CN210108319U - High-precision measuring mechanism for adjusting and butting large parts of airplane - Google Patents
High-precision measuring mechanism for adjusting and butting large parts of airplane Download PDFInfo
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- CN210108319U CN210108319U CN201920856620.3U CN201920856620U CN210108319U CN 210108319 U CN210108319 U CN 210108319U CN 201920856620 U CN201920856620 U CN 201920856620U CN 210108319 U CN210108319 U CN 210108319U
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Abstract
The utility model provides a high accuracy measurement mechanism that is used for appearance butt joint is transferred to aircraft major possession, including flexible articulated arm measurement system, flexible articulated arm measurement system includes liftable base, liftable base has rotatable magnetic chuck through the leg joint, be provided with flexible articulated arm measuring machine on the magnetic chuck, flexible articulated arm measuring machine is connected with the gauge head through flexible articulated arm, utilizes the single two required installation accuracy of inserting the ear of assurance installation department that flexible articulated arm measurement system can be more accurate.
Description
Technical Field
The utility model relates to an appearance butt joint technical field is transferred to aircraft major part, concretely relates to high accuracy measurement mechanism and measuring method that is used for appearance butt joint is transferred to aircraft major part.
Background
When the traditional large-part wing is subjected to attitude adjustment and butt joint, a laser tracker is generally adopted to measure a fuselage and a wing measuring point, an attitude adjustment system is driven to adjust the spatial attitude of the wing according to obtained data, and butt joint is performed after the spatial attitude error meets the requirement of a closing tolerance. The accuracy of the posture-adjusting involution method is restricted by the measurement accuracy of the laser tracker. In fact, when the wings of many novel airplanes are subjected to posture adjustment and butt joint, the required installation precision of the single-double insertion lugs at the installation position is higher than the measurement precision of the laser tracker. The traditional method cannot achieve required precision and cannot be assembled correctly.
SUMMERY OF THE UTILITY MODEL
For solving above-mentioned problem, especially not enough to prior art existence, the utility model provides a high accuracy measurement mechanism and measuring method for big part of aircraft transfers appearance butt joint, the utility model discloses a method can not receive the restriction that the appearance adjusted the precision of closing the method stimulated light tracker measurement accuracy, utilizes the required installation accuracy of the single pair of ear of inserting of assurance installation department that flexible articulated arm measurement system can be more accurate. In order to achieve the above object, the utility model adopts the following technical means:
the utility model provides a high accuracy measurement mechanism for appearance butt joint is transferred to aircraft major possession, includes flexible articulated arm measurement system, flexible articulated arm measurement system includes liftable base, liftable base has rotatable magnetic chuck through the leg joint, be provided with flexible articulated arm measuring machine on the magnetic chuck, flexible articulated arm measuring machine is connected with the gauge head through flexible articulated arm.
Further, liftable base includes the bed plate, threaded connection has liftable landing leg on the bed plate, support one end is fixed with the bed plate, and the other end is connected with the bearing frame, rotatable magnetic chuck lower part is provided with the rotation axis that corresponds with the bearing frame, the regulation base height that can be better, and magnetic chuck can be better rotate, and then the operation of carrying out flexible articulated arm measuring machine that can be better.
Furthermore, the flexible joint arm comprises a first joint arm which is hinged with the flexible joint arm measuring machine and can rotate up and down relative to the flexible joint arm measuring machine, a second joint arm which can rotate up and down relative to the first joint arm is hinged on the first joint arm, a third joint arm which can rotate up and down relative to the second joint arm is hinged on the second joint arm, a measuring head connected with the flexible joint arm measuring machine is arranged on the third joint arm, and the measuring head can be better controlled to measure related data through multi-joint-degree movement.
The utility model has the advantages that: the utility model discloses simple structure, simple to operate, the utility model discloses a method can not receive the restriction of the precision laser tracker measurement accuracy of the alignment method, utilizes the required installation accuracy of the single double-insert ear that flexible articulated arm measurement system can be more accurate assurance installation department, adopts laser tracker to carry out preliminary measurement earlier to tentatively transfer the appearance, adopts flexible articulated arm measurement system to carry out the precision measurement again, and the appearance is transferred to the precision; in the traditional airplane digital attitude adjusting and docking process, due to the fact that the measurement accuracy of a laser tracker is not high, high-accuracy airplane component docking cannot be completed, through step-by-step measurement, the measurement accuracy in the attitude adjusting and docking process is gradually improved, the final attitude adjusting accuracy is gradually improved, and high-accuracy docking work can be completed. The measuring method combines the advantages of the laser tracker and the flexible joint arm, can finish high-precision and high-efficiency measuring work in the process of adjusting the posture and closing, and has strong operability, wide practicability and strong applicability.
