CN102284859A - Digital assembly method of space remote sensing instrument - Google Patents
Digital assembly method of space remote sensing instrument Download PDFInfo
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- CN102284859A CN102284859A CN2011101174327A CN201110117432A CN102284859A CN 102284859 A CN102284859 A CN 102284859A CN 2011101174327 A CN2011101174327 A CN 2011101174327A CN 201110117432 A CN201110117432 A CN 201110117432A CN 102284859 A CN102284859 A CN 102284859A
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Abstract
The invention discloses a digital assembly method of a space remote sensing instrument, comprising that: (1) a substance coordinate system is established on a main frame of a substance of the space remote sensing instrument, and a coordinate of a monitoring point of a component to be assembled is measured; (2) the substance coordinate system and a datum coordinate system of a CAD model are superposed, an misadjustment of each component to be assembled is computed according to a coordinate position difference of the monitoring point of the component to be assembled; (3) each component is assembled in place by an adjusting frame with six degrees of freedom according to the misadjustment. The method has high universality, can quantify and objectify the assembly of the space remote sensing instrument, and can maximally reduce the dependence on experience and states of operators.
Description
Technical field
The present invention relates to a kind of assembly method of instrument, be specifically related to a kind of digitlization assembly method of space remote sensing instrument.
Background technology
The assembling of space remote sensing instrument is important in its a manufacturing field link.After each element all is seated, just can carries out optics and debug work.Along with the form of remote sensing instrument becomes increasingly complex, the assembling free degree of its element to be assembled is also more and more, and such as in the anti-remote sensing instrument of axle three system, two speculums to be assembled have 10 frees degree altogether, and do not have machinery location benchmark.This has brought very big difficulty to assembly work.
Traditional assembly method is based on optical measurement, even be benchmark with micrometer instrument with the optical axis of system, according to light path design figure each element to be assembled is adjusted the location.This mode need be installed the reflective marker mirror on element under test, and all sign mirrors are all wanted and can be seen by theodolite, so complicated operation, very flexible, workload is big, and the assembling result is subjected to operating personnel's the experimental technology level and the influence of state easily, and this has influenced the efficient of assembling and the uniformity of assembly quality to a great extent.
Summary of the invention
The objective of the invention is on the material object of space remote sensing instrument, to set up rectangular coordinate system in space, and measure the coordinate figure of monitoring point on the element to be assembled, and real-world coordinate system overlapped with the frame of reference of cad model, thereby obtain the misalignment rate information of each element to be assembled according to the difference of the position of both monitoring points, by the misalignment rate of obtaining, element adjustment to be assembled is seated at last with the six degree of freedom adjusting bracket.
Particularly, on the space remote sensing instrument, set up the method for rectangular coordinate system in space, be with three-coordinates measuring machine as the main frame of reference for assembling or be fixed on some speculums on the main frame and set up fixed with it rectangular coordinate system, and the direction of its initial point and reference axis is all consistent with frame of reference initial point and change in coordinate axis direction in the cad model.
Particularly, measuring the method for the coordinate figure of element to be assembled monitoring point, is according to being the monitoring point of element to be assembled definition on the cad model in advance, finds this position and measure the coordinate figure of this point on the material object of element to be assembled with three-coordinates measuring machine.
Particularly, the said method of obtaining misalignment rate, be meant after the remote sensing instrument material object is set up coordinate system and measured the monitoring point coordinate figure, the frame of reference of material object is overlapped with the frame of reference of cad model, the coordinate figure of element to be assembled monitoring point relatively more in kind and its projection of the coordinate figure in cad model on each reference axis is poor then, can obtain the misalignment rate of element to be assembled on each free degree.
Operating procedure of the present invention is as follows:
1, in the cad model of space remote sensing instrument, is monitoring position point of each element definition to be assembled, and obtains its coordinate figure in the frame of reference of cad model.
2, with the position of three-coordinates measuring machine, on its material object, set up a same rectangular coordinate system in space according to the frame of reference and the origin of coordinates of the cad model of space remote sensing instrument.
3, on the material object of element to be assembled, find monitoring point default in the step 1, and measure this coordinate figure in real-world coordinate system.
4, the frame of reference with real-world coordinate system and cad model overlaps, the monitoring point of obtaining each element to be assembled in the difference of the coordinate figure of the real-world coordinate system and the frame of reference as misalignment rate, and misalignment rate is input to the six degree of freedom adjusting bracket, element to be assembled is adjusted to the right place.
5, repeating step 3 and 4 satisfies the assembly precision requirement until the position of element to be assembled.
Advantage of the present invention is:
1, because assembling process is used as the assembling standard with rectangular coordinate system in space on the material object and cad model contrast, makes the assembling process of space remote sensing instrument realize quantification and objectify, guaranteed the stability of assembly quality and the uniformity of assembly period.
