CN103600857A - Attitude-adjusting assembly process for antenna performance test of special-shaped satellite structure - Google Patents
Attitude-adjusting assembly process for antenna performance test of special-shaped satellite structure Download PDFInfo
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- CN103600857A CN103600857A CN201310581307.0A CN201310581307A CN103600857A CN 103600857 A CN103600857 A CN 103600857A CN 201310581307 A CN201310581307 A CN 201310581307A CN 103600857 A CN103600857 A CN 103600857A
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Abstract
The invention discloses an attitude-adjusting assembly process for antenna performance test of a special-shaped satellite structure. The attitude-adjusting assembly process includes determining a fitting surface of the special-shaped satellite structure, selecting a test support according to the type of the fitting surface, fixedly connecting the selected test support to test equipment and adjusting a butt-joint surface of the test support and a special-shaped satellite into a horizontal or vertical state, assembling two single-beam double-lifting-point turnover slings to realize 90-degree turning of the special-shaped satellite, assembling a single-beam four-lifting-point horizontal sling to lift the satellite to the butt-joint surface matched with the test support and then connecting the satellite and the test support fixedly, thereby testing the antenna performance. By means of combination of the slings and different types of test supports, the essential problem in satellite attitude adjustment is solved, and tests of different types of antennas are completed.
Description
Technical field
The invention belongs to spacecraft attitude and adjust the frock technical field of class, specifically, the present invention relates to a kind of attitude adjustment assembly technique for special-shaped satellite structure performance of antenna test.
Background technology
Antenna is the important composition parts of satellite, and certain satellite is that test antenna performance is carried out special project test.Test antenna has three kinds, and is distributed on the different attachment faces of satellite, and because the setting angle of each antenna is different, test orientation is different, need to be equipped with different test brackets to reach test Gesture.Various antennas, in process of the test, need to be installed and dock with the test bracket of each test antenna to adjust attitude with suspender upset and level lifting satellite.The attitude that whole test realizes in the whole test process of satellite by two cover reversal hangers, a set of horizontal sling, three test brackets and transition parking leg is adjusted.Due to whole process of the test satellite test state complex, the frock relating to is more, therefore a set of special posture adjustment assembly technique need to be proposed, comprise the test bracket that designs different angles, satellite attitude is adjusted in lifting, satellite docks with the assembling of test bracket level or plumbness, to solve an antenna measurement posture adjustment difficult problem.
Summary of the invention
The object of the present invention is to provide a kind of safe and reliable assembly technology of realizing special-shaped satellite structure attitude adjustment, be intended to solve satellite complicated attitude in performance of antenna testing experiment and adjust a difficult problem.
To achieve these goals, the present invention has adopted following technical scheme:
A posture adjustment assembly technology for special-shaped satellite structure performance of antenna test, comprises the steps:
1) determine the attachment face of special-shaped satellite structure, attachment face comprises side, end face and bottom surface;
2), according to the type selecting test bracket of attachment face, end face is used 45 ° of test brackets, side to use 22.5 ° of test brackets, bottom surface to use 0 ° or 45 ° of test brackets; The interface of the test bracket of 45 °, 22.5 ° and 0 ° and the interface of special-shaped satellite and itself and test facility respectively at 45 °, 22.5 ° and 0 °;
3) selected test bracket is fixedly connected with test facility, test bracket and the interface of special-shaped satellite are adjusted to level or plumbness (0 ° or 45 ° of corresponding plumbnesss of test bracket, 22.5 ° of corresponding horizontalitys of test bracket);
4) assemble the reversal hanger of two cover single-beam two suspension centres, the reversal hanger of two cover single-beam two suspension centres is connected with two cover cranes and satellite suspension centre successively, two cover cranes are the independent lifting distance of controlling corresponding suspender respectively, by lifting distance (adjust crane rope long) to realize the upset of 90 °, special-shaped satellite, then be lifted into on the transition bracket of temporary supporting abnormity satellite and dock fasteningly, removed reversal hanger;
5) horizontal sling of assembling single-beam four-point lifting, after this suspender is connected with single cover crane and satellite suspension centre successively, remove the fastener of satellite and above-mentioned transition bracket, lifting satellite is to interface place that the test bracket with 45 °, 22.5 ° and 0 ° matches, connect fastener, remove suspender to carry out special-shaped satellite antenna performance testing.