Drawings
Fig. 1 is a schematic structural diagram of the flexible articulated arm measurement system of the present invention.
Fig. 2 is a schematic layout of the flexible articulated arm measurement system structure according to the present invention.
Fig. 3 is a flow chart of the using method of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described with reference to the accompanying drawings.
As shown in fig. 1 to 3, the present embodiment provides a high precision measurement mechanism for adjusting the orientation of a large part of an aircraft for docking, including a flexible articulated arm measurement system 1, the flexible articulated arm measurement system includes a liftable base 2, the liftable base is connected with a rotatable magnetic chuck 4 through a support 3, the magnetic chuck is provided with a flexible articulated arm measurement machine 5 thereon, and the flexible articulated arm measurement machine is connected with a measurement head 7 through a flexible articulated arm 6.
Wherein, liftable base 2 includes bed plate 201, threaded connection has liftable landing leg 202 on the bed plate, and 3 one end of support are fixed with the bed plate, and the other end is connected with bearing frame 301, 4 lower parts of rotatable magnetic chuck are provided with the rotation axis 401 that corresponds with the bearing frame, and the regulation base height that can be better, magnetic chuck can be better rotate, and then the operation of carrying out flexible articulated arm measuring machine that can be better.
The flexible joint arm 6 comprises a first joint arm 601 which is hinged with the flexible joint arm measuring machine and can rotate up and down relative to the flexible joint arm measuring machine, a second joint arm 602 which can rotate up and down relative to the first joint arm is hinged on the first joint arm, a third joint arm 603 which can rotate up and down relative to the second joint arm is hinged on the second joint arm, a measuring head 7 connected with the flexible joint arm measuring machine is arranged on the third joint arm, and the measuring head can be controlled better to measure related data through multi-joint-degree movement.
The embodiment also provides a high-precision measurement method using the device, which specifically comprises the following steps:
(1) measuring fuselage and wing measuring points by using a laser tracker, preliminarily adjusting the wing posture, and moving to a precise alignment distance;
(2) the flexible articulated arm measuring system is adopted to measure the single and double ear gaps, the wing postures are finely adjusted accurately, and the flexible articulated arm measuring system is adopted to check after the posture adjustment is finished, so that the single and double ear gaps are ensured;
(3) measuring the axis of the joint hole by adopting a flexible articulated arm measuring system, driving wings to be butted by an attitude adjusting system according to measured data, and checking the coaxiality by adopting the flexible articulated arm measuring system after the butting so as to ensure the coaxiality of the joint hole;
(4) and installing a fixing bolt to connect the fuselage and the wing.
The step (1) specifically comprises the following steps:
(a1) carrying the butt joint equipment by using an AGV (automatic guided vehicle), wherein the carrying butt joint equipment clamps the wings and automatically navigates to a butt joint position;
(b1) measuring ERS points on the whole platform by using a laser tracker, and establishing a global coordinate system;
(c1) measuring points on the laser tracker measuring machine body as target values;
(d1) measuring a measuring point on the wing by using a laser tracker as an actual measuring value;
(e1) the upper computer reads the measured data of the measuring points and performs virtual pre-docking in the process management software;
(f1) if not, manual intervention is carried out, and if not, the upper computer compares the measured value data with the target data and calculates the investment transfer parameters;
(g1) the upper computer sends attitude adjusting parameters to the wing attitude adjusting system;
(h1) the attitude adjusting system receives the attitude adjusting parameters and drives the positioner to adjust the attitude of the wing;
(i1) measuring a measuring point on the wing by using a laser tracker;
(j1) the upper computer reads the measured data and compares the measured data with the target data;
(k1) and (5) judging whether the tolerance requirement is met, if not, returning to the step (f), and if so, driving the wing to reach the precise alignment position by the attitude adjusting system.
The step (2) specifically comprises the following steps:
(a2) measuring a lower joint plane on the fuselage as a target value using a measurement articulated arm of the flexible articulated arm measurement system;
(b2) measuring a lower joint plane on the wing as an actual measurement value by using a measuring articulated arm of a flexible articulated arm measuring system;
(c2) the upper computer reads the actual measurement data;
(d2) the upper computer compares the measured data with the target data and calculates attitude adjusting parameters;
(e2) the attitude adjusting system receives the attitude adjusting parameters and drives the positioner to adjust the attitude of the wing;
(f2) measuring plane data of the wing joint by using the measuring articulated arm;
(g2) the upper computer reads the measured data and compares the measured data with the target data;
(h2) and (4) judging whether the tolerance is met, if not, returning to the step (d 2), and if so, performing the step (3).
