CN104477415B - Light-shading heat-insulation cover framework structure for spacecraft - Google Patents
Light-shading heat-insulation cover framework structure for spacecraft Download PDFInfo
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- CN104477415B CN104477415B CN201410675277.4A CN201410675277A CN104477415B CN 104477415 B CN104477415 B CN 104477415B CN 201410675277 A CN201410675277 A CN 201410675277A CN 104477415 B CN104477415 B CN 104477415B
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- stringer
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- shading heat
- support
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Abstract
The invention provides a light-shading heat-insulation cover framework structure for a spacecraft. The light-shading heat-insulation cover framework structure comprises multiple thermal control layers and a framework structure body, wherein the multiple thermal control layers are bound and fixed to the outer surface of the light-shading heat-insulation cover framework structure for the spacecraft to form a complete light-shading heat-insulation cover structure. The framework structure comprises a support, trusses and auxiliary trusses. The light-shading heat-insulation cover framework structure is designed by adopting a structure optimization concept, and the lightweight whole structure is achieved on the basis that enough strength, rigidity and envelope are ensured. A framework is wrapped by multiple layers to form a light-shading heat-insulation cover, a semi-airtight space is formed, the light-shading heat-insulation cover does not interfere a mechanism installed in the cover when the driving end and an on-rail mechanism operate, and good thermal control effect is also played. A material selected for the whole structure meets the spaceflight demand and has the advantages of being light in weight, simple in structure, high in universality and the like.
Description
Technical field
The present invention relates to a kind of envelope structure that supports, specifically a kind of spacecraft shading heat shield framing structure.
Background technology
For spacecraft, thermal control is an important ring.Present stage, the internal unit of spacecraft processed by surface,
The cladding mode Comprehensive Control such as multilamellar, pre-buried heat pipe, active balance, control unit temperature, it is ensured that unit is effectively transported
OK.But for the mechanism's series products being arranged on outside spacecraft, simple dependence face coat is not with directly cladding multilamellar can
Operating temperature is effectively ensured, and the mechanism outside the highest rail satellite health, within one day, sunlight straight fluidic time reaches several little
Time, the easy Long-term service temperature of movable part such as motor is too high causes short service life even to lose efficacy.
Spacecraft shading heat shield is installed on outside mechanism, and surface is the round table surface formed after multilayer coating structure, effectively
Block sunlight, the heat that isolation illumination brings, it is to avoid mechanism is operated under severe thermal environment.Therefore spacecraft
With shading heat shield, the mechanism's series products being arranged on outside spacecraft had certain thermal control value and application prospect.But
The structure of shading heat shield of the prior art is the most complicated.
Summary of the invention
For defect of the prior art, it is an object of the invention to provide a kind of spacecraft shading heat shield skeleton knot
Structure, forms the shading heat shield being installed on outside mechanism's product after coated multilamellar.
A kind of spacecraft shading heat shield framing structure provided according to the present invention, including: support, stringer and
Auxiliary stringer；
Support uses screw to be connected with stringer, and auxiliary stringer and stringer are tied up to fix and be spaced and be arranged in what stringer extended
On periphery, to form cylindrical envelope framing structure；
Installation through hole needed for reserved cladding heat-control multilayer on stringer and auxiliary stringer, provide for heat-control multilayer support and
Immobilizing foundation.
Preferably, described cylindrical envelope framing structure is provided with breach.
Preferably, number of holders be 3-4 part, stringer quantity be 4-8 part, auxiliary stringer quantity is 6-10 part.
Preferably, support is one-body molded or welds, and bracket cross section is right angled triangle, and a right-angle surface is that stringer is installed
Face, another right-angle surface is the bottom surface as spacecraft joint face, and inclined-plane plays enhancing support effect.
Preferably, support uses aluminium alloy 2A14T6 material；Stringer uses carbon fiber winding molding；Auxiliary stringer
Use fiberglass thin slice, for providing mounting interface for heat-control multilayer, and be supplied to assist support to play reinforcement entirety
Stiffness.
Preferably, stringer includes the horizontal segment that segmental arc and segmental arc two ends each extend over out, segmental arc and 2
Horizontal segment is connected with corresponding support respectively.
A kind of spacecraft shading heat shield provided according to the present invention, including: heat-control multilayer and claim 1
To the shading heat shield framing structure of the spacecraft according to any one of 6；
The outer surface that heat-control multilayer is fixed on described spacecraft shading heat shield framing structure by binding has been formed
Whole shading heat shield structure.
Preferably, heat-control multilayer forms complete face of cylinder cladding.
