Battery backup circuit of electric aircraft

Abstract

The utility model discloses an electric aircraft battery backup circuit, which comprises a cut-off module, a detection module, a battery module and a feedback module, the cut-off module is used for controlling the connection state of the battery module and an aircraft control system, one end of the cut-off module is connected to one electrode of the battery module through a lead, and the other end of the cut-off module is connected to the other electrode of the battery module. The other end is connected to the input end of the aircraft control system; the detection module is used for detecting the change of circuit current and is connected to the other electrode of the battery module through a wire; one electrode of the battery module is connected with the aircraft control system through the cut-off module, and a wire of the other electrode is arranged on one side of the detection module; the feedback module is in communication connection with the aircraft control system and is connected to a communication interface of the aircraft control system through a wire; and when the current is smaller than a set value or is reverse, the detection circuit controls the relay to be disconnected, and the normally working battery pack continues to work, so that the whole system is prevented from promoting power supply due to battery faults.

Description

Technical Field

[0001] The utility model belongs to the field of battery circuits, and in particular relates to a battery backup circuit for an electric aircraft, which improves the circuit protection capability. Background Art

[0002] At present, the battery power supply systems commonly used in aircraft or similar systems include single-battery-pack power supply and multi-battery-pack power supply. There are safety hazards in the power supply system. For example, when the traditional MCU controls the battery pack to be connected, there is a risk of MCU freezing. In addition, when the aircraft circuit is powered by multiple independent battery packs, a short circuit in one battery may cause the entire aircraft to lose power and crash.

[0003] In the relay that controls the connection status between the battery and the aircraft control system, when the aircraft power system needs to be repaired, a malfunction may cause the battery to supply power externally. Utility Model Content

[0004] Purpose of the utility model: In order to overcome the above-mentioned deficiencies, the purpose of the utility model is to provide a battery backup circuit for electric aircraft, which, through circuit switching, will not cause the entire aircraft to lose power and crash even if a battery is short-circuited, and the cut-off module will not cause malfunction, thus avoiding accidental power supply.

[0005] Technical solution:

[0006] In order to achieve the above-mentioned purpose, the utility model provides an electric aircraft battery backup circuit, including: a cut-off module, which controls the connection state of the battery module and the aircraft control system, one end of which is connected to an electrode of the battery module through a wire, and the other end is connected to the input end of the aircraft control system; a detection module, the detection module is used to detect the change of circuit current, and it is connected to the other electrode of the battery module through a wire; a battery module, one electrode of the battery module is connected to the aircraft control system through the cut-off module, and the wire of the other electrode is arranged on one side of the detection module, and the cut-off module is used to control the connection state of the battery module and the aircraft control system; a feedback module, the feedback module communicates with the aircraft control system, and it is connected to the communication interface of the aircraft control system through a wire.

[0007] Furthermore, the circuit also includes a comparison module, which is connected to the feedback module and is configured to compare changes in the input signal and output a control signal.

[0008] Furthermore, the conductive wire of the other electrode of the battery module is wound around to form a conductive coil, and the conductive coil is placed on one side of the detection module.

[0009] Furthermore, the positive electrode of the battery module is connected to the positive input terminal of the aircraft control system, and the negative electrode of the battery module is connected to the negative input terminal of the aircraft control system.

[0010] Furthermore, the battery module includes a plurality of battery packs.

[0011] Furthermore, the plurality of battery packs are connected in parallel and are independently powered.

[0012] Furthermore, the cutting module includes a shell, a static contact, a moving contact, a maintenance mechanical switch, and a sliding insulating sheet. The static contact and the moving contact are arranged inside the shell, and at least a part of the maintenance mechanical switch is located outside the shell and is connected to the moving contact. The sliding insulating sheet is located between the static contact and the moving contact and is used to isolate or connect the circuit. When the maintenance mechanical switch is at the maintenance end, the sliding insulating sheet is inserted between the static contact and the moving contact.

[0013] Furthermore, an elastic protrusion is provided on one side of the maintenance mechanical switch, and at least two locking notches are provided on the housing, and the elastic protrusion cooperates with the locking notches.

