CN114162335A - Near space vehicle energy storage battery thermal management system - Google Patents
Near space vehicle energy storage battery thermal management system Download PDFInfo
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- CN114162335A CN114162335A CN202010950549.2A CN202010950549A CN114162335A CN 114162335 A CN114162335 A CN 114162335A CN 202010950549 A CN202010950549 A CN 202010950549A CN 114162335 A CN114162335 A CN 114162335A
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- 238000004146 energy storage Methods 0.000 title claims abstract description 53
- 239000000178 monomer Substances 0.000 claims abstract description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 20
- 239000012774 insulation material Substances 0.000 claims abstract description 13
- 239000000835 fiber Substances 0.000 claims description 5
- 238000003491 array Methods 0.000 claims description 4
- 239000004964 aerogel Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 229920006300 shrink film Polymers 0.000 claims description 2
- 210000004027 cell Anatomy 0.000 description 8
- 239000002390 adhesive tape Substances 0.000 description 6
- 239000011810 insulating material Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 230000017525 heat dissipation Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004321 preservation Methods 0.000 description 2
- 210000000352 storage cell Anatomy 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
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Classifications
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- 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
-
- 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
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
-
- 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
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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- 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
- H01M10/48—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
- H01M10/486—Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte for measuring temperature
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- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
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- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/615—Heating or keeping warm
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/656—Means for temperature control structurally associated with the cells characterised by the type of heat-exchange fluid
- H01M10/6561—Gases
- H01M10/6563—Gases with forced flow, e.g. by blowers
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/657—Means for temperature control structurally associated with the cells by electric or electromagnetic means
-
- 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
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/658—Means for temperature control structurally associated with the cells by thermal insulation or shielding
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Secondary Cells (AREA)
Abstract
The invention provides an energy storage battery thermal management system of a near space vehicle, which comprises at least two battery units, wherein the front ends and the rear ends of the battery units are respectively fixed through a front cover and a rear cover, an air channel is formed between the adjacent battery units, heat insulation materials wrap the outside of the battery units, an opening cover is arranged on the heat insulation materials at the top of each air channel, and a fan is arranged at the position of the rear cover corresponding to an air channel inlet. Meanwhile, each battery monomer forming the battery unit is provided with a heating film and a temperature sensor, and the battery management system can start the heating film or the fan according to the monitored temperature of the battery monomer to control the temperature of the energy storage battery. The invention has simple structure and feasibility, can meet the performance index requirements of the near space unmanned aerial vehicle, and has better thermal control capability.
Description
Technical Field
The invention belongs to the technical field of aerospace energy systems, and particularly relates to a thermal management system for an energy storage battery of a near space aircraft.
Background
Solar energy unmanned aerial vehicle mainly constitutes energy system with solar energy collection system and energy storage battery, and energy storage battery technical level has directly decided the energy that solar energy unmanned aerial vehicle can store and utilize, is the key technology that realizes solar energy unmanned aerial vehicle and lasts the flight round clock. The environmental adaptability of the energy storage battery must be considered by solar unmanned aerial vehicles and other adjacent space or high-altitude aircrafts adopting the energy storage battery.
In the use of energy storage cells, the power margin of high energy ratio energy storage cells depends largely on the control capability of thermal management. Because the near space aircraft faces the huge temperature difference between the ground and the high altitude, and the energy storage battery faces the heat management problems of uneven temperature distribution, overhigh local temperature, difficult low-temperature discharge, difficult heat dissipation and the like in the use process, the service performance, the service life and the safety of the energy storage battery are seriously influenced. In addition, because the requirement on the energy-to-weight ratio of the near space vehicle is higher during long voyage, the traditional battery monomer can not meet the requirement on the energy-to-weight ratio, and a novel high-energy-ratio soft package battery monomer is required to be adopted as the monomer of the energy storage battery, but the heat dissipation of the soft package battery is large, and the requirement on the thermal control capacity of the energy storage battery is higher. Therefore, in order to deal with the thermal problem of the energy storage battery, the energy storage battery needs to be subjected to a thermal management design so as to improve the thermal characteristics of the battery.
