CN104708550A - Multipurpose satellite mechanics test fixture - Google Patents
Multipurpose satellite mechanics test fixture Download PDFInfo
- Publication number
- CN104708550A CN104708550A CN201410742669.8A CN201410742669A CN104708550A CN 104708550 A CN104708550 A CN 104708550A CN 201410742669 A CN201410742669 A CN 201410742669A CN 104708550 A CN104708550 A CN 104708550A
- Authority
- CN
- China
- Prior art keywords
- hole
- ring
- multipurpose
- satellite
- multipurpose satellite
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Clamps And Clips (AREA)
- Support Of Aerials (AREA)
Abstract
The invention discloses a multipurpose satellite mechanics test fixture. The multipurpose satellite mechanics test fixture comprises a base and a pressing ring, wherein the base is of a conical platform type, two circles of threaded holes are formed in the top face of the base, threaded circles on the outer side are used for being connected with an adapter, threaded circles on the inner side are used for being connected with the pressing ring, four notches 3 are formed in the edge of the top face of the base, eight square holes are formed in the side face of the base, two circles of through holes are formed in the bottom face of the base and used for being connected with a vibrating platform and a modal foundation, and the pressing ring is machined and formed through 45# steel. When the multipurpose satellite mechanics test fixture is used under the condition that the adapter exists, the adapter is connected with the fixture through a screw; when the multipurpose satellite mechanics test fixture is used under the condition that the adapter does not exist, a satellite and rocket connecting ring is pressed through a pressing block. The multipurpose satellite mechanics test fixture has the advantage of being multipurpose, and saves time and cost.
Description
Technical field
The present invention relates to field of fixtures, specifically a kind ofly can meet the fixture that can connect satellite satellite and the rocket connecting ring or adapter mode and vibration test.
Background technology
In satellite force test, mode, vibration test need to be connected with mode basis and shake table respectively with fixture, and Satellite Experiment state is divided into tape adapter unit and not tape adapter unit two states.
Satellite mode, vibration test adopted different frocks respectively in the past, and mode, vibration test frock are divided into tape adapter unit and not tape adapter unit two kinds, so just need four cover frocks, operating condition of test conversion needs frock to change, the waste of life period, cost.
Summary of the invention
The object of the invention is to overcome defect that above-mentioned prior art and application exist and provide a kind of and can meet the fixture that can be connected satellite satellite and the rocket connecting ring or adapter mode and vibration test.
Object of the present invention is achieved through the following technical solutions: a kind of multipurpose satellite clamp for mechanics experiment, comprise pedestal and pressure ring, described pedestal adopts circular cone flat form, base is larger, ensure that the rigidity of structure and bonding strength, avoid the interference of satellite antenna and pedestal and shake table, the end face of described pedestal offers two circle screwed holes, described outside screw circle is used for Payload attach fitting, the fillet of screw of inner side is for connecting pressure ring, the top edge of described pedestal has 4 breach, avoid the interference of satellite antenna and fixture, described pedestal side has offered 8 square holes, for testing the connection of Satellite inside cable, the bottom surface of described pedestal offers two ring through hole, for being connected with shake table and mode basis, described pressure ring adopts 45# steel machining, ensure that the bonding strength with satellite and the rocket connecting ring.
Wherein, described pedestal adopts 104 aluminium alloy castings to form
Wherein, the length of described square hole is 90mm.
Wherein, described two ring through hole comprise interior ring through hole and outer ring through hole, and described interior ring through hole is 8, outer ring through hole is 16, the T-shaped through hole of totally 24 φ 13mm.
Wherein, described base top surface also offers the steel-wire screw-socket of the M6 of the φ 878mm of 32 circular distributions.
Wherein, described pressure ring is provided with the T-shaped through hole of 36 φ 13mm.
The present invention has following beneficial effect:
When using under tape adapter unit state, with screw, adapter is connected with fixture; When using under not tape adapter unit state, with briquetting by satellite and the rocket connecting ring.There is multiduty feature, save time, cost.
