An aircraft aileron control shaft assembly jig and method of assembly

Abstract

The application provides an aircraft aileron control shaft assembling clamp and an assembling method thereof. The clamp comprises a base, a pull rod and a support assembly. The support assembly comprises a pressing block, a guide rod and a guide block. The application is matched with a broaching machine, and the aileron control shaft can be quickly replaced without disassembling the aileron joint. The pull rod is used as a force adding and guiding positioning device, and is matched with an auxiliary support to ensure the coaxiality requirement of the assembled aileron control shaft and the inner hole, and the assembling efficiency is high. The application has the characteristics of simple structure and convenient use. The application overcomes the problems of material waste and long replacement time in the prior art, improves the assembling quality and greatly improves the production efficiency.

Description

Technical Field

[0001] This invention relates to the field of aviation maintenance technology, specifically to an aircraft aileron control shaft assembly fixture and its assembly method. Background Technology

[0002] Ailerons of a certain type of aircraft Figure 1 As shown, the aileron has a relatively large external dimension and a long aileron pivot 14 that runs through the inner stiffener 17. The aileron pivot 14 is tightly fitted to the aileron connector 13 on the inner end face of the aileron. The aileron connector 13 has a control shaft mounting hole parallel to the mounting hole of the aileron pivot 14. The control shaft is installed in the control shaft mounting hole and connected to the wing through the control shaft. Due to the short control lever arm, the aileron control shaft is subjected to harsh operating environment and high stress, making it extremely prone to wear and failure. When the wear of the control shaft exceeds the tolerance, it must be replaced.

[0003] Because the interference fit between the aileron control shaft and the aileron joint control shaft mounting hole is large, the maximum assembly pressing force reaches tens of tons. Moreover, in order to ensure assembly accuracy, mainly the parallelism between the aileron control shaft and the aileron pivot, the aileron joint needs to be disassembled during the control shaft assembly. First, the aileron control shaft is pressed into the aileron joint with a press, and then the aileron joint with the aileron control shaft assembled is assembled with the aileron using a special riveting frame. This not only wastes aileron skin (aluminum plate) and rivet materials, but also requires three people to operate simultaneously for five working days to complete due to the many steps involved. The operation is cumbersome and the production efficiency is low. Summary of the Invention

[0004] To address the problems of material waste and long replacement times caused by disassembling the aileron joint during existing aircraft aileron control shaft assembly methods, this invention proposes an aircraft aileron control shaft assembly fixture and method. This method eliminates the need to disassemble the aileron joint. A dedicated assembly fixture is installed on a horizontal broaching machine to press-fit the aileron control shaft. A conformal support ensures the parallelism between the aileron control shaft and the aileron pivot during assembly. In practice, the aileron control shaft assembly can be completed in just 10 minutes (actual pressing time is 5 seconds), increasing assembly efficiency by hundreds of times, significantly saving labor and material costs, and providing high-quality and efficient assembly.

[0005] The technical solution of this invention is as follows:

[0006] The aircraft aileron control shaft assembly fixture includes a base, a pull rod, and a bracket assembly.

[0007] The base is a hollow conical structure;

[0008] The base has a through hole at the center of the large flange that matches the clearance of the tie rod, and U-shaped grooves around the perimeter that match the flange of the horizontal broaching machine for mounting the base onto the flange of the horizontal broaching machine.

[0009] The upper small flange block of the base also has a through hole, which is coaxial with the central through hole of the large flange at the bottom of the base. A bushing is fastened in the central through hole of the upper small flange block of the base. The bushing is used for clearance fit with the tie rod, and the inner diameter of the bushing is the same as the diameter of the control shaft mounting hole of the aileron connector. There are guide holes on both sides of the central through hole of the upper small flange block of the base for clearance sliding fit with the guide rod in the bracket assembly. The axis of the guide hole is parallel to the axis of the central through hole of the upper small flange block of the base. The end face of the upper small flange block of the base is perpendicular to the axis of the central through hole of the upper small flange block of the base, and the end face of the upper small flange block of the base is used to fit tightly against the control shaft mounting surface of the aileron connector.

[0010] The support assembly includes a pressure block, a guide rod, and a guide block; both the pressure block and the guide block have guide holes for cooperating with the guide rod; the center of the guide block also has a through hole that can be interference-fitted with the tie rod; the guide rod passes through the pressure block, the small flange block on the upper part of the base, and the guide hole on the guide block in sequence, and the two ends of the guide rod are axially limited by the pressure block and the guide block through stepped surfaces, and are fastened with nuts to form a support assembly, wherein the pressure block is located on the outside of the base, and the guide block is located in the middle space of the base;

[0011] One end of the pull rod is connected to the slider-type broach chuck of the horizontal broaching machine. The main body of the pull rod passes through the bushing in the center through hole of the large flange at the bottom of the base and the center through hole of the small flange block at the top of the base, and can extend into the control shaft mounting hole of the aileron connector. The main body of the pull rod is also interference-fitted with the center through hole of the guide block, so that the pull rod and the support assembly form an integral whole.

