CN111182774A - Space radiation radiator based on aluminum honeycomb panel - Google Patents
Space radiation radiator based on aluminum honeycomb panel Download PDFInfo
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- CN111182774A CN111182774A CN202010110326.5A CN202010110326A CN111182774A CN 111182774 A CN111182774 A CN 111182774A CN 202010110326 A CN202010110326 A CN 202010110326A CN 111182774 A CN111182774 A CN 111182774A
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- panel
- heat
- honeycomb
- heat pipe
- space radiation
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/2039—Modifications to facilitate cooling, ventilating, or heating characterised by the heat transfer by conduction from the heat generating element to a dissipating body
Abstract
A space radiation radiator based on an aluminum honeycomb plate belongs to the field of space optical remote sensing, and comprises a honeycomb interlayer; a heat dissipation panel glued with the honeycomb interlayer; an internal heat source heat conduction pipe arranged outside the heat dissipation panel; a reinforced panel bonded to the honeycomb sandwich; the soaking heat pipe is arranged in the honeycomb interlayer, the soaking heat pipe is vertically arranged with the internal heat source heat conduction heat pipe, the soaking heat pipe is in heat conduction connection with the heat dissipation panel, and the soaking heat pipe is glued with the reinforced panel; and the inserts are arranged in the honeycomb interlayer and are respectively glued with the heat dissipation panel and the reinforcing panel. The invention has the advantages of light weight, high heat dissipation efficiency, high rigidity, simple structure and easy molding, realizes the purposes of reducing the weight, improving the integral rigidity and improving the heat conductivity of the heat dissipation surface, and is suitable for the requirements of large area, light weight and high rigidity heat conductivity.
Description
Technical Field
The invention belongs to the technical field of space optical remote sensing, and particularly relates to a space radiation radiator based on an aluminum honeycomb panel.
Background
With the development of the space optical remote sensing technology, an imaging electronic system on a remote sensor is increasingly complex and large, and the corresponding working heat consumption is also increasingly high, so that the imaging electronic system is required to have good heat dissipation path and capability. The arrangement of a space radiation radiator at a proper position of a remote sensor is an effective way for solving the problem of heat dissipation.
The space radiation radiator not only needs to meet the heat dissipation requirement, but also needs to meet the rigidity and strength requirements so as to adapt to the severe emission dynamic environment, and meanwhile, the weight is required to be as light as possible. The existing radiation radiator mainly has the following structural forms: aluminum plate, aluminum plate and honeycomb panel of taking the strengthening rib. The aluminum plate is the most common structural shape of the radiation radiator, and is characterized by simple structure, light weight, high radiating efficiency, but low rigidity, and is not suitable for occasions with large radiating area requirements; the aluminum plate with the reinforcing ribs has high rigidity and high heat dissipation efficiency, but has a complex structure and is difficult to form, an internal heat conduction heat pipe is difficult to install after forming, and some thermal control coatings with long service life and high stability, such as OSR secondary surface mirrors, are difficult to implement; the honeycomb plate is high in overall rigidity and light in weight, but due to the fact that the panel is too thin and low in heat conductivity, after the honeycomb plate is connected with the internal heat source heat conduction heat pipe, a large temperature difference can be formed on a heat dissipation surface, and heat dissipation capacity is reduced.
Disclosure of Invention
The invention aims to provide a space radiation radiator based on an aluminum honeycomb plate, which has the advantages of light weight, high radiating efficiency, high rigidity, simple structure and easiness in molding, realizes the purposes of reducing the weight, improving the integral rigidity and improving the heat conductivity of a radiating surface, and is suitable for the requirements of large area, light weight and high rigidity heat conductivity.
The technical scheme adopted by the invention for solving the technical problem is as follows:
the invention discloses a space radiation radiator based on an aluminum honeycomb plate, which comprises:
a honeycomb interlayer;
a heat dissipation panel glued with the honeycomb interlayer;
an internal heat source heat conduction pipe arranged outside the heat dissipation panel;
a reinforced panel bonded to the honeycomb sandwich;
the soaking heat pipe is arranged in the honeycomb interlayer and is vertical to the internal heat source heat conduction heat pipe, the soaking heat pipe is in heat conduction connection with the heat dissipation panel, and the soaking heat pipe is connected with the reinforcing panel in an adhesive manner;
and the inserts are arranged in the honeycomb interlayer and are respectively glued with the heat dissipation panel and the reinforcing panel.