The test bracket of wherein, 45 °, 22.5 ° and 0 ° is respectively arranged with the hole for loss of weight, lifting and operation.
Wherein, the horizontal sling of single-beam four-point lifting can be converted by the suspender of two cover single-beam two suspension centres, uses a hanging beam and four suspender belts wherein to combine.
Wherein, transition parking leg is for parking after 90 ° of satellite upsets, to carry out the replacing operation of reversal hanger and horizontal sling.
Wherein, the reversal hanger of two cover single-beam two suspension centres is for realizing the upset of 0 °～90 °, satellite.
Wherein, according to the antenna arrangement of special-shaped satellite, determine the attachment face of special-shaped satellite structure.
The present invention has realized the assembly technique that employing " is broken the whole up into parts ", the Gesture of special-shaped satellite structure performance of antenna testing complex is rationally decomposed, make complicated test tool " change embarrasses letter ", by the permutation and combination to suspender and multi-form test bracket, the gordian technique difficult point that has solved satellite posture adjustment, has obtained good result of use.
Accompanying drawing explanation
Fig. 1～Fig. 3 is the structural representation of 45 ° of test brackets that use in the inventive method, 22.5 ° of test brackets, 0 ° of test bracket.
The special-shaped satellite structure vertical lifting view of Fig. 4 (a) for using in the inventive method.
Fig. 4 (b) 90 ° of lifting view of special-shaped satellite structure upset for using in the inventive method.
Wherein, 1 is single-beam two suspension centre reversal hangers; 2 is another single-beam two suspension centre reversal hangers; 3 is special-shaped satellite structure.
Fig. 5 be after 90 ° of special-shaped satellite structure upsets in the inventive method with transition parking leg mated condition schematic diagram.
Wherein, 1 is single-beam two suspension centre reversal hangers; 2 is another single-beam two suspension centre reversal hangers; 3 special-shaped satellite structures 4 are transition parking leg.
Fig. 6 is the schematic diagram of the special-shaped satellite structure level lifting on transition parking leg in the inventive method.
Wherein, 21 is single-beam four-point lifting point horizontal sling; 3 is special-shaped satellite structure; 4 transition parking leies.
The schematic diagram that Fig. 7 (a) is plumbness for the special-shaped satellite structure in the inventive method and test bracket interface.
The schematic diagram that Fig. 7 (b) is horizontality for the special-shaped satellite structure in the inventive method and test bracket interface.
Wherein, 21 is single-beam four-point lifting horizontal sling; 3 is special-shaped satellite structure; 5 is test bracket; 6 is test facility.
The specific embodiment
What below introduce is the specific embodiment as content of the present invention, below by the specific embodiment, described content of the present invention is further illustrated.Certainly, describing the following specific embodiment is only the content of example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
With reference to Fig. 1-3, provided respectively and be applicable to different attachment faces, be the test support of side, end face and bottom surface, according to the type selecting test bracket of attachment face, end face is used 45 ° of test brackets, side to use 22.5 ° of test brackets, bottom surface to use 0 ° or 45 ° of test brackets; The interface of the test bracket of 45 °, 22.5 ° and 0 ° and the interface of special-shaped satellite and itself and test facility respectively at 45 °, 22.5 ° and 0 °.Fig. 1 correspondence 45 ° of test brackets; Fig. 2 correspondence 22.5 ° of test brackets; Fig. 3 correspondence 0 ° of test bracket.Test bracket is rigid structure, a Yu Qi bottom surface, side respectively at 45 °, 22.5 ° and 0 °, and on test bracket, be also provided with the hole of being convenient to loss of weight, lifting and operation.
In antenna measurement process, require each antenna mechanical axis and test facility axially parallel, so antenna can be divided into A, B, tri-kinds of antennas of C, according to practical set needs, need respectively the corresponding test bracket that uses 45 °, 22.5 ° and 0 °.