The design of the energy storage battery thermal management system is a decisive external factor for ensuring the safe operation of the energy storage battery, is also a key point for improving performance indexes such as the service life of the energy storage battery, and is directly related to the conformity of the energy storage battery and a target use environment. Therefore, a need exists for an efficient thermal management system for an energy storage battery of a near space vehicle.
Disclosure of Invention
Aiming at the technical problem that the energy storage battery of the adjacent space aircraft is lack of effective thermal management in the prior art, the invention provides the thermal management system of the energy storage battery of the adjacent space aircraft, which has a simple structure and better thermal control performance and reliability.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a thermal management system for an energy storage battery of a near space vehicle comprises a battery unit, a front cover, a rear cover, a fan, a heating film, a temperature sensor, a thermal insulation material and a top opening cover; the battery unit comprises at least two battery units, wherein the front end and the rear end of each battery unit are fixed through a front cover and a rear cover respectively, an air channel is formed between every two adjacent battery units, heat insulation materials are wrapped outside the plurality of battery units, an opening cover is arranged on the heat insulation materials at the top of each air channel, and a fan is installed on the rear cover corresponding to an opening of the air channel; the battery unit is of a cuboid structure formed by arranging a plurality of battery monomers, and one side of each battery monomer is provided with a heating film and a temperature sensor; and a battery management system is further installed on the inner wall of the front cover, and the fan, the heating film and the temperature sensor are all connected to the battery management system.
Further, the battery unit is composed of a plurality of battery cell arrays connected in series and/or in parallel.
Furthermore, the battery core array is a cuboid formed by arranging a plurality of battery monomers in parallel, the battery monomers are fixed through fiber adhesive tapes, and a supporting adhesive tape is arranged between the battery monomers.
Furthermore, a support is arranged below the opening cover and between the two battery units and used for supporting the opening cover.
Further, the heat insulating material is aerogel material.
Furthermore, the outside of the heat-insulating material is formed by thermal shrinkage of a PVC thermal shrinkage film.
Further, the fan is mounted on the rear cover through a mounting bracket.
Further, the energy storage battery thermal management system is installed in the front cabin and the front and rear positions of the undercarriage of the aircraft.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides an energy storage battery thermal management system of a near space aircraft, which is simple and convenient in design, has better thermal control performance and reliability, meets the heat dissipation and heat preservation requirements of the flight of the near space unmanned aerial vehicle in long-term flight, does not have the unified environmental control requirement on the aircraft, and reduces the weight of the whole aircraft.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic structural diagram of an energy storage battery according to an embodiment of the invention;
fig. 2 is a schematic diagram of an internal air duct structure of an energy storage battery according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a battery cell array structure according to an embodiment of the present invention;
FIG. 4 is a schematic view of the structure of the thermal insulation material according to the embodiment of the present invention.
Wherein the figures include the following reference numerals:
1: rear cover, 2: a fan, 3: opening cover, 4: front cover, 5: strut, 6: battery cell, 7: air duct, 8: heating film, 9: temperature sensor, 10: supporting tape, 11: fiber tape, 12: an insulating material.
Detailed Description
The following provides a detailed description of specific embodiments of the present invention. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
The invention provides a thermal management system for an energy storage battery of a near space vehicle, which comprises a battery unit 6, a front cover 4, a rear cover 1, a fan 2, an intermediate air duct 7, a heating film 8, a temperature sensor 9, a heat insulating material 12 and a top opening cover 3, as shown in figures 1-4. The battery unit 6 is a cuboid structure formed by arranging a plurality of battery monomers, the front ends and the rear ends of the battery units 6 are fixed through the front cover 4 and the rear cover 1, a rectangular hollow-out part formed between every two adjacent battery units 6 is used as a middle air duct 7, and the heat insulation materials 12 are wrapped outside the battery units 6. An opening cover 3 is processed on the heat insulating material 12 at the top of each air duct 7, and a support 5 is arranged below the opening cover 3 and between the two battery units 6 and used for supporting the opening cover 3 and preventing the opening cover 3 from falling into the air duct 7. The rear cover 1 is provided with a fan 2 corresponding to the air channel 7 and used as an air channel inlet. A BMS (Battery Management System) is mounted on an inner wall of the front cover 4. Every battery monomer one side all is furnished with heating film 8 and temperature sensor 9, and fan 2, heating film 8, temperature sensor 9 all are connected to on the BMS.