[0012] Furthermore, the large flange at the bottom of the base has a variable diameter stepped structure, wherein the smaller diameter section can be embedded in the central circular groove of the horizontal broaching machine flange to prevent the base from shifting and to ensure that the axis of the tie rod coincides with the tension axis of the broaching machine.

[0013] Furthermore, the central tapered body of the base has a through groove to form a hollow structure for the pull rod to pass through and to provide axial movement space for the guide block in the bracket assembly.

[0014] Furthermore, the part of the pull rod that is interference-fitted with the central through hole of the guide block has an annular protrusion on one side and a relief groove on the other side; and the annular protrusion is in close contact with the inner end face of the guide block, which also plays a role in force transmission.

[0015] The method for assembling the aileron control shaft using the above-mentioned fixture includes the following steps:

[0016] Step 1: Fix the base to the flange of the horizontal broaching machine, and connect the tie rod to the sliding broach chuck of the broaching machine;

[0017] Step 2: Operate the broaching machine to make the front end face of the tie rod protrude from the end face of the small flange block on the upper part of the base;

[0018] Step 3: Move the entire aircraft aileron to the front end of the broaching machine, insert the control shaft mounting hole of the aileron joint into the space between the small flange block and the pressure block on the upper part of the base, move the aileron so that the front end of the tie rod extends into the control shaft mounting hole of the aileron joint, and support the rear part of the aircraft aileron with a conformal support block.

[0019] Step 4: Insert the control shaft to be assembled into the aileron connector control shaft mounting hole from the direction of the pressure block. Operate the broaching machine to pull the pull rod so that the pressure block fits against the end face of the control shaft to be assembled. Then, the end face of the small flange block on the upper part of the base fits tightly against the aileron connector control shaft mounting surface.

[0020] Step 5: Continue to pull the lever on the broaching machine to transmit force to the pressure block, press the control shaft to be assembled into the control shaft mounting hole of the aileron joint, and complete the press-fitting of the aircraft aileron control shaft.

[0021] Step 6: Operate the broaching machine to push the lever, so that the pressure block separates from the aileron joint, and remove the aircraft aileron.

[0022] Beneficial effects

[0023] The aircraft aileron control shaft assembly fixture proposed in this invention, in conjunction with a broaching machine, enables rapid replacement of the aileron control shaft without disassembling the aileron joint. Utilizing a tie rod as a force-adding and guiding positioning device, along with auxiliary supports, ensures the coaxiality of the assembled aileron control shaft with the inner bore. This results in high assembly efficiency and features a simple structure and ease of use. This invention overcomes the problems of excessive material waste and long replacement times in existing assembly methods, improving assembly quality and significantly increasing production efficiency.

[0024] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0025] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0026] Figure 1 Aileron diagram

[0027] Figure 2 Front view of the initial working state of the fixture of the present invention

[0028] Figure 3 Figure 2 Top view

[0029] Figure 4 Figure 2 isometric drawing

[0030] Figure 5 Schematic diagram of the pressing block

[0031] Figure 6 Guide rod schematic diagram

[0032] Figure 7 Guide block schematic diagram

[0033] Figure 8 Base diagram

[0034] Figure 9 Pull rod diagram

[0035] The components include: 1. Pressure block; 2. Guide rod; 3. Bushing; 4. Guide block; 5. Base; 6. Tie rod; 7. Large nut; 8. Spring washer; 9. Shaft elastic retaining ring; 10. T-bolt; 11. Small nut; 12. Flat washer; 13. Shape-retaining support block.

[0036] 13. Connector; 14. Shaft; 15. Control shaft; 16. Outer skin; 17. Inner stiffening plate. Detailed Implementation

[0037] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0038] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0039] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0040] Figure 1The image shows an aileron of a certain type of aircraft, which has a relatively long aileron pivot 14 that runs through the inner stiffener 17. The aileron pivot 14 is tightly fitted to the aileron connector 13 on the inner end face of the aileron. The aileron connector 13 has a control shaft mounting hole parallel to the mounting hole of the aileron pivot 14. A control shaft is installed in the control shaft mounting hole and connected to the wing via the control shaft. Due to the short control lever arm, the aileron control shaft operates in a harsh environment and is subjected to high stress, making it extremely prone to wear and failure. When the dimensional wear of the control shaft exceeds the tolerance, it must be replaced.

[0041] Currently, the method of assembling aileron control shafts involves disassembling the aileron joint, pressing the aileron control shaft into the aileron joint using a press, and then assembling the aileron joint with the aileron control shaft assembled using a special riveting jig. This results in material waste and very low efficiency.