Accompanying drawing explanation
Fig. 1 is embodiment of the present invention mechanics Fixture assembly structural representation.
Fig. 2 is clamp base structural representation in Fig. 1.
Fig. 3 is the internal anatomy of pressure ring in Fig. 1.
Fig. 4 is ring structure schematic diagram in Fig. 1.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
As shown in Figure 1-2, embodiments provide a kind of multipurpose satellite clamp for mechanics experiment, comprise pedestal 1 and pressure ring 2, described pedestal 1 adopts circular cone flat form, base is larger, ensure that the rigidity of structure and bonding strength, avoid the interference of satellite antenna and pedestal and shake table, the end face of described pedestal 1 offers two circle screwed holes, described outside screw circle is used for Payload attach fitting, the fillet of screw of inner side is for connecting pressure ring 2, the top edge of described pedestal 1 has 4 breach 3, avoid the interference of satellite antenna and fixture, described pedestal 1 side opening has been provided with 8 square holes 4, for testing the connection of Satellite inside cable, the bottom surface of described pedestal 1 offers two ring through hole, for being connected with shake table and mode basis, described pressure ring 1 adopts 45# steel machining, ensure that the bonding strength with satellite and the rocket connecting ring.
Pedestal 1 adopts circular cone flat form, and base is comparatively large, ensure that the rigidity of structure and bonding strength.Fixture height is 250mm, avoids the interference of satellite antenna and pedestal and shake table.Clamp base entirety first adopts 104 aluminium alloy castings to form, and the liver body side surface of casting has 8 length of sides to be the square hole of 90.The milling of pedestal 1 liver body upper and lower surface becomes plane, and becomes an annulus and satellite and the rocket connecting ring inner circle matched in clearance in upper surface milling, enhances the operability of test assembling, does not affect mechanical characteristic again.Pedestal 1 lower surface gets out the T-shaped through hole of inner ring 8,16, outer ring, totally 24 φ 13mm, for being connected with shake table and mode basis.
Pedestal 1 end face fills the steel-wire screw-socket of the M6 of 32 distribution circle φ 878mm, for Payload attach fitting.Under being applicable to tape adapter unit mechanical test operating mode, adaptor interface is of a size of the satellite of φ 878mm and the connection of pedestal and shake table.The steel-wire screw-socket that end face installs the M12 of 36 distribution circle φ 706mm is connected with pressure ring, and under not tape adapter unit mechanical test operating mode, pressure ring is pushed down satellite and the rocket connecting ring and is connected with pedestal.
As shown in Figure 3, pressure ring 2 is first processed into required profile with annulus, and processes the T-shaped through hole 5 of 36 φ 13mm, then pressure ring is cut into six equal portions, keeps the gap of 5mm between every equal portions.
When using under being originally embodied in tape adapter unit state, with screw, adapter is connected with fixture; When using under not tape adapter unit state, with briquetting, satellite and the rocket connecting ring is connected.There is multiduty feature, save time, cost.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (6)
1. a multipurpose satellite clamp for mechanics experiment, it is characterized in that, comprise pedestal and pressure ring, described pedestal adopts circular cone flat form, the end face of described pedestal offers two circle screwed holes, described outside screw circle is used for Payload attach fitting, the fillet of screw of inner side is for connecting pressure ring, the top edge of described pedestal has 4 breach 3, described pedestal side has offered 8 square holes, the bottom surface of described pedestal offers two ring through hole, and for being connected with shake table and mode basis, described pressure ring adopts 45# steel machining.
2. a kind of multipurpose satellite clamp for mechanics experiment according to claim 1, is characterized in that, described pedestal adopts 104 aluminium alloy castings to form.
3. a kind of multipurpose satellite clamp for mechanics experiment according to claim 1, is characterized in that, the length of described square hole is 90mm.
4. a kind of multipurpose satellite clamp for mechanics experiment according to claim 1, is characterized in that, described two ring through hole comprise interior ring through hole and outer ring through hole, and described interior ring through hole is 8, outer ring through hole is 16, the T-shaped through hole of totally 24 φ 13mm.