In this embodiment, there are two battery cells 6, and an intermediate air duct is formed with the inner walls of the front and rear covers, the heat insulating material on the upper and lower sides, the fan, and the opening cover.
The battery unit 6 may be composed of a plurality of battery cell arrays connected in series and/or in parallel, and the voltage range and the energy requirement are met by different series and parallel connections, as shown in fig. 3, each battery cell array is a cuboid formed by arranging a plurality of battery cells in parallel. In order to make the structure compact and the assembly convenient, a plurality of battery monomers of the battery core array are fixed through a fiber adhesive tape 11, and a supporting adhesive tape 10 is arranged between the battery monomers to form a reserved expansion space. The plurality of cell arrays are assembled into the rectangular battery unit 6 by other fixing methods such as fiber adhesive tapes or brackets. Heating film 8 and temperature sensor 9 are all pasted to every battery monomer one side, and every battery monomer surface temperature of real-time supervision through the switch of the steerable heating film of BMS, control heating film 8 carries out the even heating to every battery. In addition, for the convenience of assembly, the connecting wires of the fan 2, the heating film 8, the temperature sensor 9 and the BMS pass through the side of the thermal management system of the energy storage battery and avoid the air duct 7.
As shown in fig. 1, the rear cover 1 is provided with a mounting hole for accommodating a fan, the fan is mounted on the rear cover 1 through a mounting bracket, the fan can be mounted, and the number, model and size of the opening on the corresponding lower cover of the fan are determined according to the requirement of air volume so as to meet the heat dissipation requirement. In this embodiment, there are two fans 2.
As shown in FIG. 4, the thermal management system is wrapped with a flexible aerogel insulation material 12 around the front and back covers, fixed with double faced adhesive tape, then heat shrunk and molded with PVC heat shrink film on the outside, and three sides of the top opening cover 3 are cut out, and one side is connected without treatment. When the fan 2 is opened, air can blow the opening cover 3 outwards and flow out from the air duct in the thermal management system. In order to meet the requirements of light weight and simplification, the top opening cover 3 does not have any mechanical equipment, the top opening cover is blown open by blowing air by a fan, and the top opening cover automatically restores to a closed state when no air exists.
The working principle of the energy storage battery thermal management system provided by the invention is as follows: when the energy storage battery is in a high-altitude low-temperature environment, the temperature of the energy storage battery monomer collected by the temperature sensor is lower than the normal working temperature, the BMS can automatically control the heating film to be opened according to the set temperature threshold value, and when the temperature of the energy storage battery is at the normal working temperature, the BMS controls the heating film to be closed. When the temperature that temperature sensor monitored is higher than energy storage battery normal operating temperature, BMS control fan is automatic to be opened, wind gets into by the fan, form the forced convection in the wind channel, cuboid heat dissipation wind channel through middle fretwork, from the outflow of open top lid, the air plays heat transfer medium's effect this moment, when the temperature that energy storage battery system monitored is in normal operating temperature scope, the fan is closed, open top lid is because there is not wind effect self-closing, inside air hardly flows, the air can play thermal-insulated heat preservation effect.
