CN102882008A - Low-expansion mesh reflector using composite material connectors - Google Patents
Low-expansion mesh reflector using composite material connectors Download PDFInfo
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- CN102882008A CN102882008A CN2012103780307A CN201210378030A CN102882008A CN 102882008 A CN102882008 A CN 102882008A CN 2012103780307 A CN2012103780307 A CN 2012103780307A CN 201210378030 A CN201210378030 A CN 201210378030A CN 102882008 A CN102882008 A CN 102882008A
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Abstract
The invention relates to a low-expansion mesh reflector using composite material connectors and belongs to the technical field of space antenna reflectors. The low-expansion mesh reflector comprises back ribs, reflecting surfaces and connectors. Each refecting surface is a quasi-isotropic TWF (true wave fiber) fabric reflecting surface, and each back rib is a composite material laminate back rib in a groined shape and having a symmetrical structure. Each connector is positioned at an included angle of two crossed back ribs in the back ribs, so that the connector and the two crossed back ribs are fixedly connected. A connector embedded part is positioned on a bottom face of the connector, and the reflector is fixed or mounted by the connector embedded part so as to be convenient for transportation or storage. The reflecting surface in the low-expansion mesh reflector uses the quasi-isotropic TWF fabric, has quite high light-transmittance and a lower thermal expansivity, influence of space light pressure to a molded surface of the reflecting surface can be effectively reduced, temperature gradient generated by the reflecting surface under a space thermal environment can be lowered, and since the temperature gradient is lowered, thermal deformation of the reflecting surface can be reduced.
Description
Technical field
The present invention relates to a kind of low bulk mesh reflector that uses the composite material connector, belong to space antenna reflector technical field.
Background technology
Present develop rapidly along with space technology, space antenna technology as the important payload of spacecraft has also obtained significant progress, antenna system is more and more, version becomes increasingly complex, develop into gradually the extensible antenna with deployable reflector in space by in the past the solid face reflector antenna that does not carry out space development, and require that the antenna reflector quality is little, Rigidity and strength is large, the Space Thermal distortion is little etc.Traditional antenna reflector form can not satisfy that it is little to the reflector quality, Rigidity and strength is large, and the requirement that the Space Thermal distortion is little needs the reflector structure that a kind of quality of design is little, Rigidity and strength large, the Space Thermal distortion is little.
Summary of the invention
The object of the invention is to overcome the deficiency that the conventional reflector quality is large, the Space Thermal distortion is large, a kind of low bulk mesh reflector that uses the composite material connector is provided.
The objective of the invention is to be achieved through the following technical solutions.
A kind of low bulk mesh reflector that uses the carbon fibre composite connector of the present invention comprises backing strip, reflecting surface and connector; Reflecting surface isotropic carbon fiber braided mesh cloth (TWF) the fabric reflecting surface that is as the criterion, backing strip is the composite laminated plate backing strip, it is shaped as " well " font, and symmetrical configuration; Connector is arranged in the angle of two backing strips that backing strip intersects, thereby so that connector all be fixedly connected with two backing strips that intersect; Connector is hollow six cylinders with the bottom surface, and the cross section of cylinder is a hexagon, and wherein the length of side on three limits length of side long, in addition three limits is short; The length of side on non-conterminous three limits is identical, and the length of side on non-conterminous three limits is identical in addition; On one of them corresponding that face in long limit a trapezoidal groove is arranged; The connector embedded part is positioned on the bottom surface of connector, reflector is fixed or installs so that transport or store by the connector embedded part.
The present invention's advantage compared with prior art is:
Reflecting surface among the present invention adopts quasi-isotropic TWF fabric, it has very high light transmittance and less thermal coefficient of expansion, can effectively reduce the space optical pressure to the impact of reflecting surface profile, can reduce the temperature gradient that reflecting surface produces under spatial heat environment, and the reduction of temperature gradient can reduce the thermal deformation of reflecting surface;
" well " font composite laminated plate backing strip of the symmetrical configuration of using among the present invention, has higher specific stiffness, less thermal coefficient of expansion, simultaneously suitable with the thermal coefficient of expansion of TWF fabric mesh reflecting surface, both combine and just have good thermal matching like this, can reduce the thermal deformation of reflector, improve simultaneously the integral rigidity of reflector;
The composite material connector that adopts among the present invention has preferably structural strength and is used for the carrying launch load, has simultaneously less thermal coefficient of expansion, with mesh reflecting surface heat coupling, can effectively reduce the localized heat distortion of reflecting surface.
Low bulk mesh reflector Calculation of Thermal Deformation:
For the low bulk reflector structure of verifying this kind employing composite material connector in the rail thermal deformation, carried out corresponding thermal deformation analysis and calculated.Analyze used temperature field for according to the bad working environments temperature field of choosing in the thermoanalytical result of rail, this temperature field operating mode is worst cold case, and minimum temperature is-176 ℃, and maximum temperature is-40 ℃, and the reflector temperature gradient is 30 ℃.According to antenna maximum heat deflection in the antenna mesh slotted-type reflector surface that the severe temperatures field of rail condition calculating obtains, satisfy antenna fully to the index request of reflector type surface accuracy.
Description of drawings
Fig. 1 is the structural representation of low bulk mesh reflector;
Fig. 2 is the structural representation of connector;
Fig. 3 is the structural representation of reflecting surface;
Wherein, 1-backing strip, 2-reflecting surface, 3-connector, 4-connector embedded part.
Embodiment
The invention will be further described below in conjunction with drawings and Examples.
Embodiment
A kind of low bulk mesh reflector that uses the composite material connector comprises backing strip 1, reflecting surface 2 and connector 3, connector embedded part 4; Reflecting surface 2 is quasi-isotropic TWF fabric reflecting surface, and backing strip 1 is the composite laminated plate backing strip, and it is shaped as " well " font, and symmetrical configuration; Connector 3 is arranged in the angle of two backing strips that backing strip 1 intersects, thereby so that connector 3 all be fixedly connected with two backing strips that intersect; Connector 3 is hollow six cylinders with the bottom surface, and the cross section of cylinder is a hexagon, and wherein the length of side on three limits length of side long, in addition three limits is short; The length of side on non-conterminous three limits is identical, and the length of side on non-conterminous three limits is identical in addition; On one of them corresponding that face in long limit a trapezoidal groove is arranged; Connector embedded part 4 is positioned on the bottom surface of connector 3, is fixed or installs so that transport and store by 4 pairs of reflectors of connector embedded part.
Backing strip 1 structure adopts composite material laminated board to form the groined type symmetrical structure, and its rigidity of structure is large, the rounding state natural frequency is greater than 70Hz, has greatly strengthened the ability that reflector structure is resisted launching phase vibration mechanics environment.
Reflecting surface 2 adopts quasi-isotropic TWF fabric, and its light transmittance can effectively reduce the space optical pressure to the impact of antenna reflective face more than 60%.Thermal coefficient of expansion is less than 2.0 * 10
-6, greatly reduce the thermal deformation that reflecting surface structure produces at rail.
Connector embedded part 4 is used for reflector is fixed or installs so that transport and store.
Low bulk mesh reflector Calculation of Thermal Deformation:
For the low bulk reflector structure of verifying this kind employing composite material connector in the rail thermal deformation, carried out corresponding thermal deformation analysis and calculated.Analyze the temperature field adopt and be according to the bad working environments temperature field of choosing in the thermoanalytical result of rail, this temperature field operating mode is worst cold case, and minimum temperature is-176 ℃, and maximum temperature is-40 ℃, and the reflector temperature gradient is 30 ℃.The antenna mesh reflector maximum heat deflection that obtains in the severe temperatures field of rail condition calculating according to antenna; Adopting Finite Element Method to carry out corresponding thermal deformation analysis calculates, the temperature field of input is according to the bad working environments temperature case of antenna in the rail use procedure, the maximum heat deflection is 0.355mm in the antenna mesh slotted-type reflector surface that calculates, and this deflection satisfies antenna fully to the index request of reflector type surface accuracy.
Claims (1)
1. a low bulk mesh reflector that uses the carbon fibre composite connector is characterized in that: comprise backing strip (1), reflecting surface (2) and connector (3); Reflecting surface (2) is quasi-isotropic TWF fabric reflecting surface, and backing strip (1) is the composite laminated plate backing strip, and it is shaped as " well " font, and symmetrical configuration; Connector (3) is arranged in the angle of two backing strips of backing strip (1) intersection, and connector (3) all is fixedly connected with two backing strips that intersect; Connector (3) is hollow six cylinders with the bottom surface, and the cross section of cylinder is a hexagon, and wherein the length of side on three limits length of side long, in addition three limits is short; The length of side on non-conterminous three limits is identical, and the length of side on non-conterminous three limits is identical in addition; On one of them corresponding that face in long limit a trapezoidal groove is arranged; Connector embedded part (4) is positioned on the bottom surface of connector (3), reflector is fixed or installs so that transport or store by connector embedded part (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210378030.7A CN102882008B (en) | 2012-09-29 | 2012-09-29 | Low-expansion mesh reflector using composite material connectors |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210378030.7A CN102882008B (en) | 2012-09-29 | 2012-09-29 | Low-expansion mesh reflector using composite material connectors |
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| CN102882008A true CN102882008A (en) | 2013-01-16 |
| CN102882008B CN102882008B (en) | 2015-02-11 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103560332A (en) * | 2013-11-18 | 2014-02-05 | 中国电子科技集团公司第五十四研究所 | Method for manufacturing large-caliber high-precision antenna surface made of composite materials |
| CN110534876A (en) * | 2019-07-23 | 2019-12-03 | 西安空间无线电技术研究所 | A kind of reflector antenna and preparation method thereof |
| WO2023103474A1 (en) * | 2021-12-07 | 2023-06-15 | 北京卫星制造厂有限公司 | Spacecraft antenna reflector and preparation method |
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| JP2003347840A (en) * | 2002-05-24 | 2003-12-05 | Nec Engineering Ltd | Reflector antenna |
| US20040009728A1 (en) * | 2000-08-28 | 2004-01-15 | Kenji Kubomura | Composite material, formed product and prepreg |
| CN101320844A (en) * | 2008-07-11 | 2008-12-10 | 中国科学院国家天文台南京天文光学技术研究所 | Light reflection surface panel support mechanism of radio astronomical telescope |
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| US3716950A (en) * | 1971-10-12 | 1973-02-20 | C Mcclure | Reinforced abrasive wheels |
| US20040009728A1 (en) * | 2000-08-28 | 2004-01-15 | Kenji Kubomura | Composite material, formed product and prepreg |
| JP2003347840A (en) * | 2002-05-24 | 2003-12-05 | Nec Engineering Ltd | Reflector antenna |
| CN101320844A (en) * | 2008-07-11 | 2008-12-10 | 中国科学院国家天文台南京天文光学技术研究所 | Light reflection surface panel support mechanism of radio astronomical telescope |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103560332A (en) * | 2013-11-18 | 2014-02-05 | 中国电子科技集团公司第五十四研究所 | Method for manufacturing large-caliber high-precision antenna surface made of composite materials |
| CN103560332B (en) * | 2013-11-18 | 2016-09-28 | 中国电子科技集团公司第五十四研究所 | A kind of manufacture method of caliber high-precision composite antenna surface |
| CN110534876A (en) * | 2019-07-23 | 2019-12-03 | 西安空间无线电技术研究所 | A kind of reflector antenna and preparation method thereof |
| CN110534876B (en) * | 2019-07-23 | 2021-06-11 | 西安空间无线电技术研究所 | Preparation method of reflector antenna |
| WO2023103474A1 (en) * | 2021-12-07 | 2023-06-15 | 北京卫星制造厂有限公司 | Spacecraft antenna reflector and preparation method |
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| Publication number | Publication date |
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| CN102882008B (en) | 2015-02-11 |
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