CN111740298B - Aviation laser - Google Patents
Aviation laser Download PDFInfo
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- CN111740298B CN111740298B CN202010574517.7A CN202010574517A CN111740298B CN 111740298 B CN111740298 B CN 111740298B CN 202010574517 A CN202010574517 A CN 202010574517A CN 111740298 B CN111740298 B CN 111740298B
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 90
- 230000005693 optoelectronics Effects 0.000 claims abstract 3
- 238000010438 heat treatment Methods 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 9
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 238000001816 cooling Methods 0.000 abstract description 13
- 238000000034 method Methods 0.000 description 14
- 230000008569 process Effects 0.000 description 13
- 238000010586 diagram Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- 238000009413 insulation Methods 0.000 description 4
- 238000003384 imaging method Methods 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 230000010354 integration Effects 0.000 description 3
- 239000013307 optical fiber Substances 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000741 silica gel Substances 0.000 description 2
- 229910002027 silica gel Inorganic materials 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000004642 Polyimide Substances 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
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- 210000003205 muscle Anatomy 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
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- 229920001721 polyimide Polymers 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/02—Constructional details
- H01S3/025—Constructional details of solid state lasers, e.g. housings or mountings
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/02—Constructional details
- H01S3/04—Arrangements for thermal management
- H01S3/0404—Air- or gas cooling, e.g. by dry nitrogen
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/02—Constructional details
- H01S3/04—Arrangements for thermal management
- H01S3/042—Arrangements for thermal management for solid state lasers
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- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- Plasma & Fusion (AREA)
- Optics & Photonics (AREA)
- Semiconductor Lasers (AREA)
Abstract
本发明公开了一种航空激光器，包括激光器主体、激光器安装板和散热壳体，所述激光器主体通过所述激光器安装板固定于所述散热壳体的正面，所述散热壳体的背面具有向外凸出且表面光滑的壳面，以实现外界空气通过所述壳面对所述激光器主体的风冷散热。上述航空激光器为可应用于航空光电平台的大功率激光器结构，可以直接实现激光器与航空光电平台集成，不仅结构紧凑，而且以散热壳体的形式，在载机飞行过程中，通过热对流对散热壳体外表面快速散热，实现对激光器的散热。
The invention discloses an aviation laser, comprising a laser main body, a laser mounting plate and a heat dissipation shell. The laser main body is fixed on the front of the heat dissipation shell through the laser mounting plate, and the back of the heat dissipation shell has a direction to the heat dissipation shell. The outer convex and smooth surface of the shell is used to realize the air cooling and heat dissipation of the outside air through the shell to the laser main body. The above aviation laser is a high-power laser structure that can be applied to an aviation optoelectronic platform, which can directly integrate the laser with the aviation optoelectronic platform. It is not only compact in structure, but also in the form of a heat dissipation shell, during the flight of the carrier aircraft, through thermal convection to dissipate heat. The outer surface of the shell quickly dissipates heat to realize the heat dissipation of the laser.
Description
Technical Field
The invention relates to the technical field of aviation photoelectric loads, in particular to an aviation laser.
Background
High-power lasers have been increasingly applied to the field of aviation photoelectric loads, such as airborne laser weapons, airborne laser three-dimensional imaging and the like.
In order to avoid the adverse effect caused by the optical fiber penetrating through the shaft, a high-power laser needs to be placed inside the carrier. The airborne high-power laser can generate a large amount of heat in the working process, and the heat dissipation effect and the reliability in the aviation photoelectric platform are difficult to ensure, so that the airborne high-power laser is a severe test for the aviation photoelectric platform; if the heat accumulation can not be discharged, the normal work of the laser is influenced, and meanwhile, the stability of the aviation photoelectric load is also influenced, and the imaging quality is influenced. Meanwhile, the traditional high-power laser has a large structural volume, and equipment such as a water-cooled refrigerator and the like is difficult to arrange; the aviation photoelectric load may have 180-degree turnover in the working process, and the traditional heat pipe heat dissipation mode cannot be applied to an aviation photoelectric platform due to the existence of directionality.
Therefore, how to provide an aviation laser with compact size, fast heat dissipation speed and high stability is a technical problem that needs to be solved urgently by those skilled in the art.