Compared with prior art, the present invention has a following beneficial effect:
1, configuration of the present invention is simple, has good processing technology and assembly process process；
2, skeleton appropriate design stringer radius and horizontal section length, backing thickness, it is ensured that in powered phase, mechanism
Form hemi-closure space on the basis of not interfering under active state, after cladding multilamellar, be effectively improved thermal environment.
3, stringer uses carbon fibre material, and support uses 2A14T6, auxiliary stringer to use fiberglass.Support is carried out
Hollow out process, it is ensured that effectively reduce weight on the basis of rigidity, it is achieved light-weight design.
Accompanying drawing explanation
By the detailed description non-limiting example made with reference to the following drawings of reading, the further feature of the present invention,
Purpose and advantage will become more apparent upon:
Fig. 1 is the spacecraft shading heat shield framing structure schematic diagram of the present invention；
Fig. 2 be the present invention spacecraft shading heat shield structure in schematic diagram after installing mechanism；
Fig. 3, Fig. 4 are stent configuration schematic diagrams；
Fig. 5, Fig. 6 are stringer schematic diagrams.
In figure:
101 is support A；
102 is support B；
200 is auxiliary stringer；
201 is stringer A；
202 is stringer B；
3 is heat-control multilayer；
4 is mechanism；
5 is spacecraft shading heat shield framing structure.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in those skilled in the art
Member is further appreciated by the present invention, but limits the present invention the most in any form.It should be pointed out that, the common skill to this area
For art personnel, without departing from the inventive concept of the premise, it is also possible to make some deformation and improvement.These broadly fall into
Protection scope of the present invention.
The related art features of spacecraft shading heat shield framing structure of the present invention is as follows:
1. the present invention uses support, stringer, auxiliary stringer to connect and forms cylindrical carcass structure, and middle part is installed to be needed to hide
The mechanism that light is heat insulation, forms shading heat shield after cladding multilamellar.Because being installed on internal mechanism operationally sports envelope needs,
Can reserve during design gap with avoid and mechanism kinematic envelope interfere, as both without interfere, then can carry out complete circle cylinder bag
Cover.The height of framing structure and envelope, can carry out adaptability change according to layout and thermal control demand to support and stringer.
2. framing structure is altogether by 1 support A, two support B, two stringer A, two stringer B, forms three after assembling
The cylindrical hollow configuration of bar installation foot.Internally installed mechanism, forms the semitight working environment of a mechanism.
3. support A, support B are right triangular cross-sectional, two right-angle surface one bottom surfaces being to leave installing hole, connect boat
It device, another connects installed surface for stringer, leaves two row's installing holes.Hypotenuse plays reinforced support or even whole skeleton rigidity
Effect.Support entirety uses lightweight Integral design, and except connecting portion, hypotenuse, remaining place carries out hollowing out process.?
Frame form is consistent, and size can be the most inconsistent.
4. the basic envelope of skeleton is circular, considers mechanism configuration feature and drive end environmental effect, appropriate design purlin during design
Bar arc section radius and horizontal section length.
5. in support B, stringer connects installed surface, and institute's perforate exceedes and is actually needed, can be by selecting installing hole regulation envelope chi
Very little.I.e. support B connects stringer opened screwed hole quantity and exceedes connection needs, in particular cases may select installing hole thus changes
Become envelope, enhance versatility.
6, stringer A, stringer B, according to internal institute installing mechanism, form is consistent but size is not quite identical, wherein circular arc
Section diameter is consistent, and bending junction is according to the concrete configuration of connection requirement and internally installed mechanism, and length can be inconsistent.
The spacecraft shading heat shield and the spacecraft shading heat shield framing structure thereof that there is provided the present invention below are carried out
Describe in detail.
Spacecraft shading heat shield is mainly made up of spacecraft shading heat shield framing structure and heat-control multilayer, spacecraft
All leave aperture with on the support of shading heat shield framing structure, stringer, auxiliary stringer, heat-control multilayer is threaded through pre-
Box out, be fixed on after colligation in framing structure, form complete shading heat shield.Framing structure provides for heat-control multilayer and installs
Position and supporting role, tie up that rear heat-control multilayer is exceptionally straight to be laid in the outer round table surface of skeleton, it is ensured that thermal control after powered phase
Multilamellar, not in slack and undisciplined shape, can effectively keep being coated on outside framing structure.
Stringer of the present invention uses carbon fibre composite, support to use aluminium alloy, and two materials are respectively provided with that density is little, specific strength
The advantage high with specific modulus.Stringer simple shape, only needs at the bottom of one set of die and mould difficulty of processing.Support is engraved in a large number
Empty design, can the most solderable one-body molded molding.Thus the present invention have light weight, be simple to manufacture, the advantage of low cost.
