CN101451644A - Satellite vacuum thermal test support - Google Patents
Satellite vacuum thermal test support Download PDFInfo
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- CN101451644A CN101451644A CNA2007101955217A CN200710195521A CN101451644A CN 101451644 A CN101451644 A CN 101451644A CN A2007101955217 A CNA2007101955217 A CN A2007101955217A CN 200710195521 A CN200710195521 A CN 200710195521A CN 101451644 A CN101451644 A CN 101451644A
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Abstract
The invention relates to a test bracket which is used in a satellite vacuum thermal test. The test bracket is an L-shaped framework structure, and the aim of adopting the framework structure is to reduce the barrier to the satellite body by the test bracket as much as possible. The bracket is formed by welding 1Cr18Ni9Ti rectangular steel tubes and can bear 1500kg of satellite weight. The A surface and the B surface of the bracket can both touch the ground, when the satellite is arranged in the bracket, the B surface touches the ground, and when the test is done in a space simulator, the A surface touches the ground. An installing flange in the B surface of the test bracket is connected with a satellite coupling flange by a coupling frame which adopts an inverted cone stainless steel truss structure in order to reduce the barrier to the heat dispersing surface of the satellite body, and moreover, the test bracket has the function of regulating the levelness of the satellite. The bracket increases the whole strength and stiffness of the bracket and can avoid violent sloshing of the satellite in the process of lifting and switching. In the test process, adopting the bracket can reduce the influence to the radiation on the surface of the satellite as much as possible and ensure the levelness index of the satellite within 1mm/1m.
Description
Technical field
The invention belongs to the spacecraft thermal vacuum test field, be specifically related to a kind of large platform astrovehicle thermal test support.
Background technique
During the satellite vacuum thermal test, need special-purpose test support and carry satellite.Satisfy under the prerequisite that the required inner space of satellite is installed at the test support, generally also should satisfy following condition: reduce test support blocking as far as possible satellite body; The A face and the B face of test support all can land, to satisfy the needs that satellite is adjusted in each stage attitude; The test support should have the function of regulating the satellite levelness, and the levelness that makes the satellite surface is in 1mm/1m; The test support is generally used the stainless steel material manufacturing, to guarantee having enough intensity and stability at the vacuum low-temperature environment lower support frame; The test support should have enough rigidity, to guarantee not make satellite produce excessive rocking in lifting and the umklapp process, guarantees safety.And present thermal test support can not satisfy above-mentioned requirement fully, therefore, press for a kind of satellite is blocked little, the thermal test support that simultaneously has enough mechanical propertys again.
Summary of the invention
The objective of the invention is to overcome some problems that exist in the prior art, and provide a kind of large platform astrovehicle thermal test support, be intended to solve not high, the test support problem bigger of astrovehicle vacuum thermal test support strength and stiffness in the vacuum thermal test to blocking of satellite body, thereby for the reliability and the accuracy of spacecraft thermal vacuum test provides technical guarantee, simplified satellite test installation process, when improving Security, reduced test support blocking again to satellite body.
The present invention seeks to be achieved through the following technical solutions:
A kind of satellite vacuum thermal test support is the L frame structure, and described frame structure side is connected with interface frame, mating frame by flange, and wherein, the interface frame, mating frame cantilever connects satellite.
Further, above-mentioned side comprises two columns, two longerons, two middle standing pillars that are welded to each other and is welded in two carlings between two middle standing pillars, two middle standing pillars and two carlings are symmetrical arranged with the center, side respectively, place, right angle between two middle standing pillars and two longerons is welded with set square triangle respectively, and and two carlings between the place, right angle be welded with short cant beam respectively, the square frame that two middle standing pillars and two carlings constitute welds with flange and is connected by bolt.Wherein, preferably be connected by four bolts that are separately positioned on two middle standing pillars and two carling centers.
Further, the lower flange of above-mentioned interface frame, mating frame carries out bolt with above-mentioned flange and is connected, and interface frame, mating frame can separate with the test support, and is provided with the vertical support device below the upper flange that is connected with satellite of interface frame, mating frame.
In the above-mentioned test support, the bottom surface of described L framework comprises two crossbeams, two longerons, one of them is the public longeron with above-mentioned side, is welded with another intermediate longitudinal girder between the intermediate longitudinal girder between two crossbeams and intermediate longitudinal girder and public longeron near public longeron one side corresponding to described vertical support device.
