Aircraft power supply backup circuit

Abstract

The utility model discloses an aircraft power supply backup circuit. The circuit comprises a battery, a Hall element, a lead, a comparator, a bootstrap boost circuit, an MOS tube and a micro-control unit. The Hall element is used for monitoring the state of the battery, the power electrode is connected to the anode of the auxiliary power supply, and the output electrode is connected to the input end of the comparator; the lead is connected with the battery and surrounds to form a lead coil, and the lead coil is placed on one side of the Hall element; the comparator is used for judging the state of the battery according to the output voltage of the Hall element; the bootstrap boost circuit comprises a diode, a triode, a capacitor and a resistor and is used for generating voltage higher than that of the battery; the current of the MOS tube flows from the source electrode to the drain electrode, and the MOS tube uses a bootstrap boost circuit to control the gate electrode; and the micro-control unit is used for controlling the working state of the bootstrap booster circuit and monitoring the output of the comparator.

Description

Technical Field

[0001] The utility model belongs to the field of MOS transistor circuits, and particularly relates to an aircraft power backup circuit for detecting battery faults. Background Art

[0002] Currently, the battery backup circuits of unmanned devices such as electric aircraft face certain challenges in dealing with emergencies when battery packs fail. Traditional battery backup circuits often lack real-time monitoring and intelligent switching functions, and are unable to effectively identify and isolate faulty batteries, thus affecting the entire system and even causing serious accidents.

[0003] In addition, some backup circuits in the prior art have problems such as high complexity, high cost, and high energy consumption in design, which limit their wide application in practical applications. Summary of the Utility Model

[0004] Purpose of the utility model: In order to overcome the above deficiencies, the purpose of the utility model is to provide an aircraft power backup circuit, which adopts a bootstrap boost circuit and can realize real-time monitoring of the state of the battery pack to ensure the stable operation of the electric aircraft when some battery packs fail.

[0005] Technical solution: In order to achieve the above purpose, the utility model provides an aircraft power backup circuit, including: a battery; a Hall element, which is used to monitor the state of the battery, and its power electrode is connected to the positive pole of the auxiliary power supply, and its output electrode is connected to the input end of the comparator; a wire, which is connected to the battery and wound into a coil, and the coil is placed on one side of the Hall element; a comparator, which is used to judge the state of the battery according to the output voltage of the Hall element, its power supply end is connected to the auxiliary power supply, and its output end is connected to the micro control unit and the bootstrap circuit; a bootstrap boost circuit, which includes a diode, a triode, a capacitor and a resistor, and is used to generate a voltage higher than that of the battery. The positive pole of the diode is connected to the positive pole of the auxiliary power supply, its negative pole is connected to the capacitor, the collector of the triode is connected to the resistor, one port of the capacitor is connected to the collector of the triode, and its other port is connected to the diode; an MOS transistor, which is connected to the output end of the bootstrap boost circuit, and the MOS transistor uses the bootstrap boost circuit to control the gate; an auxiliary power supply, which is used to control the processor logic and communication circuit of the system; the micro control unit is used to control the working state of the bootstrap boost circuit and monitor the output of the comparator.

[0006] Further, when using an NMOS transistor, the current flows from the source electrode to the drain electrode, and when using a PMOS transistor, the current flows from the drain electrode to the source electrode.

[0007] Further, the microcontroller unit further includes an IO port, and the IO port is used for the microcontroller unit to establish a communication connection with the aircraft control system.

[0008] Further, the boost - up circuit includes a diode D1, a diode D2, a triode Q1, a capacitor C3, a capacitor C4, a resistor R1, and a resistor R2. The negative electrode of the diode D1 is connected to the collector of the triode Q1, the positive electrode of the diode D2 is connected to the collector of the triode Q1, the collector of the triode Q1 is connected to the ports of the capacitor C3, the capacitor C4, and the resistor R2, and its base is connected to one port of the resistor R1.

[0009] Further, the IO port is used to output pulses.

[0010] Further, when the IO port outputs a high level, the triode Q1 is turned on, and the triode Q1, the capacitor C3, the diode D1, and the auxiliary power supply form a loop, and the capacitor C3 is charged.

[0011] Further, when the IO port outputs a low level, the capacitor C3, the diode D2, and the capacitor C4 form a loop, and the capacitor C4 is charged.

[0012] Further, when the IO port outputs a pulse, the MOS transistor generates a conducting VGS voltage.

[0013] Further, the IO port is used to detect the voltage of the base of the triode Q1.

