CN106441767A - Ground vibration testing clamp for large spacecraft vibration - Google Patents
Ground vibration testing clamp for large spacecraft vibration Download PDFInfo
- Publication number
- CN106441767A CN106441767A CN201611137928.XA CN201611137928A CN106441767A CN 106441767 A CN106441767 A CN 106441767A CN 201611137928 A CN201611137928 A CN 201611137928A CN 106441767 A CN106441767 A CN 106441767A
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- Prior art keywords
- hole
- upper flange
- vibration
- reinforcement
- spacecraft
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention provides a ground vibration testing clamp for large spacecraft vibration. The clamp comprises a shell wall, reinforcing ribs, lightening holes, an upper flange face, a lower flange face, an upper flange through hole, a lower flange through hole and a limiting hole, wherein the shell wall is positioned on one sides of the reinforcing ribs; the reinforcing ribs are positioned above the lightening holes, and between the upper flange face and the lightening holes, the lightening holes are positioned below the upper flange face; the upper flange face is positioned above the lower flange face; the upper flange through hole is arranged on one side of the lower flange through hole; and the limiting hole is positioned between the upper flange through hole and the upper flange face. The ground vibration testing clamp can be used for solving the problem of a ground vibration testing clamp of a large spacecraft and can meet ground vibration tests of an ultra-large spacecraft having the mass being not more than 13000kg, and the testing clamp can meet the requirement on frequency, mass, strength and rigidity caused by a spacecraft, and is low in manufacturing and processing cost.
Description
Technical field
The present invention relates to spacecraft ground vibration test fixture, in particular it relates to a kind of Large Spacecraft vibration ground shakes
Dynamic test fixture.
Background technology
With the continuous development of space technology, the spacecraft with spacecraft as representative is also towards ultra-large type, excess weight side
To development, this proposes new requirement for the terra mechanics test of spacecraft.Vibration test fixture is to connect vibration table and boat
The tie of its device, national military standard has clear and definite technical requirements for vibration test fixture.The design of fixture should consider space flight
The demand of device vibration test, considers the feasibility manufactured again, it is contemplated that quality, frequency, intensity.Spacecraft surpasses
Large Spacecraft quality weight, barycenter is high, and test magnitude is high, so passing to power and the moment of test fixture during vibration test in addition
Would generally be very big.The quality of test fixture will control in zone of reasonableness, on the one hand will reduce unnecessary quality, is shaken with reducing
The unnecessary consumption of dynamic platform, on the other hand will reduce unnecessary quality, to improve the frequency of fixture, will have suitable quality simultaneously
And Mass Distribution, to increase stability and the intensity of fixture.The manufacturing of ultra-large type vibration test fixture is also a difficult point,
Require fixture to meet quality, intensity, rigidity, frequency aspect technical stipulation, be unsatisfactory for the ultra-large type boat that quality is less than 13000kg
The Ground Vibration Test of its device, the domestic enterprise that can cast the so big fixture of processing cans be counted on one's fingers, and shown is considering fixture
Meet cost-effective in the case of test requirements document, the design of fixture and technical requirements will reduce from the angle of technique to be manufactured
Difficulty.
Content of the invention
For defect of the prior art, it is an object of the invention to provide a kind of Large Spacecraft vibration Ground Vibration Test
Fixture, for solving the Ground Vibration Test of spacecraft super-large space capsule it is desirable to fixture meets quality, intensity, rigidity, frequency side
Surface technology specifies, requires to reduce the difficulty manufacturing processing simultaneously, cost-effective.Using the present invention, quality can be met and be less than
The Ground Vibration Test of the super-large space capsule of 13000kg, test fixture can meet spacecraft for frequency, quality, intensity, just
The requirement of degree aspect, manufactures processing cost low simultaneously.
