Aircraft skin lap joint boundary dimension scriber

Abstract

The utility model discloses an airplane skin lap joint boundary dimension scriber which comprises a transverse guide rail, the bottom of the transverse guide rail is connected with a vertical plate in a sliding mode through a sliding block, the vertical plate is perpendicular to the transverse guide rail, a notch is formed in the bottom of the vertical plate, and an annular groove is formed above the notch. A T-shaped block is arranged in the notch, a threaded hole is formed in the middle of the T-shaped block, the T-shaped block is in threaded connection with a scribing needle through the threaded hole, and a threaded pipe is slidably connected to the middle of the annular groove through a sliding block. Longitudinal scribing can be achieved through sliding of the T-shaped block in the notch, the vertical plate can move transversely through matched use of the transverse guide rail and the sliding block, the scribing needle is driven to conduct transverse scribing to press the threaded pipe and rotate the threaded rod, and the first base plate makes contact with the aircraft skin; and the vertical plate rotates around the threaded pipe, so that an arc line is conveniently scribed by the scribing needle, and the multifunctionality of the device is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of marking tools, in particular to a marking tool for the outer dimensions of overlapping aircraft skins. Background Art

[0002] The skin is a load-bearing component covering the outside of the frame. The direct function of the skin is to form a streamlined outer surface of the wing. In order to minimize the resistance of the wing, the skin should be as smooth as possible to reduce its uneven deformation during flight. From the perspective of force, the aerodynamic load acts directly on the skin, so the skin is subject to local aerodynamic loads perpendicular to its surface. In addition, the skin also participates in the overall force of the wing, that is, it is combined with the wing spar or wing wall to form a closed box-type thin-walled structure to withstand the torque of the wing; when the skin is thicker, it forms a wall panel together with the long stringer and the wing spar edge strip to withstand the shear force caused by the wing bending moment.

[0003] When aircraft skins are produced, the skin materials need to be marked according to the dimensions on the drawings, and then processed by processing equipment. The existing skin marking method is to measure with a measuring tool and mark with a marking needle, so different tools are needed to mark arcs and straight lines, which makes the marking operation more troublesome. Utility Model Content

[0004] The purpose of this section is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the specification abstract and utility model name of this application to avoid blurring the purpose of this section, specification abstract and utility model name, and such simplifications or omissions cannot be used to limit the scope of the utility model.

[0005] To solve the above problems, the utility model adopts the following technical solutions.

[0006] The invention discloses an aircraft skin lap dimension scriber, comprising a transverse guide rail, the bottom of which is slidably connected with a vertical plate via a slider, and the vertical plate and the transverse guide rail are perpendicular to each other, a notch is provided at the bottom of the vertical plate, and an annular groove is provided above the notch.

[0007] A T-block is slidably provided inside the groove, a threaded hole is opened in the middle of the T-block, and a marking needle is threadedly connected to the T-block through the threaded hole, a threaded tube is rotatably connected to the middle of the annular groove, and the inner circle of the threaded tube is a threaded structure, the inner thread of the threaded tube is connected to a screw, and the end of the screw is fixedly connected to a first pad.

[0008] Preferably, the top edge of the transverse guide rail is provided with scale bars evenly distributed laterally, both ends of the transverse guide rail are threadedly connected to a second pad via threaded columns, and the bottom surface of the transverse guide rail fits with the top surface of the vertical plate.

[0009] Preferably, one side of the vertical plate is provided with scale bars evenly distributed longitudinally, and the top and bottom ends of the notch are both arc structures.

[0010] Preferably, one end of the T-block is a plate-like structure, and the other end is a circular tube-like structure. The marking needle passes through both ends of the T-block, and a sliding structure is formed between the T-block and the notch.

[0011] Preferably, a connecting plate is sleeved on the outer side of the marking needle, and a locking bolt is threadedly connected to one end of the connecting plate away from the marking needle, and a limiting groove is provided on one side of the vertical plate close to the locking bolt.

[0012] Preferably, the sliders on the outer side of the threaded tube are evenly distributed in a ring shape, and the threaded tube is connected to the annular groove through the sliders.

[0013] Preferably, the width of the limiting groove matches the outer diameter of the locking bolt, and the length of the limiting groove is equal to the length of the notch.

[0014] Preferably, one end of the screw rod is a hexagonal structure, and the length of the threaded tube is greater than the thickness of the vertical plate.

