Aircraft skin rivet step difference detection device

Abstract

The present invention relates to the field of rivet step difference detection, and specifically to an aircraft skin rivet step difference detection device, which at least includes a depth gauge, and also includes a connecting part, a bracket, a bolt, a rotating shaft, and a rotating frame. The connecting part is arranged at the bottom end of the bracket, one end of the rotating shaft is vertically rotatably connected to the top end of the bracket, and the rotating frame is fixed to the other end of the rotating shaft. The depth gauge body is inserted into the rotating frame, and the depth gauge is perpendicular to the bracket. One end of the bolt is threadedly connected to the rotating frame, and the bolt penetrates into the rotating frame to act on the depth gauge body. The present invention adopts a bracket and a rotating frame, which effectively solves the problem of overall movement when zeroing in the prior art, and further realizes that by fixing the bracket, the depth gauge does not need to be moved to the rivet again for testing when zeroing. The use of a ring effectively solves the problem of rivets being difficult to center. The use of an alignment ball can facilitate the staff to adjust the test point, making the test more accurate and standardized.

Description

Technical Field

[0001] The invention relates to the field of rivet step difference detection, and in particular to a device for detecting the step difference of aircraft skin rivets. Background Art

[0002] The flight safety of an aircraft is closely related to the rigor of its manufacturing, especially the outer skin of an aircraft. The skin is the first line of defense for protecting the aircraft during flight, and is particularly important. The aircraft skin and the frame are generally connected with countersunk rivets, which are one of the important means of connection for aircraft assembly. The connection quality of countersunk rivets is of paramount importance to aircraft safety. Generally, a caliper is often used to measure the depth of countersunk rivets when testing the step difference of countersunk rivets. This measurement method is not rigorous. With the improvement of accuracy requirements, this method can no longer meet the test requirements. The device for testing the step difference of rivets in the prior art needs to move the test zero point as a whole during actual use, and it cannot be guaranteed that the test position is located at the center point of the rivet, which will result in errors. Therefore, a detection device that is easier to calibrate is needed to standardize the detection. Summary of the invention

[0003] The present invention provides an aircraft skin rivet step difference detection device, which solves the problem of test errors due to different test point positions and realizes accurate testing.

[0004] The technical problem solved by the present invention can be achieved by adopting the following technical solutions:

[0005] A device for detecting step difference of aircraft skin rivets comprises at least a depth gauge, a connecting part, a bracket, a bolt, a rotating shaft and a rotating frame, wherein the connecting part is arranged at the bottom end of the bracket, one end of the rotating shaft is vertically rotatably connected to the top end of the bracket, the rotating frame is fixed to the other end of the rotating shaft, the depth gauge body is inserted into the rotating frame, and the depth gauge is perpendicular to the bracket, one end of the bolt is threadedly connected to the rotating frame, and the bolt penetrates into the rotating frame to act on the depth gauge body.

[0006] The bracket comprises a ring with an opening and three legs, the three legs are threadedly connected under the ring at equal angles and distances, the connecting part is arranged under the three legs, the rotating shaft is rotatably connected on one side of the opening of the ring, and the rotating frame is located inside the ring.

[0007] The connecting part comprises three vacuum suction cups, and the three vacuum suction cups are hinged at the lower ends of the supporting legs.

[0008] The connecting part comprises three connecting blocks, which are detachably connected to the lower ends of the supporting legs and are wrapped with rubber layers.

[0009] The depth gauge is a digital depth gauge.

[0010] An alignment needle is fixed under the rotating frame, an alignment ball is fixed on the alignment end of the alignment needle, and when the rotating frame rotates out of the limit position in the ring, the alignment ball coincides with the center point of the ring.

[0011] The beneficial effect of the present invention is that the bracket and the rotating frame are adopted to effectively solve the problem of overall movement when the zero point is reset in the prior art, and then the bracket is fixed so that the depth gauge does not need to be moved to the rivet again for testing when it is reset to zero.

