CN110901396A - Anti-mutual-charging circuit and method for power supply of multiple battery packs of four-rotor aircraft - Google Patents

Anti-mutual-charging circuit and method for power supply of multiple battery packs of four-rotor aircraft Download PDF

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Publication number
CN110901396A
CN110901396A CN201911168591.2A CN201911168591A CN110901396A CN 110901396 A CN110901396 A CN 110901396A CN 201911168591 A CN201911168591 A CN 201911168591A CN 110901396 A CN110901396 A CN 110901396A
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CN
China
Prior art keywords
circuit
mutual
battery pack
vbat
charging
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Pending
Application number
CN201911168591.2A
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Chinese (zh)
Inventor
田震
郭庆
杨红喜
刘东昌
王晓东
王君凤
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Electronic Technology Research Institute Of China Aerospace
Aerospace Age Feihong Technology Co Ltd
China Academy of Aerospace Electronics Technology Co Ltd
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Electronic Technology Research Institute Of China Aerospace
Aerospace Age Feihong Technology Co Ltd
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Priority to CN201911168591.2A priority Critical patent/CN110901396A/en
Publication of CN110901396A publication Critical patent/CN110901396A/en
Pending legal-status Critical Current

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    • 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
    • B60L3/00—Electric devices on electrically-propelled vehicles for safety purposes; Monitoring operating variables, e.g. speed, deceleration or energy consumption
    • B60L3/0023—Detecting, eliminating, remedying or compensating for drive train abnormalities, e.g. failures within the drive train
    • B60L3/0046—Detecting, eliminating, remedying or compensating for drive train abnormalities, e.g. failures within the drive train relating to electric energy storage systems, e.g. batteries or capacitors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • 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
    • 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
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention discloses an anti-mutual-charging circuit and an anti-mutual-charging method for supplying power to a plurality of battery packs of a four-rotor aircraft. The invention has the beneficial effects that: by adopting a modularized design idea, the circuit is simple and reliable, and the safety of the four-rotor aircraft is improved and the miniaturization of the circuit is realized; the voltage working range of the anti-mutual-charging protection circuit is wide. When the voltages of the N battery packs are inconsistent, the anti-mutual-charging protection circuit corresponding to the low-voltage battery pack automatically turns off the Q1, so that the purpose of protecting the battery packs and the electric equipment is achieved; the withstand voltage value, the internal resistance and the overcurrent capacity are comprehensively considered, the energy loss is reduced, and the current driving capacity is improved.

