CN102794600A - Screw non-reference mounting method - Google Patents
Screw non-reference mounting method Download PDFInfo
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- CN102794600A CN102794600A CN2012102328187A CN201210232818A CN102794600A CN 102794600 A CN102794600 A CN 102794600A CN 2012102328187 A CN2012102328187 A CN 2012102328187A CN 201210232818 A CN201210232818 A CN 201210232818A CN 102794600 A CN102794600 A CN 102794600A
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- leading screw
- mounting blocks
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Abstract
The invention provides a screw non-reference mounting method which can be used for measuring and mounting by using a laser tracker. The screw non-reference mounting method comprises the following steps of: at first, determining a reference line parallel to the principle axis of a screw, so as to establish a virtual coordinate system by using the reference line; fixing a plurality of standard mounting blocks on the screw, and measuring a measuring point on each mounting block; calculating a center axis position of the screw through measurement data; and carrying out parallelism comparison on the principle axis of the screw, and then mounting when parallelism reaches to a requirement value. By utilizing the screw non-reference mounting method provided by the invention, the position of a center axis of the existing non-reference screw is converted into a standard mounting block, and the measurement mounting is carried out based on the laser tracker, so that the mounting precision of the screw is ensured, and the used standard mounting block has the advantages of simple structure and convenience in dismounting.
Description
Technical field
The present invention relates to the aircraft manufacturing technical field, particularly the installation and the debugging technique of no benchmark leading screw in the technological equipment development.
Background technology
In the aircraft assembling process, exist the technological equipment of a lot of band guide screw movement mechanism, aircraft technological equipment leading screw is installed to be divided into has benchmark and two kinds of installation methods of no benchmark.Wherein raise the dress leading screw and at first process benchmark, leading screw tentatively is installed on the benchmark, constantly rotate back and forth the depth of parallelism that leading screw and the mode of the submeter of saluting by going down on one knee are adjusted leading screw then in most of frock.But; Because the present generation aircraft technological equipment is truss Steel Structure mostly; The laser trackers that adopt are installed more; Be difficult to find or process corresponding reference for installation thereby cause these leading screws to be installed under many circumstances, the low cruise leading screw that does not much have a benchmark is installed and is generally adopted amesdial to combine with rotating threaded shaft to accomplish installation, in this case the depth of parallelism of the leading screw of installation generally ± more than the 0.08mm.
Certain large aircraft of developing at present, its size is much larger than the type in past.Thereby its technological equipment size is big, frock is many, needs to install a large amount of stock leading screws on its large-scale frock.By certain large aircraft technological equipment required precision, the stock leading screw needs its installation accuracy to satisfy between leading screw and the guide rail ± depth of parallelism of 0.03mm.The conventional mounting method can't satisfy under the situation of no benchmark.Particularly when the length of leading screw in some large-scale frock reaches more than 3 meters; The intermediate demand supporting construction is adjusted the support leading screw; Because supporting construction do not have benchmark yet, and the gravity of leading screw also can produce the influence of amount of deflection, and the depth of parallelism that satisfy leading screw is just more difficult.
To this situation, need find the installation method of a kind of leading screw under no base case, to satisfy the installation accuracy demand in the aircraft technological equipment assembling process.
Summary of the invention
Technical problem to be solved by this invention provides a kind of aircraft technological equipment installation accuracy requirement of satisfying, and measures the no benchmark leading screw installation method of installation based on laser tracker.
The invention provides a kind of no benchmark leading screw installation method for solving the problems of the technologies described above, based on adopting laser tracker to measure installation, it is characterized in that: at first confirm a datum line parallel with the theoretical axis of leading screw; Set up virtual coordinate system with this datum line; Fixing a plurality of standard mounting blocks on leading screw, each mounting blocks is provided with measurement point, the central shaft equidistance of this measurement point and leading screw; Utilize laser tracker that the measurement point on each mounting blocks is measured; Through the central axis position that measurement data is calculated leading screw, carry out depth of parallelism contrast with the theoretical axis of leading screw again,, the depth of parallelism installs after reaching required value.