[0014] It can be seen from the above technical solution that the utility model has the following beneficial effects:

[0015] 1. The utility model provides a battery backup circuit for an electric aircraft, which is powered by multiple independent battery packs. Through the switching of this circuit, it can ensure that even if a battery pack fails, the power supply of the aircraft can be maintained to maintain its normal flight operation.

[0016] 2. By using the detection module to detect current changes and cooperating with the control of the comparison module, real-time monitoring and control of the current state are achieved to ensure that the battery pack operates within a safe current range.

[0017] 3. The cut-off module has a mechanical disconnection function, which will not cause malfunction, avoid stopping the power supply to the outside or supplying power to the outside during maintenance, and will not harm the maintenance personnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of a battery backup circuit for an electric aircraft provided by an embodiment of the utility model;

[0019] Figure 2 A schematic diagram of the structure of a cutting module provided in an embodiment of the utility model;

[0020] Figure 3 A schematic diagram of the structure of the static contact and the moving contact provided in the embodiment of the utility model;

[0021] Figure 4A schematic diagram of the structure of a maintenance mechanical switch provided in an embodiment of the utility model;

[0022] Figure 5 A schematic diagram of the structure of the elastic protrusion and the locking notch provided in the embodiment of the utility model;

[0023] In the figure: 101-cut-off module, 102-detection module, 103-battery module, 1031-conductor coil, 104-feedback module, 105-comparison module, 201-housing, 2011-locking notch, 202-coil, 203-static iron core, 204-moving iron core, 205-static contact, 206-moving contact, 207-spring, 208-maintenance mechanical switch, 2081-elastic protrusion, 209-sliding insulating sheet. DETAILED DESCRIPTION

[0024] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0025] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0026] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0027] Example

[0028] This example provides a battery backup circuit for an electric aircraft to ensure that even if a battery pack fails, the aircraft can still maintain power supply to maintain its normal flight operation, such as Figure 1 As shown, the battery backup circuit of the electric aircraft includes a cut-off module 101, a detection module 102, a battery module 103 and a feedback module 104. Through the coordinated action of these modules, real-time monitoring of the battery status and the cut-off operation of the faulty battery pack are achieved.

[0029] Among them, one electrode of the battery module 103 is controlled by the disconnection module 101 to control whether it is connected to the aircraft control system. The disconnection module 101 acts as an electronic switch, which can be turned on or off when necessary to control the connection state of the battery module 103 and the aircraft control system. The wire of the other electrode of the battery module 103 is set on one side of the detection module 102, and the detection module 102 can detect the change of the current. The feedback module 104 communicates with the aircraft control system. When the disconnection operation is performed, the feedback module 104 notifies the aircraft control system that the disconnection module 101 is working, that is, the battery module 103 is faulty. This is done to reduce the MCU crash, which causes inaccurate software control when disconnection is required, and the disconnection is not successful in time, causing the entire flight system to lose power supply.

[0030] In some examples, the positive electrode of the battery module 103 is connected to the positive input terminal of the aircraft control system through the cut-off module 101, and the negative electrode of the battery module 103 is connected to the negative input terminal of the aircraft control system.

[0031] Specifically, the cut-off module 101 is arranged between the positive pole of the battery module 103 and the positive input terminal of the aircraft control system. When a current abnormality or other fault conditions are detected, the cut-off module 101 will respond quickly to cut off the connection between the positive pole of the battery module 103 and the positive input terminal of the aircraft control system, thereby blocking the faulty battery pack from supplying power to the aircraft system to ensure the safety and stability of the aircraft.

[0032] It is conceivable that the control of the cut-off module 101 may be implemented by a logic circuit in the aircraft control system or a dedicated protection controller.

[0033] The negative pole of the battery module 103 is connected to the negative input terminal of the aircraft control system through a wire to establish a closed circuit. In order to prevent the negative pole from short-circuiting with other components or structures, an insulating sleeve or insulating glue is usually used to protect the connection to ensure the safety and reliability of the connection.

[0034] It should be added that when an abnormal current situation occurs, the cut-off module 101 immediately performs a cut-off operation to isolate the positive pole of the battery module 103 from the positive input terminal of the aircraft control system to prevent abnormal current transmission. At the same time, the negative pole of the battery module 103 is always connected to ensure that the negative input terminal of the aircraft system is grounded to maintain the integrity and stability of the circuit.