Description

Anti-mutual-charging circuit and method for power supply of multiple battery packs of four-rotor aircraft
Technical Field
The invention relates to a circuit and a method for preventing mutual charging for supplying power to a plurality of battery packs of a four-rotor aircraft, which can be widely applied to supplying power to the plurality of battery packs of the four-rotor aircraft.
Background
At present, a four-rotor aircraft adopts a direct-current power supply to supply power, and generally adopts a plurality of battery packs to be connected in parallel in order to improve the endurance time of the aircraft. When a plurality of battery packs are connected in parallel for power supply, if a voltage difference exists between the battery packs, the high-voltage battery pack module charges the low-voltage battery pack, and the charging has the following disadvantages:
1. the battery pack is influenced to normally supply power to the four-rotor electric equipment, when the four-rotor aircraft works, the power required by the rotation of the four-way motor is very high, if the battery pack cannot normally supply power, the four-way motor cannot output normal power, and the four-rotor aircraft cannot normally work;
2. the battery pack is charged mutually, the charging current generally reaches the maximum discharging current of the battery, the container causes the electric connector between the battery and the airborne electric equipment to be burnt, danger is generated, and meanwhile, the long-time large-current discharging of the battery can reduce the service life of the battery.
In order to prevent the mutual charging phenomenon between the battery packs, a schottky diode is added at the rear end of the battery pack, for example, three battery packs of a four-rotor aircraft are powered in parallel, as shown in fig. 1, VBAT1, VBAT2 and VBAT3 are output ends of the three battery packs respectively, D1, D2 and D3 are three schottky diodes, and VIN is an output end for supplying power to the electric equipment after the three batteries are converged.
The above method is widely used when a plurality of battery packs are connected in parallel and simultaneously supply power, but the design method has the following disadvantages:
1. the Schottky diode has limited over-current capability and cannot meet the use requirement of high current;
2. the energy loss of the Schottky diode is high, and the influence is caused on the endurance of the four-rotor aircraft.
3. Under the condition that a plurality of battery packs supply power, the endurance of the four-rotor aircraft can generally reach more than forty minutes, so that the Schottky diode is easy to generate heat after long-time work, the device is easy to damage, and the flight safety is enhanced.
Disclosure of Invention
The invention discloses an anti-mutual-charging circuit and an anti-mutual-charging method for supplying power to a plurality of battery packs of a four-rotor aircraft, and aims to solve any one of the above and other potential problems in the prior art.
In order to achieve the purpose, the technical scheme of the invention is as follows: the utility model provides a prevent mutual circuit of charging for four rotor aircraft polylith group battery power supplies, prevent mutual protection circuit setting between group battery and four rotor aircraft avionics equipment that charges, just prevent mutual protection circuit that charges and be located the front end of every battery group, four rotor aircraft avionics equipment sets up prevent mutual protection circuit's that charges rear end, every group battery all converge through preventing mutual circuit rectification and export and supply power for consumer.
Further, the mutual charge preventing circuit comprises an input protection and on-off control circuit and a converging and filtering circuit;
the input protection and on-off control circuit is used for adjusting the output of a power supply, increasing the reliability of a power supply system, and ensuring that current is stably transmitted from one path to the other path without oscillation; if the power supply fails or is short-circuited, the quick turn-off is carried out to reduce the reverse current transient state to the minimum, so that the battery pack and the electric equipment are protected from being damaged;
the confluence and filtering circuit is used for filtering input and output voltages, so that voltage oscillation is prevented, and the influence on rear-end electric equipment caused by overlarge ripples is avoided.
Further, the input protection and on-off control circuit comprises: a connection terminal VBAT +, a connection terminal VBAT-, U1 and Q1;
the connecting terminal VBAT + is connected with the anode of the single battery pack, the connecting terminal VBAT-is connected with the cathodes of all battery packs, and a pin 1 IN of U1 is connected with the connecting terminal VBAT +; a4-pin GATE pin of U1 is connected with a grid GATE pin of Q1, an 8-pin OUT pin and a 7-pin VDD pin of U1 are both connected with a 4-pin of Q1 to lead OUT a VIN end, the VIN end is connected into an electric circuit for the rear end of the quadrotor, pins 2, 3 and 6 of U1 are suspended, and the GND pin is connected with the cathode of a battery pack.
Further, the bus and filter circuit includes a capacitor C1, a capacitor C2, and a capacitor C3;
one end of each of the capacitor C1 and the capacitor C2 is connected with the connection terminal VBAT +, the other end of each of the capacitor C1 and the capacitor C2 is connected with the connection terminal VBAT-, one end of the capacitor C3 is connected with the pin 8 of the U1, and the other end of the capacitor C3 is connected with the connection terminal VBAT-.
Further, the capacitor C1, the capacitor C2 and the capacitor C3 are all ceramic dielectric capacitors.
Furthermore, the anti-mutual-charging circuit can meet the normal work of 10V-100V.
Another object of the present invention is to provide a control method for supplying power to an avionics device of a quad-rotor aircraft using the above anti-mutual charging circuit, the method comprising the steps of:
s1) arranging an anti-mutual-charging circuit at the front end of each battery pack, and supplying power between the four-rotor aircraft avionics equipment through the anti-mutual-charging circuits;
s2) the anti-mutual-charging circuit collects the voltage value VBAT of each battery pack in real time, the collected voltage value VBAT is compared with VIN in the anti-mutual-charging circuit respectively, and the Q1 in each anti-mutual-charging circuit is controlled to be turned on or turned off according to the comparison result, so that all the battery packs are rectified and converged and then output to the quad-rotor aircraft for power supply.