In a specific embodiment, the test set-up step of certain A antenna is as follows:
The first step, first docks 45 ° of test brackets 5 in Fig. 1 with suspender belt with known test facility 6, mounting fastener, then removes suspender belt; Test facility upset, makes 45 ° of test brackets 5 be turned to the state of Fig. 7 (a) (interface is plumbness).
Second step, assembles two cover single-beam two suspension centre reversal hangers 1,2, by the connection mode of Fig. 4 (a), two cover reversal hangers 1,2 is connected with two cover cranes and satellite suspension centre successively, guarantees that suspender and satellite are fastening.Control crane is lifting two cover reversal hangers slowly, and suspender belt is tightened slightly, when special-shaped satellite structure 3 rises after certain altitudes, overlap the lifting distance of the crane of suspenders by control linkage two, by 90 ° of special-shaped satellite structure 3 upsets, state as shown in Figure 4 (b); Then lift special-shaped satellite structure 3 and dock with it to transition parking leg 4 tops, mounting fastener, as shown in Figure 5, finally removes two cover single-beam two suspension centre reversal hangers 1,2.
The 3rd step, assembling single-beam four-point lifting horizontal sling 21, is connected this suspender 21 successively by the connection mode of Fig. 6 with single cover crane and satellite suspension centre, guarantee that single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 are fastening; Then remove the fastener between special-shaped satellite structure 3 and transition parking leg 4.Lift by crane special-shaped satellite structure 3 and be lifted into the interface place of test bracket 5, with the state shown in Fig. 7 (a), dock with test bracket 5, mounting fastener, finally removes single-beam four-point lifting horizontal sling 21, carries out A antenna measurement.
The 4th step, after A antenna measurement completes, returns to by special-shaped satellite structure 3 state of initially parking by inverse process.
The 5th step, is connected with 45 ° of test brackets with suspender belt, removes the fastener between 45 ° of test brackets 5 and test facility 6, and 45 ° of test brackets 5 are lifted into appropriate location, finally removes suspender.
In the another specific embodiment, B antenna measurement step is as follows:
The first step, first docks 22.5 ° of test brackets 5 in Fig. 2 with suspender belt with test facility 6, mounting fastener, then removes suspender belt; Test facility upset, makes 22.5 ° of test brackets 5 be turned to the state of Fig. 7 (b) (interface is horizontality).
Second step, assembles two cover single-beam two suspension centre reversal hangers 1,2, by the connection mode of Fig. 4 (a), two cover single-beam two suspension centre reversal hangers 1,2 is connected with two cover cranes and satellite suspension centre successively, guarantees that single-beam two suspension centre reversal hangers 1,2 are fastening with satellite.Control slowly lifting two cover reversal hangers of crane, suspender belt is tightened slightly, when special-shaped satellite structure 3 rises after certain altitude, by control linkage single-beam two suspension centre reversal hangers 1, the lifting distance of 2 crane, by 90 ° of satellite upsets, state as shown in Figure 4 (b); Then lift special-shaped satellite structure 3 and dock with it to transition parking leg 4 tops, mounting fastener, as shown in Figure 5, finally removes two single-beam two suspension centre reversal hangers 1,2.
The 3rd step, assembling single-beam four-point lifting horizontal sling 21, is connected this single-beam four-point lifting horizontal sling 21 successively by the connection mode of Fig. 6 with single cover crane and satellite suspension centre, guarantee that single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 are fastening; Then remove the fastener between special-shaped satellite structure 3 and transition parking leg 4.Lifting satellite is lifted into the interface place of test bracket 5, with the state shown in Fig. 7 (b), docks with test bracket 5, and mounting fastener, finally removes single-beam four-point lifting horizontal sling 21, carries out B antenna measurement.
The 4th step, after B antenna measurement completes, returns to by satellite the state of initially parking by inverse process.
The 5th step, is connected with 22.5 ° of test brackets 5 with suspender belt, removes the fastener between 22.5 ° of test brackets 5 and test facility 6, and 22.5 ° of test brackets 5 are lifted into appropriate location, finally removes single-beam four-point lifting horizontal sling 21.
