CN103902781A - Method for eliminating positioning errors of flexible clamp of five-coordinate numerical-control machine tool - Google Patents
Method for eliminating positioning errors of flexible clamp of five-coordinate numerical-control machine tool Download PDFInfo
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- CN103902781A CN103902781A CN201410142885.9A CN201410142885A CN103902781A CN 103902781 A CN103902781 A CN 103902781A CN 201410142885 A CN201410142885 A CN 201410142885A CN 103902781 A CN103902781 A CN 103902781A
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- skin part
- aircraft skin
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- pilot hole
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Abstract
The invention belongs to the numerical-control process technology and relates to an improved method for eliminating positioning errors of a flexible clamp of a five-coordinate numerical-control machine tool. The method is characterized by including steps of inputting a mathematic model of an airplane skin part (5); establishing a physical simulation profile of the airplane skin part (5); measuring practical coordinates of a circular positioner (3) and a triangular positioner (4); eliminating positioning errors of the circular positioner (3) and the triangular positioner (4). By the method for eliminating positioning errors of the flexible clamp of the five-coordinate numerical-control machine tool, present adjustment steps are simplified, processing period is shortened, processing accuracy and processing efficiency are improved, and processing cost is reduced.
Description
Technical field
The invention belongs to CNC processing technology, relate to the improvement to eliminating five-coordinate numerally controlled machine tool flexible fixture positioning error method.
Prior art
Application is with the outline of the five-coordinate numerally controlled machine tool cutting aircraft skin part of flexible fixture, and on aircraft skin part, respectively there is a pilot hole at two ends along its length.Fig. 1 is the structural representation of a kind of skin part of aircraft.With the line of cut of aircraft skin part as check benchmark.Build a simulation profile similar to profile on aircraft skin part as fixture with flexible fixture, on flexible fixture, there are circular steady arm and triangle steady arm, use on the aircraft skin part of circular steady arm location the pilot hole of left end along its length, use on the aircraft skin part of triangle steady arm location the pilot hole of right-hand member along its length; Or contrary, use on the aircraft skin part of circular steady arm location the pilot hole of right-hand member along its length, use on the aircraft skin part of triangle steady arm location the pilot hole of left end along its length.According to the mathematical model machining programming of aircraft skin part, cut away unnecessary material along the line of cut of aircraft skin part.Its shortcoming is: the cutting accuracy of the outline of aircraft skin part is subject to the impact of flexible fixture positioning precision.Because the steady arm calibrated error of the circular steady arm of flexible fixture and triangle steady arm is respectively: X is to 0.4mm, Y-direction 0.2mm, Z-direction 0.2mm, above-mentioned positioning error can cause part displacement and torsion, must eliminate above-mentioned positioning error, guarantee machining precision.Current method is: adopts trial cut method to eliminate flexible fixture positioning error, is with exactly surplus trial cut aircraft skin part, and in the situation that ignoring other errors, if surplus is evenly, circular steady arm and triangle steady arm correct position; Otherwise, adjust the position of circular steady arm and triangle steady arm according to surplus bias conditions.Due to aircraft skin External Shape complexity, can not once adjust to the right place, be also difficult to reach perfect condition even if repeatedly adjust trial cut, and while taking large number quipments machine, working (machining) efficiency is low, cost is high.
Summary of the invention
The object of the invention is: propose a kind of method of improved elimination five-coordinate numerally controlled machine tool flexible fixture positioning error, to simplify current set-up procedure, shorten process-cycle and machining precision, improve working (machining) efficiency, cut down finished cost.
