CN113852169A - Low-voltage power supply device of electric airplane - Google Patents
Low-voltage power supply device of electric airplane Download PDFInfo
- Publication number
- CN113852169A CN113852169A CN202111254875.0A CN202111254875A CN113852169A CN 113852169 A CN113852169 A CN 113852169A CN 202111254875 A CN202111254875 A CN 202111254875A CN 113852169 A CN113852169 A CN 113852169A
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- China
- Prior art keywords
- voltage
- low
- battery
- electric
- dcdc
- 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
Links
- HEZMWWAKWCSUCB-PHDIDXHHSA-N (3R,4R)-3,4-dihydroxycyclohexa-1,5-diene-1-carboxylic acid Chemical compound O[C@@H]1C=CC(C(O)=O)=C[C@H]1O HEZMWWAKWCSUCB-PHDIDXHHSA-N 0.000 claims abstract description 21
- 230000002860 competitive effect Effects 0.000 claims description 2
- 238000002955 isolation Methods 0.000 claims description 2
- 230000009977 dual effect Effects 0.000 abstract 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000010485 coping Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- 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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam 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
- H02J7/34—Parallel operation in networks using both storage and other DC sources, e.g. providing buffering
-
- 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
- H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
- H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
- H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
- H02J9/061—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for DC powered loads
-
- 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
- H02J2207/00—Indexing scheme relating to details of circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J2207/20—Charging or discharging characterised by the power electronics converter
-
- 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
- Y02T50/40—Weight reduction
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a low-voltage power supply device of an electric airplane, which comprises a high-voltage battery, wherein the high-voltage battery is arranged in the electric airplane, and a high-voltage-to-low-voltage DCDC is arranged in the electric airplane; an APU battery mounted to an interior of the electric aircraft, wherein the interior of the electric aircraft is mounted with a low voltage load. This electric aircraft's low pressure power supply unit to small-size electric aircraft because its load is low, the characteristics that weight surplus is little, need reduce the weight of the inside load-bearing member of electric aircraft, adopts dual supply simultaneously, two low-voltage power converter's design, ensures that low pressure power supply system or DCDC power converter still can normally work after the single-point trouble appears, increases electric aircraft's security.
Description
Technical Field
The invention relates to the technical field of battery pack correlation, in particular to a low-voltage power supply device of an electric airplane.
Background
Can install power battery package in small-size electric aircraft, supply power for small-size electric aircraft through power battery package for small-size electric aircraft can work, and the style that is applicable to small-size electric aircraft's battery package on the market at present is various.
However, in a low-voltage power supply device of a general electric airplane, a small-sized electric airplane often suffers from the disadvantages of heavy weight, low specific energy, heavy backup cost and the like due to the characteristics of low load and small weight margin, and meanwhile, a single-branch battery and a power converter often suffer from the trouble of losing low-voltage power supply after single-point failure, so that the safety of the whole airplane is reduced, and the power supply failure response capability is insufficient.
Disclosure of Invention
The invention aims to provide a low-voltage power supply device of an electric airplane, which aims to solve the problems that most of low-voltage power supply devices of the electric airplanes proposed in the background art are small-sized electric airplanes, due to the characteristics of low load and small weight margin, the use of a lead-acid battery as a standby power supply often has the defects of heavy weight, low specific energy, high backup payment weight cost and the like, and meanwhile, a single-branch battery and a power converter often have the trouble of losing low-voltage power supply after single-point failure, so that the safety of the whole machine is reduced, and the power supply failure coping capability is insufficient.
In order to achieve the purpose, the invention provides the following technical scheme: the low-voltage power supply device of the electric airplane comprises a high-voltage battery, a high-voltage power supply unit and a low-voltage power supply unit, wherein the high-voltage battery is installed inside the electric airplane;
the battery of the APU is installed inside the electric aircraft and supplies power to low-voltage loads installed inside the electric aircraft.
Preferably, the high-voltage to low-voltage DCDC is arranged in 2 groups in the electric aircraft in a vertically symmetrical manner, and simultaneously, 2 groups of APU batteries are arranged in the aircraft in a vertically symmetrical manner.
Compared with the prior art, the invention has the beneficial effects that: according to the low-voltage power supply device of the electric airplane, the small-sized electric airplane has the characteristics of low load and small weight margin, the weight of an internal bearing component of the electric airplane needs to be reduced, and meanwhile, the design idea of double power supplies and double low-voltage power converters is adopted, so that the low-voltage battery system or the DCDC power converter can still normally work after a single-point fault occurs, and the safety of the electric airplane is improved;
1. the electric aircraft is provided with 2 groups of APU batteries which are lithium batteries and are arranged in the aircraft in a vertically symmetrical manner, so that the weight of the internal bearing component of the electric aircraft can be reduced;
2. the high-voltage-to-low-voltage DCDC power converter is arranged, and the high-voltage-to-low-voltage DCDC power converter is provided with 2 groups in the electric airplane in an up-down symmetrical mode, so that the low-voltage battery system or the DCDC power converter can still normally work after single-point faults occur, and the safety of the electric airplane is improved.
Drawings
FIG. 1 is a schematic view of the structure of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts based on the embodiments of the present invention belong to the protection scope of the present invention.
