CN202797273U - Thermal protection device for moving parts of movable spot beam antennas - Google Patents
Thermal protection device for moving parts of movable spot beam antennas Download PDFInfo
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- CN202797273U CN202797273U CN 201220351154 CN201220351154U CN202797273U CN 202797273 U CN202797273 U CN 202797273U CN 201220351154 CN201220351154 CN 201220351154 CN 201220351154 U CN201220351154 U CN 201220351154U CN 202797273 U CN202797273 U CN 202797273U
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- 239000011248 coating agent Substances 0.000 claims abstract description 13
- 238000000576 coating method Methods 0.000 claims abstract description 13
- 238000009413 insulation Methods 0.000 claims description 32
- 230000007246 mechanism Effects 0.000 claims description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 9
- 229910052782 aluminium Inorganic materials 0.000 claims description 9
- 239000011888 foil Substances 0.000 claims description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 239000010949 copper Substances 0.000 claims description 6
- 210000000056 organ Anatomy 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims 2
- 230000005855 radiation Effects 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 7
- 229920000742 Cotton Polymers 0.000 description 13
- 230000004888 barrier function Effects 0.000 description 10
- 230000000712 assembly Effects 0.000 description 5
- 238000000429 assembly Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 239000011229 interlayer Substances 0.000 description 4
- 239000010410 layer Substances 0.000 description 4
- 230000001815 facial effect Effects 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
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Abstract
本实用新型公开了一种可动点波束天线活动部件的热防护装置，该装置包括温控组件、天线衣、多层帐篷和接地组件，采用可动点波束天线活动部件的热防护装置与以往的贴体热控包覆相比，其可靠性更高，实施方便，漏热更小，不会因热控包覆的因素影响天线的转动功能；由于这种方法充分利用帐篷内的辐射换热，使得其内部部件的温度水平更加均匀，且大大减少了加热器的数量和加热器的功率。
The utility model discloses a thermal protection device for movable parts of a movable spot beam antenna. The device comprises a temperature control component, an antenna coat, a multilayer tent and a grounding component. Compared with the body-fitting thermal control coating, its reliability is higher, the implementation is convenient, the heat leakage is smaller, and the rotation function of the antenna will not be affected by the factors of the thermal control coating; because this method makes full use of the radiation exchange in the tent heat, making the temperature level of its internal components more uniform, and greatly reducing the number of heaters and the power of the heaters.
Description
Technical field
The utility model relates to temperature barrier, is specifically related to a kind of temperature barrier of movable spot beam anternma movable part.
Background technology
Movable spot beam anternma generally is comprised of main reflector, feed, rotating unit, directing mechanism, rotary joint etc., as shown in Figure 1, be installed in the spacecraft outer surface, wherein rotating unit, directing mechanism and rotary joint are the movable part of movable spot beam anternma.
Antenna direction mechanism is the actuator that antenna beam moves.Thereby it is to rotate the wave beam of realizing antenna east-west direction and North and South direction by X-axis rotating unit, X-axis rotary joint and Y-axis rotating unit, Y-axis rotary joint to move, and the movement of spot beam in visual field over the ground finished in two cover rotating units, rotary joint collaborative work.For the movable part that guarantees antenna does not have influence on the antenna rotation precision because of the space environment variations in temperature in rotation process, need to carry out to the movable part of antenna thermal control and implement to guarantee that its working temperature is between-25 ℃～+ 50 ℃, for this reason, the mode that the temperature control of taking the initiative combines with passive temperature control, the active temperature control mode is for pasting the temperature control assembly that comprises temp-controlling element and heater at rotating unit and rotary joint, heater links to each other with temp-controlling element, temp-controlling element links to each other with the computer software of spacecraft, start working being lower than under the temperature control threshold value heater when rotating unit and rotary joint temperature, disconnect being higher than temperature control threshold value upper heater when rotating unit and rotary joint temperature; Passive temperature control is the mode of taking to coat multilayer insulation assembly, spraying high emissivity coating.Traditional multilayer insulation assembly coating mode is that controlled device is carried out fit coating, the movable part of considering movable spot beam anternma moves, take fit coating, if it is not tight, fixing not firm to coat, may interfere with movable part, with near low-frequency cable line hook, rotate thereby affect antenna; And fit coating can only coat in relatively motionless zone, can not coat between the parts of relative motion, between the multilayer insulation assembly, can produce so larger leakage heat, affect the temperature levels of movable part, make movable part produce larger temperature fluctuation, and need larger heater power.