Technical scheme of the present invention is: the method for eliminating five-coordinate numerally controlled machine tool flexible fixture positioning error, the initial point O of five-coordinate numerally controlled machine tool three-dimensional system of coordinate is positioned at the left-front corner of flexible fixture, X-axis is parallel with the length direction of flexible fixture, right-hand is the positive dirction of X-axis, Y-axis is parallel with the Width of flexible fixture, rear is the positive dirction of Y-axis, and Z axis is perpendicular to the plane at X-axis and Y-axis place, the positive dirction that top is Z axis; It is characterized in that, the step of eliminating flexible fixture positioning error is:
1, input the mathematical model of processed aircraft skin part 5, in the mathematical model of this aircraft skin part 5 with two pilot holes 6, two pilot holes 6 lay respectively at the two ends of aircraft skin part 5 length directions, the theoretical coordinate that is positioned at aircraft skin part 5 left end pilot hole 6 lower port central point A is A1 (x1, y1, z1); The theoretical coordinate that is positioned at the lower port central point B of aircraft skin part 5 right-hand member pilot holes 6 is B2 (x2, y2, z2); In the mathematical model of aircraft skin part 5, with the profile of moulding, the mathematical model of aircraft skin part 5 is inputted in computing machine;
2, build the physical simulation profile of aircraft skin part 5: according to the mathematical model of aircraft skin part, utilize the dot matrix of reference column 1 upper extreme point in flexible fixture to form the digital simulation profile of an aircraft skin part 5; In above-mentioned dot matrix, in the position that is positioned at aircraft skin part 5 left end pilot holes 6, circular steady arm 3 is set, the pilot hole center of circular steady arm 3 upper ends overlaps with the lower port central point A of the pilot hole 6 that is positioned at aircraft skin part 5 left ends; In the position that is positioned at aircraft skin part 5 right-hand member pilot holes 6, triangle steady arm 4 is set, the center of the pilot hole of triangle steady arm 4 upper ends overlaps with the lower port central point B of the pilot hole 6 that is positioned at aircraft skin part 5 right-hand members; By in the computing machine of the digital simulation profile input five-coordinate numerally controlled machine tool of above-mentioned aircraft skin part 5, the reference column 1 of controlling in flexible fixture moves, and makes flexible fixture form the physical simulation profile of aircraft skin part 5;
3, measure the actual coordinate of circular steady arm 3 and triangle steady arm 4: use the gauge head 2 of five-coordinate numerally controlled machine tool to detect respectively the actual coordinate A3 (x3 of circular steady arm 3 upper end pilot hole central point A, y3, and the central point B actual coordinate B4 (x4 of triangle steady arm 4 upper end pilot holes z3), y4, z4);
4, eliminate the positioning error of circular steady arm 3 and triangle steady arm 4: with the actual coordinate A3 (x3 of the central point A of the pilot hole of circular steady arm 3 upper ends, y3, z3) replace theoretical coordinate A1 (x1, y1, z1), with the actual coordinate B4 (x4 of the central point B of the pilot hole of triangle steady arm 4 upper ends, y4, z4) replace theoretical coordinate B2 (x2, y2, z2), then machining programming, the size of the aircraft skin part 5 processing according to this job sequence, has eliminated the positioning error of five-coordinate numerally controlled machine tool flexible fixture.
Advantage of the present invention is: proposed a kind of method of improved elimination five-coordinate numerally controlled machine tool flexible fixture positioning error, simplified current set-up procedure, shortened process-cycle and machining precision, improved working (machining) efficiency, reduced processing cost.
Accompanying drawing explanation
Fig. 1 is the CNC Model schematic diagram of a kind of skin part of aircraft.
Fig. 2 utilizes the dot matrix of reference column 1 upper extreme point in flexible fixture to form the schematic diagram of the digital simulation profile of an aircraft skin part 5.