[0014] From the above technical solutions, the present utility model has the following beneficial effects:

[0015] The present utility model provides an aircraft power backup circuit. By integrating a Hall element and a comparator, this circuit can monitor the state of the battery in real - time. This real - time monitoring function enables the system to detect battery failures or abnormal conditions in a timely manner, and when a battery pack fails, it can disconnect the faulty battery pack from the main power supply of the aircraft without the participation of the MCU. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 is a schematic structural diagram of the aircraft power backup circuit provided by an embodiment of the present utility model;

[0017] Figure 2 is a schematic structural diagram of the boost - up circuit provided by an embodiment of the present utility model;

[0018] In the figure: 101 - battery, 102 - Hall element, 103 - wire, 1031 - wire coil, 104 - comparator, 105 - MOS transistor, 106 - microcontroller unit, 201 - diode D1, 202 - diode D2, 203 - triode Q1, 204 - capacitor C3, 205 - capacitor C4, 206 - resistor R1, 207 - resistor R2. Detailed implementation

[0019] The following further clarifies the present utility model in conjunction with the accompanying drawings and specific embodiments.

[0020] The following details the embodiments of the present utility model. The examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present utility model and should not be construed as limiting the present utility model.

[0021] In the present utility model, unless otherwise clearly specified and defined, terms such as "installation", "connection", "connection", "fixation", etc. 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances. Embodiment

[0022] This example provides a power backup circuit for an aircraft, as Figure 1 shown. The circuit includes a battery 101, a wire 103, a Hall element 102, a comparator 104, a bootstrap boost circuit, a MOS transistor 105, an auxiliary power supply, and a microcontroller unit 106.

[0023] It can be understood that the auxiliary power supply is used to control the processor logic, communication, and other circuits of the system, usually with voltages such as 15V, 12V, 5V, or 3.3V.

[0024] In some examples, the Hall element 102 is made of semiconductor material and includes a Hall sensor and a circuit control part inside. The Hall element 102 can detect the change of the magnetic field and convert it into a voltage signal for output. The Hall element is used to monitor the state of the battery. Its power electrodes are connected to the positive pole of the auxiliary power supply, and its output electrodes are connected to the input end of the comparator.

[0025] In some examples, as Figure 1As shown, the wire 103 is wound into a wire coil 1031, and the wire coil 1031 is placed on one side of the Hall element 102. When current passes through the wire coil 1031, a magnetic field will be generated. When this magnetic field interacts with the magnetosensitive material near the Hall element 102, it will cause a change in the output voltage of the Hall element 102. By detecting the change in the voltage output by the Hall element 102.

[0026] In some examples, the comparator 104 is composed of several operational amplifiers or electronic switches, has one or more input terminals and one output terminal, and the comparator 104 is used to compare the magnitudes of two input signals and output corresponding logic levels according to the comparison results.

[0027] In some examples, the microcontroller unit 106 also includes an IO port, and the IO port is used to establish a communication connection between the microcontroller unit 106 and the aircraft control system.

[0028] In some examples, as Figure 2 shown, the bootstrap circuit includes a diode D1201, a diode D2202, a triode Q1203, a capacitor C3204, a capacitor C4205, a resistor R1206, and a resistor R2207.

[0029] It can be understood that when an NMOS transistor is used, the current flows from the source to the drain, and when a PMOS transistor is used, the current flows from the drain to the source.

[0030] In some examples, the NMOS transistor includes a source, a drain, and a gate. When a positive voltage is applied to the gate, an electric field is formed, enabling a conductive channel to be formed between the source and the drain. The current flows from the source to the drain. The NMOS uses a bootstrap circuit to control the gate, thereby generating a voltage higher than that of the battery 101, so as to have sufficient VGS to enable the NMOS transistor to conduct normally.

[0031] Referring to Figure 2 , when the circuit provided in this example starts to work, the IO port of the microcontroller unit 106 is set to the push-pull mode. Regardless of the level output by the comparator 104, the triode Q1203 can conduct and cut off. When the IO port outputs a high level, the triode Q1203 conducts. At this time, the triode Q1203, the capacitor C3204, the diode D1201, and the auxiliary power supply form a loop, and the capacitor C3204 is charged.

[0032] When the IO port outputs a low level, the left side of the capacitor C3204 is pulled to the voltage of the battery 101 by the resistor R2207, and the right side of the capacitor C3204 is higher than the voltage of the battery 101. At this time, the capacitor C3204, the diode D2202, and the capacitor C4205 form a loop, and the capacitor C4205 is charged, that is, the MOS transistor 105 has the VGS voltage capable of conducting.

