CN115549269A - Power distribution system of double battery packs - Google Patents

Power distribution system of double battery packs Download PDF

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Publication number
CN115549269A
CN115549269A CN202211324265.8A CN202211324265A CN115549269A CN 115549269 A CN115549269 A CN 115549269A CN 202211324265 A CN202211324265 A CN 202211324265A CN 115549269 A CN115549269 A CN 115549269A
Authority
CN
China
Prior art keywords
switch
electrically connected
power distribution
unit
power
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202211324265.8A
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Chinese (zh)
Inventor
王放
徐安安
高成
王保堂
兰珂文
郝亚超
李岩
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hubei Xinghang Aviation Technology Co ltd
Original Assignee
Hubei Xinghang Aviation Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hubei Xinghang Aviation Technology Co ltd filed Critical Hubei Xinghang Aviation Technology Co ltd
Priority to CN202211324265.8A priority Critical patent/CN115549269A/en
Publication of CN115549269A publication Critical patent/CN115549269A/en
Pending legal-status Critical Current

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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
    • H02J7/14—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/42—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
    • H01M10/4207—Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells for several batteries or cells simultaneously or sequentially
    • 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
    • H02J1/00—Circuit arrangements for dc mains or dc distribution networks
    • H02J1/10—Parallel operation of dc sources
    • H02J1/109—Scheduling or re-scheduling the operation of the DC sources in a particular order, e.g. connecting or disconnecting the sources in sequential, alternating or in subsets, to meet a given demand
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M1/00—Details of apparatus for conversion
    • H02M1/0083—Converters characterised by their input or output configuration
    • H02M1/009—Converters characterised by their input or output configuration having two or more independently controlled outputs
    • 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
    • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
    • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
    • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts

Abstract

The invention discloses a power distribution system of a double battery pack, which comprises: the power supply unit is electrically connected with the power distribution unit; the first load unit is electrically connected with the power distribution unit; the second load unit is electrically connected with the power distribution unit; the power supply unit provides power, and the power distribution unit distributes the power to the first load unit and/or the second load unit; the power system and the control system are powered on at different times, primary distribution of power provided by the power supply unit is completed, current crosstalk and electromagnetic interference between the first load unit and the second load unit are avoided, and flight safety of the unmanned helicopter is improved.