In the above-mentioned test support, be welded with set square triangle between bottom surface two crossbeams of described L framework and L frame facet two columns, and two column tops are welded with oblique reinforcement between the set square triangle soldering point to two crossbeams.
In the above-mentioned test support, the bottom surface of L framework and side all can land, and landing ground is provided with the adjusting supporting leg that can adjust the satellite levelness.The quantity of the adjusting supporting leg of every side is preferably 4.
In the above-mentioned test support, two columns and two beam top all are provided with suspension hook.
In the above-mentioned test support, interface frame, mating frame adopts inverted cone stainless steel truss structure, and it comprises that upper flange, lower flange and some poles are welded.
Wherein, each parts of support all adopt the 1Cr18Ni9Ti rectangular steel pipe, and test support main structure is directly in the face of heat sink part spraying high emissivity black fever control coating layer, test support main structure surface to celestial body partly, all twine on the interface frame, mating frame surface or paste two-sided aluminized polyester film.
The invention has the advantages that: by improving structural type, further improved the bulk strength and the rigidity of support, in lifting, umklapp process, can avoid satellite to produce excessive rocking.In process of the test, adopt this support, can farthest reduce influence to the satellite table surface radiation, the levelness index that can guarantee satellite is in 1mm/1m.
Description of drawings
Fig. 1 (a) is the plan view of test support of the present invention;
Fig. 1 (b) is the side view of test support of the present invention;
Fig. 1 (c) is the plan view of test support of the present invention;
Wherein, 1, crossbeam; 2, intermediate longitudinal girder; 3 intermediate longitudinal girders; 4, column; 5, set square triangle; 6, longeron; 7, longeron; 8, middle standing pillar; 9, carling; 10, lack cant beam; 11, flange; 12, interface frame, mating frame; 13, satellite; 14, bolt; 15, bolt; 16, interface frame, mating frame lower flange; 17, interface frame, mating frame upper flange; 18, vertical support device; 19, longeron; 20, oblique reinforcement; 21, regulate supporting leg; 22, suspension hook;
Fig. 2 is the structural drawing of interface frame, mating frame among the present invention.Wherein, 23, pole.
Embodiment
The present invention is further illustrated below in conjunction with accompanying drawing.
As shown in Figure 1, satellite vacuum thermal test support of the present invention is the L frame structure, and this texture edge of framework (B face) is connected with interface frame, mating frame 12 by flange 11, and wherein, interface frame, mating frame 12 cantilevers connect satellite 14.The side comprises two columns 4, two longerons 6,7, two middle standing pillars 8 that are welded to each other and is welded in two carlings 9 between two middle standing pillars 8, two middle standing pillars 8 and two carlings 9 are symmetrical arranged with the center, side respectively, place, right angle between two middle standing pillars 8 and two longerons 6,7 is welded with set square triangle 5 respectively, and and two carlings 9 between the place, right angle be welded with square frame that short cant beam 10, two middle standing pillars 8 and two carlings 9 constitute respectively and weld with flange 11 and be connected by bolt 14.Wherein, preferably be connected by four bolts 14 that are separately positioned on two middle standing pillars and two carlings, 9 centers.The lower flange 16 of interface frame, mating frame 12 carries out bolt 15 with above-mentioned flange 11 and is connected, and interface frame, mating frame 12 can separate with the test support, and upper flange 17 belows that interface frame, mating frame 12 is connected with satellite 13 are provided with vertical support device 18.Wherein, the bottom surface of L framework (A face) comprises two crossbeams 1, two longerons 7,19, one of them is the public longeron 7 with upper side, is welded with another intermediate longitudinal girder 3 between the intermediate longitudinal girder 2 between two crossbeams 1 and intermediate longitudinal girder 2 and public longeron 7 near public longeron 7 one sides corresponding to vertical support device 18.Be welded with set square triangle 5 between bottom surface two crossbeams 1 of above-mentioned L framework and L frame facet (B face) two columns 4, and two columns, 4 tops are welded with oblique reinforcement 20 between set square triangle 5 soldering points to two crossbeams 1.The bottom surface of L framework and side all can land, and landing ground is provided with the adjusting supporting leg 21 that can adjust the satellite levelness.The quantity of the adjusting supporting leg 21 of every side is preferably 4.Wherein, the top of two columns 4 and two crossbeams 1 all is provided with suspension hook 22.
The A face and the B face of test support of the present invention all can land, and A face and B face all have the function that levelness is regulated, and are lined with thermal insulating pad between the interface of support and satellite.
Fig. 2 has provided and has been used for the structure that the present invention tests the interface frame, mating frame of support, and this interface frame, mating frame comprises that annular upper flange 17, annular lower flange 16 and some poles 23 are welded, and interface frame, mating frame adopts inverted cone stainless steel truss structure and satellite to couple together.
Test support of the present invention is the L frame structure, and purpose is intended to reduce test support blocking satellite body as far as possible.Simultaneously, support adopts the 1Cr18Ni9Ti rectangular steel pipe to be welded, and support can bear the about 1500kg of satellite weight.The A face and the B face of support all can land, and when on support satellite being installed, the B face lands.And when testing in space simulator, then the A face lands.Mounting flange on the test support B face is connected with the satellites coupling flange by interface frame, mating frame, and for reducing the blocking of celestial body heat dispersing surface, interface frame, mating frame adopts inverted cone stainless steel truss structure, and the processing of through hole use satellite-rocket docking is processed and used drill jig on the interface frame, mating frame.The test support has the function of regulating the satellite levelness.
Above-mentioned mode of execution only is used for illustrating the present invention, and it should not be construed is that protection scope of the present invention is carried out any restriction.And, it will be apparent to those skilled in the art that do not breaking away under the present invention spirit and the principle, to various equivalent variation that the present invention carried out, modification and in the text not the various improvement of description all within the protection domain of this patent.
Claims (10)
1, a kind of satellite vacuum thermal test support is the L frame structure, and the side of described frame structure is connected with interface frame, mating frame by flange, it is characterized in that, described interface frame, mating frame cantilever connects satellite.
2, support as claimed in claim 1, it is characterized in that, the side of described frame structure comprises two columns (4) that are welded to each other, two longerons (6,7), two middle standing pillars (8) and be welded in two carlings (9) between two middle standing pillars (8), two middle standing pillars (8) and two carlings (9) are symmetrical arranged with the center, side respectively, two middle standing pillars (8) and two longerons (6,7) place, right angle between is welded with set square triangle (5) respectively, and and two carlings (9) between the place, right angle be welded with short cant beam (10) respectively, the square frame that two middle standing pillars (8) and two carlings (9) constitute welds with flange (11) and is connected by bolt (14).
3, support as claimed in claim 2 is characterized in that, is connected by four bolts (14) that are separately positioned on two middle standing pillars (8) and two carlings (9) center.
4, support as claimed in claim 2 is characterized in that, the lower flange (16) of described interface frame, mating frame (12) carries out bolt with described flange (11) and is connected.
5, support as claimed in claim 4 is characterized in that, affiliated interface frame, mating frame (12) can separate with the test support, and upper flange (17) below that interface frame, mating frame (12) is connected with satellite (13) is provided with vertical support device (18).
6, as each described support of claim 1-5, it is characterized in that, the bottom surface of described L framework comprises two crossbeams (1), two longerons (19,7), one of them is the public longeron (7) with described side, is welded with the intermediate longitudinal girder (2) that is positioned between two crossbeams (1) and another intermediate longitudinal girder (3) between intermediate longitudinal girder (2) and the public longeron (7) near public longeron (7) one sides corresponding to described vertical support device (18).
7, support as claimed in claim 6 is characterized in that, described another intermediate longitudinal girder (3) is arranged on intermediate longitudinal girder (2) and public longeron (7) central authorities.
8, support as claimed in claim 6, it is characterized in that, be welded with set square triangle (5) between bottom surface two crossbeams (1) of described L framework and L frame facet two columns (4), and two columns (4) top upward is welded with oblique reinforcement (20) between the set square triangle soldering point to two crossbeams (1).
9, as each described support of claim 1-5, it is characterized in that the bottom surface of described L framework and side all can land, and landing ground is provided with the adjusting supporting leg (21) that can adjust the satellite levelness.