5. a kind of multipurpose satellite clamp for mechanics experiment according to claim 1, is characterized in that, described base top surface also offers the steel-wire screw-socket of the M6 of the φ 878mm of 32 circular distributions.
6. a kind of multipurpose satellite clamp for mechanics experiment according to claim 1, is characterized in that, described pressure ring is provided with the T-shaped through hole of 36 φ 13mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410742669.8A CN104708550B (en) | 2014-12-05 | 2014-12-05 | Multipurpose satellite mechanics test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410742669.8A CN104708550B (en) | 2014-12-05 | 2014-12-05 | Multipurpose satellite mechanics test fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104708550A true CN104708550A (en) | 2015-06-17 |
| CN104708550B CN104708550B (en) | 2017-05-03 |
Family
ID=53408539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410742669.8A Active CN104708550B (en) | 2014-12-05 | 2014-12-05 | Multipurpose satellite mechanics test fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104708550B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106441767A (en) * | 2016-12-07 | 2017-02-22 | 上海卫星装备研究所 | Ground vibration testing clamp for large spacecraft vibration |
| CN106596010A (en) * | 2016-11-09 | 2017-04-26 | 上海卫星装备研究所 | Ground vibration test clamp used for large-scale spacecraft |
| CN107053104A (en) * | 2017-05-26 | 2017-08-18 | 北京航天新风机械设备有限责任公司 | A kind of attitude of satellite adjusts frock |
| CN107643154A (en) * | 2017-09-11 | 2018-01-30 | 上海微小卫星工程中心 | Satellite Vibration Test frock |
| 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 |
| CN107991047A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | For spacecraft ground vibration test fixture |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58151538A (en) * | 1982-03-05 | 1983-09-08 | Mitsubishi Electric Corp | Vibration testing device |
| CN101975651A (en) * | 2010-10-27 | 2011-02-16 | 中国科学院西安光学精密机械研究所 | Vibration test fixture for aerospace camera |
| CN102012303A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Clamping device in vibration distressing of satellite mechanical experiment pressure ring |
| 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 |
| CN202562722U (en) * | 2012-03-29 | 2012-11-28 | 浙江吉利汽车研究院有限公司 | Clamping and fixing device of storage battery vibration test |
-
2014
- 2014-12-05 CN CN201410742669.8A patent/CN104708550B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS58151538A (en) * | 1982-03-05 | 1983-09-08 | Mitsubishi Electric Corp | Vibration testing device |
| CN102012303A (en) * | 2009-09-08 | 2011-04-13 | 上海卫星工程研究所 | Clamping device in vibration distressing of satellite mechanical experiment pressure ring |
| CN101975651A (en) * | 2010-10-27 | 2011-02-16 | 中国科学院西安光学精密机械研究所 | Vibration test fixture for aerospace camera |
| 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 |
| CN202562722U (en) * | 2012-03-29 | 2012-11-28 | 浙江吉利汽车研究院有限公司 | Clamping and fixing device of storage battery vibration test |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106596010A (en) * | 2016-11-09 | 2017-04-26 | 上海卫星装备研究所 | Ground vibration test clamp used for large-scale spacecraft |
| CN106596010B (en) * | 2016-11-09 | 2019-08-02 | 上海卫星装备研究所 | One kind being used for large space aircraft ground vibration test fixture |
| CN106441767A (en) * | 2016-12-07 | 2017-02-22 | 上海卫星装备研究所 | Ground vibration testing clamp for large spacecraft vibration |
| CN107053104A (en) * | 2017-05-26 | 2017-08-18 | 北京航天新风机械设备有限责任公司 | A kind of attitude of satellite adjusts frock |
| CN107643154A (en) * | 2017-09-11 | 2018-01-30 | 上海微小卫星工程中心 | Satellite Vibration Test frock |
| 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 |
| CN107991047A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | For spacecraft ground vibration test fixture |
| CN107991047B (en) * | 2017-11-27 | 2021-05-28 | 上海卫星装备研究所 | Ground vibration test fixture for spacecraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104708550B (en) | 2017-05-03 |
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