The utility model content
In view of this, the utility model provides a kind of temperature barrier of movable spot beam anternma movable part, can guarantee the temperature of movable part in the antenna, can guarantee that again the thermal control coating can not affect antenna and rotate.
The temperature barrier of a kind of movable spot beam anternma movable part of the present invention comprises temperature control assembly, day cotton knitwear, multilayer tent and grounding assembly, wherein:
Cotton knitwear was made according to the size at the main reflector back of antenna by the multilayer insulation assembly in described day, and a day cotton knitwear is paved with the main reflector back and fits together with it;
The cylinder-like structure of described multilayer tent for being made by the multilayer insulation assembly, the multilayer tent extends to the spacecraft module plate straight down from the main reflector back, and in directing mechanism, X-axis rotating unit, X-axis rotary joint, Y-axis rotating unit, Y-axis rotary joint, locking releasing device and the waveguide assemblies of movable spot beam anternma be coated on, simultaneously, the multilayer tent has the surplus that the antenna release is rotated in short transverse; The upper end of multilayer tent is fixed on the main reflector back of antenna, and with its on sky cotton knitwear overlap joint; The bottom of multilayer tent is fixed on the spacecraft module plate, and with the spacecraft module plate on the multilayer insulation assembly overlap joint laid;
Described multilayer insulation assembly comprises 5 layers of radiation shield, 5 interlayer interlayers and 1 aspect film, and radiation shield and wall interfolded form multilayer core by sewing up, and facial mask is coated on respectively on the outermost layer radiation shield of multilayer core, finally forms the multilayer insulation assembly;
Described temperature control assembly has 4 covers, includes heater and temp-controlling element, and a cover temperature-controlling component respectively is set on X-axis rotating unit, X-axis rotary joint, Y-axis rotating unit, the Y-axis rotary joint;
Described grounding assembly comprises aluminum foil strip, hollow copper rivet and earth connection, aluminum foil strip is the lamination organ type structure with 5 bendings, each bending is embedded on one deck radiation shield of multilayer insulation assembly, and aluminum foil strip is linked together by hollow copper rivet and earth connection, and earth connection connects the ground of spacecraft.
Device of the present invention comprises that also the emissivity that is sprayed on directing mechanism, X-axis rotating unit, X-axis rotary joint, Y-axis rotating unit, Y-axis rotary joint, locking releasing device and waveguide assemblies surface in the multilayer tent is greater than 0.85 high emissivity coating.
Described multilayer tent is formed through the velcro overlap joint by two multilayer insulation assemblies.
The sky cotton knitwear at the main reflector back of described antenna is fixed on main reflector back by pin and compressing tablet.
The temperature barrier of a kind of movable spot beam anternma movable part of the present utility model, adopt the temperature barrier of movable spot beam anternma movable part to compare with fit thermal control coating in the past, its reliability is higher, it is convenient to implement, it is less to leak heat, the rotating function of the factor affecting antenna that can not coat because of thermal control; Because this method takes full advantage of the radiation heat transfer in the tent, so that the temperature levels of its internal part is more even, and has greatly reduced the quantity of heater and the power of heater.
Description of drawings
Fig. 1 is certain movable spot beam anternma structural representation of the prior art.
Fig. 2 is certain the movable spot beam anternma structural representation that has coated temperature barrier of the present invention.
Fig. 3 has coated certain movable spot beam anternma directing mechanism of temperature barrier of the present invention at the rail temperature curve.
Wherein, 1-subreflector, 2-feed, 3-main reflector, 4-directing mechanism, 5-Y axle rotating unit, 6-Y axle rotary joint, 7-X axle rotary joint, 8-X axle rotating unit, 9-locking releasing device, the 10-mounting panel, 11-spacecraft module plate, 12-multilayer tent, 13-days cotton knitwears.
Embodiment
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, the utility model is described in detail.
The utility model provides a kind of temperature barrier of movable spot beam anternma movable part, comprises temperature control assembly, day cotton knitwear 13, multilayer tent 12 and grounding assembly, wherein:
As shown in Figure 2, a day cotton knitwear 13 is made according to the size at main reflector 3 backs of antenna by the multilayer insulation assembly, and a day cotton knitwear 13 is paved with main reflector 3 backs and fits together with it.For the fastness that guarantees that day cotton knitwear 13 and main reflector 3 are fixing, present embodiment adopts pin and compressing tablet to be fixed, and beats pin holes at sky cotton knitwear 13 in advance, passes successively the back that is fixed on again main reflector 3 behind compressing tablet and the pin hole with pin.