Further, the specific conditions in S2) are as follows:
if the voltage value VBAT of each battery pack is equal, VIN (VIN) is obtained, and Q1 in the anti-mutual-charging circuit of the battery pack is conducted to supply power to the circuit;
if the voltage value of one or more battery packs is VBATIs low inThen VIN is VBAT > VBATIs low inAt the moment, Q1 in the anti-mutual-charging circuit of the low-voltage battery pack is turned off, Q1 in the anti-mutual-charging circuits of other high-voltage battery packs are turned on, and the high-voltage battery pack is prevented from charging the low-voltage battery pack;
when the battery pack for power supply is continuously discharged, the voltage value VBAT of the discharged battery pack and the voltage value VBAT of the low-voltage battery packIs low inEqual to each other, VIN VBAT is obtainedIs low inAt this time, Q1 is conducted in the anti-mutual-charging circuits of all the battery packs, and power is supplied to the quad-rotor aircraft by means of avionics.
Further, the number of the battery packs is at least 2.
The utility model provides a four rotor crafts, be equipped with above-mentioned circuit of preventing charging each other on four rotor crafts's the power supply battery group.
The invention has the beneficial effects that: due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages:
(1) by adopting a modularized design idea, the circuit is simple and reliable, and the safety of the four-rotor aircraft is improved and the miniaturization of the circuit is realized;
(2) the voltage working range of the anti-mutual-charging protection circuit is wide. An ideal secondary tube controller with a wide working range and an N-channel MOSFET are selected to realize a wide working voltage range;
(3) the anti-mutual-charging protection circuit has high reliability. When the voltages of the N battery packs are inconsistent, the mutual charge prevention protection circuit corresponding to the low-voltage battery pack automatically turns off the MOSFET, so that the purpose of protecting the battery packs and the electric equipment is achieved;
(4) the invention has strong capability of outputting the driving current. By adopting the design idea of an ideal diode and reasonably selecting the N-channel MOSFET, the withstand voltage value, the internal resistance and the over-current capability are comprehensively considered, the energy loss is reduced, and the current driving capability is improved.
Drawings
Fig. 1 is a schematic diagram of a conventional anti-mutual-charging circuit in the prior art.
Fig. 2 is a working block diagram of an anti-mutual-charging circuit for supplying power to a plurality of battery packs of a quad-rotor aircraft according to the invention.
Fig. 3 is a schematic diagram of an anti-mutual-charging circuit for supplying power to a plurality of battery packs of a quad-rotor aircraft according to the present invention.
Detailed Description
The following combination prevents that mutual protection circuit that charges includes input protection and on-off control circuit, and it constitutes to converge circuit and filter circuit two parts, as shown in fig. 3, a prevent mutual circuit that charges for the power supply of four rotor craft polylith group battery, prevent that mutual protection circuit that charges sets up between group battery and four rotor craft avionics equipment, just prevent the front end that mutual protection circuit that charges is located every group battery, four rotor craft avionics equipment sets up prevent mutual protection circuit's rear end, every group battery all converges through preventing mutual circuit rectification and exports for consumer and supplies power.
Further, the mutual charge preventing circuit comprises an input protection and on-off control circuit and a converging and filtering circuit;
the input protection and on-off control circuit is used for adjusting the output of a power supply, increasing the reliability of a power supply system, and ensuring that current is stably transmitted from one path to the other path without oscillation; if the power supply fails or is short-circuited, the quick turn-off is carried out to reduce the reverse current transient state to the minimum, so that the battery pack and the electric equipment are protected from being damaged;
the confluence and filtering circuit is used for filtering input and output voltages, so that voltage oscillation is prevented, and the influence on rear-end electric equipment caused by overlarge ripples is avoided.
Further, the input protection and on-off control circuit comprises: a connection terminal VBAT +, a connection terminal VBAT-, U1 and Q1;
the connecting terminal VBAT + is connected with the anode of the single battery pack, the connecting terminal VBAT-is connected with the cathodes of all battery packs, and a pin 1 IN of U1 is connected with the connecting terminal VBAT +; a4-pin GATE pin of U1 is connected with a grid GATE pin of Q1, an 8-pin OUT pin and a 7-pin VDD pin of U1 are both connected with a 4-pin of Q1 to lead OUT a VIN end, the VIN end is connected into an electric circuit for the rear end of the quadrotor, pins 2, 3 and 6 of U1 are suspended, and the GND pin is connected with the cathode of a battery pack.
Further, the bus and filter circuit includes a capacitor C1, a capacitor C2, and a capacitor C3;
one end of each of the capacitor C1 and the capacitor C2 is connected with the connection terminal VBAT +, the other end of each of the capacitor C1 and the capacitor C2 is connected with the connection terminal VBAT-, one end of the capacitor C3 is connected with the pin 8 of the U1, and the other end of the capacitor C3 is connected with the connection terminal VBAT-.
Further, the capacitor C1, the capacitor C2 and the capacitor C3 are all ceramic dielectric capacitors.
Furthermore, the anti-mutual-charging circuit can meet the normal work of 10V-100V.
Another object of the present invention is to provide a method for controlling an anti-overcharging circuit for a quad-rotor aircraft powered by a plurality of battery packs, the method comprising the steps of:
s1) disposing the anti-overcharging circuit between a battery pack and a quad-rotor aircraft avionics device;
s2) the U1 collects the voltage VBAT of each battery pack in real time and collects the collected voltage VBATiAnd respectively comparing with VIN, controlling the Q1 in each circuit to be turned on or turned off according to the comparison result, avoiding the high-voltage battery pack from charging to the low voltage, and outputting all the battery packs after rectification and convergence to the four-rotor aircraft for power supply.