Description

Power distribution system of double battery packs
Technical Field
The invention relates to the technical field of power distribution systems, in particular to a power distribution system with double battery packs.
Background
The power distribution system of the unmanned helicopter consists of a power supply, a protection device and a power distribution device, and is used for transmitting and distributing electric energy generated by different power supplies in the unmanned helicopter to various electric equipment. In the flight process, when a main power supply system cannot work normally, an emergency power supply must be used for supplying power to key electric equipment such as a flight control system, measurement and control equipment and the like of the unmanned helicopter so as to ensure flight safety and return as soon as possible.
The power distribution system of the existing unmanned helicopter usually adopts a single battery pack power supply mode, and adopts a single-voltage battery pack to simultaneously power on a power system and a control system. Such as: power and radio frequency equipment often interfere with autopilots, load cameras, servo steering engines, and the like.
In view of the above, it is desirable to provide a novel dual-battery power distribution system to overcome the above-mentioned drawbacks.
Disclosure of Invention
The invention aims to provide a power distribution system with double battery packs, which can realize power distribution provided by a power supply unit and avoid current crosstalk and electromagnetic interference among load units.
In order to achieve the above object, the present invention provides a power distribution system of a dual battery pack, comprising:
a power supply unit for supplying power to the power supply unit,
the power distribution unit is electrically connected with the power supply unit;
the first load unit is electrically connected with the power distribution unit;
the second load unit is electrically connected with the power distribution unit; the power supply unit provides power, and the power distribution unit distributes the power to the first load unit and/or the second load unit.
Preferably, the power supply unit includes a distribution box, and a first generator, a first lithium battery, a second generator and a second lithium battery installed in the distribution box, the distribution unit includes a first current collecting bar and a second current collecting bar, the first current collecting bar and the second current collecting bar are installed in the distribution box, the first generator is electrically connected with the first lithium battery and the first current collecting bar, the first load unit is electrically connected with the first current collecting bar, the second generator is electrically connected with the second lithium battery and the second current collecting bar, and the second load unit is electrically connected with the second current collecting bar.
Preferably, a first positive pole electrifying plate, a first negative pole electrifying plate, a second positive pole electrifying plate and a second negative pole electrifying plate are further arranged in the distribution box; the power distribution box is also internally provided with two input aerial sockets and a control switch, wherein the two input aerial sockets are respectively a first input aerial socket and a second input aerial socket;
the control switches comprise a power supply main electric switch, an accelerator switch, an oil pump switch, a flight control switch, a steering engine switch and a fan switch; the positive electrode of the second lithium battery is electrically connected with the positive electrode of the second generator and the second input aerial plug, the second input aerial plug is connected with the second positive electrode electrifying plate through the second current collecting bar, and the power supply main electric switch is electrically connected with the accelerator switch and the oil pump switch; the first lithium battery positive electrode and the first generator positive electrode are connected with the first input aerial plug, the first input aerial plug is connected with the first positive electrode electrifying plate through the first current collecting bar, and the flight control switch, the steering engine switch and the fan switch are electrically connected with the first positive electrode electrifying plate.
Preferably, the first input aerial plug is electrically connected with the flight control switch, the steering engine switch and the fan switch, the flight control switch is electrically connected with the flight control device, the steering engine switch is electrically connected with the steering engine box in the steering engine box, the fan switch is electrically connected with the fan, and a lubricating oil radiator and a cooling liquid radiator are installed at the position adjacent to the fan.
Preferably, a fuse box is connected between the second generator and the second input aerial plug.
Preferably, a relay is connected between the fan switch and the fan.
Compared with the prior art, beneficial effect lies in: the power system and the control system are powered on at different times, primary distribution of power provided by the power supply unit is completed, current crosstalk and electromagnetic interference between the first load unit and the second load unit are avoided, and flight safety of the unmanned helicopter is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic diagram of a power distribution system of a dual battery pack according to the present invention.
Fig. 2 is a partial schematic diagram of the power distribution system of the dual battery pack shown in fig. 1.
Reference numerals are as follows: 1. a power supply unit; 2. a power distribution unit; 3. a first load unit; 4. a second load unit; 110. a first generator; 111. a first lithium battery; 112. a second generator; 113. a second lithium battery; 114. a first collector bar; 115. a second collector bar; 116. a first positive electrode current-carrying plate; 117. a first negative electrode current-carrying plate; 118. a second positive electrode current-carrying plate; 119. a second negative electrode current-carrying plate; 12. a first input navigation plug; 13. a second input navigation plug; 14. a 12V power supply main electric switch; 15. an accelerator switch; 16. an oil pump switch; 17. a flight control switch; 18. a steering engine switch; 19. a fan switch; 101. a flight control device; 102. the steering engine box is inserted; 103. a fan; 104. a lubricant radiator; 105. a coolant radiator; 106. a three-terminal voltage stabilizer; 107. a relay.
Detailed Description
In order to make the objects, technical solutions and advantageous effects of the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and the detailed description. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are given by way of illustration only and not by way of limitation.
Referring to fig. 1 to 2, the present invention provides a power distribution system with two battery packs, including:
the power supply unit 1 is provided with a power supply unit,
the power distribution unit 2 is electrically connected with the power supply unit 1;
