CN205221138U - Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft - Google Patents
Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft Download PDFInfo
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- CN205221138U CN205221138U CN201520734367.6U CN201520734367U CN205221138U CN 205221138 U CN205221138 U CN 205221138U CN 201520734367 U CN201520734367 U CN 201520734367U CN 205221138 U CN205221138 U CN 205221138U
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- heat pipe
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- keysets
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Abstract
The utility model provides an integrative heat -transmission accuse device of outer load section of thick bamboo aircraft, include instrument mounting panel, pre -buried heat pipe, expand the hot plate, paste heat pipe, extension heating panel and heat conduction keysets outward, wherein, pre -buried heat pipe setting is in in the instrument mounting panel, it is in to expand the hot plate setting the upper surface of instrument mounting panel, paste outward the heat pipe on the one hand with expanding the hot plate and connecting, on the other hand is connected with the heat conduction keysets, the extension heating panel is connected the heat conduction keysets. Still include two -seater clamp and single seat clamp, wherein, it is two to paste heat pipe quantity outward, two it passes through on the one hand to paste the heat pipe outward the two -seater clamp connection expand the hot plate, on the other hand is respectively through two heat conduction keysetss of single seat clamp connection. The utility model discloses a heat transmission device's on the outer load section of thick bamboo aircraft of complicated configuration installation convenience has effectively been solved to heat conduction keysets and outer crooked heat pipe combination.
Description
Technical field
The utility model relates to aircraft thermal controls apparatus, particularly, relates to a kind of complex configuration outer loaded cylinder aircraft integration thermal controls apparatus.
Background technology
6:30 ± 30min local time the in that certain model aircraft test objective track needing to adapt to descending node, orbit altitude changes between 500 ~ 800km.Rail conditions change causes greatly aircraft Orbital heat flux condition to change greatly, and aircraft mode of operation is changeable simultaneously causes complete machine hear rate vary within wide limits, requires that aircraft thermal control design has high adaptive capacity.This aircraft adopts the outer loaded cylinder structure of complex configuration, and the large large quality unit of power consumption such as power-supply system power-supply controller of electric cannot realize being directly installed on heat delivery surface and carry out temperature control.The region of the main heat delivery surface of this aircraft is the thin-walled skin of heat conductivility difference, and heat dissipation efficiency is low.Therefore, need for complex configuration that outer special technique to high-efficiency taked by loaded cylinder aircraft, failure-free realizes heat collection, transmission is loose with row, also need to ensure simultaneously the convenience of realization and aggregate resource occupancy little.
Usual satellite adopts the collection of the isothermal design of pre-buried heat pipe real-time performance dashboard and heat, the transmission that main dependence radiation heat transfer mode realizes heat is loose with row, this thermal design mode is to the change bad adaptability of orbit external thermal flux and interior power consumption, and heat transfer efficiency is low and not easily solve the heat dissipation problem of large power consumption unit.The large power consumption unit such as power-supply controller of electric usually adopts and is directly installed on side plate heat delivery surface, loose with row by the collection of Heat Pipes heat pre-buried on side plate, transmission, and which cannot to be applied to outside complex configuration on loaded cylinder structural aircraft.It is loose that loop circuit heat pipe (LHP) technology can realize large power consumption unit heat collection, transmission and row, the enhancing of heat control system adaptive capacity can be realized by combining with pre-buried heat pipe, but its reliability is not high, quality is large, need extra electric power resource, nor the constraint condition of the carry-on layout of complex configuration and being dismounted for multiple times can be adapted to.Adopt outer subsides heat pipe can promote the thin-walled skin heat delivery surface thermal discharge efficiency of heat conductivility difference, but will certainly increase too much weight resource, the mounting process of outer subsides heat pipe on thin-walled skin is also very difficult to realize.
Utility model content
For defect of the prior art, the purpose of this utility model is to provide a kind of outer loaded cylinder aircraft integration thermal controls apparatus.
According to the outer loaded cylinder aircraft integration thermal controls apparatus that the utility model provides, comprise apparatus installation plate, pre-buried heat pipe, expansion hot plate, outer subsides heat pipe, expansion heating panel and heat conduction keysets;
Wherein, described pre-buried heat pipe is arranged in described apparatus installation plate; Described expansion hot plate is arranged on the upper surface of described apparatus installation plate;
Described outer subsides heat pipe is connected with described expansion hot plate on the one hand, is connected on the other hand with heat conduction keysets; Described expansion heating panel connects described heat conduction keysets.