Described standard mounting blocks is combined through connector with following mounting blocks by the last mounting blocks of correspondence; Center at last mounting blocks and following mounting blocks is provided with corresponding V-type notch; On the body of last mounting blocks and following mounting blocks, be provided with measurement point, the center equidistance of measurement point and V-type notch.
The invention has the advantages that will not having the leading screw central shaft of benchmark position originally has been transformed on the standard mounting blocks, measures installation based on laser tracker again.Laser tracker is a high-acruracy survey equipment, thereby measures the installation accuracy that the installation code locating piece has guaranteed leading screw with it.The standard mounting blocks is simple in structure, directly combine through connector, easy accessibility, measure to install and later check measurement all very convenient, and be easy to preserve, structure is light, not excessive increase leading screw weight causes distortion.
Below in conjunction with the specific embodiment accompanying drawing this application is described in further detail.
Description of drawings
Fig. 1 sets up datum line and virtual coordinate system schematic diagram;
Fig. 2 standard mounting blocks structural representation;
Fig. 3 leading screw is installed detail drawing.
Label declaration among the figure: mounting blocks on 1 leading screw, 2 left bracing frames, 3 sliding beams, 4 rail plates, 5 slip measurement points, 6 beam measurement points, 7 leading screw mount pads, 8 primary importances, 9 second places, 10 standard mounting blocks, the 11 mounting blocks measurement points, 12,13 times mounting blocks, 14V type notch, 15 connectors, 16 inclined-planes, 17 leading screw central axis
The specific embodiment
It is example that this specific embodiment is hung general assembly type frame with certain aircraft inboard, referring to accompanying drawing 1, on the type frame left and right sidesing supporting frame rail plate 4 is installed, and sliding beam 3 is placed on the rail plate 4.Existing as shown in Figure 1 1.1 meters long leading screws 1 will be installed on left bracing frame 2 one sides, in use motor will drive leading screw 1 and move, and sliding beam 3 is moved along rail plate 4.Therefore, according to design and operational requirement, leading screw 1 must be parallel with rail plate 4, could guarantee that leading screw 1 drives sliding beam 3 and steadily moves along rail plate 4.This kind of frame peripheral does not all have base point of installation, guarantee that leading screw 1 is parallel with rail plate 4, and a slip measurement point 5 can be set on sliding beam 3.When sliding beam 3 when rail plate 4 moves, the movement locus of slip measurement point 5 diverse location in front and back, the shape row a virtual axis that is parallel to rail plate 4, this axis promptly is the datum line parallel with the theoretical axis of leading screw.Choose a beam measurement point 6 away from axis more arbitrarily, datum line and this beam measurement point 6 can be set up out the required virtual coordinate system of installation leading screw 1.In the actual installation process, slip measurement point 5 and beam measurement point 6 can be set on sliding beam 3 at first; Then,, manually shift primary importance 8 and fixing onto, measure the value of slip measurement point 5 and 6 two of beam measurement points along rail plate 4 with the sliding beam that places 3; Then, shift sliding beam 3 onto the second place 9 and fixing along rail plate 4, measure the value of slip measurement point 5 at the second place 9 places.Slip measurement point 5 has promptly formed datum line at the line at two diverse location places.Can set up the virtual coordinate system that leading screw is installed with datum line and beam measurement point 6.This datum line is a certain reference axis (for example, can be made as the X axle) of virtual coordinate system.Gathering slip measurement point 5 after the value of the value of diverse location and beam measurement point 6, the formation of datum line and the foundation of virtual coordinate system Survey Software function all capable of using generates automatically.
When carrying out leading screw 1 installation, because of the leading screw central axis also is a virtual axis, can't directly measure, so on leading screw 1, fix a plurality of standard mounting blocks 10, each standard mounting blocks is provided with measurement point 11.Referring to shown in Figure 2; Standard mounting blocks 10 is combined through connector 15 (comprising handle nut and burnished bolt) with following mounting blocks 13 by the last mounting blocks 12 of correspondence; The center of last mounting blocks 12 and following mounting blocks 13 processes the V-type notch 14 at corresponding leading screw 1 center; On the body of last mounting blocks 12 and following mounting blocks 13, be provided with measurement point 11, the center equidistance of measurement point 11 and V-type notch 14, two inclined-planes 7 of V-type notch 4 also are processed into and measurement point 11 complete symmetries.Therefore, when standard mounting blocks 10 is installed in 1 last time of leading screw, the central point of V-type notch 14 has just dropped on the central axis of leading screw 1.A plurality of standard mounting blocks 10 are installed in 1 last time of leading screw, and the central point line of V-type notch 14 has just formed the central axis of leading screw 1 or the parallel lines of central axis.