Further, the specific conditions in S2) are as follows:
if the voltage value VBAT of each battery pack is equal, VIN (VIN) is obtained, and Q1 in the anti-mutual-charging circuit of the battery pack is conducted to supply power to the circuit;
if the voltage value of one or more battery packs is VBATIs low inThen VIN is VBAT > VBATIs low inAt the moment, Q1 in the anti-mutual-charging circuit of the low-voltage battery pack is turned off, Q1 in the anti-mutual-charging circuits of other high-voltage battery packs are turned on, and the high-voltage battery pack is prevented from charging the low-voltage battery pack;
when the high-voltage battery pack is continuously discharged, the voltage value VBAT of the battery pack is equal to VBATIs low inThen VIN VBATIs low inMutual charging prevention of all battery packsAnd the Q1 in the road is conducted to supply power for the four-rotor aircraft to supply power for the avionics.
Further, the number of the battery packs is at least 2.
The utility model provides a four rotor crafts, be equipped with above-mentioned circuit of preventing charging each other on four rotor crafts's the power supply battery group.
The principle of the invention is as follows: the input protection and on-off control circuit mainly comprises a high-voltage ideal diode controller, the withstand voltage of a power supply end, an input end and an output end can reach 100V, the input protection and on-off control circuit can drive an external N-channel MOSFET to replace a Schottky diode, if VBAT plus is not less than VIN, Q1 is conducted, otherwise Q1 is turned off, the output of a power supply can be adjusted, the reliability of the power supply system is improved, the current is ensured to be stably transmitted to another path from one path, and the power supply is ensured not to generate oscillation. If power failure or short circuit, the controller will turn off fast and reduce the reverse current transient state to minimum, and protection group battery and consumer are not damaged, and circuit peripheral device is few, and the design is simple, has withstand voltage height, dead zone turn-off protection and the characteristics that the encapsulation is small.
2. The confluence circuit and the filter circuit mainly comprise an N-channel MOSFET and 3 ceramic dielectric capacitors. The overcurrent capacity of a single MOSFET can reach 300A, the internal resistance is only 0.67m omega, the MOSFET has the characteristics of strong overcurrent capacity, small internal resistance and small packaging volume, and the on-off of the drain electrode of the MOSFET is controlled by controlling the grid electrode of the MOSFET. The three ceramic dielectric capacitors are used for filtering input and output voltages, so that voltage oscillation is prevented, and the influence on rear-end electric equipment caused by overlarge ripples is prevented.
Example (b):
two battery packs supply power for the four-rotor aircraft simultaneously, two anti-mutual-charging protection circuits in fig. 3 need to be added, VBAT1 and VBAT2 are voltage input ends of the two battery packs respectively, high-voltage ideal diode controllers U1 and U2 compare battery voltages VBAT1 and VBAT2 with VIN respectively, and if VBAT1 is VBAT2, VIN is VBAT1 which is VBAT2, and Q1 and Q2 are both conducted to supply power for the circuit; if VBAT1 > VBAT2, VIN-VBAT 1 > VBAT2, Q1 is turned on, Q2 is turned off, VBAT1 is prevented from charging VBAT2, VBAT1 is discharged until VBAT 1-VBAT 2, VIN-VBAT 1-VBAT 2, Q1 and Q2 are all turned on to supply power to the circuit; if VBAT1 < VBAT2, VIN VBAT2 > -VBAT
VBAT1, Q2 is turned on, Q1 is turned off, VBAT2 is prevented from charging VBAT1, VBAT2 is discharged until VBAT1 is VBAT2, and VIN-VBAT 1 is VBAT2, Q1 and Q2 are all turned on to power the circuit.
In conclusion, the power input adaptability range of the invention is wide, if the embodiment can meet the normal work of 10V-100V, the power input requirement of the current four-rotor aircraft design can be met; the circuit is easy to realize, the number of single-path mutual-charge-preventing circuit devices is small, the modular design is realized, and the number of modules can be selected according to the number of the battery packs. The invention has strong output current, the energy consumption loss of the anti-mutual-charging circuit is small, and high-efficiency and large-current power output can be realized; the devices designed and selected by the invention fully consider the voltage, the current and the use environment, and the application reliability of the system is greatly improved.
The anti-mutual-charging circuit for supplying power to the plurality of battery packs of the four-rotor aircraft provided by the embodiment of the application is described in detail above. The above description of the embodiments is only for the purpose of helping to understand the method of the present application and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
As used in the specification and claims, certain terms are used to refer to particular components. As one skilled in the art will appreciate, manufacturers may refer to a component by different names. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. "substantially" means within an acceptable error range, and a person skilled in the art can solve the technical problem within a certain error range to substantially achieve the technical effect. The following description is of the preferred embodiment for carrying out the present application, and is made for the purpose of illustrating the general principles of the application and not for the purpose of limiting the scope of the application. The protection scope of the present application shall be defined by the appended claims.
It is also noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a good or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such good or system. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a commodity or system that includes the element.
It should be understood that the term "and/or" as used herein is merely one type of association that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
The foregoing description shows and describes several preferred embodiments of the present application, but as aforementioned, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the application as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the application, which is to be protected by the claims appended hereto.

