, etc.), causes the processor to perform some or all of the steps of the above-described methods according to the present application.
The embodiments of the present application have been described above, the foregoing description is exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described. The terminology used herein was chosen in order to best explain the principles of the embodiments, the practical application, or the improvement of technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims (3)

1. A method of controlling the charge of an electric manned aircraft, comprising:
limiting the magnitude of the charging current of the charging device includes: when judging that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft, indicating the charging equipment to reduce the charging current to a first preset threshold value;
detecting a charging current of the charging device;
when the charging current of the charging device is detected to meet the preset condition, performing operation on a relay, wherein the relay is used for conducting or disconnecting connection between the charging device and a rechargeable battery of the electric manned aircraft, and the operation comprises the following steps: when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing the relay to conduct connection between the charging equipment and the rechargeable battery; or after detecting that the rechargeable battery is fully charged, indicating the charging equipment to reduce the charging current to a second preset threshold value; the value range of the second preset threshold value is smaller than that of the first preset threshold value; and when detecting that the charging current of the charging equipment is smaller than or equal to a second preset threshold value, disconnecting the relay so as to disconnect the charging equipment from the rechargeable battery.
2. An electric manned vehicle charge control device, comprising:
the indication module is used for limiting the charging current of the charging equipment;
the detection module is used for detecting the charging current of the charging equipment;
the control module is used for executing the operation of the relay when the detection module detects that the charging current of the charging equipment meets the preset condition, wherein the relay is used for connecting or disconnecting the charging equipment and the charging battery of the electric manned aircraft, and the control module comprises the following components: when detecting that the charging current of the charging equipment is smaller than or equal to a first preset threshold value, closing the relay to conduct connection between the charging equipment and the rechargeable battery; or when detecting that the charging current of the charging device is less than or equal to a second preset threshold value, disconnecting the relay so as to disconnect the charging device from the rechargeable battery;
the indication module comprises:
the first indication module is used for indicating the charging equipment to reduce the charging current to the first preset threshold value when judging that the relay needs to be closed to charge the rechargeable battery of the electric manned aircraft;
and the second indication module is used for indicating the charging equipment to reduce the charging current to a second preset threshold value after the detection module detects that the rechargeable battery is fully charged, and the value range of the second preset threshold value is smaller than that of the first preset threshold value.
3. An electric manned vehicle charge control system, comprising: charging device, rechargeable battery of an electric manned aircraft and electric manned aircraft charging control apparatus as claimed in claim 2.
CN202110493568.1A 2021-05-07 2021-05-07 Electric manned aircraft charging control method, device and system Active CN113162188B (en)

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CN107546790A (en) * 2016-06-29 2018-01-05 深圳市华思旭科技有限公司 power supply assembly and method
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Publication number Priority date Publication date Assignee Title
CN101807490A (en) * 2009-12-31 2010-08-18 深圳和而泰智能控制股份有限公司 Method and circuit for prolonging service life of relay and device
CN105449762A (en) * 2015-12-14 2016-03-30 青岛海汇德电气有限公司 Method, device and system for controlling battery charging
CN205319756U (en) * 2016-01-19 2016-06-15 江门市甜的电器有限公司 Fill electric pile control circuit
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