The cylinder-like structure of multilayer tent 12 for being made by the multilayer insulation assembly, multilayer tent 12 extends to spacecraft module plate 11 straight down from main reflector 3 backs, and with the directing mechanism 4 of movable spot beam anternma, X-axis rotating unit 8, X-axis rotary joint 7, Y-axis rotating unit 5, Y-axis rotary joint 6, in locking releasing device 9 and partial waveguide assembly are coated on, for making antenna at locking state, in deployed condition and the rotation process, multilayer tent 12 not can with tent in parts interfere, can not affect the motion of antenna, need to make sizeable multilayer insulation assembly, and under the antenna deployed condition, carry out trial assembly, to guarantee that antenna launches and rotation.If tent is too large, may hook antenna movable part in the vacuum deflation process or block movable part; If tent is too little, may interfere movable part in antenna expansion or the rotation process, hinder antenna movement.Therefore, multilayer tent 12 has the surplus that the antenna release is rotated in short transverse; The upper end of multilayer tent 12 is fixed on main reflector 3 backs of antenna, and with its on sky cotton knitwear 13 overlap joint; The bottom of multilayer tent is fixed on the spacecraft module plate 11, and with spacecraft module plate 11 on the multilayer insulation assembly overlap joint laid.
Consider that movable spot beam anternma is to coating inner temperature, the weight of multilayer insulation assembly and the needs of pliability, the multilayer insulation assembly that the present invention adopts comprises 5 layers of radiation shield, 5 interlayer interlayers and 1 aspect film, sew up after radiation shield and the wall interfolded, form multilayer core, facial mask is coated on respectively on the outermost layer radiation shield of multilayer core, finally forms the multilayer insulation assembly.
For convenient processing, the multilayer tent adopts two multilayer insulation assemblies to process, and in the lap-joint of two multilayer insulation assemblies, adopts " hook " and " circle " aligning of velcro to compress.
After adopting day cotton knitwear 13 and multilayer tent 12 with the antenna parcel, the multilayer insulation assembly can go back the emission of antenna outside heat, simultaneously the parts of its inside are played the effect of insulation, because temperature contrast is larger in the space, it is inadequate only adopting the multilayer insulation assembly that antenna is carried out solar heat protection, all can under the temperature conditions that requires, work under the various environment for guaranteeing the antenna movable part, need to the temperature control assembly be set at each rotating unit and each rotary joint, namely comprise temp-controlling element and heater, identical with the principle of prior art, temp-controlling element and heater are by the computer software control of spacecraft, the temperature control threshold value also can be changed according to surface instruction, when temperature is lower than the threshold value of setting, open heater, make it to each rotating unit and the heating of each rotary joint, when temperature is higher than the threshold value of setting, close heater, reduce the temperature of rotating unit and each rotary joint.
In order to prevent the too much static of accumulation on the multilayer insulation assembly, static discharge occurs, the present invention also is provided with grounding assembly, grounding assembly comprises aluminum foil strip, hollow copper rivet and earth connection, aluminum foil strip is the lamination organ type structure with 5 bendings, each bending is embedded on one deck radiation shield of multilayer insulation assembly, and aluminum foil strip is linked together by hollow copper rivet and earth connection, and earth connection connects the ground of spacecraft.When producing electric charge on the multilayer insulation assembly, can be guided to by grounding assembly the ground of spacecraft.
In order to strengthen the radiation heat transfer of all parts in the tent, make each part temperatures level more even, the parts surface in the multilayer tent 12 on all antennas all sprays high emissivity coating, requires emissivity ε H 〉=0.85.
Certain satellite was launched in September, 2011, the satellite rear movable spot beam anternma of entering the orbit is working properly, rotating unit and the rotary joint temperature of movable spot beam anternma directing mechanism satisfy its work and storage temperature requirement, Fig. 3 provided movable spot beam anternma rotating unit and rotary joint at beginning of lifetime to some temperature curve in orbit, can find out that each rotating unit and each rotary joint temperature are between-11 ℃～+ 26 ℃, apart from its working temperature and storage temperature upper and lower limit larger surplus is arranged all, maximum temperature difference only is 4 ℃ between each movable part.