Claims (10)

1. An anti-mutual-charging circuit for supplying power to a plurality of battery packs of a four-rotor aircraft is characterized by comprising an input protection and on-off control circuit, a confluence circuit and a filter circuit;
the input protection and on-off control circuit is used for adjusting the output of a power supply, increasing the reliability of a power supply system, ensuring that current is stably transmitted from one path to the other path and generating no oscillation; if the power supply fails or is short-circuited, the quick turn-off is carried out to reduce the reverse current transient state to the minimum, so that the battery pack and the electric equipment are protected from being damaged;
the confluence and filtering circuit is used for filtering input and output voltages, so that voltage oscillation is prevented, and the influence on rear-end electric equipment caused by overlarge ripples is avoided.
2. The anti-overcharging circuit of claim 1, wherein said input protection and on-off control circuit comprises: a connection terminal VBAT +, a connection terminal VBAT-, U1 and Q1;
the connecting terminal VBAT + is connected with the anode of the single battery pack, the connecting terminal VBAT-is connected with the cathodes of all battery packs, and the IN pin of U1 is connected with the connecting terminal VBAT +; the GATE pin of U1 is connected with the GATE pin of Q1, and OUT pin and VDD pin of U1 are connected with 4 feet of Q1, draw OUT VIN end, VIN end is connected into the electric circuit for the rear end of the quadrotor, 2 feet, 3 feet and 6 feet of U1 are suspended, and GND pin is connected with the negative pole of the battery pack.
3. The anti-overcharging circuit of claim 2, wherein said bus and filter circuit comprises a capacitor C1, a capacitor C2 and a capacitor C3;
one end of each of the capacitor C1 and the capacitor C2 is connected with the connecting terminal VBAT +, the other end of each of the capacitor C1 and the capacitor C2 is connected with the connecting terminal VBAT-, one end of the capacitor C3 is connected with the pin 8 of the U1, and the other end of the capacitor C3 is connected with the connecting terminal VBAT-.
4. The anti-mutual-charging circuit of claim 3, wherein the capacitor C1, the capacitor C2 and the capacitor C3 are all ceramic dielectric capacitors.
5. The anti-mutual-charging circuit according to any one of claims 1 to 4, wherein the anti-mutual-charging protection circuit is arranged between a battery pack and a quad-rotor aircraft avionic device, the anti-mutual-charging protection circuit is positioned at the front end of each battery pack, the quad-rotor aircraft avionic device is arranged at the rear end of the anti-mutual-charging protection circuit, and each battery pack is rectified and converged by the anti-mutual-charging protection circuit and then output to the electric equipment for supplying power.
6. The anti-overcharging circuit of claim 5, wherein said anti-overcharging circuit can satisfy 10V-100V normal operation.
7. A power supply control method of an anti-mutual-charging circuit according to any one of claims 1 to 4, characterized in that the method comprises the steps of:
s1) arranging an anti-mutual-charging circuit at the front end of each battery pack, and supplying power between the four-rotor aircraft avionics equipment through the anti-mutual-charging circuits;
s2) the anti-mutual-charging circuit collects the voltage value VBAT of each battery pack in real time, the collected voltage value VBAT is compared with VIN in the anti-mutual-charging circuit respectively, and the Q1 in each anti-mutual-charging circuit is controlled to be turned on or turned off according to the comparison result, so that all the battery packs are rectified and converged and then output to the quad-rotor aircraft for power supply.
8. The control method according to claim 7, wherein the specific conditions in S2) are:
if the voltage value VBAT of each battery pack is equal, VIN is obtained as VBAT, and Q1 in the anti-mutual-charging circuit of the battery pack is conducted to supply power to the circuit;
if the voltage value of one or more battery packs is VBATIs low inThen VIN is VBAT > VBATIs low inAt the moment, Q1 in the anti-mutual-charging circuit of the low-voltage battery pack is turned off, Q1 in the anti-mutual-charging circuits of other high-voltage battery packs are turned on, and the high-voltage battery pack is prevented from charging the low-voltage battery pack;
when the battery pack for power supply is continuously discharged, the voltage value VBAT of the discharged battery pack and the voltage value VBAT of the low-voltage battery packIs low inEqual to each other, VIN VBAT is obtainedIs low inAt this time, Q1 in the anti-mutual-charging circuit of all the battery packs is conductedAnd the power supply is provided for the avionics of the four-rotor aircraft.
9. The control method according to claim 8, wherein the number of the battery packs is at least 2.
10. A quad-rotor craft, characterized in that the anti-overcharging circuit of any one of claims 1-6 is provided on the battery pack of said quad-rotor craft.
CN201911168591.2A 2019-11-25 2019-11-25 Anti-mutual-charging circuit and method for power supply of multiple battery packs of four-rotor aircraft Pending CN110901396A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021212843A1 (en) * 2020-04-24 2021-10-28 深圳市大疆创新科技有限公司 Battery apparatus and charging and discharging protection circuit