Preferably, two-seater clip and single seat clip is also comprised;
Wherein, described outer subsides heat pipe quantity is two; Two described outer subsides heat pipes expand hot plate, on the one hand on the other hand respectively by single seat anulated connection two heat conduction keysetss described in described two-seater anulated connection.
Preferably, described expansion hot plate is arranged on the upside of described pre-buried heat pipe.
Preferably, described expansion hot plate connects described apparatus installation plate by structural adhesion;
Between described heat conduction keysets and expansion heating panel, described outer subsides heat pipe and expand between hot plate and all adopt heat-conducting silicon rubber to bond between described outer subsides heat pipe and heat conduction keysets.
Preferably, wool carpet veneer is provided with between described two-seater clip and outer subsides heat pipe and between described single seat clip and outer subsides heat pipe.
Preferably, described apparatus installation plate adopts the lead-covering bending block that 30mm is thick.
Preferably, described outer subsides heat pipe employing cast is the outer subsides heat pipe of RG-CDRG-NH3-O1-50 × φ 15; Described outer subsides heat pipe adopts 6063 type aluminum alloy materials to make.
Preferably, described outer subsides heat pipe is Curved; The bending spring of described outer subsides heat pipe is 75mm.
Preferably, the thickness of described expansion heating panel is 1mm.
Preferably, described heat-conducting silicon rubber 6 adopts the trade mark to be 6GDA-508 type space level heat-conducting silicon rubber.
Compared with prior art, the utility model has following beneficial effect:
1, the utility model adopts and expands hot plate strengthening and achieve the design of pre-buried heat pipe isothermalization and outer subsides heat pipe in apparatus installation plate and be coupled with effective heat transfer of pre-buried heat pipe, alleviates large power consumption unit heat dissipation problem, enhances the adaptive capacity of thermal control;
2, the utility model adopts heat conduction keysets and bending outer subsides heat pipe combination, efficiently solves the installation convenience of heat transporting device on the outer loaded cylinder aircraft of complex configuration;
3, the utility model adopts outer subsides between heat pipe and expansion hot plate to adopt heat-conducting silicon rubber to connect, outer subsides heat pipe is fixed on by two-seater clip on the one hand and expands on hot plate and apparatus installation plate, be fixed on heat conduction keysets by single seat clip on the other hand, meet the demand reducing thermal contact resistance and anti-vibration mechanical condition;
4, expand the design of heating panel in the utility model, improve heat dissipation efficiency, heat delivery surface region stablized by the outer loaded cylinder aircraft of efficiency utilization complex configuration;
5, the utility model is convenient to enforcement, reliability is high, heat dissipation efficiency is high, weight resource occupation is few, is applicable to the outer loaded cylinder aircraft thermal design of complex configuration.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present utility model will become more obvious:
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the scheme of installation of the element such as pre-buried heat pipe and outer subsides heat pipe in the utility model.
In figure:
1 is apparatus installation plate;
2 is pre-buried heat pipe;
3 for expanding hot plate;
4 is outer subsides heat pipe;
5 is structural adhesion;
6 is heat-conducting silicon rubber;
7 is two-seater clip;
8 is expansion heating panel;
9 is single seat clip;
10 is heat conduction keysets.
Detailed description of the invention
Below in conjunction with specific embodiment, the utility model is described in detail.Following examples will contribute to those skilled in the art and understand the utility model further, but not limit the utility model in any form.It should be pointed out that to those skilled in the art, without departing from the concept of the premise utility, some distortion and improvement can also be made.These all belong to protection domain of the present utility model.
In the present embodiment, as depicted in figs. 1 and 2, the outer loaded cylinder aircraft integration thermal controls apparatus that the utility model provides comprises apparatus installation plate 1, pre-buried heat pipe 2, expansion hot plate 3, outer subsides heat pipe 4, structural adhesion 5, heat-conducting silicon rubber 6, two-seater clip 7, expansion heating panel 8, single seat clip 9 and heat conduction keysets 10; Wherein, pre-buried heat pipe 2 is positioned at apparatus installation plate 1, expands hot plate 3 and to be bonded on apparatus installation plate 1 by structural adhesion 5 and to stablize heat delivery surface side near aircraft; The one side of outer subsides heat pipe 4 is connected with expansion hot plate 3, is connected on the other hand with heat conduction keysets 10; Heat-conducting silicon rubber 6 is adopted to bond between heat conduction keysets 10 and expansion heating panel 8; Outer subsides heat pipe 4 one aspect is fixed on by two-seater clip 7 and expands on hot plate 3 and apparatus installation plate 1, is fixed on heat conduction keysets 10 on the other hand by single seat clip 9.