When leading screw is installed, leading screw 1 and leading screw Connection Block 7 just are positioned on left bracing frame 2 sidewalls.As shown in Figure 3 then, three standard mounting blocks 10 are installed in the preceding posterior segment of leading screw 1 respectively.Setting up under the good virtual coordinate system coordinate figure of measuring two measurement points 11 at diagonal angle on each standard mounting blocks 10 with laser tracker; 2 line mid points are the point on the leading screw central axis 17; Utilize this two point coordinates value to calculate leading screw central axis 17 positions; With the datum line of having set up (being the X axle of virtual coordinate system) the comparison depth of parallelism, when the depth of parallelism reach ± 0.1mm after more repeatedly after the debugging for several times, finely tune; Constantly carry out the measurement of measurement point 11 and the adjustment of leading screw mount pad 7, till the depth of parallelism of leading screw satisfies installation requirement.After adjusting to the right place, leading screw mount pad 7 usefulness connectors are fixed on the left bracing frame 2, accomplish the installation of leading screw 1.
Claims (2)
1. a no benchmark leading screw installation method based on adopting laser tracker to measure installation, is characterized in that: at first confirm a datum line parallel with the theoretical axis of leading screw; Set up virtual coordinate system with this datum line; Fixing a plurality of standard mounting blocks on leading screw, each mounting blocks is provided with measurement point, the central shaft equidistance of this measurement point and leading screw; Utilize laser tracker that the measurement point on each mounting blocks is measured; Through the central axis position that measurement data is calculated leading screw, carry out depth of parallelism contrast with the theoretical axis of leading screw again,, the depth of parallelism installs after reaching required value.
2. no benchmark leading screw installation method as claimed in claim 1; It is characterized in that described standard mounting blocks is combined through connector with following mounting blocks by the last mounting blocks of correspondence; Center at last mounting blocks and following mounting blocks is provided with corresponding V-type notch; On the body of last mounting blocks and following mounting blocks, be provided with measurement point, the center equidistance of measurement point and V-type notch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102328187A CN102794600A (en) | 2012-07-06 | 2012-07-06 | Screw non-reference mounting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102328187A CN102794600A (en) | 2012-07-06 | 2012-07-06 | Screw non-reference mounting method |
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| CN102794600A true CN102794600A (en) | 2012-11-28 |
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| CN2012102328187A Pending CN102794600A (en) | 2012-07-06 | 2012-07-06 | Screw non-reference mounting method |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101776440A (en) * | 2010-02-03 | 2010-07-14 | 北京航空航天大学 | Method for assembling and locating web-type wing ribs on basis of laser measurement |
| US20110088271A1 (en) * | 2009-10-20 | 2011-04-21 | Faro Technologies, Inc. | Mounted scale bar |
| CN102059670A (en) * | 2010-11-26 | 2011-05-18 | 北京工业大学 | Rod-like fatigue test piece scale distance positioning device |
| CN102221350A (en) * | 2011-04-06 | 2011-10-19 | 西安交通大学 | Measuring mechanism based on coupled-column structural axial lead of laser tracker |
-
2012
- 2012-07-06 CN CN2012102328187A patent/CN102794600A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110088271A1 (en) * | 2009-10-20 | 2011-04-21 | Faro Technologies, Inc. | Mounted scale bar |
| CN101776440A (en) * | 2010-02-03 | 2010-07-14 | 北京航空航天大学 | Method for assembling and locating web-type wing ribs on basis of laser measurement |
| CN102059670A (en) * | 2010-11-26 | 2011-05-18 | 北京工业大学 | Rod-like fatigue test piece scale distance positioning device |
| CN102221350A (en) * | 2011-04-06 | 2011-10-19 | 西安交通大学 | Measuring mechanism based on coupled-column structural axial lead of laser tracker |
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Application publication date: 20121128 |