In sum, more than be preferred embodiment of the present utility model only, be not be used to limiting protection range of the present utility model.All within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., all should be included within the protection range of the present utility model.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220351154 CN202797273U (en) | 2012-07-19 | 2012-07-19 | Thermal protection device for moving parts of movable spot beam antennas |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220351154 CN202797273U (en) | 2012-07-19 | 2012-07-19 | Thermal protection device for moving parts of movable spot beam antennas |
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| Publication Number | Publication Date |
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| CN202797273U true CN202797273U (en) | 2013-03-13 |
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| CN 201220351154 Expired - Lifetime CN202797273U (en) | 2012-07-19 | 2012-07-19 | Thermal protection device for moving parts of movable spot beam antennas |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104319455A (en) * | 2014-09-29 | 2015-01-28 | 西安空间无线电技术研究所 | Satellite-borne movable antenna single-point locking system |
| CN107994338A (en) * | 2017-11-20 | 2018-05-04 | 航天材料及工艺研究所 | Integrated antenna protective cover for Mars exploration and landing patrol device and preparation method thereof |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN109004335A (en) * | 2018-06-19 | 2018-12-14 | 上海卫星工程研究所 | A kind of thermal control design method of the large aperture antenna suitable for mars exploration |
| CN109326866A (en) * | 2018-11-06 | 2019-02-12 | 上海航天测控通信研究所 | A kind of two-dimentional directional antenna with initial direction-pointing function suitable for high rail satellite |
| CN109413964A (en) * | 2018-12-14 | 2019-03-01 | 北京无线电测量研究所 | A kind of and integrated spaceborne phase array radar load of satellite platform structure thermal control |
| CN111799559A (en) * | 2020-07-14 | 2020-10-20 | 中国电子科技集团公司第五十四研究所 | Two-dimensional pointing mechanism of waveguide type satellite-borne antenna |
| CN112298619A (en) * | 2020-11-05 | 2021-02-02 | 上海卫星工程研究所 | Ultra-stable temperature control device and method for cables between SAR antenna boards |
| CN113964473A (en) * | 2021-09-30 | 2022-01-21 | 亚太卫星宽带通信（深圳）有限公司 | Thermal protection device for movable part of movable spot beam antenna |
-
2012
- 2012-07-19 CN CN 201220351154 patent/CN202797273U/en not_active Expired - Lifetime
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104319455B (en) * | 2014-09-29 | 2017-01-25 | 西安空间无线电技术研究所 | Satellite-borne movable antenna single-point locking system |
| CN104319455A (en) * | 2014-09-29 | 2015-01-28 | 西安空间无线电技术研究所 | Satellite-borne movable antenna single-point locking system |
| CN107994338B (en) * | 2017-11-20 | 2021-06-11 | 航天材料及工艺研究所 | Integrated antenna protective cover for Mars detection landing patrol and preparation method thereof |
| CN107994338A (en) * | 2017-11-20 | 2018-05-04 | 航天材料及工艺研究所 | Integrated antenna protective cover for Mars exploration and landing patrol device and preparation method thereof |
| CN109004335A (en) * | 2018-06-19 | 2018-12-14 | 上海卫星工程研究所 | A kind of thermal control design method of the large aperture antenna suitable for mars exploration |
| CN109004335B (en) * | 2018-06-19 | 2021-07-30 | 上海卫星工程研究所 | Thermal control design method of large-caliber antenna suitable for Mars detection |
| CN108820259A (en) * | 2018-06-25 | 2018-11-16 | 上海卫星工程研究所 | A kind of whole temperature barrier being adapted to the outer rotating mechanism multi-dimensional movement of star |
| CN109326866A (en) * | 2018-11-06 | 2019-02-12 | 上海航天测控通信研究所 | A kind of two-dimentional directional antenna with initial direction-pointing function suitable for high rail satellite |
| CN109413964A (en) * | 2018-12-14 | 2019-03-01 | 北京无线电测量研究所 | A kind of and integrated spaceborne phase array radar load of satellite platform structure thermal control |
| CN111799559A (en) * | 2020-07-14 | 2020-10-20 | 中国电子科技集团公司第五十四研究所 | Two-dimensional pointing mechanism of waveguide type satellite-borne antenna |
| CN112298619A (en) * | 2020-11-05 | 2021-02-02 | 上海卫星工程研究所 | Ultra-stable temperature control device and method for cables between SAR antenna boards |
| CN113964473A (en) * | 2021-09-30 | 2022-01-21 | 亚太卫星宽带通信（深圳）有限公司 | Thermal protection device for movable part of movable spot beam antenna |
| CN113964473B (en) * | 2021-09-30 | 2024-08-20 | 亚太卫星宽带通信（深圳）有限公司 | Thermal protection device for movable part of movable spot beam antenna |
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Granted publication date: 20130313 |
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| CX01 | Expiry of patent term |