Embodiment
Below the present invention is described in further details.Referring to Fig. 1,2, eliminate the method for five-coordinate numerally controlled machine tool flexible fixture positioning error, the initial point O of five-coordinate numerally controlled machine tool three-dimensional system of coordinate is positioned at the left-front corner of flexible fixture, X-axis is parallel with the length direction of flexible fixture, right-hand is the positive dirction of X-axis, and Y-axis is parallel with the Width of flexible fixture, the positive dirction that rear is Y-axis, Z axis is perpendicular to the plane at X-axis and Y-axis place, the positive dirction that top is Z axis; It is characterized in that, the step of eliminating flexible fixture positioning error is:
1, input the mathematical model of processed aircraft skin part 5, in the mathematical model of this aircraft skin part 5 with two pilot holes 6, two pilot holes 6 lay respectively at the two ends of aircraft skin part 5 length directions, the theoretical coordinate that is positioned at aircraft skin part 5 left end pilot hole 6 lower port central point A is A1 (x1, y1, z1); The theoretical coordinate that is positioned at the lower port central point B of aircraft skin part 5 right-hand member pilot holes 6 is B2 (x2, y2, z2); In the mathematical model of aircraft skin part 5, with the profile of moulding, the mathematical model of aircraft skin part 5 is inputted in computing machine;
2, build the physical simulation profile of aircraft skin part 5: according to the mathematical model of aircraft skin part, utilize the dot matrix of reference column 1 upper extreme point in flexible fixture to form the digital simulation profile of an aircraft skin part 5; In above-mentioned dot matrix, in the position that is positioned at aircraft skin part 5 left end pilot holes 6, circular steady arm 3 is set, the pilot hole center of circular steady arm 3 upper ends overlaps with the lower port central point A of the pilot hole 6 that is positioned at aircraft skin part 5 left ends; In the position that is positioned at aircraft skin part 5 right-hand member pilot holes 6, triangle steady arm 4 is set, the center of the pilot hole of triangle steady arm 4 upper ends overlaps with the lower port central point B of the pilot hole 6 that is positioned at aircraft skin part 5 right-hand members; By in the computing machine of the digital simulation profile input five-coordinate numerally controlled machine tool of above-mentioned aircraft skin part 5, the reference column 1 of controlling in flexible fixture moves, and makes flexible fixture form the physical simulation profile of aircraft skin part 5;
3, measure the actual coordinate of circular steady arm 3 and triangle steady arm 4: use the gauge head 2 of five-coordinate numerally controlled machine tool to detect respectively the actual coordinate A3 (x3 of circular steady arm 3 upper end pilot hole central point A, y3, and the central point B actual coordinate B4 (x4 of triangle steady arm 4 upper end pilot holes z3), y4, z4);
4, eliminate the positioning error of circular steady arm 3 and triangle steady arm 4: with the actual coordinate A3 (x3 of the central point A of the pilot hole of circular steady arm 3 upper ends, y3, z3) replace theoretical coordinate A1 (x1, y1, z1), with the actual coordinate B4 (x4 of the central point B of the pilot hole of triangle steady arm 4 upper ends, y4, z4) replace theoretical coordinate B2 (x2, y2, z2), then machining programming, the size of the aircraft skin part 5 processing according to this job sequence, has eliminated the positioning error of five-coordinate numerally controlled machine tool flexible fixture.
Embodiment
1, eliminate the method for five-coordinate numerally controlled machine tool flexible fixture positioning error, the initial point O of five-coordinate numerally controlled machine tool three-dimensional system of coordinate is positioned at the left-front corner of flexible fixture, X-axis is parallel with the length direction of flexible fixture, right-hand is the positive dirction of X-axis, Y-axis is parallel with the Width of flexible fixture, rear is the positive dirction of Y-axis, and Z axis is perpendicular to the plane at X-axis and Y-axis place, the positive dirction that top is Z axis; It is characterized in that, the step of eliminating flexible fixture positioning error is:
1.1, input the mathematical model of processed aircraft skin part (5): in the mathematical model of this aircraft skin part (5) with two pilot holes (6), two pilot holes (6) lay respectively at the two ends of aircraft skin part (5) length direction, the theoretical coordinate that is positioned at aircraft skin part (5) left end pilot hole (6) lower port central point A is A1 (22.527,11106.271,711.840); The theoretical coordinate that is positioned at the lower port central point B of aircraft skin part (5) right-hand member pilot hole (6) is B2 (2168.224,1106.271,400.000); In the mathematical model of aircraft skin part (5), with the profile of the profile of moulding, circular steady arm (3) and the profile of triangle steady arm (4), the mathematical model of aircraft skin part (5) is inputted in computing machine;
1.2, build the physical simulation profile of aircraft skin part (5): according to the mathematical model of aircraft skin part, utilize the dot matrix of reference column (1) upper extreme point in flexible fixture to form the digital simulation profile of an aircraft skin part (5); In above-mentioned dot matrix, in the position that is positioned at aircraft skin part (5) left end pilot hole (6), circular steady arm (3) is set, the pilot hole center of circular steady arm (3) upper end overlaps with the lower port central point A of the pilot hole (6) that is positioned at aircraft skin part (5) left end; In the position that is positioned at aircraft skin part (5) right-hand member pilot hole (6), triangle steady arm (4) is set, the center of the pilot hole of triangle steady arm (4) upper end overlaps with the lower port central point B of the pilot hole (6) that is positioned at aircraft skin part (5) right-hand member; By in the computing machine of the digital simulation profile input five-coordinate numerally controlled machine tool of above-mentioned aircraft skin part (5), control reference column (1) motion in flexible fixture, make flexible fixture form the physical simulation profile of aircraft skin part (5);
1.3, measure the actual coordinate of circular steady arm (3) and triangle steady arm (4): use the gauge head (2) of five-coordinate numerally controlled machine tool to detect respectively the actual coordinate A3 (22.325 of circular steady arm (3) upper end pilot hole central point A, 1106.271,710.728) and the central point B actual coordinate B4 (2169.157 of triangle steady arm (4) upper end pilot hole, 1106.067,398.486);
1.4, eliminate the positioning error of circular steady arm (3) and triangle steady arm (4): with the actual coordinate A3 (22.325 of the central point A of the pilot hole of circular steady arm (3) upper end, 1106.271, 710.728) replace theoretical coordinate A1 (22.527, 11106.271, 711.840), with the actual coordinate B4 (2169.157 of the central point B of the pilot hole of triangle steady arm (4) upper end, 1106.067, 398.486) replace theoretical coordinate B2 (2168.224, 1106.271, 400.000), then machining programming, the size of the aircraft skin part (5) processing according to this job sequence, eliminate the positioning error of five-coordinate numerally controlled machine tool flexible fixture.
Claims (1)
1. eliminate the method for five-coordinate numerally controlled machine tool flexible fixture positioning error, the initial point O of five-coordinate numerally controlled machine tool three-dimensional system of coordinate is positioned at the left-front corner of flexible fixture, X-axis is parallel with the length direction of flexible fixture, right-hand is the positive dirction of X-axis, Y-axis is parallel with the Width of flexible fixture, rear is the positive dirction of Y-axis, and Z axis is perpendicular to the plane at X-axis and Y-axis place, the positive dirction that top is Z axis; It is characterized in that, the step of eliminating flexible fixture positioning error is:
1.1, input the mathematical model of processed aircraft skin part (5): in the mathematical model of this aircraft skin part (5) with two pilot holes (6), two pilot holes (6) lay respectively at the two ends of aircraft skin part (5) length direction, the theoretical coordinate that is positioned at aircraft skin part (5) left end pilot hole (6) lower port central point A is A1 (x1, y1, z1); The theoretical coordinate that is positioned at the lower port central point B of aircraft skin part (5) right-hand member pilot hole (6) is B2 (x2, y2, z2); In the mathematical model of aircraft skin part (5), with the profile of moulding, the mathematical model of aircraft skin part (5) is inputted in the computing machine of five-coordinate numerally controlled machine tool;