Disclosure of Invention
The invention aims to provide an aviation laser, which is a high-power laser structure applicable to an aviation photoelectric platform, can directly realize the integration of the laser and the aviation photoelectric platform, has a compact structure, and quickly dissipates heat of the outer surface of a heat dissipation shell through heat convection in the flying process of a carrier in the form of the heat dissipation shell so as to realize the heat dissipation of the laser.
In order to achieve the purpose, the invention provides an aviation laser, which comprises a laser main body, a laser mounting plate and a heat dissipation shell, wherein the laser main body is fixed on the front surface of the heat dissipation shell through the laser mounting plate, and the back surface of the heat dissipation shell is provided with a shell surface which protrudes outwards and has a smooth surface, so that air cooling and heat dissipation of the laser main body by external air through the shell surface are realized.
Preferably, the heat dissipation shell is in a hollow hemispherical shape, and the shell surface is a hemispherical surface.
Preferably, a heat conducting plate is arranged between the laser mounting plate and the heat dissipation shell.
Preferably, the laser main body is located at a central position of the laser mounting board.
Preferably, the laser main body comprises a main body mounting plate and an electronic component arranged on the front surface of the main body mounting plate.
Preferably, the laser device further comprises a heating device arranged on the front surface of the laser mounting plate, and the heating device is arranged on the back surface of the main body mounting plate.
Preferably, a heat conducting structure is arranged in the heat dissipation shell, and the heat conducting structure corresponds to the position of the heating device.
Preferably, the quantity of the device that generates heat is a plurality of, and is a plurality of the device that generates heat is uneven distribution, the quantity of heat conduction structure is a plurality of, and is a plurality of heat conduction structure uses the device that generates heat is the light muscle of radiation all around to the center.
Preferably, the front and the back of the laser mounting plate are respectively provided with a first mounting boss and a second mounting boss which are used for being fixedly connected with the laser main body and the heat dissipation shell, and a heat insulation gasket is arranged between the first mounting boss and the laser main body
Preferably, the outer peripheral side of the laser mounting plate is provided with a laser mechanical mounting interface so as to realize the mounting of the aviation laser on a frame of an aviation photoelectric load.
Compared with the background art, the aviation laser provided by the invention comprises a laser main body, a laser mounting plate and a heat dissipation shell, wherein the laser main body is fixed on the front surface of the heat dissipation shell through the laser mounting plate, the back surface of the heat dissipation shell is provided with a shell surface, the shell surface protrudes outwards, and the surface of the shell surface is smooth; the aviation laser realizes the installation and fixation of the laser main body on the front surface of the heat dissipation shell through the laser installation plate, realizes the air cooling heat dissipation of the laser main body through the shell surface on the back surface of the heat dissipation shell, and the protruded and smooth shell surface is favorable for the rapid heat dissipation in a heat convection mode; the aviation laser has the characteristic of compact structure, particularly is a high-power laser structure applicable to an aviation photoelectric platform, the integration of the laser and the aviation photoelectric platform can be directly realized, the outer surface of a heat dissipation shell is in direct contact with the atmospheric environment, in the working process of the aviation photoelectric load, a carrier has a certain flying height, the external environment is in a low-temperature state, in the flying process of the carrier, external cold air passes through the outer surface of the heat dissipation shell, the outer surface of the heat dissipation shell is rapidly cooled in a heat convection mode, the temperature of the outer surface of the heat dissipation shell is reduced, and rapid heat dissipation is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an airborne laser provided in an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of the laser body of FIG. 1;
FIG. 3 is an internal schematic view of the laser body of FIG. 2;
FIG. 4 is a schematic front view of the laser mounting board of FIG. 1;
FIG. 5 is a schematic view of the back side of the laser mounting board of FIG. 1;
fig. 6 is a schematic structural diagram of the heat dissipation housing in fig. 1.
Wherein:
1-a laser main body, 2-a laser mounting plate, 3-a heat dissipation shell, 4-a heat insulation gasket, 11-an electronic component, 12-a main body mounting plate, 13-a cylindrical end face, 14-an optical fiber outlet, 16-a heating device, 21-a first mounting boss, 22-a laser mechanical mounting interface, 23-a second mounting boss, 31-a shell mechanical mounting interface, 32-a spherical shell rear part, 33-a heat conduction structure, 34-a lightweight rib and 35-a heat conduction plate.