First pre-buried heat pipe 2 is imbedded in apparatus installation plate 1 by the utility model, need ensure that pre-buried heat pipe 2 is fitted well with the apparatus installation face lead-covering of apparatus installation plate 1, realizes the isothermalization design on apparatus installation plate with less cost; The lead-covering bending block that described apparatus installation plate 1 adopts 30mm thick, the lead-covering that its apparatus installation face 1 adopts 0.3mm thick; The cast of described pre-buried heat pipe 2 is RG-CDRG-NH3-J2-25 × 12 (Ω), and heat transfer capability is 440Wm, adopts 6063 type aluminum alloy materials to make.Then adopt structural adhesion 5 to be bonded in by worked-out expansion hot plate 3 on apparatus installation plate 1 and to stablize heat delivery surface side near aircraft, while realizing the heat collection on apparatus installation plate like this, alleviate large power consumption unit heat dissipation problem; Described expansion hot plate 3 adopts model to be that the aluminium sheet of 2A120 is made, and the definition base of its size is large power consumption unit attachment face size and covers all pre-buried heat pipes 2 to a certain extent.The trade mark of described structural adhesion 5 is J-133.
Further, use the tubing of the outer subsides heat pipe 4 of brake forming as technology and pattern assembly, one end of outer subsides heat pipe 4 is connected with expansion hot plate 3, the other end of outer subsides heat pipe 4 is connected with heat conduction keysets 10, to determine that heat conduction keysets 10 and expansion heating panel 8 are at the outer carry-on layout state of loaded cylinder of complex configuration, realize the transmitting of heat.Be connected to relending after adopting heat-conducting silicon rubber 6 to bond between heat conduction keysets 10 and expansion heating panel 8 in the outer loaded cylinder main structure of aircraft with Flight Vehicle Structure tightening of rivet after this trial assembly operation completes, the efficient discharge realizing heat is loose.Described outer subsides heat pipe 4 cast is RG-CDRG-NH3-O1-50 × φ 15 (Ω), heat transfer capability is 521Wm, 6063 type aluminum alloy materials are adopted to make, the bending spring 75mm of outer subsides heat pipe 4, the spademan of the bending area both sides of outer subsides heat pipe 4 can do suitable pruning, so that heat pipe tubing brake forming and be installed as principle, need ensure that outer subsides heat pipe 4 and the attachment face area planar degree expanding hot plate 3 are better than 200 × 200: 0.1mm and fits well.Described heat conduction keysets 10 designs its construction profile according to actual configuration, thickness 5mm, size dimension is to meet heat transfer capability for principle, adopt 2A120 model aluminum alloy to make, need ensure that outer subsides heat pipe 4 and the attachment face area planar degree of heat conduction keysets 10 are better than 200 × 200: 0.1mm and fit good.The thickness of described expansion heating panel 8 is 1mm, size dimension is to meet heat removal capacity for principle, adopt 2A120 model aluminum alloy to make, need ensure that heat conduction keysets 10 and the attachment face area planar degree of expansion heating panel 8 are better than 200 × 200: 0.1mm and fit good.Described heat-conducting silicon rubber 6 adopts the trade mark to be that 6GDA-508 type space level heat-conducting silicon rubber is made.Heat-conducting silicon rubber 6 is adopted to bond by between outer subsides heat pipe 4 one end and expansion hot plate 3; pad between two-seater clip 7 and outer subsides heat pipe 4 after adhesion process completes and fill wool felt; make two-seater clip 7 entangle outer subsides heat pipe 4 with screw again and be fixed on to expand on hot plate 3 and apparatus installation plate 1, thus protection outer subsides heat pipe 4 is not impaired.Described heat-conducting silicon rubber 6 adopts the trade mark to be 6GDA-508 type space level heat-conducting silicon rubber.Finally heat-conducting silicon rubber 6 can be adopted to bond the other end of outer subsides heat pipe 4 and heat conduction keysets 10, pad between single seat clip 9 and outer subsides heat pipe 4 after bonding process completes and fill wool felt, then make single seat clip 9 entangle outer subsides heat pipe 4 and be fixed on heat conduction keysets 10 with screw.
Above specific embodiment of the utility model is described.It is to be appreciated that the utility model is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present utility model.