In the specific embodiment again, C antenna measurement step is as follows:
The first step, first docks 0 ° of test bracket 5 in Fig. 3 with suspender belt with test facility 6, mounting fastener is removed suspender belt, and test facility upset, makes 0 ° of test bracket 5 be turned to the state of Fig. 7 (a) (interface is plumbness).
Second step, assembles two cover single-beam two suspension centre reversal hangers 1,2, by the connection mode of Fig. 4 (a), two cover reversal hangers is connected with two cover cranes and satellite suspension centre successively, guarantees that single-beam two suspension centre reversal hangers 1,2 are fastening with special-shaped satellite structure 3.Control crane and slowly lift by crane single-beam two suspension centre reversal hangers 1,2, suspender belt is tightened slightly, when special-shaped satellite structure 3(satellite) rise after certain altitude, by control linkage two cover single-beam two suspension centre reversal hangers 1,2 with the lifting distance of crane, by special-shaped satellite structure 3(satellite) overturn 90 °, state as shown in Figure 4 (b); Then lift special-shaped satellite structure 3(satellite) to transition parking leg 4 tops, dock with it, mounting fastener, as shown in Figure 5, finally removes two cover single-beam two suspension centre reversal hangers 1,2.
The 3rd step, assembling single-beam four-point lifting horizontal sling 21, is connected this single-beam four-point lifting horizontal sling 21 successively by the connection mode of Fig. 6 with single cover crane and satellite suspension centre, guarantee that single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 are fastening; Then remove the fastener between special-shaped satellite structure 3 and transition parking leg 4.Lift by crane special-shaped satellite structure 3 and be lifted into the interface place of test bracket 5, with the state shown in Fig. 7 (a), dock with test bracket 5, mounting fastener, finally removes single-beam four-point lifting horizontal sling 21, carries out C antenna measurement.
The 4th step, after C antenna measurement completes, returns to by special-shaped satellite structure 3 state of initially parking by inverse process.
The 5th step, is connected with 0 ° of test bracket 5 with suspender belt, removes the fastener between 0 ° of test bracket 5 and test facility 6, and 0 ° of test bracket 5 is lifted into appropriate location, finally removes suspender.
Although above the specific embodiment of the present invention is described in detail and is illustrated, but what should indicate is, we can make various changes and modifications above-mentioned embodiment, but these do not depart from the scope that spirit of the present invention and appended claim are recorded.
Claims (7)
1. for a posture adjustment assembly technology for special-shaped satellite structure performance of antenna test, comprise the steps:
1) determine the attachment face of special-shaped satellite structure, attachment face comprises side, end face and bottom surface;
2), according to the type selecting test bracket of attachment face, end face is used 45 ° of test brackets, side to use 22.5 ° of test brackets, bottom surface to use 0 ° or 45 ° of test brackets; The interface of the test bracket of 45 °, 22.5 ° and 0 ° and the interface of special-shaped satellite and itself and test facility respectively at 45 °, 22.5 ° and 0 °;
3) selected test bracket is fixedly connected with test facility, the interface of test bracket and special-shaped satellite is adjusted to level or plumbness;
4) assemble the reversal hanger of two cover single-beam two suspension centres, the reversal hanger of two cover single-beam two suspension centres is connected with two cover cranes and satellite suspension centre successively, two cover cranes are the independent lifting distance of controlling corresponding suspender respectively, by lifting distance (adjust crane rope long) to realize the upset of 90 °, special-shaped satellite, then hang and be mounted to on the transition bracket of temporary supporting abnormity satellite and dock fasteningly, remove reversal hanger;
5) horizontal sling of assembling single-beam four-point lifting, after this suspender is connected with single cover crane and satellite suspension centre successively, remove the fastener of satellite and above-mentioned transition bracket, lifting satellite is to interface place that the test bracket with 45 °, 22.5 ° and 0 ° matches, connect fastener, remove suspender to carry out special-shaped satellite antenna performance testing.
2. posture adjustment assembly technology as claimed in claim 1, wherein, the test bracket of 45 °, 22.5 ° and 0 ° is respectively arranged with the hole for loss of weight, lifting and operation.
3. posture adjustment assembly technology as claimed in claim 1, wherein, the horizontal sling of single-beam four-point lifting can be converted by the suspender of two cover single-beam two suspension centres, uses a hanging beam and four suspender belts wherein to combine.