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 of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 to 6, in which fig. 1 is a schematic structural diagram of an airborne laser provided in an embodiment of the present invention, fig. 2 is a schematic structural diagram of a laser main body in fig. 1, fig. 3 is a schematic internal diagram of the laser main body in fig. 2, fig. 4 is a schematic front view of a laser mounting board in fig. 1, fig. 5 is a schematic back view of the laser mounting board in fig. 1, and fig. 6 is a schematic structural diagram of a heat dissipation housing in fig. 1.
In a first specific embodiment, the aviation laser provided by the invention is a high-power laser, and can be applied to an aviation photoelectric platform and directly realize the integration of the laser and the aviation photoelectric platform; including laser instrument main part 1, laser instrument mounting panel 2 and heat dissipation casing 3, laser instrument main part 1 installation is fixed in laser instrument mounting panel 2, laser instrument mounting panel 2 again with 3 fixed connection of heat dissipation casing, make laser instrument main part 1 be fixed in the front of heat dissipation casing 3 through the installation of laser instrument mounting panel 2, and the back of heat dissipation casing 3 has the shell face, the shell face is outside protrusion and the surface is smooth, be favorable to with outside air heat exchange, make the outside air carry out the forced air cooling heat dissipation to laser instrument main part 1 through the shell face.
The existing aviation laser, especially the high-power laser structure which can be applied to the aviation photoelectric platform, has the problems that the heat accumulation is difficult to remove, the normal work of the laser and the stability of the aviation photoelectric load are influenced, and the imaging quality is influenced because the existing aviation laser is integrated in the aviation photoelectric platform; due to the high-power characteristic of the aviation laser, the structure volume is large, the arrangement of water cooling equipment is difficult, the working condition of aviation photoelectric load is complex, and the heat pipe heat dissipation mode is difficult to implement.
Aiming at the problems, the aviation laser adopts air cooling heat dissipation, and adopts the heat dissipation shell 3 capable of realizing air cooling heat dissipation, so that the laser main body 1 generates heat in the front work of the heat dissipation shell 3 and the laser mounting plate 2, the heat dissipation shell 3 on the back exchanges heat with the outside through the shell surface, and the air cooling heat dissipation of the laser main body 1 is realized through the heat dissipation shell 3. The shell surface of the heat dissipation shell 3 is directly contacted with the atmospheric environment, the aircraft has a certain flight height in the aviation photoelectric load working process, the external environment is in a low-temperature state, and in the aircraft flight process, external cold air passes through the outer surface of the heat dissipation shell 3 to quickly dissipate heat of the outer surface of the heat dissipation shell 3 in a heat convection mode, so that the temperature of the outer surface of the heat dissipation shell 3 is reduced, and the heat dissipation of the aviation laser is realized.
One of the core improvement points of the invention is to use the heat dissipation shell 3 to perform air cooling heat dissipation of the aviation laser, the shell surface of the heat dissipation shell 3 plays a main role in air cooling heat dissipation, and the shape and quality of the shell surface play a crucial role in heat dissipation; therefore, the outer surface of the shell 3, namely the shell surface, should have smooth and uniform transition surface, and the contact area with the outside atmosphere is large enough while the structural strength is ensured, so as to ensure the comprehensive and sufficient air cooling and heat dissipation.
The structural form of the heat dissipation housing 3 is various, including but not limited to regular conventional shapes, and shapes having an arc surface, such as an ellipsoid, a sphere, and the like, may also be adopted. Illustratively, the heat dissipation housing 3 is hollow and hemispherical, and the shell surface is a hemispherical surface.
In this embodiment, the heat dissipating casing 3 is a hollow heat dissipating spherical shell, the hollow is defined in that no filler is present inside the heat dissipating casing 3, and air is used as the only medium to directly participate in heat exchange with the outside, thereby ensuring the heat dissipating effect.
