CN202915005U - Integrally installed star sensor support - Google Patents
Integrally installed star sensor support Download PDFInfo
- Publication number
- CN202915005U CN202915005U CN 201220617104 CN201220617104U CN202915005U CN 202915005 U CN202915005 U CN 202915005U CN 201220617104 CN201220617104 CN 201220617104 CN 201220617104 U CN201220617104 U CN 201220617104U CN 202915005 U CN202915005 U CN 202915005U
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- star sensor
- support
- attachment face
- installing
- face
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Abstract
An integrally installed star sensor support comprises two support supporting bodies, a support installing bottom face, support installing holes, a star sensor installing face, a through hole and connecting holes, the star sensor installing face is fixedly connected above the support installing bottom face and is used for fixing and installing a star sensor, the support supporting bodies are triangular, the two support supporting bodies are positioned between the star sensor installing face and the support installing bottom face, and fixedly connected with the star sensor installing face and the support installing bottom face, and the support supporting bodies are a supporting structure of the star sensor installing face. The through hole is formed in the star sensor installing face and used for enabling the bottom of the star sensor to extend out, a plurality of the connecting holes are distributed around the through hole and used for fixing the star sensor, and a plurality of support installing holes are formed in the support installing bottom face and used for the fixed connection of the integrally installed star sensor support and the exterior. Integral installation of the star sensor is adopted without the splitting of a star sensor head and a light shield, and the integrally installed star sensor support is convenient to assemble and beneficial for ensuring installation accuracy and structural stability.
Description
Technical field
The utility model relates to a kind of integral installation formula star sensor support, belongs to the overall final assembly technique of space flight field.
Background technique
The overall final assembly technique of space flight is to guarantee each instrument and equipment correct position of satellite, and is working properly, the satisfactory technology of working environment of living in.Star sensor is attitude measurement parts crucial on the star, is to be connected with the celestial body structural panel by rack form, requires support to have certain installation precision and requires and reliable bearing capacity.The quick integral installation support of star of the present utility model for domestic star sensor provide one easy for installation, satisfy the advantage of work.
The technology of the quick mounting bracket of existing domestic star is that star sensor is connected the partial installation form that adopts with support, at first the star sensor head is separated with eyeshade, the star sensor head is connected with the mounting flange face from support is inboard, then eyeshade is installed on the quick head of star and finishes installation.The problem that this mounting type mainly exists is to have increased the quick head of a secondary star to separate with eyeshade, and complicated operation is installed again.
For the problems referred to above, the utility model proposes star sensor novel overall Design of mounting plate method.It not only reduces the star sensor fixing link, improves star sensor installation reliability and structure stability, and also under the prerequisite that guarantees enough strength and stiffness, own wt reduces to some extent.
The model utility content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, a kind of integral installation formula star sensor support is provided, solved the problem that star sensor is forced to decompose because being subjected to the restriction of general assembly condition as a whole parts.
Technical solution of the present utility model is:
A kind of integral installation formula star sensor support comprises: two cradle support, supports are installed bottom surface, support mounting hole, star sensor attachment face, through hole and attachment hole;
The star sensor attachment face is fixed on the top that support is installed the bottom surface, the star sensor attachment face is used for the fixed installation star sensor, cradle support is triangle, two cradle support are fixedly connected with between star sensor attachment face and support installation bottom surface and with star sensor attachment face and support installation bottom surface, and cradle support is the supporting structure of described star sensor attachment face;
Be useful on the through hole that the bottom with star sensor leans out on the star sensor attachment face, distribute around the through hole a plurality of for the fixing attachment hole of star sensor; Support is installed on the bottom surface a plurality of support mounting holes for described integral installation formula star sensor support is connected with external stability.
Gap is left in described cradle support and star sensor attachment face joint.
The angle that described star sensor attachment face and support are installed between the bottom surface is 75～85 degree.
The bottom surface is installed for described cradle support, support and the star sensor attachment face adopts magnesium alloy cast.
The thickness that described support is installed bottom surface and cradle support is 2～5mm.
The thickness of described star sensor attachment face is 4～7mm.
The utility model beneficial effect compared with prior art is:
(1) the utility model adopts the star sensor integral installation, no longer splits star sensor head and eyeshade, and convenient for assembly, simplified control is conducive to guarantee installation precision and structure stability.
(2) the utility model weight support frame is compared the quick mounting bracket of existing domestic star, and in the situation of suitable strength and stiffness, weight alleviates greatly.This has the very harsh space product important in inhibiting that requires to weight.
Description of drawings
Fig. 1 is the utility model integral installation formula star sensitive stent structural drawing
Fig. 2 is that the A of Fig. 1 is to view
Fig. 3 is that the B of Fig. 1 is to view
Fig. 4 is the utility model star sensor and star sensitive stent erection drawing
Embodiment
The utility model provides a kind of integral installation formula star sensor support, such as Fig. 1, Fig. 2 and shown in Figure 3, comprising: two cradle support 1, supports are installed bottom surface 2, support mounting hole 3, star sensor attachment face 4, through hole 5 and attachment hole 6;
Star sensor attachment face 4 is fixed on the top that support is installed bottom surface 2, star sensor attachment face 4 is used for the fixed installation star sensor, cradle support 1 is triangle, two cradle support 1 are fixedly connected with between star sensor attachment face 4 and support installation bottom surface 2 and with star sensor attachment face 4 and support installation bottom surface 2, and cradle support 1 is the supporting structure of described star sensor attachment face 4;
Be useful on the through hole 5 that the bottom with star sensor leans out on the star sensor attachment face 4, distribute around the through hole 5 a plurality of for the fixing attachment hole 6 of star sensor; Support is installed on the bottom surface 2 a plurality of support mounting holes 3 for described integral installation formula star sensor support is connected with external stability.
