Hole center positioning tool for opening of aircraft skin

Abstract

The utility model belongs to the technical field of structural assembly of aircraft products, and relates to a hole center positioning tool for opening a hole in an aircraft skin. Comprising a main body part (1a), a positioning needle (1b), a limiting piece (1c) and a telescopic spring (1d), the main body part 1a is of a variable-diameter cylindrical structure, one end of the main body part 1a is a plane end, the other end of the main body part 1a is a horn-mouth-shaped end, and a positioning needle (1b) passing hole is formed in the main body part 1a; a limiting stop block is arranged at the end of the positioning pin (1b), a limiting piece (1c) is arranged in the middle of the positioning pin (1b), the telescopic spring (1d) is arranged on the positioning pin (1b) in a sleeved mode and arranged at the plane end of the limiting piece (1c) and the main body part (1a), and the limiting piece (1c) is in threaded fit with the positioning pin (1b). The precision of the hole forming position is improved, the problem of part assembly caused by assembly error accumulation caused by multiple times of positioning is avoided, the product quality is guaranteed, the product percent of pass is improved, and the hole forming assembly period is effectively shortened.

Description

Technical Field

[0001] The utility model belongs to the technical field of structural assembly of aircraft products, and relates to a positioning tool for the hole centers of aircraft skin openings. Background Technique

[0002] Openings are made on the on-board skin of a certain type of aircraft for system ducts to pass through. The pipe orifice that extends outside the skin at the opening is required to be coaxial with the finished pipe orifice on the outer surface of the skin. The connection method is a ball head orifice to flare connection, and the connection is made by screwing through the movable flange and screws carried by the pipe orifice. The connection method between the duct passing through the skin and the skin is flange and skin hole drilling and screwing. The finished product is fixed on the skin by four brackets fixed on the outer surface of the skin. During the actual production and assembly process, it often occurs that after the duct is fixed at the skin opening, the pipe orifice that extends out of the duct is not concentric with the finished pipe orifice, resulting in uncoordinated assembly of the duct pipe orifice and the finished pipe orifice. The current assembly process is that the opening on the skin is drilled through the backing plate riveted on the skin to the skin. The opening on the backing plate is carried in the part state. During the assembly process of the skin assembly, the positional relationship between the backing plate and the skin is positioned by scribing according to the design drawing dimensions. The skin is positioned on the tool by relying on the tool locator. After the skin is positioned on the corresponding tool together with the entire component, the four brackets used to fix the finished product are positioned on the skin by relying on the positioning tool of the component, and then the brackets are riveted and fixed to the fuselage skin. When the system is working, after the finished product is fixed on the bracket on the skin, the system duct is installed at the opening of the fuselage skin. During the entire assembly process, due to the scribing positioning of the backing plate on the skin, there is an error of 1 mm - 2 mm. The positioning of the entire skin on the tool, the positioning of the skin on the lower tool, and the positioning of the finished product bracket, the cumulative error of multiple times leads to the situation that when the system duct is installed through the hole on the subsequent skin, the system duct pipe orifice is not coordinated with the upper pipe orifice of the finished product. To avoid such problems, by improving the process method, that is, canceling the duct passing holes carried in the part state on the backing plate, when installing the duct through the hole on the skin, relying on the positioning tool for the hole centers of the aircraft skin opening to fix it on the finished pipe orifice, and then coordinating and positioning the corresponding duct passing hole centers on the outer surface of the fuselage skin, the hole center positioning, reaming, and installation of the duct are carried out. In this way, it can not only reduce the waste of re-sampling caused by structural assembly errors of the duct, but also greatly improve the production efficiency and ensure the product quality. Content of the Utility Model

[0003] The utility model overcomes the deficiencies in the prior art, and in view of the problems existing in the above prior art, it is designed and provided with a positioning tool for the hole centers of aircraft skin openings. Its purpose is to use the tool to solve the assembly error problems caused by the original scribing positioning and multiple tool positionings, meet the assembly requirements of ducts with a flare connection to a ball head hole form, so as to improve the production efficiency and ensure the product quality.