the first load unit 3, the first load unit 3 is electrically connected with the power distribution unit 2;
and the second load unit 4, wherein the second load unit 4 is electrically connected with the power distribution unit 2.
The power supply unit 1 provides a power supply, the power distribution unit 2 distributes the power supply to the first load unit 3 and/or the second load unit 4, so that the power system and the control system are powered on at different times, the power supply provided by the power supply unit 1 is distributed at one time, current crosstalk and electromagnetic interference between the first load unit 3 and the second load unit 4 are avoided, and the flight safety of the unmanned helicopter is improved.
In one embodiment, the power supply unit 1 includes a distribution box, and a first generator 110 (24V), a first lithium battery 111 (24V), a second generator 112 (12V), and a second lithium battery 113 (12V) installed in the distribution box, the distribution unit 2 includes a first collector bar 114 and a second collector bar 115, the first collector bar 114 and the second collector bar 115 are installed in the distribution box, the first generator 110 is electrically connected to the first lithium battery 111 and the first collector bar 114, the first load unit 3 is electrically connected to the first collector bar 114, the second generator 112 is electrically connected to the second lithium battery 113 and the second collector bar 115, and the second load unit 4 is electrically connected to the second collector bar 115, so as to complete secondary distribution of power provided to the power supply unit 1.
In one embodiment, a first positive electrode conduction plate 116, a first negative electrode conduction plate 117, a second positive electrode conduction plate 118 and a second negative electrode conduction plate 119 are further disposed in the power distribution box; the power distribution box is also internally provided with two input aerial sockets and a control switch, wherein the two input aerial sockets are respectively a first input aerial socket 12 (24V) and a second input aerial socket 13 (12V);
the control switches comprise a 12V power supply main electric switch 14, an accelerator switch 15, an oil pump switch 16, a flight control switch 17, a steering engine switch 18 and a fan switch 19; the positive electrode of the second lithium battery 113 is electrically connected with the positive electrode of the second generator 112 and a second input aerial plug 13 (12V) of the unmanned helicopter, the second input aerial plug 13 (12V) is connected with a second positive electrode electrifying plate 118 through a second current collecting bar 115, the 12V power supply main electric switch 14 is electrically connected with the accelerator switch 15 and the oil pump switch 16, and the second positive electrode electrifying plate 118 is connected with a second negative electrode electrifying plate 119 to form a loop; the positive electrode of the first lithium battery 111 and the positive electrode of the first generator 110 are connected with a first input aerial plug 12 (24V) of the unmanned helicopter, the first input aerial plug 12 (24V) is connected with a first positive electrode electrifying plate 116 through a first current collecting bar 114, the flight control switch 17, the steering engine switch and the fan switch 19 are electrically connected with the first positive electrode electrifying plate 116, and the first positive electrode electrifying plate 116 is connected with a first negative electrode electrifying plate 117 to form a loop.
In one embodiment, the first load unit 3 includes a flight control device, a rudder box, a fan, a coolant radiator, and a lubricant radiator; the second load unit 4 comprises an accelerator and an oil pump, and the distribution box is also provided with a flight control aerial plug, a steering engine box aerial plug 102, a fan aerial plug, an accelerator aerial plug and an oil pump aerial plug; the flight control device, the steering engine box, the fan, the accelerator and the oil pump are respectively electrically connected with the flight control aerial plug, the steering engine box aerial plug, the fan aerial plug, the accelerator aerial plug and the oil pump aerial plug.
In one embodiment, the first load unit 3 and the second load unit 4 of the unmanned helicopter are respectively required by 24V and 12V power voltages, when the unmanned helicopter is in a ground starting state, the power of the first generator 110 is directly transmitted to the first positive pole electrifying plate 116 by the first current collecting bar 114 to complete primary power supply, a fuse box is connected between the second generator 112 and the second input aerial plug 13 (12V) to ensure that the second generator 112 generates power after completing a series of work tasks such as self-test, and if a fault occurs, a fuse in the fuse box is fused to ensure the safety of the power supply of the second load unit 4, so that a protection effect can be achieved.
In one embodiment, the first input aviation plug 12 (24V) is electrically connected to the flight control switch 17, the steering engine switch and the fan switch 19, the flight control switch 17 is electrically connected to the flight control device 101, the steering engine switch is electrically connected to the steering engine box aviation plug 102 in the steering engine box, the fan switch 19 is electrically connected to the fan 103, a lubricating oil radiator 104 and a cooling liquid radiator 105 are installed at a position adjacent to the fan 103, and the heat dissipation effect of the lubricating oil radiator 104 and the cooling liquid radiator 105 is improved by the fan 103.
In one embodiment, a three-terminal regulator 106 is connected between the flight control switch 17 and the flight control device 101, so as to reduce the voltage of 24V to 12V and divide the voltage into three voltages; one voltage is used for supplying power to a signal control board in the steering engine box, the other voltage is used for supplying power to a circuit board in the signal acquisition box, and the rest voltage is connected with a voltage reducer to reduce the voltage of 12V to 5V again to supply power to the flight control device 101.
In one embodiment, a relay 107 is connected between the fan switch 19 and the fan 103 to ensure the safety of the fan 103.
When the unmanned helicopter is used, the power supply provided by the power supply unit 1 is subjected to secondary distribution, so that the power system and the control system are not electrified at the same time, the current crosstalk and the electromagnetic interference between the first load unit 3 and the second load unit 4 can be avoided, and the flight safety of the unmanned helicopter is improved.
The invention is not limited solely to that described in the specification and embodiments, and additional advantages and modifications will readily occur to those skilled in the art, so that the invention is not limited to the specific details, representative apparatus, and examples shown and described herein, without departing from the spirit and scope of the general concept as defined by the appended claims and their equivalents.