Cradle support 1 leaves gap with star sensor attachment face 4 joints, is used for dodging the quick plug-in connector for electric connection of star.The angle that star sensor attachment face 4 and support are installed between the bottom surface 2 is 75～85 degree.Bottom surface 2 is installed for cradle support 1, support and star sensor attachment face 4 adopts magnesium alloy cast.The thickness that support is installed bottom surface 2 and cradle support 1 is 2～5mm.The thickness of star sensor attachment face 4 is 4～7mm.
On the basis that guarantees stiffness of support and intensity, have lightening core 8 on the cradle support 1 He on the star sensor attachment face 4 simultaneously, be convenient to support loss of weight and easy to operate.
As shown in Figure 4, the star sensor probe base passes the through hole 5 on the star sensor attachment face 4, be screwed into screw fastening from star sensor mounting flange face and support attachment hole 6, star sensor probe and the quick eyeshade one of star are mounted on the star sensor support, then are screwed into screw fastener by mounting hole 3 support is connected with satellite capsule plate with the star sensor one.
Claims (6)
1. an integral installation formula star sensor support is characterized in that comprising: two cradle support (1), support installation bottom surface (2), support mounting hole (3), star sensor attachment face (4), through hole (5) and attachment hole (6);
Star sensor attachment face (4) is fixed on the top that support is installed bottom surface (2), star sensor attachment face (4) is used for the fixed installation star sensor, cradle support (1) is triangle, two cradle support (1) are positioned between star sensor attachment face (4) and the support installation bottom surface (2) and with star sensor attachment face (4) and support bottom surface (2) are installed and are fixedly connected with, and cradle support (1) is the supporting structure of described star sensor attachment face (4);
Be useful on the through hole (5) that the bottom with star sensor leans out on the star sensor attachment face (4), distribute around the through hole (5) a plurality of for the fixing attachment hole of star sensor (6); Support is installed on the bottom surface (2) a plurality of support mounting holes (3) for described integral installation formula star sensor support is connected with external stability.
2. a kind of integral installation formula star sensor support according to claim 1 is characterized in that: described cradle support (1) leaves gap with star sensor attachment face (4) joint.
3. a kind of integral installation formula star sensor support according to claim 1 is characterized in that: the angle that described star sensor attachment face (4) and support are installed between the bottom surface (2) is 75～85 degree.
4. a kind of integral installation formula star sensor support according to claim 1 is characterized in that: described cradle support (1), support installation bottom surface (2) and star sensor attachment face (4) employing magnesium alloy cast.
5. a kind of integral installation formula star sensor support according to claim 1 is characterized in that: the thickness that described support is installed bottom surface (2) and cradle support (1) is 2～5mm.
6. a kind of integral installation formula star sensor support according to claim 1, it is characterized in that: the thickness of described star sensor attachment face (4) is 4～7mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220617104 CN202915005U (en) | 2012-11-20 | 2012-11-20 | Integrally installed star sensor support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220617104 CN202915005U (en) | 2012-11-20 | 2012-11-20 | Integrally installed star sensor support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202915005U true CN202915005U (en) | 2013-05-01 |
Family
ID=48163321
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220617104 Expired - Lifetime CN202915005U (en) | 2012-11-20 | 2012-11-20 | Integrally installed star sensor support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202915005U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
| CN103662088A (en) * | 2013-11-26 | 2014-03-26 | 中国空间技术研究院 | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN104729503A (en) * | 2015-03-17 | 2015-06-24 | 中国空间技术研究院 | Rod-type supporting structure earth sensor support |
| CN106197401A (en) * | 2016-06-24 | 2016-12-07 | 中国科学院国家空间科学中心 | A kind of compact micro-nano star sensor |
| CN106197476A (en) * | 2016-06-29 | 2016-12-07 | 西安中科微精光子制造科技有限公司 | A kind of split type fixing device |
| CN107792394A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Suitable for the satellite high-precision star sensor support of pin screw mounting means |
-
2012
- 2012-11-20 CN CN 201220617104 patent/CN202915005U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103448925A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | High-precision temperature control device for star sensors for satellites |
| CN103448920A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Precise temperature control device for spaceborne star sensors |
| CN103448920B (en) * | 2013-08-08 | 2016-04-20 | 上海卫星工程研究所 | The precise temperature control device of spaceborne star sensor |
| CN103662088A (en) * | 2013-11-26 | 2014-03-26 | 中国空间技术研究院 | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite |
| CN103662088B (en) * | 2013-11-26 | 2015-08-19 | 中国空间技术研究院 | A kind of star sensor thermal control layout method of GEO orbiter |
| CN104443435A (en) * | 2014-11-21 | 2015-03-25 | 上海卫星工程研究所 | Star sensor mounting structure for thermal deformation isolation and control |
| CN104443435B (en) * | 2014-11-21 | 2016-06-29 | 上海卫星工程研究所 | For the star sensor mounting structure being thermomechanically separated and control |
| CN104729503A (en) * | 2015-03-17 | 2015-06-24 | 中国空间技术研究院 | Rod-type supporting structure earth sensor support |
| CN104729503B (en) * | 2015-03-17 | 2017-11-07 | 中国空间技术研究院 | A kind of flow resistance of rod-support structure earth sensor support |
| CN106197401A (en) * | 2016-06-24 | 2016-12-07 | 中国科学院国家空间科学中心 | A kind of compact micro-nano star sensor |
| CN106197476A (en) * | 2016-06-29 | 2016-12-07 | 西安中科微精光子制造科技有限公司 | A kind of split type fixing device |
| CN107792394A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Suitable for the satellite high-precision star sensor support of pin screw mounting means |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130501 |