According to an aspect of the present invention, provide a kind of Large Spacecraft vibration ground vibration test fixture, it includes shell
Wall, reinforcement, lightening hole, upper flange surface, lower flange face, upper flange through hole, lower flange through hole, spacing hole, shell wall is located to be strengthened
The side of muscle, reinforcement is located at the top of lightening hole, and reinforcement is located between upper flange surface and lightening hole, and lightening hole is located at upper
The lower section of flange face, upper flange surface is located at the top in lower flange face, and upper flange through hole is in the side of lower flange through hole, spacing hole position
Between upper flange through hole and upper flange surface.
Preferably, described fixture height is 1400mm, and quality is 4280kg.
Preferably, described fixture shell thickness is 50mm.
Preferably, described reinforcement lower surface outer dia 4000mm, inside diameter 3200mm；Outside reinforcement upper surface
Diameter 4070mm, inside diameter 3810mm.
Preferably, described lightening hole is divided into two rows, totally three ten two, bore dia 400mm, and the height away from lower surface divides
Wei not 350mm and 550mm.
Compared with prior art, the present invention has following beneficial effect：For solving the ground of spacecraft super-large space capsule
Surface vibration is tested it is desirable to fixture meets quality, intensity, rigidity, frequency aspect technical stipulation, requires to reduce manufacturing processing simultaneously
Difficulty, cost-effective.Using the present invention, the ground vibration examination that quality is less than the super-large space capsule of 13000kg can be met
Test, test fixture meet spacecraft for frequency, quality, intensity, rigidity aspect requirement, simultaneously manufacture processing cost low.
Brief description
The detailed description with reference to the following drawings, non-limiting example made by reading, the further feature of the present invention,
Objects and advantages will become more apparent upon：
Fig. 1 is Large Spacecraft Ground Vibration Test fixture schematic diagram.
Fig. 2 is Large Spacecraft Ground Vibration Test fixture top view.
Specific embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, some deformation can also be made and improve.These broadly fall into the present invention
Protection domain.
As shown in figure 1, the present invention provides a kind of Large Spacecraft to vibrate ground vibration test fixture, this laboratory holder includes
Shell wall 1, reinforcement 2, lightening hole 3, upper flange surface 4, lower flange face 5, upper flange through hole 6, lower flange through hole 7, spacing hole 8, shell
Wall 1 is located at the side of reinforcement 2, and reinforcement 2 is located at the top of lightening hole 3, and reinforcement 2 is located at upper flange surface 4 and lightening hole 3
Between, lightening hole 3 be located at upper flange surface 4 lower section, upper flange surface 4 be located at lower flange face 5 top, upper flange through hole 6 under
The side of flange through hole 7, spacing hole 8 is located between upper flange through hole 6 and upper flange surface 4.Keeping limitation in height weights
Under, vibration table interface Φ 3000mm, Φ 3400mm, Φ 3800mm are expanded to Φ 4100mm, the horizontal frequency of fixture single order
200Hz, can meet Large Spacecraft and spacecraft ground vibration test needs within 13000kg.
Fixture height is 1400mm, and quality is 4280kg, and fixture shell thickness is 50mm, and so meeting technical stipulation will
Ask, cost-effective.
Reinforcement lower surface outer dia 4000mm, inside diameter 3200mm；Reinforcement upper surface outer dia 4070mm,
Inside diameter 3810mm, is so effectively improved fixture rigidity and is not interfered with product.
Lightening hole is divided into two rows, totally three ten two, bore dia 400mm, the height away from lower surface be respectively 350mm and
550mm, so meets prescription.
In vibration test, test fixture passes through lower flange face through hole and 96 Φ 18 through holes and vibration table to spacecraft
Connect, attachment screw is M16, screw length is less than 80mm.Spacecraft passes through upper flange surface through hole and 144 Φ 11
Screw and test fixture connect, and connected mode is bucketing screw, and screw specification is M11, and screw length is not less than 80mm.In space flight
Device and test fixture farther out when, limit rocking of spacecraft, a diameter of 400mm of lightening hole, both reduced the quality of test fixture,
Facilitate people to enter operation in fixture again.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various modifications or modification within the scope of the claims, this not shadow
Ring the flesh and blood of the present invention.