As each described support of claim 1-5, it is characterized in that 10, described interface frame, mating frame (12) adopts inverted cone stainless steel truss structure, it comprises that upper flange (17), lower flange (16) and some poles (23) are welded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101955217A CN101451644A (en) | 2007-12-04 | 2007-12-04 | Satellite vacuum thermal test support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101955217A CN101451644A (en) | 2007-12-04 | 2007-12-04 | Satellite vacuum thermal test support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101451644A true CN101451644A (en) | 2009-06-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101955217A Pending CN101451644A (en) | 2007-12-04 | 2007-12-04 | Satellite vacuum thermal test support |
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| Country | Link |
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| CN (1) | CN101451644A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102539181A (en) * | 2011-12-08 | 2012-07-04 | 北京空间飞行器总体设计部 | Method for testing ground surface heat of complex space mechanism |
| CN102556371A (en) * | 2011-12-14 | 2012-07-11 | 北京卫星环境工程研究所 | Movable support capable of adjusting test piece angle in vacuum container |
| CN102768126A (en) * | 2012-08-03 | 2012-11-07 | 北京卫星环境工程研究所 | Foot pad abutting mechanism for lander thermal test |
| CN103605372A (en) * | 2013-08-19 | 2014-02-26 | 北京卫星环境工程研究所 | Inclination angle automatic adjustment platform for thermal test under vacuum low-temperature environment |
| CN104074629A (en) * | 2014-07-14 | 2014-10-01 | 北京卫星环境工程研究所 | Star catalogue protruding large-diameter engine non-contacting type protecting device and method |
| CN104724299A (en) * | 2014-12-08 | 2015-06-24 | 上海卫星装备研究所 | Novel satellite parking device |
| CN106647117A (en) * | 2017-01-23 | 2017-05-10 | 长光卫星技术有限公司 | Truss type main support structure of long-focus wide-view-field large off-axis three-lens-reflex space camera |
| CN106647116A (en) * | 2016-12-09 | 2017-05-10 | 中国科学院长春光学精密机械与物理研究所 | Deployable supporting truss for long-focal length space camera secondary mirror assembly |
| CN111717425A (en) * | 2020-06-01 | 2020-09-29 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
-
2007
- 2007-12-04 CN CNA2007101955217A patent/CN101451644A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102539181B (en) * | 2011-12-08 | 2014-06-25 | 北京空间飞行器总体设计部 | Method for testing ground surface heat of complex space mechanism |
| CN102539181A (en) * | 2011-12-08 | 2012-07-04 | 北京空间飞行器总体设计部 | Method for testing ground surface heat of complex space mechanism |
| CN102556371A (en) * | 2011-12-14 | 2012-07-11 | 北京卫星环境工程研究所 | Movable support capable of adjusting test piece angle in vacuum container |
| CN102556371B (en) * | 2011-12-14 | 2015-04-08 | 北京卫星环境工程研究所 | Movable support capable of adjusting test piece angle in vacuum container |
| CN102768126A (en) * | 2012-08-03 | 2012-11-07 | 北京卫星环境工程研究所 | Foot pad abutting mechanism for lander thermal test |
| CN102768126B (en) * | 2012-08-03 | 2015-04-08 | 北京卫星环境工程研究所 | Foot pad abutting mechanism for lander thermal test |
| CN103605372A (en) * | 2013-08-19 | 2014-02-26 | 北京卫星环境工程研究所 | Inclination angle automatic adjustment platform for thermal test under vacuum low-temperature environment |
| CN104074629B (en) * | 2014-07-14 | 2016-04-06 | 北京卫星环境工程研究所 | Star catalogue gives prominence to the contactless protective equipment of heavy caliber motor and protecting method |
| CN104074629A (en) * | 2014-07-14 | 2014-10-01 | 北京卫星环境工程研究所 | Star catalogue protruding large-diameter engine non-contacting type protecting device and method |
| CN104724299A (en) * | 2014-12-08 | 2015-06-24 | 上海卫星装备研究所 | Novel satellite parking device |
| CN106647116A (en) * | 2016-12-09 | 2017-05-10 | 中国科学院长春光学精密机械与物理研究所 | Deployable supporting truss for long-focal length space camera secondary mirror assembly |
| CN106647116B (en) * | 2016-12-09 | 2019-08-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of deployable sub-truss of long-focus space camera time mirror assembly |
| CN106647117A (en) * | 2017-01-23 | 2017-05-10 | 长光卫星技术有限公司 | Truss type main support structure of long-focus wide-view-field large off-axis three-lens-reflex space camera |
| CN106647117B (en) * | 2017-01-23 | 2018-12-25 | 长光卫星技术有限公司 | The large-scale off-axis three anti-space camera truss-like main supporting structure of long-focus wide visual field |
| CN111717425A (en) * | 2020-06-01 | 2020-09-29 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
| CN111717425B (en) * | 2020-06-01 | 2022-03-04 | 北京空间飞行器总体设计部 | Heat source isolation and automatic temperature control system based on multi-satellite parallel thermal vacuum test |
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Open date: 20090610 |