Furthermore, the heat conduction heat pipe of the internal heat source is made of an omega-shaped heat pipe.
Further, the thickness of the heat dissipation panel is greater than or equal to 3 mm.
Further, the thickness of the heat dissipation panel is 3 mm.
Further, the heat dissipation panel is made of an aluminum plate.
Furthermore, the honeycomb sandwich layer is made of aluminum honeycomb plates.
Furthermore, the soaking heat pipe is made of an omega-shaped heat pipe.
Further, the insert is made of aluminum alloy 2A 12.
Further, the thickness of the reinforced panel is 0.5 mm.
Further, the reinforced panel is made of an aluminum plate.
The invention has the beneficial effects that:
1) the space radiation radiator has the advantages of simple structure, light weight, high rigidity and easy molding and assembly.
2) The space radiation radiator has good radiating surface flatness, and is easy to implement the OSR secondary surface mirror with the thermal control coating layer with long service life and high stability.
3) According to the space radiation radiator, the heat conductivity of the radiating surface in the direction vertical to the heat conducting heat pipe is remarkably improved, the temperature gradient of the radiating surface is effectively reduced, and the radiating capacity is remarkably enhanced.
Drawings
Fig. 1 is a schematic structural diagram of a space radiation radiator based on an aluminum honeycomb panel according to the present invention.
Fig. 2 is a schematic structural diagram of a space radiation heat sink based on an aluminum honeycomb panel (with a heat dissipation panel hidden) according to the present invention.
In the figure, 1, an internal heat source heat conduction heat pipe, 2, a heat dissipation panel, 3, a honeycomb interlayer, 4, a soaking heat pipe, 5, an insert, 6 and a reinforcing panel.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1 and fig. 2, the space radiation radiator based on aluminum honeycomb panel of the present invention mainly includes: the heat pipe comprises an internal heat source heat conduction heat pipe 1, a heat dissipation panel 2, a honeycomb interlayer 3, a soaking heat pipe 4, an insert 5 and a reinforcing panel 6.
The internal heat source heat conduction heat pipe 1 is arranged on the outer side of the heat dissipation panel 2, and the internal heat source heat conduction heat pipe 1 is in threaded connection with the heat dissipation panel 2 and used for transferring heat in the remote sensor.
The heat dissipation panel 2 is bonded with the honeycomb interlayer 3 and is used for radiating heat transferred by the internal heat source heat conduction pipe 1 to the cold and black space.
The reinforced panel 6 is glued to the honeycomb sandwich 3 for overall stiffness enhancement.
The soaking heat pipe 4 is arranged in the honeycomb interlayer 3, and the soaking heat pipe 4 is vertical to the internal heat source heat conduction heat pipe 1.
The soaking heat pipe 4 is respectively glued with the radiating panel 2 and the reinforcing panel 6, and the soaking heat pipe 4 is installed with the radiating panel 2 in a heat conducting manner and used for realizing the transverse heat conduction of the radiating panel 2.
The insert 5 is arranged in the honeycomb interlayer 3, and the insert 5 is respectively glued with the heat dissipation panel 2 and the reinforcing panel 6 for realizing the connection of the space radiation radiator and the remote sensor body.
In this embodiment, the internal heat source heat conduction heat pipe 1 is made of an Ω -shaped heat pipe.
In the present embodiment, the thickness of the heat dissipation panel 2 is 3mm or more, and the thickness of the heat dissipation panel 2 is preferably 3 mm.
In the present embodiment, the heat radiation panel 2 is made of an aluminum plate.
In the present embodiment, the honeycomb sandwich 3 is made of an aluminum honeycomb plate.
In the present embodiment, the soaking heat pipe 4 is made of an Ω -shaped heat pipe.
In the present embodiment, the insert 5 is made of aluminum alloy 2a 12.
In the present embodiment, the thickness of the reinforcing panel 6 is 0.5 mm.