For better technical effect, the heat exchange process of air cooling heat dissipation is considered, the heat exchange process between the outside and the heat dissipation shell 3 is not only involved, but also the heat exchange process between the heat dissipation shell 3 and the laser installation plate 2 is involved, therefore, in order to improve the heat exchange effect between the heat dissipation shell 3 and the laser installation plate 2, a layer of heat conduction plate 35 is arranged between the laser installation plate 2 and the heat dissipation shell 3, and the heat conduction plate 35 is used for promoting the heat exchange process between the laser installation plate and the heat dissipation shell, and assisting in rapid heat conduction.
In a specific embodiment, when the heat dissipation housing 3 is a hemisphere, the laser main body 1 is circular with a similar cross-sectional shape, the laser main body 1 is a cylindrical structure, the cylindrical structure includes a cylindrical inner cavity and a cylindrical end surface 13 for closing the inner cavity, the inside of the cylindrical structure is a main portion of the laser main body 1, and the laser main body 1 further includes an optical fiber outlet 14 and an electrical interface, etc. connected to the outside by the cylindrical end surface 13.
In the present embodiment, the laser body 1 is disposed at the center of the laser mounting board 2, and when the laser mounting board 2 is a flat plate having a racetrack structure, the laser body 1 is located at the center of the flat plate.
More specifically, when the laser main body 1 is a cylindrical structure, the laser main body 1 includes a main body mounting plate 12 disposed on the bottom surface of the inner cavity, an electronic component 11 is fixedly mounted on the front surface of the main body mounting plate 12, and the electronic component 11 can be cooled through the main body mounting plate 12 and then through the laser mounting plate 2 and then through the heat-dissipating housing 3.
In addition, the laser device further comprises a heating device 16 which is fixedly arranged on the front surface of the laser mounting plate 2, and the heating device 16 is positioned on the back surface of the main body mounting plate 12. The heating device 16 is a main heating component, and in the working state, the heating device 16 generates heat, conducts heat to the heat dissipation shell 3 through the laser mounting plate 2, and then conducts cold distribution and heat dissipation through the heat dissipation shell 3.
In this embodiment, the heat generating device 16 is the most important heat generating component of the aviation laser, and not only needs to ensure that the heat generating device 16 is fully cooled and dissipated, but also needs to protect other components adjacent to the heat generating device 16 from heat, such as the electronic component 11 on the front surface of the main body mounting plate 12.
In other words, the main body mounting board 12 and the laser mounting board 2 correspond to two layers of the aviation laser, the first layer includes the main body mounting board 12 and the electronic component 11 disposed thereon, the second layer includes the laser mounting board 2 and the heat generating device 16 disposed thereon, the electronic component 11 generates less heat, and the heat generating device 16 is a main heat generating component.
In order to reduce or completely insulate the influence of heat generated by the heat generating device 16 on the electronic component 11, a heat insulating spacer 4 for heat insulation is provided between the heat generating device 16 and the electronic component 11, that is, between the laser mounting board 2 and the body mounting board 12.
That is to say, connect and realize thermal-insulated through heat insulating gasket 4 that thermal insulation material made between the first layer of aviation laser and the second floor, avoid the heat conduction of second floor to the first layer, cause local heating to influence the laser and normally work.
In this embodiment, the front surface of the laser mounting board 2 is provided with a first mounting boss 21, the back surface of the laser mounting board 2 is provided with a second mounting boss 23, the laser mounting board 2 is fixedly connected with the laser main body 1 through the first mounting boss 21, the laser mounting board 2 is fixedly connected with the heat dissipation housing 3 through the second mounting boss 23, wherein the main body mounting board 12 of the laser main body 1 is connected with the first mounting boss 21 on the laser mounting board 2 through the heat insulation gasket 4, and the heat dissipation housing 3 is connected with the second mounting boss 23 on the laser mounting board 2 through the housing mechanical mounting interface 31 on the peripheral side.
In addition, a laser mechanical mounting interface 22 is arranged on the outer periphery of the laser mounting plate 2, and the aviation laser is used as a rear spherical shell of the aviation photoelectric platform and is mounted on a frame of the aviation photoelectric load through the laser mechanical mounting interface 22.
In a specific embodiment, the interior of the heat dissipation housing 3 is a lightweight structure, and the inner surface of the heat dissipation housing 3 can improve the heat dissipation effect by providing the heat conduction structure 33.