Claims (7)
1. an outer loaded cylinder aircraft integration thermal controls apparatus, is characterized in that, comprises apparatus installation plate, pre-buried heat pipe, expansion hot plate, outer subsides heat pipe, expansion heating panel and heat conduction keysets;
Wherein, described pre-buried heat pipe is arranged in described apparatus installation plate; Described expansion hot plate is arranged on the upper surface of described apparatus installation plate;
Described outer subsides heat pipe is connected with described expansion hot plate on the one hand, is connected on the other hand with heat conduction keysets; Described expansion heating panel connects described heat conduction keysets;
Also comprise two-seater clip and single seat clip;
Wherein, described outer subsides heat pipe quantity is two; Two described outer subsides heat pipes expand hot plate, on the one hand on the other hand respectively by single seat anulated connection two heat conduction keysetss described in described two-seater anulated connection;
Described expansion hot plate is arranged on the upside of described pre-buried heat pipe;
Described expansion hot plate connects described apparatus installation plate by structural adhesion;
Between described heat conduction keysets and expansion heating panel, described outer subsides heat pipe and expand between hot plate and all adopt heat-conducting silicon rubber to bond between described outer subsides heat pipe and heat conduction keysets.
2. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, is characterized in that, be provided with wool carpet veneer between described two-seater clip and outer subsides heat pipe and between described single seat clip and outer subsides heat pipe.
3. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, it is characterized in that, described apparatus installation plate adopts the lead-covering bending block that 30mm is thick.
4. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, is characterized in that, described outer subsides heat pipe employing cast is the outer subsides heat pipe of RG-CDRG-NH3-O1-50 × φ 15; Described outer subsides heat pipe adopts 6063 type aluminum alloy materials to make.
5. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, it is characterized in that, described outer subsides heat pipe is Curved; The bending spring of described outer subsides heat pipe is 75mm.
6. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, it is characterized in that, the thickness of described expansion heating panel is 1mm.
7. outer loaded cylinder aircraft integration thermal controls apparatus according to claim 1, it is characterized in that, described heat-conducting silicon rubber 6 adopts the trade mark to be 6GDA-508 type space level heat-conducting silicon rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520734367.6U CN205221138U (en) | 2015-09-21 | 2015-09-21 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520734367.6U CN205221138U (en) | 2015-09-21 | 2015-09-21 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
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|---|---|
| CN205221138U true CN205221138U (en) | 2016-05-11 |
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|---|---|---|---|
| CN201520734367.6U Active CN205221138U (en) | 2015-09-21 | 2015-09-21 | Integrative heat -transmission accuse device of outer load section of thick bamboo aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184825A (en) * | 2016-09-18 | 2016-12-07 | 电子科技大学 | A kind of method improving fast respone space moonlet thermal control ability |
| CN106428634A (en) * | 2016-09-22 | 2017-02-22 | 北京空间飞行器总体设计部 | Main load-bearing structure suitable for ballistic reentry recovery capsule |
| CN108216694A (en) * | 2017-12-27 | 2018-06-29 | 中国科学院国家空间科学中心 | A kind of more equipment thermal vacuum test facilities |
| CN108791961A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of GEO satellite large span heat pipe configuration |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
| CN110143294B (en) * | 2019-04-11 | 2021-03-09 | 上海卫星工程研究所 | Thermal design structure of full-orbit full-attitude aircraft |
-
2015
- 2015-09-21 CN CN201520734367.6U patent/CN205221138U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184825A (en) * | 2016-09-18 | 2016-12-07 | 电子科技大学 | A kind of method improving fast respone space moonlet thermal control ability |
| CN106184825B (en) * | 2016-09-18 | 2018-04-06 | 电子科技大学 | A kind of method for improving fast respone space moonlet thermal control ability |
| CN106428634A (en) * | 2016-09-22 | 2017-02-22 | 北京空间飞行器总体设计部 | Main load-bearing structure suitable for ballistic reentry recovery capsule |
| CN106428634B (en) * | 2016-09-22 | 2018-12-18 | 北京空间飞行器总体设计部 | A kind of main force support structure reentering recovery capsule suitable for ballistic |
| CN108216694A (en) * | 2017-12-27 | 2018-06-29 | 中国科学院国家空间科学中心 | A kind of more equipment thermal vacuum test facilities |
| CN108791961A (en) * | 2018-06-14 | 2018-11-13 | 上海卫星工程研究所 | A kind of GEO satellite large span heat pipe configuration |
| CN109878764A (en) * | 2019-02-28 | 2019-06-14 | 上海微小卫星工程中心 | A kind of mechanical, electrical and heating integrated satellite structure plate |
| CN110143294B (en) * | 2019-04-11 | 2021-03-09 | 上海卫星工程研究所 | Thermal design structure of full-orbit full-attitude aircraft |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |