Wing main beam through hole roughness testing device and testing method thereof

Abstract

The invention discloses a wing main beam through hole roughness testing device and a testing method thereof.The wing main beam through hole roughness testing device comprises a linear sliding block guide rail pair, a universal arm, a connecting frame and a roughness tester, the two ends of a guide rail of the linear sliding block guide rail pair are fixedly connected with two first magnetometer bases, and the two first magnetometer bases can be attracted and fixed to one side of a wing main beam; the two ends of the universal arm are fixedly connected to the second magnetometer base and the T-shaped groove base respectively, the second magnetometer base is fixedly connected to a sliding block of the linear sliding block guide rail pair, the T-shaped groove base is connected with a T-shaped strip arranged on one side of the connecting frame through a T-shaped groove, and the roughness tester is detachably and fixedly connected into the connecting frame. After the universal arm is bent, a probe of the tester can extend into the through hole of the wing main beam and is kept coaxial with the through hole of the wing main beam, the device further comprises a position calibration block capable of calibrating the coaxiality of the through hole of the wing main beam, and the position calibration block is detachably connected into the connecting frame. The test precision of the wing girder through hole can be improved, the test difficulty and the test error are reduced, and the operation is convenient and fast.

Description

Technical Field

[0001] The present invention relates to the technical field of wing main beam through-hole roughness testing, in particular to a wing main beam through-hole roughness testing device and a testing method for the wing main beam through-hole roughness testing device. Background Art

[0002] The wing main beam is the core load-bearing structure of the aircraft wing, bearing the bending, shear and torsional loads during flight. Its design directly affects the strength, stiffness and fatigue life of the wing. There are multiple mounting holes arranged near the length of the wing main beam. The inner surface of the through hole is used as the mounting surface. The roughness requirement of the inner hole is high. The orientation is vertical, but it is not perpendicular to the horizontal panel along the length of the wing main beam. Therefore, it is difficult to achieve coaxiality between the probe of the roughness tester and the through hole of the wing main beam when testing the roughness, and the test error is large. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a wing main beam through-hole roughness testing device and a testing method thereof, which can achieve coaxiality between the probe of the roughness tester and the through-hole, reduce testing errors and improve testing accuracy.

[0004] The solution adopted by the present invention is: a wing main beam through-hole roughness testing device, including a linear slider guide pair, a universal arm, a connecting frame and a roughness tester, two first magnetic meter bases are fixedly connected at both ends of the guide rail of the linear slider guide pair, and the two first magnetic meter bases can be adsorbed and fixed on one side of the wing main beam, the universal arm adopts three universal joints, one end is fixedly connected to the second magnetic meter base, and the other end is fixedly connected to the T-slot seat, the second magnetic meter base is fixedly connected to the slider of the linear slider guide pair, the T-slot seat has a T-slot, and one side of the connecting frame is provided with a There is a T-shaped bar, which is movably inserted into the T-shaped slot and locked with a set screw. The roughness tester is detachably fixed in the connecting frame. After the universal arm is bent, the probe of the tester can be inserted into the through hole of the wing main beam and remain coaxial with it. It also includes a position calibration block consistent with the shape of the roughness tester. The position calibration block can be detachably connected to the connecting frame. The position calibration block is provided with a locating pin that is docked to the through hole of the wing main beam. The locating pin maintains a clearance fit with the through hole of the wing main beam. The locating pin and the probe of the roughness tester are located in the same position.

[0005] Furthermore, the above-mentioned universal arm includes a first universal ball hinge, a first connecting arm, a second universal ball hinge, a second connecting arm, a third universal ball hinge and a third connecting arm. The hinge seat of the first universal ball hinge is fixedly connected to the second magnetic table seat. The two ends of the first connecting arm are respectively connected to the first universal ball hinge and the second universal ball hinge. The two ends of the second connecting arm are respectively connected to the second universal ball hinge and the third universal ball hinge. One end of the third connecting arm is connected to the third universal ball hinge, and the other end is connected to the T-slot seat. The first universal ball hinge, the second universal ball hinge and the third universal ball hinge are all locked with fasteners.

[0006] Furthermore, two sets of identical universal arms, sliders, second magnetic bases and T-shaped slides are symmetrically arranged on both sides of the connection frame, sharing a guide rail.

[0007] Furthermore, a locking assembly is installed on the slider to lock its movement.

[0008] Furthermore, the T-slot seat is provided with a fastener for locking the T-strip.

[0009] Furthermore, the above-mentioned positioning pins are detachably connected to the calibration block, and multiple positioning pins of different specifications are used, and multiple positioning pins match the wing main beam through holes of different diameters.

[0010] A testing method using the wing main beam through-hole roughness testing device is disclosed. The method comprises the following steps: fixing a track to the top surface of the wing main beam through a first magnetic table seat, moving a slider to a set position of the track and locking it, installing a calibration block in a connecting frame, controlling the rotation of a robotic arm, inserting a locating pin of the calibration block into the through-hole of the wing main beam, fixing the spherical joints, the connecting frame and the slider of the robotic arm, removing the calibration block, installing a roughness tester, inserting the probe of the tester into the through-hole of the wing main beam, starting the roughness tester, and performing a roughness test on the through-hole of the wing main beam. After the test is completed for the through-hole of the wing main beam at that location, the tester is moved to the next location. If the size of the through-hole of the wing main beam changes, the locating pin is replaced, and the installation process of the previous through-hole of the wing main beam is repeated, and then a roughness test on the second through-hole of the wing main beam is performed. The process is repeated until all the through-holes are completed.

