CN108974392A - A kind of more star transmitting Upper Stage satellite separating supports - Google Patents
A kind of more star transmitting Upper Stage satellite separating supports Download PDFInfo
- Publication number
- CN108974392A CN108974392A CN201810623976.2A CN201810623976A CN108974392A CN 108974392 A CN108974392 A CN 108974392A CN 201810623976 A CN201810623976 A CN 201810623976A CN 108974392 A CN108974392 A CN 108974392A
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- China
- Prior art keywords
- separating support
- upper stage
- cable
- heater
- multilayer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Thermal Insulation (AREA)
Abstract
The invention discloses a kind of more stars to emit Upper Stage satellite separating support, including more star adapters, separating support, heat insulating mattress, heater, thermistor, multilayer insulation component, heat-conducting silicon rubber, multilayer fixing buckle, thermal control cable, transit cable and transit cable electric connector；Separating support is connect by heat insulating mattress with more star adapters, heater and thermistor are pasted on separating support, thermal control cable is fixed by heat-conducting silicon rubber, thermal control cable and transit cable are connected at each separating support by transit cable electric connector, heater on each bracket is connected to form circuit by series-parallel system by transit cable, multilayer insulation component is coated outside separating support, multilayer insulation component is wrapped in heater, outside thermistor, and multilayer insulation component is fixed on separating support by multilayer fixing buckle.The present invention is convenient for general assembly and test, and high reliablity is adaptable, and aggregate resource occupancy is few.
Description
Technical field
The invention belongs to spacecraft thermal control design fields, more particularly to a kind of more star transmitting Upper Stage satellite separation branch
Frame.
Background technique
The more star adapters of certain Upper Stage are connect with satellite bracket by mounting bracket, and rack upper surface is to connect with satellite
Face, lower end are connect by connecting box with cylinder.Before satellite is separated with Upper Stage, Upper Stage need to guarantee Upper Stage satellite installation branch
Frame and satellite mounting surface temperature are not less than -10 DEG C.Entire more star adapter cylinders are passive body, and are exposed to deep cooling for a long time
In the outer space, external environment is severe.And separating support is often in discrete state due to total reload request with Upper Stage, but tests
When need to bring difficulty to thermal control design, test etc. in connection status again, meanwhile, in order to not influence the normal separation of satellite,
Thermal control will also pay close attention to anti-hook problem in the design process.
Currently, the development of Upper Stage has become gradually mature in foreign countries, but it is still in a completely new field at home, and it is similar
The thermal design of type separating support still belongs to the first time at home.Usual satellite bracket in thermal design, except in addition to the heat-insulated installation of celestial body, outside
Portion coats multilayer insulation component again, will not generally paste heater and carry out temperature-compensating, and Upper Stage separating support is due to its spy
Different temperature requirement, it is necessary to which leakage thermal compensation is carried out using compensating heater；General satellite is to improve reliability, is mostly used between cable
Crimping or welding mode, and if Upper Stage separating support inherit conventional satellite Thermal design, in order to meet in development process
General assembly and test request repeatedly will certainly be cut out and be connected to cable, to reduce the reliability of product, bring greatly
Risk；Separating support distribution simultaneously is at random, according to series-parallel system between the heater in conventional thermal design, will lead to parting surface
Place's cable is more and dissipates, and is difficult to meet anti-hook requirement, have an adverse effect to satellite separation, therefore during thermal design, needs
To use special and independent thermal design, while meeting general assembly and test request, improve product reliability.
Summary of the invention
For blank in the prior art and defect, the present invention provides a kind of Upper Stage satellite separating supports, are convenient for
General assembly and test, high reliablity is adaptable, and aggregate resource occupancy is few.
To achieve the above object, the invention is realized by the following technical scheme:
A kind of Upper Stage satellite separating support, which is characterized in that including more star adapters, separating support, heat insulating mattress, heating
Device, thermistor, multilayer insulation component, heat-conducting silicon rubber, multilayer fixing buckle, thermal control cable, transit cable and transit cable electricity
Connector；Separating support is connect by heat insulating mattress with more star adapters, and heater and thermistor, thermal control are pasted on separating support
Cable is fixed by heat-conducting silicon rubber, and thermal control cable passes through transit cable electric connector phase with transit cable at each separating support
Heater on each bracket is connected to form circuit by series-parallel system, coats multilayer outside separating support by connection, transit cable
Insulating assembly, multilayer insulation component are wrapped in heater, outside thermistor, and multilayer insulation component is fixed on by multilayer fixing buckle
On separating support.
Preferably, the separating support is aluminum alloy materials.