[0015] Beneficial Effects

[0016] Compared with the prior art, the beneficial effects of the utility model are:

[0017] The utility model utilizes the sliding of the T-block in the groove to realize longitudinal marking. Through the coordinated use of the transverse guide rail and the slider, the vertical plate can be moved transversely, driving the marking needle to mark transversely and press the threaded tube, rotating the screw rod, so that the first pad is in contact with the aircraft skin, and utilizing the coordinated use of the annular groove and the slider to make the vertical plate rotate around the threaded tube, thereby facilitating the marking needle to carve arcs, thereby improving the versatility of the device. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall three-dimensional structure of the utility model;

[0019] Figure 2 This is a schematic diagram of the back three-dimensional structure of the utility model;

[0020] Figure 3 It is a schematic diagram of the overall front view structure of the utility model;

[0021] Figure 4 It is a partial three-dimensional structural schematic diagram of the utility model;

[0022] Figure 5 This is a schematic diagram of the three-dimensional structure of the T-block of the utility model;

[0023] Figure 6It is a schematic diagram of the three-dimensional structure of the threaded pipe of the utility model.

[0024] The corresponding relationship between the illustrations and component names in the figure is as follows:

[0025] 1. Horizontal guide rail; 2. Vertical plate; 3. Notch; 4. Ring groove; 5. T-block; 6. Scribing needle; 7. Threaded pipe; 8. Screw; 9. First pad; 10. Second pad; 11. Connecting plate; 12. Locking bolt; 13. Limiting groove. DETAILED DESCRIPTION

[0026] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0027] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0028] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure or characteristic that may be included in at least one implementation of the present invention. The term "in one embodiment" that appears in different places in this specification does not refer to the same embodiment, nor is it a separate or selective embodiment that is mutually exclusive with other embodiments. The present invention provides the following embodiments.

[0029] See also Figure 1-6 The utility model provides an embodiment: an aircraft skin overlap dimension scriber, comprising a transverse guide rail 1, a vertical plate 2 is slidably connected to the bottom of the transverse guide rail 1 through a slider, and the vertical plate 2 and the transverse guide rail 1 are perpendicular to each other, a notch 3 is provided at the bottom of the vertical plate 2, and an annular groove 4 is provided above the notch 3.

[0030] The notch 3 is located at the center of the vertical board 2 and is consistent with the direction of the vertical board 2. The top of the vertical board 2 fits with the bottom of the horizontal guide rail 1 to ensure that the vertical board 2 will not deviate when moving horizontally.

[0031] A T-block 5 is provided for sliding inside the slot 3. As a specific implementation manner of the present application, one side of the vertical plate 2 is provided with longitudinally evenly distributed scale bars. The top and bottom ends of the slot 3 are both arc structures. The sliding of the T-block 5 in the slot 3 can achieve longitudinal marking. The arc structures at both ends of the slot 3 facilitate good fit with the T-block 5. A threaded hole is provided in the middle of the T-block 5, and the T-block 5 is threadedly connected to a marking needle 6 through the threaded hole. As a specific implementation manner of the present application, one end of the T-block 5 is a plate-like structure, and the other end is a circular tubular structure.

[0032] The outer diameter of the round tube of the T-block 5 matches the width of the slot 3, so that there is friction between the T-block 5 and the vertical plate 2, preventing the T-block 5 from loosening and ensuring the sliding stability of the T-block 5. The arc of the round tube of the T-block 5 matches the arc of the slot 3, making it easy to slide the T-block 5 to one end of the slot 3 and place it.

[0033] The marking needle 6 passes through both ends of the T-block 5, and a sliding structure is formed between the T-block 5 and the notch 3. The marking needle 6 is rotated to move forward and backward, and the marking needle 6 is brought into contact with the surface of the aircraft skin. The middle of the annular groove 4 is rotatably connected with a threaded tube 7, and the inner circle of the threaded tube 7 is a threaded structure. The internal thread of the threaded tube 7 is connected with a screw 8. As a specific implementation method of the present application, one end of the screw 8 is a hexagonal structure, the length of the threaded tube 7 is greater than the thickness of the vertical plate 2, and the end of the screw 8 is fixedly connected with a first pad 9. As a specific implementation method of the present application, the sliders on the outside of the threaded tube 7 are evenly distributed in an annular shape, and the threaded tube 7 is connected to the annular groove 4 through the sliders. Press the threaded tube 7 and rotate the screw 8 to make the first pad 9 contact with the aircraft skin.

[0034] One end of the screw rod 8 is a hexagonal structure, which is convenient for the user to manually rotate the screw rod 8 without the aid of external tools, and is convenient and quick.

[0035] In this embodiment, a scale bar evenly distributed laterally is provided on the top edge of the transverse guide rail 1, and second pads 10 are threadedly connected to both ends of the transverse guide rail 1 through threaded columns, and the bottom surface of the transverse guide rail 1 is fitted with the top surface of the vertical plate 2. Through the second pad 10, the device is fitted with the surface of the aircraft skin material, and the vertical plate 2 can be moved laterally by the coordinated use of the transverse guide rail 1 and the slider.

[0036] The second pad 10 is a circular sheet structure, the center line of the second pad 10 coincides with the center axis of the threaded column to which it is connected, and the second pad 10 is made of soft rubber material, which is convenient for close fitting with the surface of the skin to prevent sliding during fitting.