Framing structure can effectively support whole shading heat shield, it is ensured that whole shading heat shield has certain strength and stiffness,
Powered phase ensure shading heat shield both will not stress excessive and produce destruction, owing to deformation is excessive, inside will not be pacified again
Mounting mechanism produces interferes.
Will not be because of self-deformation in powered phase through simulation analysis and verification experimental verification shading heat shield in design process of the present invention
Produce with mechanism and interfere, analysis institution's sports envelope simultaneously, reserved space or gap, it is ensured that will not to mechanism in-orbit
Running status produces interferes.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in
Stating particular implementation, those skilled in the art can make various deformation or amendment within the scope of the claims,
This has no effect on the flesh and blood of the present invention.
Claims (3)
1. a spacecraft shading heat shield framing structure, it is characterised in that including: support, stringer and auxiliary stringer；
Support uses screw to be connected with stringer, and auxiliary stringer and stringer are tied up fixing and be spaced on the periphery being arranged in stringer extension, to form cylindrical envelope framing structure；
The reserved installation through hole being coated with needed for heat-control multilayer on stringer and auxiliary stringer, provides for heat-control multilayer and supports and immobilizing foundation；
Described cylindrical envelope framing structure is provided with breach；
Number of holders be 3-4 part, stringer quantity be 4-8 part, auxiliary stringer quantity is 6-10 part；
Support is one-body molded or welds, and bracket cross section is right angled triangle, and a right-angle surface is stringer installed surface, and another right-angle surface is as the bottom surface of spacecraft joint face, and inclined-plane plays enhancing support effect；
Support uses aluminium alloy 2A14T6 material；Stringer uses carbon fiber winding molding；Auxiliary stringer uses fiberglass thin slice, for providing mounting interface for heat-control multilayer, and is supplied to assist support to play reinforcement integral rigidity effect；
Stringer includes that the horizontal segment that segmental arc and segmental arc two ends each extend over out, segmental arc and 2 horizontal segments are connected with corresponding support respectively.
2. a spacecraft shading heat shield, it is characterised in that including: the spacecraft shading heat shield framing structure described in heat-control multilayer and claim 1；
The outer surface that heat-control multilayer is fixed on described spacecraft shading heat shield framing structure by binding forms complete shading heat shield structure
。
Spacecraft shading heat shield the most according to claim 2, it is characterised in that heat-control multilayer forms complete face of cylinder cladding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675277.4A CN104477415B (en) | 2014-11-21 | 2014-11-21 | Light-shading heat-insulation cover framework structure for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675277.4A CN104477415B (en) | 2014-11-21 | 2014-11-21 | Light-shading heat-insulation cover framework structure for spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104477415A CN104477415A (en) | 2015-04-01 |
| CN104477415B true CN104477415B (en) | 2017-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410675277.4A Active CN104477415B (en) | 2014-11-21 | 2014-11-21 | Light-shading heat-insulation cover framework structure for spacecraft |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428642B (en) * | 2016-08-16 | 2019-02-12 | 北京空间飞行器总体设计部 | A kind of spacecraft thruster open type rotary table heat-proof device |
| CN108820259B (en) * | 2018-06-25 | 2020-07-10 | 上海卫星工程研究所 | Integral thermal protection device suitable for multidimensional movement of extraterrestrial rotating mechanism |
| 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 |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6022600A (en) * | 1983-07-18 | 1985-02-05 | 日本電気株式会社 | Despun platform type spin satellite |
| US5372183A (en) * | 1991-08-22 | 1994-12-13 | Strickberger; Harold P. | Thermal control arrangements for a geosynchronous spacecraft |
| US5848767A (en) * | 1996-08-05 | 1998-12-15 | The Boeing Company | One piece spacecraft frame |
| US6102339A (en) * | 1998-04-17 | 2000-08-15 | Turbosat Technology, Inc. | Sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body |
| JP4296795B2 (en) * | 2003-02-20 | 2009-07-15 | 三菱電機株式会社 | Multi-layer insulation blanket |
| RU2390480C1 (en) * | 2009-05-18 | 2010-05-27 | Федеральное Государственное унитарное предприятие Государственный научно-производственный ракетно-космический центр (ФГУП ГНПРКЦ "ЦСКБ-Прогресс") | Spacecraft blind cover flap |
| CN102303710B (en) * | 2011-06-08 | 2013-05-01 | 航天东方红卫星有限公司 | General propelling module for small satellites |
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