[0035] In some examples, such as Figure 1 As shown, the battery module 103 includes a plurality of battery packs, which are connected in parallel so that their positive and negative electrodes are connected, thereby increasing the overall current capacity and charge capacity, and each battery pack is independently powered.

[0036] Since the battery packs are powered independently, each battery pack needs to be managed and balanced to ensure that their voltage and capacity remain consistent to avoid circuit instability or damage due to mismatch between battery packs.

[0037] It is conceivable that each battery pack needs to be equipped with a monitoring device for real-time monitoring of the voltage, temperature and status of the battery pack so as to promptly detect any abnormal conditions and take measures to deal with them.

[0038] In other examples, such as Figure 1 As shown, the circuit further includes a comparison module 105, which is connected to the feedback module 104 and configured to compare changes in input signals and output a control signal. The input signal of the comparison module 105 is configured as a current value or a current direction.

[0039] Specifically, when the current is less than the set value or in the reverse direction, the cut-off module 101 is disconnected, that is, the connection between the faulty battery pack and the overall power supply circuit is disconnected, and the normally working battery pack continues to work. In this process, the comparison module 105 is responsible for comparing the magnitude relationship between the current and the preset threshold value or the change in the current direction.

[0040] In some examples, the aircraft control system communicates with the feedback module 104 through a predefined communication protocol to monitor and control the status of the battery module 103. When the aircraft is charging, the aircraft control system communicates with the feedback module 104, and the feedback module 104 controls the comparison module 105 to output a control signal. After the cut-off module 101 receives the control signal output by the comparison module 105, it closes to connect the charger and the battery module 103 to complete the charging.

[0041] It is conceivable that the cut-off module 101 is a relay, and the closing of the relay establishes a circuit connection between the charger and the battery pack, so that the battery pack can start to receive electrical energy from the charger and perform a charging operation.

[0042] The aircraft control system continuously monitors the voltage, current, temperature and other parameters of the battery module 103 during the charging process. Once the battery pack reaches the end of charging state, the disconnection module 101 will disconnect and stop the charging process.

[0043] In some examples, such as Figure 1As shown, the conductive wire of one electrode of the battery module 103 is wrapped to form a conductive coil 1031, and the conductive coil 1031 is placed on one side of the detection module 102, wherein the detection module 102 includes a Hall element, and the conductive coil 1031 is placed near the Hall element. When current passes through the conductive coil 1031, a magnetic field is generated. When this magnetic field interacts with the magnetic sensitive material near the Hall element, it causes a change in the output voltage of the Hall element. By detecting the voltage change output by the Hall element, the change in current can be indirectly detected.

[0044] This example provides a complete working principle of the circuit. When the battery module 103 supplies power to the outside, the wire will generate a magnetic field near the Hall element. The Hall element indirectly obtains the current value by detecting the magnetic field strength. When the current reaches a certain intensity and the direction is correct, the output voltage of the Hall element reaches a certain value. At this time, the comparison circuit outputs a control signal to turn on the relay protection, that is, to continue to supply power to the outside. When there is a problem with the voltage of a battery pack, or a short circuit occurs in the battery pack, the magnetic field formed by the wire decreases or even reverses, and the output voltage of the Hall element decreases. At this time, the comparison module 105 stops outputting the control signal, and the relay disconnects the battery pack from the overall power supply system. The feedback module 104 can also detect whether the signal to control the relay exists through R6, and confirm whether this battery pack is connected to work.