[0037] In this embodiment, a connecting plate 11 is sleeved on the outer side of the marking needle 6, and a locking bolt 12 is threadedly connected to the end of the connecting plate 11 away from the marking needle 6. A limiting groove 13 is provided on the side of the vertical plate 2 close to the locking bolt 12. As a specific implementation method of the present application, the width of the limiting groove 13 is consistent with the outer diameter of the locking bolt 12, and the length of the limiting groove 13 is equal to the length of the notch 3. By rotating the locking bolt 12, the T-block 5 can be locked and fixed in cooperation with the connecting plate 11 and the limiting groove 13.

[0038] When the locking bolt 12 is tightened, in conjunction with the limiting groove 13 , the connecting plate 11 can press the vertical rod 2 , thereby locking and fixing the T-block 5 .

[0039] When using the device, firstly, the device is fitted with the surface of the aircraft skin material through the second pad 10, and the marking needle 6 is rotated to move the marking needle 6 forward and backward, and the marking needle 6 is brought into contact with the aircraft skin surface. The sliding of the T-block 5 in the notch 3 can realize longitudinal marking, and the locking bolt 12 is rotated to cooperate with the connection plate 11 and the limit groove 13 to lock and fix the T-block 5. The vertical plate 2 can be moved horizontally through the cooperation of the transverse guide rail 1 and the slider, so as to drive the marking needle 6 to make a horizontal marking on the aircraft skin surface, which is convenient for making a cross mark when marking the skin size. The threaded tube 7 is pressed and the screw 8 is rotated to make the first pad 9 contact with the aircraft skin. The ring groove 4 and the slider are used together to make the vertical plate 2 rotate around the threaded tube 7, so as to facilitate the marking needle 6 to mark an arc, thereby improving the versatility of the device and facilitating the marking operation. The scale bars on the transverse guide rail 1 and the vertical plate 2 are convenient for users to check the marking distance.

[0040] It is obvious to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be regarded as exemplary and non-limiting from any point of view, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention. Any reference numeral in a claim should not be regarded as limiting the claim to which it relates.

[0041] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. An aircraft skin lap dimension marking device, comprising a transverse guide rail (1), characterized in that: The bottom of the transverse guide rail (1) is slidably connected to a vertical plate (2) via a slider, and the vertical plate (2) and the transverse guide rail (1) are perpendicular to each other. A notch (3) is provided at the bottom of the vertical plate (2), and an annular groove (4) is provided above the notch (3); A T-shaped block (5) is slidably provided inside the notch (3), a threaded hole is provided in the middle of the T-shaped block (5), and a marking needle (6) is threadedly connected to the T-shaped block (5) through the threaded hole. A threaded tube (7) is rotatably connected to the middle of the annular groove (4), and the inner ring of the threaded tube (7) is a threaded structure. A screw rod (8) is threadedly connected to the inside of the threaded tube (7), and a first pad (9) is fixedly connected to the end of the screw rod (8).

2. The aircraft skin overlap dimension marking tool according to claim 1, characterized in that: The top edge of the transverse guide rail (1) is provided with scale bars evenly distributed laterally, the two ends of the transverse guide rail (1) are threadedly connected to a second pad (10) via threaded columns, and the bottom surface of the transverse guide rail (1) is in contact with the top surface of the vertical plate (2).

3. The aircraft skin overlap dimension marking tool according to claim 2, characterized in that: One side of the vertical plate (2) is provided with scale bars evenly distributed in the longitudinal direction, and the top and bottom ends of the notch (3) are both arc structures.

4. The aircraft skin overlap dimension marking tool according to claim 1, characterized in that: One end of the T-shaped block (5) is a plate-shaped structure, and the other end is a circular tube-shaped structure. The marking needle (6) passes through both ends of the T-shaped block (5).

5. The aircraft skin overlap dimension marking tool according to claim 1, characterized in that: A connecting plate (11) is sleeved on the outer side of the marking needle (6); a locking bolt (12) is threadedly connected to one end of the connecting plate (11) away from the marking needle (6); and a limiting groove (13) is provided on one side of the vertical plate (2) close to the locking bolt (12).

6. The aircraft skin overlap dimension marking tool according to claim 1, characterized in that: The sliders on the outside of the threaded tube (7) are evenly distributed in a ring shape, and the threaded tube (7) is connected to the annular groove (4) via the sliders.

7. The aircraft skin overlap dimension marking tool according to claim 5, characterized in that: The width of the limiting groove (13) matches the outer diameter of the locking bolt (12), and the length of the limiting groove (13) is equal to the length of the notch (3).

8. The aircraft skin overlap dimension marking tool according to claim 1, characterized in that: One end of the screw rod (8) is a hexagonal structure, and the length of the threaded tube (7) is greater than the thickness of the vertical plate (2).

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