1.2, build the physical simulation profile of aircraft skin part (5): according to the mathematical model of aircraft skin part, utilize the dot matrix of reference column (1) upper extreme point in flexible fixture to form the digital simulation profile of an aircraft skin part (5); In above-mentioned dot matrix, in the position that is positioned at aircraft skin part (5) left end pilot hole (6), circular steady arm (3) is set, the pilot hole center of circular steady arm (3) upper end overlaps with the lower port central point A of the pilot hole (6) that is positioned at aircraft skin part (5) left end; In the position that is positioned at aircraft skin part (5) right-hand member pilot hole (6), triangle steady arm (4) is set, the center of the pilot hole of triangle steady arm (4) upper end overlaps with the lower port central point B of the pilot hole (6) that is positioned at aircraft skin part (5) right-hand member; By in the computing machine of the digital simulation profile input five-coordinate numerally controlled machine tool of above-mentioned aircraft skin part (5), control reference column (1) motion in flexible fixture, make flexible fixture form the physical simulation profile of aircraft skin part (5);
1.3, measure the actual coordinate of circular steady arm (3) and triangle steady arm (4): use the gauge head (2) of five-coordinate numerally controlled machine tool to detect respectively the actual coordinate A3 (x3 of circular steady arm (3) upper end pilot hole central point A, y3, and the central point B actual coordinate B4 (x4 of triangle steady arm (4) upper end pilot hole z3), y4, z4);
1.4, eliminate the positioning error of circular steady arm (3) and triangle steady arm (4): with the actual coordinate A3 (x3 of the central point A of the pilot hole of circular steady arm (3) upper end, y3, z3) replace theoretical coordinate A1 (x1, y1, z1), with the actual coordinate B4 (x4 of the central point B of the pilot hole of triangle steady arm (4) upper end, y4, z4) replace theoretical coordinate B2 (x2, y2, z2), then machining programming, the size of the aircraft skin part (5) processing according to this job sequence, eliminate the positioning error of five-coordinate numerally controlled machine tool flexible fixture.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410142885.9A CN103902781A (en) | 2014-04-10 | 2014-04-10 | Method for eliminating positioning errors of flexible clamp of five-coordinate numerical-control machine tool |
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| CN201410142885.9A CN103902781A (en) | 2014-04-10 | 2014-04-10 | Method for eliminating positioning errors of flexible clamp of five-coordinate numerical-control machine tool |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105825023A (en) * | 2016-03-25 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Correction method for cured honeycomb-structured composite part |
| CN107421476A (en) * | 2017-05-11 | 2017-12-01 | 成都飞机工业（集团）有限责任公司 | A kind of spatial hole position Measuring datum error compensation method |
| CN108746788A (en) * | 2018-05-29 | 2018-11-06 | 沈阳飞机工业（集团）有限公司 | A kind of trial cut and milling integration covering five-axis robot method |
| CN110217405A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of aircraft delivery device installation method |
| CN112525108A (en) * | 2020-12-12 | 2021-03-19 | 江西洪都航空工业集团有限责任公司 | Method for detecting contour error of sheet part on line by adopting laser tracker |
| CN112613130A (en) * | 2021-03-05 | 2021-04-06 | 成都飞机工业（集团）有限责任公司 | Dimensional positioning pose simulation matching method based on two three-coordinate positioners |
| CN115338691A (en) * | 2022-06-17 | 2022-11-15 | 中航西安飞机工业集团股份有限公司 | Method for measuring error of feeding shaft of numerical control machine tool |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105825023A (en) * | 2016-03-25 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Correction method for cured honeycomb-structured composite part |
| CN107421476A (en) * | 2017-05-11 | 2017-12-01 | 成都飞机工业（集团）有限责任公司 | A kind of spatial hole position Measuring datum error compensation method |
| CN108746788A (en) * | 2018-05-29 | 2018-11-06 | 沈阳飞机工业（集团）有限公司 | A kind of trial cut and milling integration covering five-axis robot method |
| CN110217405A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of aircraft delivery device installation method |
| CN112525108A (en) * | 2020-12-12 | 2021-03-19 | 江西洪都航空工业集团有限责任公司 | Method for detecting contour error of sheet part on line by adopting laser tracker |
| CN112613130A (en) * | 2021-03-05 | 2021-04-06 | 成都飞机工业（集团）有限责任公司 | Dimensional positioning pose simulation matching method based on two three-coordinate positioners |
| CN115338691A (en) * | 2022-06-17 | 2022-11-15 | 中航西安飞机工业集团股份有限公司 | Method for measuring error of feeding shaft of numerical control machine tool |
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