[0045] like Figure 2 and 3 As shown, this example provides a cut-off module 101, which includes a housing 201, a coil 202, a static iron core 203, a moving iron core 204, a static contact 205, a moving contact 206, a spring 207, a maintenance mechanical switch 208 and a sliding insulating sheet 209, wherein the cut-off module 101 is a relay, and the housing adopts a closed structure to protect the internal components and circuits. The coil 202 is wound by a wire. When a current is passed through the coil 202, a magnetic field is generated, so that the moving iron core 204 of the relay is attracted or released, thereby realizing the closing or disconnection of the contact. The static iron core 203 and the moving iron core 204 are magnetic elements inside the relay, and their relative positions and changes in the magnetic field determine the state of the contact. The static contact 205 and the moving contact 206 are electrical contacts inside the relay, the static contact 205 is fixed, and the moving contact 206 is movable, and their closing and disconnection determine the on-off state of the relay, thereby realizing the connection or disconnection of the circuit. The spring 207 is connected to the moving contact 206 to provide elastic force for closing the contact so that the contact can be stably closed or opened to ensure reliable connection of the circuit. The maintenance mechanical switch 208 is located outside the housing 201 and is connected to the moving contact 206. The maintenance mechanical switch 208 is used for manual operation. The sliding insulating sheet 209 is located between the static contact 205 and the moving contact 206 of the relay to isolate the two and prevent accidental short circuit when the contacts are closed.

[0046] like Figure 2 As shown, the cut-off module 101 has a mechanical disconnection function. When the aircraft power system needs to be repaired, the maintenance mechanical switch 208 is moved to the maintenance end. At this time, the sliding insulating sheet 209 is inserted between the moving contact 206 and the static contact 205, which mechanically ensures that the battery module 103 does not supply power to the outside and will not harm maintenance personnel.

[0047] In some examples, such as Figure 4 and 5 As shown, an elastic protrusion 2081 is provided on one side of the maintenance mechanical switch 208, and two locking notches 2011 are provided on the outer shell 201. When the maintenance mechanical switch 208 is moved, the elastic protrusion 2081 on the maintenance mechanical switch 208 can be stuck in one of the locking notches 2011 on the outer shell 201, that is, the mechanical disconnection position and the release position, which can reduce false operation and cause the external power supply to be stopped or the external power supply to be supplied during maintenance.

[0048] The above is only a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be regarded as within the protection scope of the present invention.

Claims

1. A battery backup circuit for an electric aircraft, characterized in that: It includes a cut-off module, a detection module, a battery module and a feedback module, wherein: The disconnection module controls the connection state between the battery module and the aircraft control system, one end of which is connected to an electrode of the battery module through a wire, and the other end is connected to the input end of the aircraft control system; The detection module is used to detect the change of circuit current, and is connected to another electrode of the battery module through a wire; One electrode of the battery module is connected to the aircraft control system through the cut-off module, and the wire of the other electrode is arranged on one side of the detection module; The feedback module is in communication connection with the aircraft control system and is connected to the communication interface of the aircraft control system through a wire.

2. The electric aircraft battery backup circuit according to claim 1, characterized in that: The circuit further comprises a comparison module, which is connected to the feedback module and configured to compare the change of the input signal and output a control signal.

3. The electric aircraft battery backup circuit according to claim 1, characterized in that: The conductive wire of the other electrode of the battery module is wound around to form a conductive coil, and the conductive coil is placed on one side of the detection module.

4. The electric aircraft battery backup circuit according to claim 1, characterized in that: The positive electrode of the battery module is connected to the positive input terminal of the aircraft control system, and the negative electrode of the battery module is connected to the negative input terminal of the aircraft control system.

5. The electric aircraft battery backup circuit according to claim 1, characterized in that: The battery module includes a plurality of battery packs.

6. The electric aircraft battery backup circuit according to claim 5, characterized in that: The plurality of battery packs are connected in parallel and are powered independently.

7. The electric aircraft battery backup circuit according to claim 1, characterized in that: The cutting module includes a shell, a static contact, a moving contact, a maintenance mechanical switch, and a sliding insulating sheet. The static contact and the moving contact are arranged inside the shell, and at least a part of the maintenance mechanical switch is located outside the shell and is connected to the moving contact. The sliding insulating sheet is located between the static contact and the moving contact and is used to isolate or connect the circuit. When the maintenance mechanical switch is at the maintenance end, the sliding insulating sheet is inserted between the static contact and the moving contact.

8. The electric aircraft battery backup circuit according to claim 7, characterized in that: One side of the maintenance mechanical switch is provided with an elastic protrusion, and the housing is provided with at least two locking notches, and the elastic protrusion matches with the locking notches.

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