Preferably, the heat-insulated cushion material is titanium alloy.
Preferably, the heater is spacecraft Kapton type electric heater.
Preferably, the thermistor trade mark is MF501.
Preferably, the multilayer insulation component is made of T20-A terylene silk net and 6 μm of two-sided aluminized mylars, outermost
Layer is that 25 μm of conductivity type polyimides are aluminized second surface mirror.
Preferably, the heat-conducting silicon rubber trade mark is GDA508.
Preferably, the multilayer fixing buckle is velcro fastener.
Preferably, the thermal control cable and transit cable are the auspicious 55/0112-24-9 that chats about.
Preferably, the transit cable electric connector model Y4-7ZJL.
The technology belongs at home to be applied for the first time, compared with existing similar technique, the present invention have it is following the utility model has the advantages that
1, separating support and more heat-insulated installations of star adapter are reduced by leakage heat loss using titanium alloy material；
2, heater and thermistor are pasted on the outside of separating support, are realized to the autonomous temperature control of separating support, are guaranteed
Before satellite separation, separating support temperature index meets requirement；
3, stent outer coats multilayer insulation component, reduces radiation leakage heat；
4, using heat-conducting silicon rubber by thermal control cable away from bracket parting surface 3mm fix, will be more using multilayer fixing buckle
Layer is fixed on bracket, is prevented cable and multilayer from hooking and is had an impact to satellite separation；
5, thermal control cable and transit cable are docked at separating support using electrical adapter connector, is convenient for general assembly and test
The separation and assembling of bracket and more star adapters in the process.
6, the technology is convenient for general assembly and test, and high reliablity is adaptable, and aggregate resource occupancy is few, is suitable for more stars
Emit the thermal design of Upper Stage separating support.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the structural schematic diagram that a kind of more stars of the embodiment of the present invention emit Upper Stage satellite separating support.
Fig. 2 is cable connection schematic diagram of transferring in the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As depicted in figs. 1 and 2, the embodiment of the invention provides a kind of Upper Stage satellite separating support Thermal designs includes
Separating support 1, heat insulating mattress 2, heater 3, multilayer insulation component 4, heat-conducting silicon rubber 5, multilayer fixing buckle 6, thermistor 7, heat
Electric control cable 8, transit cable 9, electrical adapter connector 10；Separating support 1 is connect by heat insulating mattress 2 with more star adapters, separation branch
Heater 3 and thermistor 7 are pasted on the outside of frame 1, multilayer insulation component 4 are coated outside separating support 1, using multilayer fixing buckle 6
Multilayer insulation component 4 is fixed on separating support 1, multilayer insulation component is wrapped in heater, outside thermistor；Thermal control cable
8 are pasted on separating support by heat-conducting silicon rubber 5, and distance separation face at least 3mm, thermal control cable 8 and transit cable 9 are at each point
It is connected from transit cable electric connector 10 is passed through at bracket 1, transit cable 9 passes through series-parallel system for the heater on each bracket
3 are connected to form circuit.
Separating support 1 is connect by heat insulating mattress 2 with more star adapters by the present invention first, reduces leakage heat, while being reduced total
Body resource consumption；Preferably, 2 material of heat insulating mattress is titanium alloy；1 surface mount heater 3 of separating support and thermistor
7, to carry out temperature-compensating to separating support 1 when temperature is lower, guarantee the temperature levels of the separating support 1 before satellite separates
In the range of index request；Preferably, the heater 3 is spacecraft Kapton type electric heater, temperature-sensitive electricity
The resistance trade mark is MF501；Multilayer insulation component 4 is coated outside separating support 1, it is effective to reduce radiation leakage heat, multilayer insulation component 4
It is fixed on separating support 1 by multilayer fixing buckle 6, prevents multilayer from falling off and cause to hook；Preferably, multilayer insulation component 4 by
T20-A terylene silk net and 6 μm of two-sided aluminized mylars and outermost layer are that 25 μm of conductivity type polyimides are aluminized secondary surface
Microscope group is at multilayer fixing buckle is velcro fastener；Thermal control cable 8 by heat-conducting silicon rubber 5 paste with separating support 1 on, distance separation
Face at least 3mm prevents from hooking problem because caused by cable is at random；Preferably, 5 trade mark of heat-conducting silicon rubber is GDA508, thermal control
Cable 8 is the auspicious 55/0112-24-9 that chats about；Transit cable 9 will be distributed over adding on different separating supports 1 by series-parallel mode
The hot connection of device 3 forming circuit, and docked at separating support 1 with electrical adapter connector 10, finally it is connected with thermal control cable 8,
System reliability can be improved, risk is reduced to avoid the contradiction because of caused by general assembly with test request difference；Preferably, it transfers
Cable 9 is the auspicious 55/0112-24-9 that chats about, electrical adapter connector model Y4-7ZJL.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (10)
1. a kind of more stars emit Upper Stage satellite separating support, which is characterized in that including more star adapters, separating support, heat-insulated
Pad, heater, thermistor, multilayer insulation component, heat-conducting silicon rubber, multilayer fixing buckle, thermal control cable, transit cable and switching
Cable electrical connector；Separating support is connect by heat insulating mattress with more star adapters, and heater and temperature-sensitive electricity are pasted on separating support
Resistance, thermal control cable are fixed by heat-conducting silicon rubber, and thermal control cable and transit cable pass through transit cable electricity at each separating support
Connector is connected, and the heater on each bracket is connected to form circuit by series-parallel system by transit cable, outside separating support
Multilayer insulation component is coated, multilayer insulation component is wrapped in heater, outside thermistor, and multilayer insulation component is fixed by multilayer
Button is fixed on separating support.
2. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the separation branch
Frame is aluminum alloy materials.
3. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the heat insulating mattress
Material is titanium alloy.
4. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the heater
For spacecraft Kapton type electric heater, two-way is set, each other master backup.
5. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the temperature-sensitive electricity
The resistance trade mark is MF501.
6. a kind of more stars according to claim 1 emit Upper Stage satellite separating supports, which is characterized in that the multilayer every
Hot component aluminizes two by T20-A terylene silk net, 6 μm of two-sided aluminized mylars and outermost 25 μm of conductivity type polyimides
Subsurface microscope group at.
7. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the thermal conductive silicon
The rubber trade mark is GDA508.
8. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the multilayer is solid
Fixed button is velcro fastener.
9. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the thermal control electricity
Cable and transit cable are the auspicious 55/0112-24-9 that chats about.
10. a kind of more stars according to claim 1 emit Upper Stage satellite separating support, which is characterized in that the switching
Cable electrical connector model Y4-7ZJL.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810623976.2A CN108974392A (en) | 2018-06-15 | 2018-06-15 | A kind of more star transmitting Upper Stage satellite separating supports |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810623976.2A CN108974392A (en) | 2018-06-15 | 2018-06-15 | A kind of more star transmitting Upper Stage satellite separating supports |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108974392A true CN108974392A (en) | 2018-12-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810623976.2A Pending CN108974392A (en) | 2018-06-15 | 2018-06-15 | A kind of more star transmitting Upper Stage satellite separating supports |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5429875A (en) * | 1992-07-15 | 1995-07-04 | National Aerospace Laboratory Of Science & Technology Agency | Mounting object provided with a metallic heat-resistant two-dimensional fastener |
| JPH09207897A (en) * | 1996-02-09 | 1997-08-12 | Nissan Motor Co Ltd | Heat controller of penetrator |
| CN103332302A (en) * | 2013-06-18 | 2013-10-02 | 上海宇航系统工程研究所 | Thermal control device and thermal control method for disengaging mechanism |
| CN104369876A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星工程研究所 | Low-temperature differential thermal control device for infrared horizon sensors of orbit transfer vehicle |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
| US20150344157A1 (en) * | 2012-12-25 | 2015-12-03 | Kawasaki Jukogyo Kabushiki Kaisha | Separation mechanism of space structure |
-
2018
- 2018-06-15 CN CN201810623976.2A patent/CN108974392A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5429875A (en) * | 1992-07-15 | 1995-07-04 | National Aerospace Laboratory Of Science & Technology Agency | Mounting object provided with a metallic heat-resistant two-dimensional fastener |
| JPH09207897A (en) * | 1996-02-09 | 1997-08-12 | Nissan Motor Co Ltd | Heat controller of penetrator |
| US20150344157A1 (en) * | 2012-12-25 | 2015-12-03 | Kawasaki Jukogyo Kabushiki Kaisha | Separation mechanism of space structure |
| CN103332302A (en) * | 2013-06-18 | 2013-10-02 | 上海宇航系统工程研究所 | Thermal control device and thermal control method for disengaging mechanism |
| CN104369876A (en) * | 2014-10-31 | 2015-02-25 | 上海卫星工程研究所 | Low-temperature differential thermal control device for infrared horizon sensors of orbit transfer vehicle |
| CN104443441A (en) * | 2014-10-31 | 2015-03-25 | 上海卫星工程研究所 | Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927940A (en) * | 2019-02-19 | 2019-06-25 | 上海卫星工程研究所 | Solar array driving mechanism temperature barrier |
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| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181211 |