[0012] The use of a ring effectively solves the problem of difficult rivet alignment, making it convenient to test the same point of all rivets.

[0013] The use of the alignment ball can facilitate the staff to adjust the test points, making the test more accurate and standardized. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0015] Figure 1 It is a structural schematic diagram of the present invention.

[0016] Figure 2 It is a cross-sectional view of the connection block of the present invention.

[0017] Figure 3 It is a top view of the present invention.

[0018] Figure 4 It is a diagram of the limit position of the rotating rack of the present invention.

[0019] In the figure: 1-depth gauge; 2-bracket; 21-ring; 22-leg; 3-bolt; 4-rotating shaft; 5-rotating frame; 6-vacuum suction cup; 7-connecting block; 8-rubber layer; 9-alignment needle; 10-alignment ball. DETAILED DESCRIPTION

[0020] Embodiment 1:

[0021] Reference Figures 1 to 3 , is a structural schematic diagram of embodiment 1 of the present invention, an aircraft skin rivet step difference detection device, at least including a depth gauge 1, characterized in that it also includes a connecting portion, a bracket 2, a bolt 3, a rotating shaft 4, and a rotating frame 5, the connecting portion is arranged at the bottom end of the bracket 2, one end of the rotating shaft 4 is vertically rotatably connected to the top of the bracket 2, the rotating frame 5 is fixed to the other end of the rotating shaft 4, the body of the depth gauge 1 is inserted into the rotating frame 5, and the depth gauge 1 is perpendicular to the bracket 2, one end of the bolt 3 is threadedly connected to the rotating frame 5, and the bolt 3 penetrates into the rotating frame 5 to act on the body of the depth gauge 1.

[0022] In actual use: first, the staff holds the bracket 2 with one hand, and the bracket 2 is supported on the aircraft skin through the connection part, and the test part is located directly below the bracket 2, and then the turntable 5 is rotated, and the turntable 5 is rotated on the bracket 2 through the rotating shaft 4. After rotation, the depth gauge 1 is located directly above the nearby skin, and then the test end of the depth gauge 1 contacts the skin for zeroing, and then the turntable 5 is rotated to move the depth gauge 1 to directly above the test part for depth testing, thereby completing the rivet step difference test. When the test part is located at the skin angle, the depth gauge 1 is unlocked by loosening the bolt 3, and the depth gauge 1 is adjusted to slide in the turntable 5. The distance between the depth gauge 1 and the skin is adjusted for measurement, which can increase the measurement accuracy.

[0023] Embodiment 2:

[0024] Reference Figures 1 to 3 Compared with Example 1, the difference of this embodiment is that: the bracket 2 includes a ring 21 with an opening and three legs 22, the three legs 22 are threadedly connected under the ring 21 at equal angles and distances, the connecting part is arranged under the three legs 22, the rotating shaft 4 is rotatably connected on one side of the opening of the ring 21, and the rotating frame 5 is located inside the ring 21.

[0025] In actual use: During measurement, the three legs 22 are in contact with the skin through the connection part, and the turntable 5 is rotated out of the ring 21 through the rotating shaft 4, the turntable 5 is rotated out from the opening of the ring 21, and then the ring 21 is used to align with the test part, and then the depth gauge 1 is reset to zero, and then the turntable 5 is rotated back to the extreme position in the ring 21, and then the depth gauge 1 can be used for measurement. At the same time, the legs 22 and the ring 21 are threadedly connected, and the legs 22 of different lengths can be replaced according to different test parts to increase the test efficiency.

[0026] Embodiment 3:

[0027] Reference Figure 1 Compared with Embodiment 1 or 2, the present embodiment is different in that: the connection portion includes three vacuum suction cups 6 , and the three vacuum suction cups 6 are hinged to the lower ends of the legs 22 .

[0028] In actual use: after the bracket 2 is aligned with the test position, it is adsorbed on the aircraft skin through the vacuum suction cup 6, so that the bracket 2 is more stable during the test. After the test is completed, the vacuum suction cup 6 is opened and the air release valve is opened to move to the next test position.