[0033] After repeating several cycles, MOS transistor 105 is already conducting. At this time, the IO port of microcontroller unit 106 is set to open-drain mode. If the current direction is the output direction of battery 101, the output voltage of Hall element 102 is higher than the reference voltage of comparator 104. At this time, the comparator 104 outputs open-drain, and the IO port flips. A pulse is formed under the pull-up of resistor R1206 to maintain the operation of the bootstrap boost circuit, and MOS transistor 105 remains conducting.

[0034] When battery 101 fails and the current is input to battery 101, the output voltage of Hall element 102 is lower than the reference voltage of comparator 104. The comparator 104 flips and its output is pulled low. At this time, due to the relatively large resistance value of resistor R1206, the base voltage of transistor Q1203 cannot reach the state to make it conduct. The bootstrap boost circuit loses the pulse, and the electricity of capacitor C4205 is discharged by resistor R3. The VGS voltage of MOS transistor 105 is lost, and at this time MOS transistor 105 is cut off, that is, this battery 101 group quits working, and other battery 101 groups will not be affected by this battery 101 group and can continue to supply power to the aircraft.

[0035] During the operation of microcontroller unit 106, this IO port mode will also be switched to AD mode. When switched to AD mode, the voltage of the base of transistor Q1203 can be detected. If the voltage is very low, it means that this battery 101 group has a fault.

[0036] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements can be made, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A power backup circuit for an aircraft, characterized in that, It includes a battery, a Hall element, wires, a comparator, a bootstrap boost circuit, a MOS transistor, an auxiliary power supply, and a microcontroller unit, where: The Hall element is used to monitor the state of the battery. Its power electrodes are connected to the positive pole of the auxiliary power supply, and its output electrode is connected to the input terminal of the comparator; The wire is connected to the battery and wound into a wire coil, and the wire coil is placed on one side of the Hall element; The comparator is used to judge the state of the battery according to the output voltage of the Hall element. Its power terminal is connected to the auxiliary power supply, and its output terminal is connected to the microcontroller unit and the bootstrap circuit; The bootstrap boost circuit includes a diode, a triode, a capacitor, and a resistor, and is used to generate a voltage higher than that of the battery. The positive pole of the diode is connected to the positive pole of the auxiliary power supply, its negative pole is connected to the capacitor, the collector of the triode is connected to the resistor, one port of the capacitor is connected to the collector of the triode, and its other port is connected to the diode; The MOS transistor is connected to the output terminal of the bootstrap boost circuit, and the MOS transistor uses the bootstrap boost circuit to control the gate; The microcontroller unit is used to control the working state of the bootstrap boost circuit and monitor the output of the comparator.

2. The aircraft power backup circuit according to claim 1, wherein When using an NMOS transistor, the current flows from the source to the drain. When using a PMOS transistor, the current flows from the drain to the source.

3. The aircraft power backup circuit according to claim 1, characterized in that The microcontroller unit further includes an IO port, and the IO port is used to establish a communication connection between the microcontroller unit and the aircraft control system.

4. The aircraft power backup circuit according to claim 3, characterized in that, The bootstrap boost circuit includes diode D1, diode D2, triode Q1, capacitor C3, capacitor C4, resistor R1, and resistor R2. The negative pole of diode D1 is connected to the collector of triode Q1, the positive pole of diode D2 is connected to the collector of triode Q1, the collector of triode Q1 is connected to the ports of capacitor C3, capacitor C4, and resistor R2, and its base is connected to one port of resistor R1.

5. The aircraft power backup circuit according to claim 4, characterized in that, The IO port is used to output pulses.

6. The aircraft power backup circuit according to claim 4, wherein When the IO port outputs a high level, the triode Q1 conducts, and the triode Q1, capacitor C3, diode D1, and the auxiliary power supply form a loop, and charge the capacitor C3.

7. The aircraft power backup circuit according to claim 4, characterized in that When the IO port outputs a low level, the capacitor C3, diode D2, and capacitor C4 form a loop, and charge the capacitor C4.

8. The aircraft power backup circuit according to claim 5, characterized in that, When the IO port outputs a pulse, the MOS transistor generates a conducting VGS voltage.

9. The aircraft power backup circuit according to claim 4, wherein The IO port is used to detect the voltage of the base of the triode Q1.

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