Illustratively, the heat conducting structure 33 is disposed in the heat dissipating housing 3, the heat conducting structure 33 corresponds to the heat generating device 16, after the laser main body 1, the laser mounting board 2 and the heat dissipating housing 3 are assembled and fixed, the heat conducting structure 33 corresponds to the position of the heat generating device 16, and the heat conducting structure 33 connects the heat generating device 16 to the rear portion 32 of the spherical shell of the heat dissipating housing 3.
On this basis, the number of the heat generating devices 16 includes, but is not limited to, one or more than one.
Illustratively, the number of the heat generating devices 16 is plural, the plurality of heat generating devices 16 are unevenly distributed, the number of the heat conducting structures 33 is plural, and the heat conducting structures 33 and the heat generating devices 16 are in one-to-one correspondence.
For better technical effect, the inside of the heat dissipation case 3 has a light weight structure and a divergent structure with the heat generating device 16 of the second layer as the center.
Specifically, when a plurality of heat generating devices 16 are provided, the light-weight ribs 34 are radially outwardly radiated from the light-weight structure of the heat dissipating case 3 with each heat generating device 16 as a center, wherein the light-weight ribs 34 are located on the peripheral side of the heat conducting structure 33, and the light-weight ribs 34 are divergent in order to improve the heat conduction efficiency, and the heat conducting structure 33 is integrally connected by the light-weight ribs 34.
For example, the material of the heat insulating spacer 4 may be polytetrafluoroethylene, polyimide, or the like; the heat conducting plate 35 may be made of heat conducting silica gel, so that the heat conducting structure 33 of the heat dissipating housing 3 and the laser are connected by a heat conducting material such as heat conducting silica gel, and the heat generating device 16 transfers heat to the outer surface of the heat dissipating housing 3 in a heat conducting manner.
In the embodiment, the aviation laser is in a hemispherical body or umbrella shape, the outer surface of the heat dissipation shell 3 is directly contacted with the atmospheric environment, during the aviation photoelectric load working process, the aircraft has a certain flight height, the external environment is in a low-temperature state, during the flight process of the aircraft, the external cold air passes through the outer surface of the heat dissipation shell 3, the outer surface of the heat dissipation shell 3 is rapidly dissipated by means of heat convection, the temperature of the outer surface of the heat dissipation shell 3 is reduced, the heat dissipation of the heating device 16 is realized, the characteristics of the aviation environment are fully utilized, heat dissipation equipment such as laser water cooling and the like is saved, and the volume and the weight are saved; because the front spherical shell of the aviation photoelectric platform is an optical window, the back spherical shell generally needs to be considered to be added with a counterweight, and the laser replaces the position of the back spherical shell of the traditional aviation photoelectric platform, so that the internal space of the whole aviation photoelectric platform is compactly arranged, and the laser plays a role of the counterweight.
It is noted that, in this specification, relational terms such as first and second, and the like are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The aviation laser provided by the invention is described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010574517.7A CN111740298B (en) | 2020-06-22 | 2020-06-22 | Aviation laser |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010574517.7A CN111740298B (en) | 2020-06-22 | 2020-06-22 | Aviation laser |
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| Publication Number | Publication Date |
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| CN111740298A CN111740298A (en) | 2020-10-02 |
| CN111740298B true CN111740298B (en) | 2021-09-03 |
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| CN202010574517.7A Active CN111740298B (en) | 2020-06-22 | 2020-06-22 | Aviation laser |
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| CN104812670A (en) * | 2012-09-26 | 2015-07-29 | 西门子公司 | Cooling system for components in (airborne) vehicle structures |
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2020
- 2020-06-22 CN CN202010574517.7A patent/CN111740298B/en active Active
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| CN101382273A (en) * | 2007-09-07 | 2009-03-11 | 富准精密工业(深圳)有限公司 | LED lamp with heat radiation structure |
| CN102089208A (en) * | 2008-07-08 | 2011-06-08 | 空中客车作业有限公司 | System for cooling an aircraft zone, to be connected to an aircraft-external air unit |
| CN102470925A (en) * | 2009-07-06 | 2012-05-23 | 空中客车营运有限公司 | Cooling concept for a fuel cell emergency power system |
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|---|---|
| CN111740298A (en) | 2020-10-02 |
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