The step (3) specifically comprises the following steps:
(a3) measuring the joint axis on the machine body by using the measuring articulated arm as a target value;
(b3) measuring the axis of the joint on the wing as a target value by using the measuring articulated arm;
(c3) the upper computer reads the actual measurement data;
(d3) the upper computer compares the measured value data with the target data and calculates attitude adjusting parameters;
(e3) the attitude adjusting system receives the attitude adjusting parameters, drives the positioner to adjust the attitude of the wing, and moves the wing to a butt joint completion position;
(f3) measuring the joint axis on the wing by using the measuring articulated arm;
(g3) the upper computer reads the measured value data and compares the measured value data with the target data;
(h3) judging whether the tolerance requirement is met, if not, returning to the step (d 3); and (4) if so, performing the step.
The step (4) specifically comprises the following steps:
(a4) mounting a fixed bolt to connect the fuselage and the wing;
(b4) the AGV transports the butt joint equipment to an appointed parking position;
(c4) and finishing the installation and debugging work of the wings.
The utility model discloses simple structure, simple to operate, the utility model discloses a method can not receive the restriction of the precision laser tracker measurement accuracy of the alignment method, utilizes the required installation accuracy of the single double-insert ear that flexible articulated arm measurement system can be more accurate assurance installation department, adopts laser tracker to carry out preliminary measurement earlier to tentatively transfer the appearance, adopts flexible articulated arm measurement system to carry out the precision measurement again, and the appearance is transferred to the precision; in the traditional airplane digital attitude adjusting and docking process, due to the fact that the measurement accuracy of a laser tracker is not high, high-accuracy airplane component docking cannot be completed, through step-by-step measurement, the measurement accuracy in the attitude adjusting and docking process is gradually improved, the final attitude adjusting accuracy is gradually improved, and high-accuracy docking work can be completed. The measuring method combines the advantages of the laser tracker and the flexible joint arm, can finish high-precision and high-efficiency measuring work in the process of adjusting the posture and closing, and has strong operability, wide practicability and strong applicability.
The present invention is illustrated by way of example and not by way of limitation. It will be apparent to those skilled in the art that other variations and modifications of the present invention can be made in light of the above teachings, and it is not necessary or necessary to exhaustively enumerate all embodiments herein, and it is intended that all such obvious variations and modifications are within the scope of the present invention.
Claims (3)
1. The utility model provides a high accuracy measurement mechanism for big part of aircraft transfers appearance butt joint which characterized in that, includes flexible articulated arm measurement system, flexible articulated arm measurement system includes liftable base, liftable base has rotatable magnetic chuck through the leg joint, be provided with flexible articulated arm measuring machine on the magnetic chuck, flexible articulated arm measuring machine is connected with the gauge head through flexible articulated arm.
2. The high-precision measuring mechanism for the posture-adjusting butt joint of the large parts of the airplane as claimed in claim 1, wherein the liftable base comprises a base plate, liftable legs are connected to the base plate through threads, one end of the support is fixed to the base plate, the other end of the support is connected with a bearing seat, and a rotating shaft corresponding to the bearing seat is arranged on the lower portion of the rotatable magnetic sucker.
3. The mechanism of claim 2, wherein the flexible articulated arm comprises a first articulated arm articulated with the flexible articulated arm measuring machine and capable of rotating up and down relative to the flexible articulated arm measuring machine, a second articulated arm articulated with the first articulated arm and capable of rotating up and down relative to the first articulated arm is arranged on the first articulated arm, a third articulated arm articulated with the second articulated arm and capable of rotating up and down relative to the second articulated arm is arranged on the second articulated arm, and the third articulated arm is provided with a measuring head connected with the flexible articulated arm measuring machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920856620.3U CN210108319U (en) | 2019-06-06 | 2019-06-06 | High-precision measuring mechanism for adjusting and butting large parts of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920856620.3U CN210108319U (en) | 2019-06-06 | 2019-06-06 | High-precision measuring mechanism for adjusting and butting large parts of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210108319U true CN210108319U (en) | 2020-02-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920856620.3U Active CN210108319U (en) | 2019-06-06 | 2019-06-06 | High-precision measuring mechanism for adjusting and butting large parts of airplane |
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| Country | Link |
|---|---|
| CN (1) | CN210108319U (en) |
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- 2019-06-06 CN CN201920856620.3U patent/CN210108319U/en active Active
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