CN202147847U - Device for mounting large diameter thin wall structure on spacecraft - Google Patents
Device for mounting large diameter thin wall structure on spacecraft Download PDFInfo
- Publication number
- CN202147847U CN202147847U CN201020624487U CN201020624487U CN202147847U CN 202147847 U CN202147847 U CN 202147847U CN 201020624487 U CN201020624487 U CN 201020624487U CN 201020624487 U CN201020624487 U CN 201020624487U CN 202147847 U CN202147847 U CN 202147847U
- Authority
- CN
- China
- Prior art keywords
- spacecraft
- radiator
- exciter
- fixed
- thin wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a device for mounting large diameter thin wall structure, and specifically relates to a mounting device suitable for radiator out of spacecraft cabin. The surface of a supporting column (3) is provided with a screw thread; before a radiator (1) is installed, the supporting column (3) is firstly fastened to the surface of a spacecraft structure body (2); after the supporting column (3) is installed, the radiator (1) is lifted to the installing position; the inner surface of the radiator (1) is fixed with a tray nut (9); a supporting sleeve (4) is fixed to the radiator through two screws (7) and a gasket (8) and is connected with the supporting column (3) through a screw (5) and a gasket (6); and the radiator (1) is fixed to the surface of the spacecraft body (2). The difficult problem that large thin wall structure is difficult to install is solved by multi-point supporting installation method, mechanical environment of the radiator of the spacecraft launching phase is effectively improved, mounted stiffness of the radiator is improved and reliability of the system is improved.
Description
Technical field
The utility model relates to a kind of device that is used to install large-scale diameter thin-wall construction, relates in particular to a kind of erecting device that is applicable to spacecraft module external irradiation device.
Background technology
Exciter is the visual plant of spacecraft thermal control system, and exciter is dissipated to the deep cooling space through circulating of medium with spacecraft in-to-in used heat row.Exciter is a thin-wall construction, and rigidity is lower, needs design one cover exciter erecting device, guarantees that exciter can bear the load of carrier rocket ascent stage.Traditional thin-wall construction adopts fastener to cooperate the form of cushion block to install more; For large-scale closed thin-wall construction; It is huge that cushion block quantity is installed, and be difficult to realize being in place near the cushion block at thin-walled middle part, so the utility model proposes a kind of new installation form; Solve the problem of large thin-wall structure difficult installation, also satisfy the mechanical environment requirement of spacecraft simultaneously.
Summary of the invention
To the deficiency that traditional exciter mounting means exists, the purpose of the utility model is to provide a kind of and satisfies the exciter installation requirement and can bear the erecting device of the load of carrier rocket ascent stage.
The technical scheme that the utility model adopts is; A kind ofly adopt a plurality of screwed pillars that the erecting device of multi-point support is provided; Constitute by support post (3), plate nut (9), support sleeve (4), long spiro nail (5), pad (6), screw (7), pad (8), plate nut (9); Exciter (1) at first is fastened on spacecraft structure body (2) surface with support post (3), after support post (3) installation before installing; Exciter (1) is lifted to the installation site; Exciter (1) inside face is fixed with plate nut (9), and support sleeve (4) is fixed on the exciter (1) through two groups of screws (7) and pad (8), through long spiro nail (5) and pad (6) exciter (1) is fixed in spacecraft structure body (2) surface at last.
The invention has the beneficial effects as follows: through the mounting means of multi-point support; Solved the difficult problem that the large thin-wall structure is difficult to install; Actv. has improved the mechanical environment of spacecraft transmitter section exciter, has improved the installation rigidity of exciter, has improved the reliability of system.This mounting means also can be extended to the installation of guar plate structure, and field of application is wider in the spacecraft general assembly.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the present invention is explained further details.
Fig. 1 is spacecraft structure body and exciter position view;
Fig. 2 is the installation situation section plan of an attachment point.
Among the figure, 1 exciter, 2 spacecraft structure bodies, 3 support posts, 4 support sleeves, 5 screws, 1,6 pad, 1,7 screw, 2,8 pads, 2,9 plate nuts.
The specific embodiment
Below in conjunction with accompanying drawing this being installed concrete solution is elaborated.
As shown in Figure 1, exciter (1) is fixed on spacecraft structure body (2) surface through a plurality of strong points.Fig. 2 is the installation situation section plan of one of them attachment point of exciter (1).
At first support post (3) is fastened on spacecraft structure body (2) surface; In order to reduce installation risk and difficulty; Support post (3) at the distribution circle diameter on spacecraft structure body (2) surface less than exciter (1) inner surface diameter, can be through guide piece easily with exciter (1) lifting to the installation site;
With exciter (1) perforate, there are certain interval in this bore dia and support sleeve (4), and support sleeve (4) passes this hole; Be connected with support post (3); Support sleeve (4) is " T " word structure, and the both sides, upper end are porose respectively, and screw (7) can pass this hole and link to each other with plate nut (9);
After support post (3) installation; Exciter (1) is lifted to the installation site guide piece control support post (3) and support sleeve (4) consistency from top to bottom, support sleeve (4) upper end two side holes and fixing plate nut (9) consistency from top to bottom of exciter (1) inside face through guide piece;
Plate nut (9), two group screws (7) and the pad (8) fixing through exciter (1) inside face are fixed on support sleeve (4) on the exciter;
At last, support sleeve (4) is connected with support post (3) with pad (6) through screw (5), and exciter (1) is fixed on spacecraft structure body (2) surface.
Support sleeve (4) diameter of bore increases and regulates surplus greater than the nominal diameter of screw (5), has reduced the installation difficulty of bringing because of manufacturing errors.
Through a plurality of this erecting devices are set at this external surface of spacecraft structure, a plurality of strong points are provided for the exciter of thin-wall construction, increased the installation rigidity of exciter, increased the reliability of system.
Claims (1)
1. device that the large diameter thin wall structure is installed on spacecraft; It is characterized in that: constitute by support post (3), plate nut (9), support sleeve (4), long spiro nail (5), pad (6), screw (7), pad (8), plate nut (9); Before exciter (1) is installed; At first support post (3) is fastened on spacecraft structure body (2) surface, after support post (3) installation, exciter (1) is lifted to the installation site; Through the fixing plate nut (9) of exciter (1) inside face; Support sleeve (4) is fixed on the exciter (1) through two groups of screws (7) and pad (8), is connected with support post (3) with pad (6) through long spiro nail (5) at last, exciter (1) is fixed in spacecraft structure body (2) surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020624487U CN202147847U (en) | 2010-11-25 | 2010-11-25 | Device for mounting large diameter thin wall structure on spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020624487U CN202147847U (en) | 2010-11-25 | 2010-11-25 | Device for mounting large diameter thin wall structure on spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202147847U true CN202147847U (en) | 2012-02-22 |
Family
ID=45588915
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020624487U Expired - Fee Related CN202147847U (en) | 2010-11-25 | 2010-11-25 | Device for mounting large diameter thin wall structure on spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202147847U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026394A (en) * | 2018-06-12 | 2018-12-18 | 北京空天技术研究所 | The deformation-compensated method of thermal protection structure and temperature barrier |
-
2010
- 2010-11-25 CN CN201020624487U patent/CN202147847U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026394A (en) * | 2018-06-12 | 2018-12-18 | 北京空天技术研究所 | The deformation-compensated method of thermal protection structure and temperature barrier |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Beijing Space Technology Research and Test Center Document name: Notification to Pay the Fees |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120222 Termination date: 20131125 |