The energy storage battery thermal management system provided by the invention can be installed in the front cabin, the front and the rear of the landing gear and the like of an aircraft to provide energy for the aircraft. When the aircraft climbs, energy storage battery discharge power is great, and the calorific capacity is great, and when energy storage battery reached the temperature upper limit of setting for, BMS automatic control fan opened, formed in the wind channel and forced the convection current, the air flowed out energy storage battery heat from top opening lid. When the aircraft flies high above the ground, the lowest external temperature can reach-55 ℃, and when the lowest temperature monitored by the energy storage battery thermal management system is lower than a preset temperature threshold value, the BMS automatically controls the heating film to be started to heat the battery monomer so as to maintain the working temperature of the energy storage battery. The battery monomer wind channel side lateral wall surface is direct and the air contact, and during the 0 rotational speed of fan, inside air is unable almost from the inside outflow of energy storage battery, and the air can play the thermal-insulated effect that keeps warm, and when the fan was opened, the air played heat transfer medium's effect.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (8)
1. The thermal management system for the energy storage battery of the near space vehicle is characterized by comprising a battery unit, a front cover, a rear cover, a fan, a heating film, a temperature sensor, a thermal insulation material and a top opening cover; the battery unit comprises at least two battery units, wherein the front end and the rear end of each battery unit are fixed through a front cover and a rear cover respectively, an air channel is formed between every two adjacent battery units, heat insulation materials are wrapped outside the plurality of battery units, an opening cover is arranged on the heat insulation materials at the top of each air channel, and a fan is installed on the rear cover corresponding to an opening of the air channel; the battery unit is of a cuboid structure formed by arranging a plurality of battery monomers, and one side of each battery monomer is provided with a heating film and a temperature sensor; and a battery management system is further installed on the inner wall of the front cover, and the fan, the heating film and the temperature sensor are all connected to the battery management system.
2. The near space vehicle energy storage battery thermal management system of claim 1, wherein the battery unit is comprised of a plurality of cell arrays connected in series and/or in parallel.
3. The near space vehicle energy storage battery thermal management system of claim 2, wherein the cell array is a cuboid formed by arranging a plurality of battery cells in parallel, the plurality of battery cells are fixed by fiber tapes, and support tapes are arranged between the battery cells.
4. The near space vehicle energy storage battery thermal management system of claim 1, wherein a brace is disposed between two battery cells below the opening cover for supporting the opening cover.
5. The near space vehicle energy storage battery thermal management system of claim 1, wherein the thermal insulation material is an aerogel material.
6. The near space vehicle energy storage battery thermal management system of claim 1, wherein the thermal insulation material is externally heat shrunk with a PVC heat shrink film.
7. The near space vehicle energy storage battery thermal management system of claim 1, wherein the fan is mounted to the aft cover by a mounting bracket.
8. The near space vehicle energy storage battery thermal management system of claim 1, wherein the energy storage battery thermal management system is mounted in a forward cabin, landing gear fore-aft position of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010950549.2A CN114162335B (en) | 2020-09-11 | 2020-09-11 | Energy storage battery thermal management system of near space vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010950549.2A CN114162335B (en) | 2020-09-11 | 2020-09-11 | Energy storage battery thermal management system of near space vehicle |
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| CN114162335A true CN114162335A (en) | 2022-03-11 |
| CN114162335B CN114162335B (en) | 2024-05-07 |
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| CN109560350A (en) * | 2018-12-04 | 2019-04-02 | 卧龙电气集团股份有限公司 | A kind of Li-ion batteries piles that can be worked in low temperature environment |
| CN208939055U (en) * | 2018-12-13 | 2019-06-04 | 上海精虹新能源科技有限公司 | A kind of energy-storage battery Pack |
| CN209544438U (en) * | 2019-02-20 | 2019-10-25 | 扬州道爵新能源发展有限公司 | A kind of battery pack |
| CN110137624A (en) * | 2019-06-13 | 2019-08-16 | 赵耀华 | A kind of the lithium battery pack double mode heat management system and method for energy-saving safe |
| CN110911779A (en) * | 2019-12-03 | 2020-03-24 | 西安电子科技大学芜湖研究院 | Lithium battery pack mixing heat dissipation device |
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