[0011] Furthermore, the roughness test of each of the wing main beam through holes mentioned above requires multiple tests to obtain an average value.

[0012] Compared with the prior art, the present invention adopts a universal arm to position the calibration block which is consistent with the appearance of the roughness tester, and ensures that the positioning pin which is coaxial with the probe in the same position can be inserted into the through hole of the wing main beam and maintains a clearance fit with it. After the initial positioning of the tester is achieved, the calibration block is disassembled, and the roughness tester is installed on the connecting frame of the calibration block and ensures that the probe is inserted into the through hole of the wing main beam to achieve coaxiality with the through hole of the wing main beam, thereby improving the test accuracy of the through hole of the wing main beam, reducing the test difficulty and test error, and the operation is convenient and quick. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the top view of the wing main beam through-hole roughness testing device; Figure 2 This is a front view structural diagram of the wing main beam through-hole roughness testing device. DETAILED DESCRIPTION

[0014] Example 1: Figure 1-Figure 2 As shown, a wing main beam through-hole roughness test device includes a linear slider guide pair 1, a universal arm 2, a connecting frame 3 and a roughness tester 4. Two first magnetic meter bases 5 are fixedly connected at both ends of the guide rail 101 of the linear slider guide pair 1. The two first magnetic meter bases 5 can be adsorbed and fixed on the wing main beam 6 (such as Figure 1 1 and 2. As shown in the figure, the universal arm 2 is placed horizontally) on one side, the universal arm 2 adopts three universal joints, one end of which is fixedly connected to the second magnetic base 7, and the other end is fixedly connected to the T-slot base 8. The second magnetic base 7 is fixedly connected to the slider 102 of the linear slider guide pair 1. The T-slot base 8 has a T-slot 801. A T-bar 301 is provided on one side of the connecting frame 3. The T-bar 301 is movably inserted into the T-slot 801 and locked with a set screw 9. The roughness tester 4 is fixedly connected to the connecting frame 3. After the universal arm 2 is bent, the probe 401 of the roughness tester 4 can be inserted into the through hole 10 of the wing main beam and kept coaxial therewith. It also includes a position calibration block 11 that is consistent with the appearance of the roughness tester 4. The position calibration block 11 can be detachably connected to the connecting frame 3 Inside, the position calibration block 11 is provided with a locating pin 1101 connected to the wing main beam through hole 10, and the locating pin 1101 maintains a clearance fit with the wing main beam through hole 10, and the locating pin 1101 is located at the same position as the probe 401 of the roughness tester 4; a universal arm is used to position the calibration block with the same appearance as the roughness tester, and ensure that the locating pin coaxial with the same position as the probe can be inserted into the wing main beam through hole and maintain a clearance fit with it, and after the initial positioning of the tester is achieved, the calibration block is disassembled, and the roughness tester is installed on the connecting frame of the calibration block and ensure that the probe is inserted into the wing main beam through hole to achieve coaxiality with the wing main beam through hole, thereby improving the test accuracy of the wing main beam through hole, reducing the test difficulty and test error, and the operation is convenient and quick.

[0015] Specifically, the universal arm 2 includes a first universal ball hinge 201, a first connecting arm 202, a second universal ball hinge 203, a second connecting arm 204, a third universal ball hinge 205 and a third connecting arm 206. The hinge seat of the first universal ball hinge 201 is fixedly connected to the second magnetic table seat 7. The two ends of the first connecting arm 202 are respectively connected to the first universal ball hinge 201 and the second universal ball hinge 203. The two ends of the second connecting arm 204 are respectively connected to the second universal ball hinge 203 and the third universal ball hinge 205. One end of the third connecting arm 20 is connected to the third universal ball hinge 205, and the other end is connected to the T-slot seat 8. The first universal ball hinge 201, the second universal ball hinge 203 and the third universal ball hinge 205 are all locked with a fastener 207 (using a second set screw). The three-section connecting arm and the universal ball hinge are used to achieve rapid adjustment of the universal arm to any angle.

[0016] In order to improve the support stability, two sets of support structures are designed to support the connecting frame. Two sets of identical universal arms 2, sliders 102, second magnetic table bases 7 and T-shaped slides 8 are symmetrically arranged on both sides of the connecting frame 3, sharing a guide rail 101. The two sets of support structures support the connecting frame, which can ensure the stability of the connecting frame during the test after it is connected to the roughness tester, thereby reducing the test error.

[0017] In order to fix the slider after sliding it to a certain position, a locking assembly is installed on the slider 102 to lock its movement. The locking assembly includes a connecting plate 103 and a set screw 104. One end of the connecting plate 103 is cantilevered and fixedly connected to the slider 102. The set screw 104 is spirally connected to the connecting plate 103 and the inner end can rest against the side edge of the guide rail 101.