2, because the quantification of assembling process and objectifying, it is minimum to make that the assembling process of space remote sensing instrument is reduced to by the influence of operating personnel's experience and state, makes this method have very strong versatility.
Description of drawings
Fig. 1 is the operating procedure flow chart of the inventive method.
The specific embodiment
Case history: the digitlization assembling of certain type infrared remote sensing camera.
Reference for assembling: be fixed in the secondary mirror on the main frame
Assembling and positioning precision: be not less than 0.1mm
Three-coordinates measuring machine model: Leica LTD706, certainty of measurement 0.02-0.05mm
Six degree of freedom adjusting bracket model: PI M824, positioning accuracy 0.5um
On the secondary mirror of scanning camera, set up real-world coordinate system with Leica LTD706 measuring instrument, measure the coordinate figure of monitoring point on principal reflection mirror and three speculums respectively, again the frame of reference on the secondary mirror in real-world coordinate system and the cad model is overlapped, can get the misalignment rate of principal reflection mirror and three speculum monitoring points, see Table 1:
Table 1
The misalignment rate of obtaining is input in the PI M824 six degree of freedom adjusting bracket, element to be assembled is adjusted to the right place, and then with laser tracker the second time is carried out in the monitoring point on principal reflection mirror and three speculums and measure.Because previous step has been carried out the reference coordinate coupling, therefore in measuring for the second time, can save, the results are shown in Table 2:
Table 2
As seen after taking turns adjustment through one, the position monitoring point misalignment rate of principal reflection mirror to be assembled and three speculums has reached the required precision of assembling and positioning all less than 0.1mm.Therefore assembly work is finished.If fail to reach required required precision, then the misalignment rate of measuring for the second time can be re-entered in the six degree of freedom adjusting bracket, carry out again taking turns and regulate and measure, misalignment rate is constantly restrained finally reach the required precision of assembling.
Claims (1)
1. the digitlization assembly method of a space remote sensing instrument is characterized in that may further comprise the steps:
1) in the cad model of space remote sensing instrument, is monitoring position point of each element definition to be assembled, and obtains its coordinate figure in the frame of reference of cad model;
2) with the position of three-coordinates measuring machine, on its material object, set up a same rectangular coordinate system in space according to the frame of reference and the origin of coordinates of the cad model of space remote sensing instrument;
3) on the material object of element to be assembled, find monitoring point default in the step 1, and measure this coordinate figure in real-world coordinate system;
4) frame of reference with real-world coordinate system and cad model overlaps, the monitoring point of obtaining each element to be assembled in the difference of the coordinate figure of the real-world coordinate system and the frame of reference as misalignment rate, and misalignment rate is input to the six degree of freedom adjusting bracket, element to be assembled is adjusted to the right place;
5) repeating step 3 and 4 satisfies the assembly precision requirement until the position of element to be assembled.
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| CN2011101174327A CN102284859A (en) | 2011-05-06 | 2011-05-06 | Digital assembly method of space remote sensing instrument |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034315A (en) * | 2014-06-30 | 2014-09-10 | 中国科学院长春光学精密机械与物理研究所 | Assembling method of truss structure of ultra-long focal length remote sensing camera |
| CN106600685A (en) * | 2016-12-06 | 2017-04-26 | 中国航空工业集团公司洛阳电光设备研究所 | Optical element space measurement and assembly method in optical assembly |
| CN110057332A (en) * | 2019-05-05 | 2019-07-26 | 大连理工大学 | A kind of test structure assembly precision regulation method based on basis of sensitivity analysis |
| CN110539162A (en) * | 2019-09-06 | 2019-12-06 | 首都航天机械有限公司 | digital sampling manufacturing method for conduit based on actual assembly space on arrow |
| CN110968914A (en) * | 2019-11-28 | 2020-04-07 | 江南造船(集团)有限责任公司 | Ship outfitting composite board assembling method, system, terminal and medium |
| CN112066923A (en) * | 2020-08-14 | 2020-12-11 | 苏州环球科技股份有限公司 | Virtual measurement method for position degree |
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| CN110968914A (en) * | 2019-11-28 | 2020-04-07 | 江南造船(集团)有限责任公司 | Ship outfitting composite board assembling method, system, terminal and medium |
| CN110968914B (en) * | 2019-11-28 | 2023-11-07 | 江南造船(集团)有限责任公司 | Ship outfitting compound plate assembly method, system, terminal and medium |
| CN112066923A (en) * | 2020-08-14 | 2020-12-11 | 苏州环球科技股份有限公司 | Virtual measurement method for position degree |
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Application publication date: 20111221 |