Claims (5)
1. a kind of Large Spacecraft vibration ground vibration test fixture it is characterised in that it include shell wall, reinforcement, lightening hole,
Upper flange surface, lower flange face, upper flange through hole, lower flange through hole, spacing hole, shell wall is located at the side of reinforcement, reinforcement position
In the top of lightening hole, reinforcement is located between upper flange surface and lightening hole, and lightening hole is located at the lower section of upper flange surface, upper method
Blue face is located at the top in lower flange face, and in the side of lower flange through hole, spacing hole is located at upper flange through hole and upper to upper flange through hole
Between flange face.
2. Large Spacecraft vibration ground vibration test fixture according to claim 1 is it is characterised in that described fixture is high
Spend for 1400mm, quality is 4280kg.
3. Large Spacecraft according to claim 1 vibration ground vibration test fixture is it is characterised in that described fixture shell
Wall thickness is 50mm.
4. Large Spacecraft according to claim 1 vibration ground vibration test fixture is it is characterised in that described reinforcement
Lower surface outer dia 4000mm, inside diameter 3200mm；Reinforcement upper surface outer dia 4070mm, inside diameter
3810mm.
5. Large Spacecraft according to claim 1 vibration ground vibration test fixture is it is characterised in that described lightening hole
It is divided into two rows, totally three ten two, bore dia 400mm, the height away from lower surface is respectively 350mm and 550mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611137928.XA CN106441767A (en) | 2016-12-07 | 2016-12-07 | Ground vibration testing clamp for large spacecraft vibration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611137928.XA CN106441767A (en) | 2016-12-07 | 2016-12-07 | Ground vibration testing clamp for large spacecraft vibration |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106441767A true CN106441767A (en) | 2017-02-22 |
Family
ID=58216292
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611137928.XA Pending CN106441767A (en) | 2016-12-07 | 2016-12-07 | Ground vibration testing clamp for large spacecraft vibration |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106441767A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840565A (en) * | 2017-02-27 | 2017-06-13 | 中国工程物理研究院总体工程研究所 | A kind of Double earthquakes attachment structure |
| CN107643154A (en) * | 2017-09-11 | 2018-01-30 | 上海微小卫星工程中心 | Satellite Vibration Test frock |
| CN107991047A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | For spacecraft ground vibration test fixture |
| CN107991046A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Test fixture for large space station ground vibration |
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|---|---|---|---|---|
| CN102539095A (en) * | 2011-11-15 | 2012-07-04 | 上海卫星工程研究所 | High-frequency anti-water-leakage satellite vibration test clamp for large interface expanding |
| CN103048104A (en) * | 2012-12-06 | 2013-04-17 | 上海裕达实业公司 | Ground vibration test fixture for large-scale spacecraft |
| CN202947849U (en) * | 2012-10-24 | 2013-05-22 | 北京强度环境研究所 | Vibration testing clamp of instrument cabin of lunch vehicle |
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2016
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| CN102539095A (en) * | 2011-11-15 | 2012-07-04 | 上海卫星工程研究所 | High-frequency anti-water-leakage satellite vibration test clamp for large interface expanding |
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| CN204183440U (en) * | 2014-09-09 | 2015-03-04 | 北京强度环境研究所 | Future Launch Rocket cabin section multiple stage excited vibration test fixture |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840565A (en) * | 2017-02-27 | 2017-06-13 | 中国工程物理研究院总体工程研究所 | A kind of Double earthquakes attachment structure |
| CN106840565B (en) * | 2017-02-27 | 2023-08-15 | 中国工程物理研究院总体工程研究所 | Double-vibrating table connecting structure |
| CN107643154A (en) * | 2017-09-11 | 2018-01-30 | 上海微小卫星工程中心 | Satellite Vibration Test frock |
| CN107991047A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | For spacecraft ground vibration test fixture |
| CN107991046A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Test fixture for large space station ground vibration |
| CN107991047B (en) * | 2017-11-27 | 2021-05-28 | 上海卫星装备研究所 | Ground vibration test fixture for spacecraft |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170222 |
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| RJ01 | Rejection of invention patent application after publication |