[0029] Embodiment 4:

[0030] 2 , compared with Embodiment 2 or 3 , the difference of this embodiment is that the connecting portion includes three connecting blocks 7 , the three connecting blocks 7 are detachably connected to the lower end of the bracket 2 , and the three connecting blocks 7 are wrapped with a rubber layer 8 .

[0031] In actual use: the bracket 2 is supported on the aircraft skin through the connecting block 7 and the rubber layer 8. The rubber layer 8 can increase the friction between the connecting block 7 and the aircraft skin to prevent sliding during testing. At the same time, the connecting block 7 is threadedly connected to the support leg 22, so the connecting block 7 can be replaced after being worn, reducing the replacement cost.

[0032] In this embodiment, the rubber layer 8 is made of hard rubber.

[0033] Embodiment 5:

[0034] 1 , compared with Embodiment 4, the difference of this embodiment is that: the depth gauge 1 is a digital depth gauge.

[0035] In actual use: Depth gauge 1 is a digital depth gauge that can measure the step difference value more accurately.

[0036] Embodiment 6:

[0037] Reference Figure 4 Compared with Example 5, the difference of this embodiment is that: an alignment needle 9 is fixed under the rotating frame 5, an alignment ball 10 is fixed to the alignment end of the alignment needle 9, and the rotating frame 5 rotates out of the extreme position in the ring 21, and the alignment ball 10 coincides with the center point of the ring 21.

[0038] In actual use: first rotate the rotating frame 5 out of the ring 21 and to the limit position, and at the same time, the alignment needle 9 moves accordingly, so that the alignment ball 10 coincides with the center of the ring 21, so that the user can accurately locate the measuring point, and then position the bracket 2 through the connecting part before conducting the test.

[0039] The housing of the alignment ball 10 is covered with a striking color coating, such as a red coating, to facilitate positioning.

[0040] The above is a detailed description of the embodiments of the present invention in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Within the knowledge scope of ordinary technicians in the field, various changes can be made without departing from the purpose of the present invention, which are all within the protection scope of this technology.

Claims

1. An aircraft skin rivet step difference detection device, comprising at least a depth gauge (1), characterized in that: It also comprises a connecting portion, a bracket (2), a bolt (3), a rotating shaft (4), and a rotating frame (5), wherein the connecting portion is arranged at the bottom end of the bracket (2), one end of the rotating shaft (4) is vertically rotatably connected to the top end of the bracket (2), the rotating frame (5) is fixed to the other end of the rotating shaft (4), the body of the depth gauge (1) is inserted into the rotating frame (5), and the depth gauge (1) is perpendicular to the bracket (2), one end of the bolt (3) is threadedly connected to the rotating frame (5), and the bolt (3) is deeply inserted into the rotating frame (5) to act on the body of the depth gauge (1); The support (2) comprises a ring (21) with an opening and three legs (22), the three legs (22) being threadedly connected under the ring (21) at equal angles and distances, the connecting portion being arranged under the three legs (22), the rotating shaft (4) being rotatably connected to one side of the opening of the ring (21), and the rotating frame (5) being located inside the ring (21); An alignment needle (9) is fixed under the rotating frame (5), and an alignment ball (10) is fixed at the alignment end of the alignment needle (9); when the rotating frame (5) rotates out of the limit position in the ring (21), the alignment ball (10) coincides with the center point of the ring (21); The rotating frame (5) rotates on the bracket (2) via the rotating shaft (4); The depth gauge (1) is a digital depth gauge.

2. The aircraft skin rivet step difference detection device according to claim 1, characterized in that: The connection portion comprises three vacuum suction cups (6), and the three vacuum suction cups (6) are respectively hinged to the lower ends of the supporting legs (22).

3. The aircraft skin rivet step difference detection device according to claim 1, characterized in that: The connection portion comprises three connection blocks (7), the three connection blocks (7) being detachably connected to the lower ends of the legs (22), and the three connection blocks (7) being wrapped with a rubber layer (8).

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