4. posture adjustment assembly technology as claimed in claim 1, wherein, transition parking leg is for parking after 90 ° of satellite upsets, to carry out the replacing operation of reversal hanger and horizontal sling.
5. posture adjustment assembly technology as claimed in claim 1, wherein, the reversal hangers of two cover single-beam two suspension centres are for realizing the upset of 0 °～90 °, satellite.
6. the posture adjustment assembly technology as described in claim 1-5 any one, wherein, determines the attachment face of special-shaped satellite structure according to the antenna arrangement of special-shaped satellite.
7. the posture adjustment assembly technology as described in claim 1-5 any one, wherein, 0 ° or the corresponding plumbness with special-shaped satellites coupling face of 45 ° of test brackets, the corresponding horizontality with special-shaped satellites coupling face of 22.5 ° of test brackets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310581307.0A CN103600857B (en) | 2013-11-19 | 2013-11-19 | For the posture adjustment assembly technology of special-shaped satellite structure performance of antenna test |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310581307.0A CN103600857B (en) | 2013-11-19 | 2013-11-19 | For the posture adjustment assembly technology of special-shaped satellite structure performance of antenna test |
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| Publication Number | Publication Date |
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| CN103600857A true CN103600857A (en) | 2014-02-26 |
| CN103600857B CN103600857B (en) | 2016-04-06 |
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| CN201310581307.0A Expired - Fee Related CN103600857B (en) | 2013-11-19 | 2013-11-19 | For the posture adjustment assembly technology of special-shaped satellite structure performance of antenna test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107855745A (en) * | 2017-10-24 | 2018-03-30 | 北京航空航天大学 | A kind of suspension type aero-engine principal unit centered assembling mechanical system |
| CN109848669A (en) * | 2019-01-21 | 2019-06-07 | 燕山大学 | Has the function of the soft or hard mixed connection tipping clamp device of Three Degree Of Freedom posture adjustment |
| TWI677136B (en) * | 2018-12-13 | 2019-11-11 | 中衛科技股份有限公司 | Antenna mounting tube bundle platform adjustment mechanism |
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| EP2262052A1 (en) * | 2009-05-25 | 2010-12-15 | Janky Technology Co., Ltd. | Mounting bracket for satellite dish antenna and satellite dish antenna assembly using the same |
| CN102975184A (en) * | 2012-11-21 | 2013-03-20 | 中国航空工业集团公司北京航空精密机械研究所 | Double-shaft rotating table for adjusting satellite postures |
| US20130249754A1 (en) * | 2012-03-20 | 2013-09-26 | I Paul Stoddard Rice | Polarization phase device and a feed assembly using the same in the antenna system |
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2013
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Patent Citations (4)
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| CN101739478A (en) * | 2008-11-17 | 2010-06-16 | 北京卫星环境工程研究所 | Spacecraft assembly simulation technique-based virtual assembly system and virtual assembly method |
| EP2262052A1 (en) * | 2009-05-25 | 2010-12-15 | Janky Technology Co., Ltd. | Mounting bracket for satellite dish antenna and satellite dish antenna assembly using the same |
| US20130249754A1 (en) * | 2012-03-20 | 2013-09-26 | I Paul Stoddard Rice | Polarization phase device and a feed assembly using the same in the antenna system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107855745A (en) * | 2017-10-24 | 2018-03-30 | 北京航空航天大学 | A kind of suspension type aero-engine principal unit centered assembling mechanical system |
| CN107855745B (en) * | 2017-10-24 | 2019-06-28 | 北京航空航天大学 | A kind of suspension type aero-engine principal unit centered assembling mechanical system |
| TWI677136B (en) * | 2018-12-13 | 2019-11-11 | 中衛科技股份有限公司 | Antenna mounting tube bundle platform adjustment mechanism |
| CN109848669A (en) * | 2019-01-21 | 2019-06-07 | 燕山大学 | Has the function of the soft or hard mixed connection tipping clamp device of Three Degree Of Freedom posture adjustment |
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| CN103600857B (en) | 2016-04-06 |
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