CN103600857B - For the posture adjustment assembly technology of special-shaped satellite structure performance of antenna test - Google Patents
For the posture adjustment assembly technology of special-shaped satellite structure performance of antenna test Download PDFInfo
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- CN103600857B CN103600857B CN201310581307.0A CN201310581307A CN103600857B CN 103600857 B CN103600857 B CN 103600857B CN 201310581307 A CN201310581307 A CN 201310581307A CN 103600857 B CN103600857 B CN 103600857B
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Abstract
The invention discloses a kind of posture adjustment assembly technology for special-shaped satellite structure performance of antenna test, comprise the attachment face determining special-shaped satellite structure; According to the type selecting test bracket of attachment face; Selected test bracket is fixedly connected with test facility, the interface of test bracket and special-shaped satellite is adjusted to level or plumbness; The reversal hanger of assembling two cover single-beam two suspension centre realizes the upset of 90 °, special-shaped satellite; The horizontal sling of assembling single-beam four-point lifting, is lifted into the interface place matched with test bracket and is fixed and is connected with test antenna performance by satellite.The present invention, by the permutation and combination to suspender and multi-form test bracket, solves the crucial problem of satellite posture adjustment, completes the test of different antennae type.
Description
Technical field
The invention belongs to the frock technical field of spacecraft attitude adjustment class, specifically, the present invention relates to a kind of pose adjustment assembly technology 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 carries 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, needs to be equipped with different test brackets to reach test Gesture.Various antenna, in process of the test, needs to lift satellite with suspender upset and level and to install with the test bracket of each test antenna dock to adjust attitude.Whole test realizes the pose adjustment in the whole test process of satellite by two cover reversal hangers, a set of horizontal sling, three test brackets and transition parking leg.Due to whole process of the test satellite test state complex, the frock related to is more, therefore need to propose a set of special posture adjustment assembly technique, comprise the test bracket of design different angles, lifting adjustment satellite attitude, 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 realizing special-shaped satellite structure pose adjustment, be intended to solve a satellite pose adjustment difficult problem complicated in performance of antenna testing experiment.
To achieve these goals, present invention employs following technical scheme:
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 uses 45 ° of test brackets, side uses 22.5 ° of test brackets, bottom surface uses 0 ° or 45 ° of test brackets; The interface of 45 °, 22.5 ° and the test bracket of 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 is adjusted to level or plumbness (0 ° or 45 ° of corresponding plumbnesss of test bracket, 22.5 ° of corresponding horizontalitys of test bracket);
4) reversal hanger of two cover single-beam two suspension centres is assembled, the reversal hanger of two cover single-beam two suspension centres is overlapped crane with two successively and satellite suspension centre is connected, two cover cranes independently control the lifting distance of corresponding suspender, by lifting distance (adjustment crane rope is long) to realize the upset of 90 °, special-shaped satellite, then to be lifted on the transition bracket of temporary support abnormity satellite and to carry out docking fastening, dismounting reversal hanger;
5) horizontal sling of single-beam four-point lifting is assembled, this suspender is overlapped after crane and satellite suspension centre be connected with single successively, remove the fastener of satellite and above-mentioned transition bracket, the interface place that lifting satellite matches to the test bracket with 45 °, 22.5 ° and 0 °, connect fastener, remove suspender to carry out special-shaped satellite antenna performance testing.
Wherein, the test bracket of 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, namely uses wherein hanging beam and four suspender belts to combine.
Wherein, parking, to carry out the replacement operation of reversal hanger and horizontal sling after transition parking leg overturns 90 ° for satellite.
Wherein, the reversal hanger of two cover single-beam two suspension centres is for realizing the upset of 0 ° ~ 90 °, satellite.
Wherein, the attachment face of special-shaped satellite structure is determined according to the antenna arrangement of special-shaped satellite.
Present invention achieves 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, solve the key technical problems of satellite posture adjustment, achieve good result of use.
Accompanying drawing explanation
Fig. 1 ~ Fig. 3 is the structural representation of the 45 ° of test brackets used 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) lifts view for the special-shaped satellite structure used in the inventive method overturns 90 °.
Wherein, 1 is single-beam two suspension centre reversal hanger; 2 is another single-beam two suspension centre reversal hanger; 3 is special-shaped satellite structure.
Fig. 5 be after the special-shaped satellite structure in the inventive method overturns 90 ° with transition parking leg mated condition schematic diagram.
Wherein, 1 is single-beam two suspension centre reversal hanger; 2 is another single-beam two suspension centre reversal hanger; 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.
Fig. 7 (a) for the special-shaped satellite structure in the inventive method and test bracket interface be the schematic diagram of plumbness.
Fig. 7 (b) for the special-shaped satellite structure in the inventive method and test bracket interface be the schematic diagram of horizontality.
Wherein, 21 is single-beam four-point lifting horizontal sling; 3 is special-shaped satellite structure; 5 is test bracket; 6 is test facility.