In the present embodiment, the reinforcing panel 6 is made of an aluminum plate.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the preferred embodiment of the present invention; it should be noted that, for those skilled in the art, without departing from the principle of the present invention, several modifications and decorations, such as size, material selection, shape change, can be made, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A space radiation radiator based on aluminum honeycomb plates is characterized by comprising:
a honeycomb sandwich layer (3);
the heat dissipation panel (2) is glued with the honeycomb interlayer (3);
an inner heat source heat conduction pipe (1) arranged outside the heat dissipation panel (2);
a reinforced panel (6) glued to the honeycomb sandwich (3);
the soaking heat pipe (4) is arranged in the honeycomb interlayer (3), the soaking heat pipe (4) is perpendicular to the internal heat source heat conduction heat pipe (1), the soaking heat pipe (4) is in heat conduction connection with the heat dissipation panel (2), and the soaking heat pipe (4) is connected with the reinforcing panel (6) in a bonding mode;
and the inserts (5) are arranged in the honeycomb sandwich layer (3), and the inserts (5) are respectively glued with the heat dissipation panel (2) and the reinforcing panel (6).
2. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the internal heat source heat conducting heat pipe (1) is made of omega-shaped heat pipe.
3. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterised in that the thickness of the radiator panel (2) is greater than or equal to 3 mm.
4. An aluminium honeycomb panel-based space radiation radiator according to claim 3, characterized in that the thickness of the radiating panel (2) is 3 mm.
5. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the radiator panel (2) is made of aluminium sheet.
6. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the honeycomb sandwich (3) is made of aluminium honeycomb panels.
7. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the soaking heat pipe (4) is made of omega-shaped heat pipe.
8. An aluminium honeycomb panel-based space-radiating radiator according to claim 1, characterized in that the insert (5) is made of aluminium alloy 2a 12.
9. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the thickness of the reinforcing panel (6) is 0.5 mm.
10. An aluminium honeycomb panel-based space radiation radiator according to claim 1, characterized in that the reinforcing panel (6) is made of aluminium sheet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010110326.5A CN111182774A (en) | 2020-02-24 | 2020-02-24 | Space radiation radiator based on aluminum honeycomb panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010110326.5A CN111182774A (en) | 2020-02-24 | 2020-02-24 | Space radiation radiator based on aluminum honeycomb panel |
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| Publication Number | Publication Date |
|---|---|
| CN111182774A true CN111182774A (en) | 2020-05-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010110326.5A Pending CN111182774A (en) | 2020-02-24 | 2020-02-24 | Space radiation radiator based on aluminum honeycomb panel |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284172A (en) * | 2020-10-29 | 2021-01-29 | 上海卫星装备研究所 | Space radiation radiator |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659750B (en) * | 2006-06-26 | 2009-07-01 | 北京空间飞行器总体设计部 | Mixed type orthogonal heat pipes network radiator |
| CN103274061A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Heat tube-fluid loop coupling heating radiator used for spacecraft |
| CN204210109U (en) * | 2014-10-10 | 2015-03-18 | 西安嘉业航空科技有限公司 | A kind of spoke cooler honeycomb sandwich construction |
| CN108910090A (en) * | 2018-03-29 | 2018-11-30 | 北京空间飞行器总体设计部 | A kind of star sensor and thermal controls apparatus integrative installation technology bracket |
| CN210072163U (en) * | 2019-05-17 | 2020-02-14 | 中国科学院上海技术物理研究所 | Isothermal structure of multifunctional optical mounting base plate |
-
2020
- 2020-02-24 CN CN202010110326.5A patent/CN111182774A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659750B (en) * | 2006-06-26 | 2009-07-01 | 北京空间飞行器总体设计部 | Mixed type orthogonal heat pipes network radiator |
| CN103274061A (en) * | 2013-04-25 | 2013-09-04 | 上海卫星工程研究所 | Heat tube-fluid loop coupling heating radiator used for spacecraft |
| CN204210109U (en) * | 2014-10-10 | 2015-03-18 | 西安嘉业航空科技有限公司 | A kind of spoke cooler honeycomb sandwich construction |
| CN108910090A (en) * | 2018-03-29 | 2018-11-30 | 北京空间飞行器总体设计部 | A kind of star sensor and thermal controls apparatus integrative installation technology bracket |
| CN210072163U (en) * | 2019-05-17 | 2020-02-14 | 中国科学院上海技术物理研究所 | Isothermal structure of multifunctional optical mounting base plate |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112284172A (en) * | 2020-10-29 | 2021-01-29 | 上海卫星装备研究所 | Space radiation radiator |
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Application publication date: 20200519 |