[0004] Technical solution

[0005] An aircraft skin hole center positioning tooling, characterized in that: it includes a main body part 1a, a positioning pin 1b, a limit piece 1c, and a telescopic spring 1d; the main body part 1a is a variable-diameter cylindrical structure, one end is a flat end, and the other end is a flared end. The main body part 1a is provided with a through hole for the positioning pin 1b to pass through; a limit stop block is provided at the end of the positioning pin 1b, a limit piece 1c is provided in the middle of the positioning pin 1b, the telescopic spring 1d is sleeved on the positioning pin 1b, and is placed between the limit piece 1c and the flat end of the main body part 1a. The limit piece 1c is in threaded cooperation with the positioning pin 1b.

[0006] Furthermore, the flared end of the main body part 1a uses a flange and bolts to fix the conduit.

[0007] Furthermore, the positioning pin 1b is made of metal material, and its strength can be guaranteed.

[0008] Furthermore, the top of the positioning pin 1b is a conical structure, and the conical structure of the positioning pin 1b makes the positioning more accurate and reliable.

[0009] Furthermore, the radii of the limit piece 1c and the limit stop block should be greater than the radius of the through hole on the main body part 1a. This can ensure the constraint of the maximum and minimum strokes of the positioning pin 1b.

[0010] Furthermore, the main body part 1a and the positioning pin 1b are in clearance fit. This can better ensure the translation accuracy of the positioning pin 1b on the axis.

[0011] Technical effect

[0012] The utility model provides a method for positioning the hole center of an aircraft skin opening. The advantages are that it improves the accuracy of the opening position, avoids the accumulation of assembly errors caused by multiple positionings, thus avoiding problems in part assembly, ensures product quality, improves the product qualification rate, and effectively shortens the hole-making and assembly cycle. Brief description of the drawings

[0013] Figure 1 It is a schematic diagram of the tooling structure

[0014] Figure 2 It is a partially enlarged schematic diagram of the tooling structure;

[0015] Figure 3 It is the forward view of this tooling during use. Detailed implementation manners

[0016] As Figure 1 shown:

[0017] An aircraft skin opening hole center positioning tooling, characterized in that: it includes a main body part 1a, a positioning pin 1b, a limiting piece 1c, and a telescopic spring 1d; the main body part 1a is a variable-diameter cylindrical structure, one end is a flat end, and the other end is a flared end. The main body part 1a is provided with a through hole for the positioning pin 1b to pass through; a limiting block is provided at the end of the positioning pin 1b, a limiting piece 1c is provided in the middle of the positioning pin 1b, the telescopic spring 1d is sleeved on the positioning pin 1b, and is placed between the limiting piece 1c and the flat end of the main body part 1a, and the limiting piece 1c is in threaded cooperation with the positioning pin 1b.

[0018] Further, the flared end of the main body part 1a uses a flange and bolts to fix the conduit.

[0019] Further, the positioning pin 1b is made of a metal material, and its strength can be guaranteed.

[0020] Further, the top of the positioning pin 1b is a conical structure, and the conical structure of the positioning pin 1b makes the positioning more accurate and reliable.

[0021] Further, the radii of the limiting piece 1c and the limiting block should be greater than the radius of the through hole on the main body part 1a. It can ensure the constraint of the maximum and minimum strokes of the positioning pin 1b.

[0022] Further, the main body part 1a and the positioning pin 1b are in clearance fit. It can better ensure the translation accuracy of the positioning pin 1b on the axis.

[0023] Next, we will make a further description of the utility model through the attached Figures 1-3 Make a further description of the utility model:

[0024] The main body part 1a mainly bears the positioning pin 1b, the limiting piece 1c and the spring 1d. The outer shape of the main body part 1a is the same as the outer shape of the flared part on the conduit installed at the skin through hole. By borrowing the original movable flange with screw holes on the conduit flared part, the aircraft skin opening hole center positioning tooling is connected to the finished product pipe orifice ball head through screws. During the connection process, according to the assembly requirements, coordinate and position the concentricity of the aircraft skin opening hole center positioning tooling and the finished product pipe orifice. After the aircraft skin opening hole center positioning tooling is installed on the finished product pipe orifice, first manually compress the telescopic spring 1d on the aircraft skin opening hole center positioning tooling. By using the function of the limiting piece 1c and the rebounding function of the telescopic spring 1d, let the tip end of the positioning pin 1b punch out the corresponding hole center position of the finished product pipe orifice on the outer surface of the skin. Then remove the finished product and the aircraft skin opening hole center positioning tooling, and use the corresponding reaming tooling to ream and expand the hole on the skin according to the found center point and the drawing size requirements. In this way, it can not only eliminate the errors generated in each assembly process, but also directly avoid the waste of resources caused by resampling due to the non-concentricity between the finished product pipe orifice and the conduit orifice, greatly improving the production capacity and product quality.