Detailed description of the invention
What below introduce is detailed description of the invention as content of the present invention, further illustrates described content of the present invention below by detailed description of the invention.Certainly, describe the content that following detailed description is only 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, sets forth and be applicable to different attachment face, the i.e. test support of side, end face and bottom surface, according to the type selecting test bracket of attachment face, end face uses 45 ° of test brackets, side uses 22.5 ° of test brackets, bottom surface uses 0 ° or 45 ° of test brackets; The interface of 45 °, 22.5 ° and the test bracket of 0 ° and the interface of special-shaped satellite and itself and test facility respectively at 45 °, 22.5 ° and 0 °.Fig. 1 correspond to 45 ° of test brackets; Fig. 2 correspond to 22.5 ° of test brackets; Fig. 3 correspond to 0 ° of test bracket.Test bracket is rigid structure, a side and its bottom surface respectively at 45 °, 22.5 ° and 0 °, and test bracket is also provided with the hole being convenient to loss of weight, lifting and operation.
In antenna measurement process, require that each mechanical axis of antenna is axially parallel with test facility, therefore antenna can be divided into A, B, C tri-kinds of antennas, according to practical set needs, needs the corresponding test bracket using 45 °, 22.5 ° and 0 ° respectively.
In a detailed description of the invention, the test set-up step of certain A antenna is as follows:
The first step, first docked with known test facility 6 by ° test bracket of 45 in Fig. 15 with suspender belt, mounting fastener, then removes suspender belt; Test facility overturns, and makes 45 ° of test brackets 5 be turned to the state of Fig. 7 (a) (interface is plumbness).
Second step, two cover reversal hangers 1,2 are overlapped crane with two by the connection mode of Fig. 4 (a) by assembling two cover single-beam two suspension centre reversal hangers 1,2 successively and satellite suspension centre is connected, guarantee suspender and satellite fastening.Control crane and slowly lift by crane two cover reversal hangers, suspender belt is tightened slightly, after special-shaped satellite structure 3 rises certain altitude, is overlapped the lifting distance of the crane of suspender by control linkage two, special-shaped satellite structure 3 is overturn 90 °, state as shown in Figure 4 (b); Then lift above special-shaped satellite structure 3 to transition parking leg 4 and dock with it, mounting fastener, as shown in Figure 5, finally remove two cover single-beam two suspension centre reversal hangers 1,2.
3rd step, assembling single-beam four-point lifting horizontal sling 21, overlap crane with single by the connection mode of Fig. 6 successively by this suspender 21 and satellite suspension centre is connected, guarantee single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 fastening; Then the fastener between special-shaped satellite structure 3 and transition parking leg 4 is removed.Lift by crane the interface place that special-shaped satellite structure 3 is lifted into test bracket 5, dock with test bracket 5 with the state shown in Fig. 7 (a), mounting fastener, finally remove single-beam four-point lifting horizontal sling 21, carry out A antenna measurement.
4th step, after A antenna measurement completes, returns to initial parked state by inverse process by special-shaped satellite structure 3.
5th step, is connected with 45 ° of test brackets with suspender belt, removes the fastener between 45 ° of test brackets 5 and test facility 6,45 ° of test brackets 5 is lifted into appropriate location, finally removes suspender.
In another detailed description of the invention, B antenna measurement step is as follows:
The first step, first docked with test facility 6 by ° test bracket of 22.5 in Fig. 25 with suspender belt, mounting fastener, then removes suspender belt; Test facility overturns, and makes 22.5 ° of test brackets 5 be turned to the state of Fig. 7 (b) (interface is horizontality).
Second step, two cover single-beam two suspension centre reversal hangers 1,2 overlaps crane with two by the connection mode of Fig. 4 (a) by assembling two cover single-beam two suspension centre reversal hangers 1,2 successively and satellite suspension centre is connected, guarantee single-beam two suspension centre reversal hanger 1,2 and satellite fastening.Control crane and slowly lift by crane two cover reversal hangers, suspender belt is tightened slightly, after special-shaped satellite structure 3 rises certain altitude, by control linkage single-beam two suspension centre reversal hanger 1, the lifting distance of the crane of 2, overturns 90 °, state as shown in Figure 4 (b) by satellite; Then lift above special-shaped satellite structure 3 to transition parking leg 4 and dock with it, mounting fastener, as shown in Figure 5, finally remove two single-beam two suspension centre reversal hangers 1,2.
3rd step, assembling single-beam four-point lifting horizontal sling 21, overlap crane with single by the connection mode of Fig. 6 successively by this single-beam four-point lifting horizontal sling 21 and satellite suspension centre is connected, guarantee single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 fastening; Then the fastener between special-shaped satellite structure 3 and transition parking leg 4 is removed.Lifting satellite is lifted into the interface place of test bracket 5, docks, mounting fastener with the state shown in Fig. 7 (b) with test bracket 5, finally removes single-beam four-point lifting horizontal sling 21, carries out B antenna measurement.
4th step, after B antenna measurement completes, returns to initial parked state by inverse process by satellite.