Referring to fig. 1, the present invention provides a technical solution: when the low-voltage power supply device of the electric airplane is used, the APU battery is a lithium battery with higher energy density which is greater than 270Wh/Kg (power electronic device) in the figure, and the power electronic device based on silicon carbide can lighten the weight of a module in the figure to the maximum extent, reduce the efficiency loss of an electric system and further facilitate the reduction of the weight of a bearing component in the electric airplane;
referring to fig. 1, when the high voltage battery fails, energy is transferred to the high voltage to low voltage DCDC, energy is transferred to the low voltage load through the high voltage to low voltage DCDC, and when the APU battery operates, electric energy is transferred to the low voltage load, wherein 2 groups of high-voltage to low-voltage DCDC and APU batteries are arranged in the electric aircraft, so that in the high-voltage batteries, or under the condition that any high-voltage to low-voltage DCDC or APU battery fails, the aircraft control module still has a complete control function on low-voltage devices (such as a control surface), so that the electric aircraft can still normally work, wherein the high voltage to low voltage DCDC realizes the electrical isolation and the voltage following, ensures the competitive power supply relationship with the APU battery, when the electric airplane is idle, the APU battery can be charged, and the function of supplying power to the pressing load cannot be influenced by the functional failure of any one of the high-voltage battery, the 2 groups of high-voltage-to-low-voltage DCDC and the 2 groups of APU batteries, which is the working principle of the low-voltage power supply device of the electric airplane.
The standard parts used in the invention can be purchased from the market, the special-shaped parts can be customized according to the description of the specification and the accompanying drawings, the specific connection mode of each part adopts conventional means such as bolts, rivets, welding and the like mature in the prior art, the machinery, parts and equipment adopt conventional models in the prior art, and the circuit connection adopts the conventional connection mode in the prior art, and the details are not described, and the content not described in detail in the specification belongs to the prior art known by persons skilled in the art.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (2)
1. A low-voltage power supply device for an electric aircraft, characterized in that it comprises:
the high-voltage battery is installed inside the electric airplane, and a high-voltage-to-low-voltage DCDC is installed inside the electric airplane;
the battery of the APU is arranged in the electric aircraft, so that power can be supplied to low-voltage loads arranged in the electric aircraft;
the high-voltage to low-voltage DCDC is provided with 2 groups of batteries which are vertically symmetrical in the electric airplane, and 2 groups of APU batteries are vertically symmetrical in the airplane.
2. A low-voltage power supply device for an electric aircraft according to claim 1, characterized in that said battery pack operates according to the principle: the high-voltage battery transfers energy to the high-voltage to low-voltage DCDC when working, the energy is transferred to the low-voltage load through the high-voltage to low-voltage DCDC, and the APU battery transfers electric energy to the low-voltage load when working, wherein 2 groups of the high-voltage to low-voltage DCDC and the APU battery are arranged in the electric aircraft, so that under the condition that the high-voltage battery, or any one of the high-voltage to low-voltage DCDC or the APU battery is invalid, the aircraft control module still has a complete control function on a low-voltage device, and the electric aircraft can still work normally, wherein the high-voltage to low-voltage DCDC realizes electrical isolation and voltage following, a competitive power supply relation with the APU battery is ensured, when in idle, the APU battery can be charged, and any one of the high-voltage battery, the 2 groups of high-voltage to low-voltage DCDC and the 2 groups of APU batteries is invalid, and the function of supplying power to the pressing load is not influenced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111254875.0A CN113852169A (en) | 2021-10-27 | 2021-10-27 | Low-voltage power supply device of electric airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111254875.0A CN113852169A (en) | 2021-10-27 | 2021-10-27 | Low-voltage power supply device of electric airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113852169A true CN113852169A (en) | 2021-12-28 |
Family
ID=78983213
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111254875.0A Pending CN113852169A (en) | 2021-10-27 | 2021-10-27 | Low-voltage power supply device of electric airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113852169A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100038961A1 (en) * | 2007-11-14 | 2010-02-18 | Rocco Divito | Enhanced dc electric main engine start system |
| US20160036220A1 (en) * | 2014-08-01 | 2016-02-04 | Thales | Electrical network of an aircraft |
| US20160107758A1 (en) * | 2013-06-07 | 2016-04-21 | Airbus Group Sas | Electrical power supply device for aircraft with electric propulsion |
| CN106532916A (en) * | 2016-12-07 | 2017-03-22 | 中国直升机设计研究所 | Parallel power supply control method for storage battery packs |
| US20190391577A1 (en) * | 2018-06-20 | 2019-12-26 | Faraday&Future Inc. | Redundant low-voltage battery system operation in electric vehicles |
| CN110682877A (en) * | 2018-07-06 | 2020-01-14 | 福特全球技术公司 | Autonomous vehicle critical load backup |
| CN110697057A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Unmanned helicopter electrical power generating system |
| CN214112886U (en) * | 2020-12-25 | 2021-09-03 | 辽宁通用航空研究院 | Electric propulsion electric system suitable for new energy airplane |
-
2021
- 2021-10-27 CN CN202111254875.0A patent/CN113852169A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100038961A1 (en) * | 2007-11-14 | 2010-02-18 | Rocco Divito | Enhanced dc electric main engine start system |
| US20160107758A1 (en) * | 2013-06-07 | 2016-04-21 | Airbus Group Sas | Electrical power supply device for aircraft with electric propulsion |
| US20160036220A1 (en) * | 2014-08-01 | 2016-02-04 | Thales | Electrical network of an aircraft |
| CN106532916A (en) * | 2016-12-07 | 2017-03-22 | 中国直升机设计研究所 | Parallel power supply control method for storage battery packs |
| US20190391577A1 (en) * | 2018-06-20 | 2019-12-26 | Faraday&Future Inc. | Redundant low-voltage battery system operation in electric vehicles |
| CN110682877A (en) * | 2018-07-06 | 2020-01-14 | 福特全球技术公司 | Autonomous vehicle critical load backup |
| CN110697057A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Unmanned helicopter electrical power generating system |
| CN214112886U (en) * | 2020-12-25 | 2021-09-03 | 辽宁通用航空研究院 | Electric propulsion electric system suitable for new energy airplane |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211228 |
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| RJ01 | Rejection of invention patent application after publication |