[0018] In order to adapt to the testing of through holes of different sizes, the locating pin 1101 is detachably connected to the calibration block 11. The locating pin 1101 adopts multiple locating pins of different specifications. Multiple locating pins 1101 match wing main beam through holes 10 of different diameters. For wing main beam through holes of different sizes, locating pins of different sizes are matched to facilitate loading and unloading.

[0019] Example 2: A testing method using the wing main beam through-hole roughness testing device, the method is: fix the track on the top surface of the wing main beam through the first magnetic table seat, move the slider to the set position of the track and lock it, install the calibration block in the connecting frame, control the rotation of the mechanical arm, insert the locating pin of the calibration block into the wing main beam through-hole, and fix the various spherical joints, connecting frame and slider of the mechanical arm, remove the calibration block, install the roughness tester, insert the probe of the tester into, start the roughness tester, perform the roughness test of the wing main beam through-hole, complete the test of the wing main beam through-hole at that location, move to the next position, if the size of the wing main beam through-hole changes, replace the locating pin, repeat the installation process of the previous wing main beam through-hole, and then perform the roughness test of the second wing main beam through-hole, and repeat until all are completed; the roughness test of each wing main beam through-hole requires multiple tests to obtain the average value.

Claims

1. A wing main beam through-hole roughness testing device, characterized in that: It includes a linear slider guide pair, a universal arm, a connecting frame and a roughness tester. The two ends of the guide rail of the linear slider guide pair are fixedly connected to two first magnetic bases. The two first magnetic bases can be adsorbed and fixed on one side of the wing main beam. The universal arm adopts three universal joints, one end of which is fixedly connected to the second magnetic base, and the other end is fixedly connected to the T-slot seat. The second magnetic base is fixedly connected to the slider of the linear slider guide pair. The T-slot seat has a T-slot. A T-bar is provided on one side of the connecting frame. The T-bar is movably snapped into the T The groove is locked with a set screw, and the roughness tester is detachably fixed in the connecting frame. After the universal arm is bent, the probe of the tester can be inserted into the through hole of the wing main beam and remain coaxial with it. It also includes a position calibration block consistent with the shape of the roughness tester. The position calibration block can be detachably connected to the connecting frame. The position calibration block is provided with a locating pin that is docked to the through hole of the wing main beam. The locating pin maintains a clearance fit with the through hole of the wing main beam, and the locating pin and the probe of the roughness tester are located in the same position.

2. A wing main beam through-hole roughness testing device according to claim 1, characterized in that: The universal arm includes a first universal ball hinge, a first connecting arm, a second universal ball hinge, a second connecting arm, a third universal ball hinge and a third connecting arm. The hinge seat of the first universal ball hinge is fixedly connected to the second magnetic table seat. The two ends of the first connecting arm are respectively connected to the first universal ball hinge and the second universal ball hinge. The two ends of the second connecting arm are respectively connected to the second universal ball hinge and the third universal ball hinge. One end of the third connecting arm is connected to the third universal ball hinge, and the other end is connected to the T-slot seat. The first universal ball hinge, the second universal ball hinge and the third universal ball hinge are all locked with fasteners.

3. A wing main beam through-hole roughness testing device according to claim 1, characterized in that: Two sets of identical universal arms, sliders, second magnetic meter bases and T-shaped sliders are symmetrically arranged on both sides of the connection frame and share a guide rail.

4. A wing main beam through-hole roughness testing device according to claim 1, characterized in that: A locking assembly is mounted on the slider to lock its movement.

5. The wing main beam through-hole roughness testing device according to claim 1, characterized in that: The T-slot seat is provided with a fastener for locking the T-strip.

6. The wing main beam through-hole roughness testing device according to claim 1, characterized in that: The locating pins are detachably connected to the calibration block. A plurality of locating pins of different specifications are used, and the plurality of locating pins match the through holes of the wing main beams of different diameters.

7. A testing method using the wing main beam through-hole roughness testing device according to claim 1, characterized in that: The method comprises the following steps: fixing a track on the top surface of a wing main beam through a first magnetic table seat, moving a slider to a set position of the track and locking it, installing a calibration block in a connection frame, controlling the rotation of a mechanical arm, inserting a positioning pin of the calibration block into a through hole of the wing main beam, fixing the spherical joints, the connection frame and the slider of the mechanical arm, removing the calibration block, installing a roughness tester, inserting a probe of the tester into the through hole of the wing main beam, starting the roughness tester, and performing a roughness test on the through hole of the wing main beam. After the test is completed on the through hole of the wing main beam at that location, the tester is moved to the next location. If the size of the through hole of the wing main beam changes, the positioning pin is replaced, and the installation process of the previous through hole of the wing main beam is repeated, and then the roughness test of the second through hole of the wing main beam is performed. The process is repeated until all the through holes are completed.

8. The testing method of a wing main beam through-hole roughness testing device according to claim 6, characterized in that: The roughness test of each wing main beam through hole requires multiple tests to obtain the average value.

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