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 6,22.5 ° of test brackets 5 are lifted into appropriate location, finally removes single-beam four-point lifting horizontal sling 21.
In a detailed description of the invention again, C antenna measurement step is as follows:
The first step, first docks 0 ° of test bracket 5 in Fig. 3 with test facility 6 with suspender belt, mounting fastener, removes suspender belt, and test facility overturns, and makes 0 ° of test bracket 5 be turned to the state of Fig. 7 (a) (interface is plumbness).
Second step, two cover reversal hangers overlaps crane with two by the connection mode of Fig. 4 (a) by assembling two cover single-beam two suspension centre reversal hangers 1,2 successively and satellite suspension centre is connected, guarantee single-beam two suspension centre reversal hanger 1,2 and special-shaped satellite structure 3 fastening.Control crane and slowly lift by crane single-beam two suspension centre reversal hanger 1,2, suspender belt is tightened slightly, when special-shaped satellite structure 3(satellite) rise certain altitude after, single-beam two suspension centre reversal hanger 1 is overlapped by control linkage two, 2 with the lifting distance of crane, by special-shaped satellite structure 3(satellite) overturn 90 °, state as shown in Figure 4 (b); Then special-shaped satellite structure 3(satellite is lifted) dock with it above transition parking leg 4, mounting fastener, as shown in Figure 5, finally remove two cover single-beam two suspension centre reversal hangers 1,2.
3rd step, assembling single-beam four-point lifting horizontal sling 21, overlap crane with single by the connection mode of Fig. 6 successively by this single-beam four-point lifting horizontal sling 21 and satellite suspension centre is connected, guarantee single-beam four-point lifting horizontal sling 21 and special-shaped satellite structure 3 fastening; Then the fastener between special-shaped satellite structure 3 and transition parking leg 4 is removed.Lift by crane the interface place that special-shaped satellite structure 3 is lifted into test bracket 5, dock with test bracket 5 with the state shown in Fig. 7 (a), mounting fastener, finally remove single-beam four-point lifting horizontal sling 21, carry out C antenna measurement.
4th step, after C antenna measurement completes, returns to initial parked state by inverse process by special-shaped satellite structure 3.
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 6,0 ° of test bracket 5 is lifted into appropriate location, finally removes suspender.
Although be described in detail the specific embodiment of the present invention above and illustrate, but what should indicate is, we can make various changes and modifications above-mentioned embodiment, but these do not depart from spirit of the present invention and the scope described in appended claim.
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 uses 45 ° of test brackets, side uses 22.5 ° of test brackets, bottom surface uses 0 ° or 45 ° of test brackets; The test bracket of 45 °, 22.5 ° and the test bracket of 0 ° and the interface of special-shaped satellite and 45 °, 22.5 ° and 0 ° and the interface of 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) reversal hanger of two cover single-beam two suspension centres is assembled, the reversal hanger of two cover single-beam two suspension centres is overlapped crane with two successively and satellite suspension centre is connected, two cover cranes independently control the lifting distance of corresponding suspender, by lifting distance to realize the upset of 90 °, special-shaped satellite, then special-shaped satellite to be lifted on the transition parking leg of temporary support abnormity satellite and to carry out docking fastening, dismounting reversal hanger;
5) horizontal sling of single-beam four-point lifting is assembled, the horizontal sling of single-beam four-point lifting is overlapped after crane and satellite suspension centre be connected with single successively, remove the fastener of satellite and above-mentioned transition parking leg, the interface place that lifting satellite matches to the test bracket with 45 °, 22.5 ° and 0 °, 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, namely uses wherein hanging beam and four suspender belts to combine.
4. posture adjustment assembly technology as claimed in claim 1, wherein, parking, to carry out the replacement operation of reversal hanger and horizontal sling after transition parking leg overturns 90 ° for satellite.
5. posture adjustment assembly technology as claimed in claim 1, wherein, the reversal hanger of two cover single-beam two suspension centres is for realizing the upset of 0 ° ~ 90 °, satellite.
6. the posture adjustment assembly technology as described in any one of claim 1-5, 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 any one of claim 1-5, wherein, 0 ° or 45 ° of test brackets correspond to the plumbness in special-shaped satellites coupling face, and 22.5 ° of test brackets correspond to the horizontality in special-shaped satellites coupling face.
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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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| 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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| CN103600857A CN103600857A (en) | 2014-02-26 |
| CN103600857B true CN103600857B (en) | 2016-04-06 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN109848669B (en) * | 2019-01-21 | 2020-02-04 | 燕山大学 | Soft-hard mixed connecting device with three-degree-of-freedom posture adjusting function |
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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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8723747B2 (en) * | 2012-03-20 | 2014-05-13 | Kvh Industries, Inc. | Polarization phase device and a feed assembly using the same in the antenna system |
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Patent Citations (3)
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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 |
| 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 |
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| 月球探测器紧缩场测试调姿方案设计与实现;冯伟，李晓欢，易旺民，张延磊，翟怡，刘涛;《航天制造技术》;20141031(第5期);全文 * |
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