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080285191A1 (en) * 2005-12-09 2008-11-20 Ricoh Company, Ltd. Backflow preventing circuit capable of preventing reverse current efficiently
CN202372918U (en) * 2011-11-30 2012-08-08 中国航空工业集团公司第六三一研究所 Fault isolation circuit
CN106300321A (en) * 2016-08-31 2017-01-04 四川升华电源科技有限公司 Power supply anti-back flow circuit
CN206685893U (en) * 2017-01-23 2017-11-28 中国第一汽车股份有限公司 A kind of power input protection circuit of the road vehicle controller based on discrete component
CN107800186A (en) * 2016-09-07 2018-03-13 亿航智能设备（广州）有限公司 The feedback and device of more rotor manned aircraft powers
CN109660121A (en) * 2019-01-09 2019-04-19 深圳航天东方红海特卫星有限公司 A kind of spaceborne DC-DC converter combining output circuit of low transmission power consumption
CN109755928A (en) * 2019-02-19 2019-05-14 深圳市科比特航空科技有限公司 Anti-reverse electromotive force circuit and unmanned plane
CN209313501U (en) * 2019-03-11 2019-08-27 成都迅翼卫通科技有限公司 A kind of double cell group parallel connection isolation circuit based on ideal diode

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080285191A1 (en) * 2005-12-09 2008-11-20 Ricoh Company, Ltd. Backflow preventing circuit capable of preventing reverse current efficiently
CN202372918U (en) * 2011-11-30 2012-08-08 中国航空工业集团公司第六三一研究所 Fault isolation circuit
CN106300321A (en) * 2016-08-31 2017-01-04 四川升华电源科技有限公司 Power supply anti-back flow circuit
CN107800186A (en) * 2016-09-07 2018-03-13 亿航智能设备（广州）有限公司 The feedback and device of more rotor manned aircraft powers
CN206685893U (en) * 2017-01-23 2017-11-28 中国第一汽车股份有限公司 A kind of power input protection circuit of the road vehicle controller based on discrete component
CN109660121A (en) * 2019-01-09 2019-04-19 深圳航天东方红海特卫星有限公司 A kind of spaceborne DC-DC converter combining output circuit of low transmission power consumption
CN109755928A (en) * 2019-02-19 2019-05-14 深圳市科比特航空科技有限公司 Anti-reverse electromotive force circuit and unmanned plane
CN209313501U (en) * 2019-03-11 2019-08-27 成都迅翼卫通科技有限公司 A kind of double cell group parallel connection isolation circuit based on ideal diode

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021212843A1 (en) * 2020-04-24 2021-10-28 深圳市大疆创新科技有限公司 Battery apparatus and charging and discharging protection circuit

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