[0025] The following will further elaborate on this technical solution in conjunction with the attached drawings and examples:

[0026] Refer to the attached Figures 1-3 as shown. Figure 3 It is a state diagram of the tooling during use. Figure 3 In it: 1 is the positioning tooling for the hole center of this kind of skin opening; 2 is the fuselage skin; 3 is the ball head of the finished conduit. The characteristics of this hole center positioning tooling are as follows:

[0027] During use, first put the bell mouth on the positioning tooling for the hole center of the skin opening over the ball head of the finished pipe mouth, and use the movable flange and connecting screws used during conduit connection to make a preliminary connection of the two. During the connection process, coordinate the relative positions of the bell mouth of the hole center positioning tooling and the finished ball head at any time. The relative position relationship between the two can be determined by drawing the circumferential contour line of the bell mouth of the hole center positioning tooling on the finished ball head pipe mouth. After ensuring the above assembly requirements, tighten the connecting screws and fix the finished product on the bracket on the outer surface of the aircraft. The operator manually compresses the positioning pin, borrows the spring's rebound effect and the tip effect of the positioning pin to coordinate and locate the corresponding hole center position of the finished pipe mouth on the outer surface of the fuselage skin and mark it. After completing the above operation content, remove the hole center positioning tooling, and the operator continues with the subsequent hole making and reaming work. This can not only ensure the accuracy of the opening hole position but also greatly save the waste of resources caused by the uncoordinated conduit assembly.

[0028] The above tooling adopts the original conduit connection method. By adding a hole center positioning tooling to the finished pipe mouth, on the basis of ensuring the conduit assembly requirements, the hole center position is found and the hole is opened through the way of position conversion. The operator has three steps when using it: Step 1, fix the hole center positioning tooling on the finished pipe mouth according to the assembly requirements; Step 2, find the required hole center position on the outer surface of the skin through the compression and rebound of the positioning pin; Step 3, the operator makes holes and reams the skin according to the found hole center position.

[0029] Compared with the existing technology, the tooling of the present utility model is very convenient to use and easy for the operator to master, avoiding the problem of uncoordinated assembly caused by multiple positionings. Due to the original assembly process flow, problems are only found during the final conduit installation. At this time, it can only be remedied by remanufacturing the conduit, which greatly affects the aircraft assembly cycle. The use of the hole center positioning tooling can not only avoid the assembly errors caused by multiple positionings, but also meet the assembly requirements, and at the same time improve the product qualification rate and production efficiency.

Claims

1. A hole center positioning tool for opening a hole in an aircraft skin, characterized in that: The invention comprises a main body (1a), a positioning needle (1b), a limiting plate (1c), and a telescopic spring (1d); the main body (1a) is a variable diameter cylindrical structure, one end of which is a flat end and the other end is a bell-shaped end; the main body (1a) is provided with a hole for the positioning needle (1b) to pass through; a limiting block is provided at the end of the positioning needle (1b); a limiting plate (1c) is provided in the middle of the positioning needle (1b); the telescopic spring (1d) is sleeved on the positioning needle (1b) and is placed between the limiting plate (1c) and the flat end of the main body (1a); the limiting plate (1c) and the positioning needle (1b) are threadedly matched.

2. The aircraft skin hole center positioning tool according to claim 1, characterized in that: The bell-mouth shaped end of the main body part (1a) is fixed with a conduit by a flange and bolts.

3. The aircraft skin hole center positioning tool according to claim 1, characterized in that: The positioning pin (1b) is made of metal material.

4. The aircraft skin hole center positioning tool according to claim 1, characterized in that: The top of the positioning pin (1b) is a conical structure.

5. The aircraft skin hole center positioning tool according to claim 1, characterized in that: The radius of the limiting plate (1c) and the limiting block should be greater than the radius of the through hole on the main body (1a).

6. The aircraft skin hole center positioning tool according to claim 1, characterized in that: The main body part (1a) and the positioning pin (1b) are clearance-fitted.

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