[0042] Therefore, this embodiment proposes an aircraft aileron control shaft assembly fixture and its assembly method. Without disassembling the aileron joint, a special assembly fixture is installed on a horizontal broaching machine to press-fit the aileron control shaft. The parallelism between the aileron control shaft and the aileron pivot shaft is ensured during assembly by using a conformal support.

[0043] like Figure 2 As shown, the assembly fixture includes a base, a pull rod, and a support assembly.

[0044] like Figure 8 As shown, the base has a hollow conical structure. The large flange at the bottom of the base has a through hole at its center for clearance fit with the tie rod, and U-shaped grooves around its perimeter for mounting the base onto the horizontal broaching machine flange. The upper small flange block also has a through hole, coaxial with the central through hole of the large flange at the bottom of the base. A bushing is fastened within the central through hole of the upper small flange block, and the bushing is used for clearance fit with the tie rod. The inner diameter of the bushing is the same as the diameter of the control shaft mounting hole of the aileron connector. Guide holes are located on both sides of the central through hole of the upper small flange block, for clearance sliding fit with the guide rod in the support assembly. The axis of the guide holes is parallel to the axis of the central through hole of the upper small flange block. The end face of the upper small flange block is perpendicular to the axis of the central through hole of the upper small flange block, and the end face of the upper small flange block is used to tightly contact the control shaft mounting surface of the aileron connector.

[0045] The large flange at the bottom of the base has a variable-diameter stepped structure, in which the smaller diameter section can be embedded in the central circular groove of the horizontal broaching machine flange to prevent the base from shifting and to ensure that the axis of the tie rod coincides with the tension axis of the broaching machine. The central tapered body of the base has a through groove in the center, forming a hollow structure for the tie rod to pass through and to provide axial movement space for the guide block in the support assembly.

[0046] like Figure 2 , Figure 3 and Figure 4As shown, the support assembly includes a pressure block, a guide rod, and a guide block; both the pressure block and the guide block have guide holes for cooperating with the guide rod; the center of the guide block also has a through hole that can be interference-fitted with the tie rod; the guide rod passes through the pressure block, the small flange block on the upper part of the base, and the guide hole on the guide block in sequence, and the two ends of the guide rod are axially limited by the pressure block and the guide block through stepped surfaces, and are fastened with nuts to form the support assembly, wherein the pressure block is located on the outside of the base, the guide block is located in the middle space of the base, and the guide rod slides with the guide hole of the small flange block on the upper part of the base, so that the entire support assembly can move left and right in the guide hole of the small flange block on the upper part of the base.

[0047] like Figure 2 , Figure 3 , Figure 4 as well as Figure 9 As shown, one end of the pull rod is connected to the slider-type broach chuck of the horizontal broaching machine. The main body of the pull rod passes through the bushing in the center through hole of the large flange at the bottom of the base and the center through hole of the small flange block at the top of the base, and can extend into the control shaft mounting hole of the aileron connector. It has a small clearance fit with the control shaft mounting hole of the aileron connector, which has a positioning function for the aircraft aileron. The main body of the pull rod is also interference-fitted with the center through hole of the guide block, so that the pull rod and the support assembly form an integral whole. The axis of the pull rod coincides with the tension axis of the broaching machine. The part of the pull rod that is interference-fitted with the center through hole of the guide block has an annular protrusion on one side and a tool relief groove on the other side. The tool relief groove is equipped with a shaft elastic retaining ring. The elastic retaining ring and the annular protrusion are in close contact with the two end faces of the guide block. The pull rod can drive the support to move left and right.

[0048] The method for assembling the aileron control shaft using the above-mentioned fixture includes the following steps:

[0049] Step 1: Fix the base to the horizontal broaching machine flange using T-bolts, small nuts, and flat washers; connect the tie rod to the sliding broach chuck of the broaching machine.

[0050] Step 2: Operate the broaching machine to make the front end face of the tie rod protrude 55-65 mm beyond the end face "B side" of the small flange block on the upper part of the base;

[0051] Step 3: Move the aircraft aileron as a whole to the front end of the broaching machine, insert the control shaft mounting hole of the aileron joint into the space between the small flange block and the pressure block on the upper part of the base, move the aileron so that the front end of the tie rod extends into the control shaft mounting hole of the aileron joint, position the aircraft aileron, and support the rear part of the aircraft aileron with a conformal support block.

[0052] Step 4: Insert the control shaft to be assembled into the aileron connector control shaft mounting hole from the direction of the pressure block. Operate the broaching machine to pull the pull rod so that the pressure block fits against the end face of the control shaft to be assembled. Then, the end face "B side" of the small flange block on the upper part of the base fits tightly against the mounting surface "A side" of the aileron connector control shaft.