Claims (6)

1. A dual battery pack power distribution system, comprising:
a power supply unit (1),
the power distribution unit (2), the power distribution unit (2) is electrically connected with the power supply unit (1);
a first load unit (3), the first load unit (3) being electrically connected with the power distribution unit (2);
a second load unit (4), the second load unit (4) being electrically connected to the power distribution unit (2); the power supply unit (1) provides power, and the power distribution unit (2) distributes power to the first load unit (3) and/or the second load unit (4).
2. The power distribution system of a double battery pack according to claim 1, wherein the power supply unit (1) comprises a distribution box and a first generator (110), a first lithium battery (111), a second generator (112) and a second lithium battery (113) mounted in the distribution box, the distribution unit (2) comprises a first collector bar (114) and a second collector bar (115), the first collector bar (114) and the second collector bar (115) are mounted in the distribution box, the first generator (110) is electrically connected with the first lithium battery (111) and the first collector bar (114), the first load unit (3) is electrically connected with the first collector bar (114), the second generator (112) is electrically connected with the second lithium battery (113) and the second collector bar (115), and the second load unit (4) is electrically connected with the second collector bar (115).
3. The electric power distribution system of the double battery pack according to claim 2, wherein a first positive pole energizing plate (116), a first negative pole energizing plate (117), a second positive pole energizing plate (118), and a second negative pole energizing plate (119) are further provided in the power distribution box; the power distribution box is also internally provided with two input aerial sockets and a control switch, and the two input aerial sockets are a first input aerial socket (12) and a second input aerial socket (13) respectively;
the control switches comprise a power supply main electric switch (14), an accelerator switch (15), an oil pump switch (16), a flight control switch (17), a steering engine switch (18) and a fan switch (19); the positive electrode of the second lithium battery (113) is electrically connected with the positive electrode of the second generator (112) and the second input aerial plug (13), the second input aerial plug (13) is connected with a second positive electrode electrifying plate (118) through a second current collecting bar (115), and the power supply main electric switch (14) is electrically connected with the accelerator switch (15) and the oil pump switch (16); the positive electrode of the first lithium battery (111) and the positive electrode of the first generator (110) are connected with the first input aerial plug (12), the first input aerial plug (12) is connected with the first positive electrode electrifying plate (116) through the first current collecting bar (114), and the flight control switch (17), the steering engine switch (18) and the fan switch (19) are electrically connected with the first positive electrode electrifying plate (116).
4. The electric power distribution system of the double battery pack as claimed in claim 3, wherein the first input aerial plug (12) is electrically connected with the flight control switch (17), the steering engine switch (18) and the fan switch (19), the flight control switch (17) is electrically connected with the flight control device (101), the steering engine switch (18) is electrically connected with the steering engine box aerial plug (102) in the steering engine box (11), the fan switch (19) is electrically connected with the fan (103), and a lubricating oil radiator (104) and a cooling liquid radiator (105) are installed at a position adjacent to the fan (103).
5. The power distribution system of a double battery as set forth in claim 1, characterized in that a fuse box is connected between the second generator (112) and the second input aerial device (13).
6. The electric power distribution system of the double battery pack according to claim 1, wherein a relay (107) is connected between the fan switch (19) and the fan (103).
CN202211324265.8A 2022-10-27 2022-10-27 Power distribution system of double battery packs Pending CN115549269A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211324265.8A CN115549269A (en) 2022-10-27 2022-10-27 Power distribution system of double battery packs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211324265.8A CN115549269A (en) 2022-10-27 2022-10-27 Power distribution system of double battery packs

Publications (1)

Publication Number Publication Date
CN115549269A true CN115549269A (en) 2022-12-30

Family

ID=84717717

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211324265.8A Pending CN115549269A (en) 2022-10-27 2022-10-27 Power distribution system of double battery packs

Country Status (1)

Country Link
CN (1) CN115549269A (en)

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