[0053] Step 5: Continue to pull the lever on the broaching machine to transmit force to the pressure block, press the control shaft to be assembled into the control shaft mounting hole of the aileron joint, and complete the press-fitting of the aircraft aileron control shaft.

[0054] Step 6: Operate the broaching machine to push the lever, so that the pressure block separates from the aileron joint, and remove the aircraft aileron.

[0055] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. An assembly fixture for an aircraft aileron control shaft, characterized in that: Includes base, pull rod, and bracket assembly; The base is a hollow conical structure; The base has a through hole at the center of the large flange that matches the clearance of the tie rod, and U-shaped grooves around the perimeter that match the flange of the horizontal broaching machine for mounting the base onto the flange of the horizontal broaching machine. The upper small flange block of the base also has a through hole, which is coaxial with the central through hole of the large flange at the bottom of the base. A bushing is fastened in the central through hole of the upper small flange block of the base. The bushing is used for clearance fit with the tie rod, and the inner diameter of the bushing is the same as the diameter of the control shaft mounting hole of the aileron connector. There are guide holes on both sides of the central through hole of the upper small flange block of the base for clearance sliding fit with the guide rod in the bracket assembly. The axis of the guide hole is parallel to the axis of the central through hole of the upper small flange block of the base. The end face of the upper small flange block of the base is perpendicular to the axis of the central through hole of the upper small flange block of the base, and the end face of the upper small flange block of the base is used to fit tightly against the control shaft mounting surface of the aileron connector. The support assembly includes a pressure block, a guide rod, and a guide block; both the pressure block and the guide block have guide holes for cooperating with the guide rod; the center of the guide block also has a through hole that can be interference-fitted with the tie rod; the guide rod passes through the pressure block, the small flange block on the upper part of the base, and the guide hole on the guide block in sequence, and the two ends of the guide rod are axially limited by the pressure block and the guide block through stepped surfaces, and are fastened with nuts to form a support assembly, wherein the pressure block is located on the outside of the base, and the guide block is located in the middle space of the base; One end of the pull rod is connected to the slider-type broach chuck of the horizontal broaching machine. The main body of the pull rod passes through the bushing in the center through hole of the large flange at the bottom of the base and the center through hole of the small flange block at the top of the base, and can extend into the control shaft mounting hole of the aileron connector. The main body of the pull rod is also interference-fitted with the center through hole of the guide block, so that the pull rod and the support assembly form an integral whole.

2. The aircraft aileron control shaft assembly fixture according to claim 1, characterized in that: The large flange at the bottom of the base has a variable diameter stepped structure, in which the small diameter section can be embedded in the central circular groove of the horizontal broaching machine flange to prevent the base from shifting and to ensure that the axis of the tie rod coincides with the tension axis of the broaching machine.

3. The aircraft aileron control shaft assembly fixture according to claim 1, characterized in that: The central tapered body of the base has a through groove to form a hollow structure, which is used to pass through the tie rod and to provide axial movement space for the guide block in the bracket assembly.

4. The aircraft aileron control shaft assembly fixture according to claim 1, characterized in that: The middle part of the pull rod that is interference-fitted with the central through hole of the guide block has an annular protrusion on one side and a tool relief groove on the other side; a shaft elastic retaining ring is installed in the tool relief groove, and the elastic retaining ring and the annular protrusion are in close contact with the two end faces of the guide block.

5. A method for assembling an aircraft aileron control shaft using any one of the fixtures described in claims 1 to 4, characterized in that: Includes the following steps: Step 1: Fix the base to the horizontal broaching machine flange using T-bolts, small nuts, and flat washers; connect the tie rod to the sliding broach chuck of the broaching machine. Step 2: Operate the broaching machine to make the front end face of the tie rod protrude 55-65 mm beyond the end face "B side" of the small flange block on the upper part of the base; Step 3: Move the aircraft aileron as a whole to the front end of the broaching machine, insert the control shaft mounting hole of the aileron joint into the space between the small flange block and the pressure block on the upper part of the base, move the aileron so that the front end of the tie rod extends into the control shaft mounting hole of the aileron joint, position the aircraft aileron, and support the rear part of the aircraft aileron with a conformal support block. Step 4: Insert the control shaft to be assembled into the aileron connector control shaft mounting hole from the direction of the pressure block. Operate the broaching machine to pull the pull rod so that the pressure block fits against the end face of the control shaft to be assembled. Then, the end face "B side" of the small flange block on the upper part of the base fits tightly against the mounting surface "A side" of the aileron connector control shaft. Step 5: Continue to pull the lever on the broaching machine to transmit force to the pressure block, press the control shaft to be assembled into the control shaft mounting hole of the aileron joint, and complete the press-fitting of the aircraft aileron control shaft. Step 6: Operate the broaching machine to push the lever, so that the pressure block separates from the aileron joint, and remove the aircraft aileron.

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