Adjustable force setting through clamps for riveting or bolting positioning assembly of aircraft parts

Abstract

The application discloses a constant-force adjustable through-clamp for riveting or screwing positioning assembly of airplane parts, and belongs to the technical field of airplane assembly process equipment design and manufacturing. The application provides a constant-force adjustable through-clamp for riveting or screwing positioning assembly of airplane parts, which can accurately control the clamping force and effectively control the axial clamping force. The constant-force adjustable through-clamp comprises a positioning through-clamping assembly, a through-clamp operating frame and a constant-force adjusting and mounting assembly, the positioning through-clamping assembly is movably arranged on the through-clamp operating frame through the constant-force adjusting and mounting assembly; during the riveting or screwing positioning assembly of airplane parts, the clamping end of the positioning through-clamping assembly is sleeved in the riveting hole or the screwing hole of the adjacent two airplane parts to be connected, and the positioning clamping force is adjusted and transmitted to the positioning through-clamping assembly from the other end to clamp the adjacent two airplane parts through the cooperation of the through-clamp operating frame and the constant-force adjusting and mounting assembly.

Description

Technical Field

[0001] This invention relates to a mandrel with adjustable constant force, and more particularly to a mandrel with adjustable constant force for positioning and assembling aircraft parts by riveting or screwing, belonging to the field of aircraft assembly process equipment design and manufacturing technology. Background Technology

[0002] Riveting and bolting are the most common connection methods in aerospace component manufacturing. This involves creating a series of spaced holes between parts, installing rivets (for riveting) or tightening bolts to achieve a tight connection. The general assembly process involves placing the parts to be assembled in the correct position (positioning the parts), clamping them together, and drilling the necessary mounting holes according to design requirements. After removing burrs, metal shavings, and other excess material from the holes, rivets and other connectors can be installed. To ensure the airtightness, watertightness, and corrosion resistance requirements of aircraft components, some parts require a trial application of sealant to their mating surfaces. For composite materials, adhesives may be used. Ensuring the correct position of parts, identifying gaps, and appropriately filling gaps during part positioning, hole drilling, sealing, and installation are prerequisites for ensuring product manufacturing quality. Therefore, a tool is needed that can clamp and hold parts using the mounting holes of the connectors, and the clamping force should not be too large. This tool is used to detect gaps between parts and ensure the uniformity of sealant or adhesive on the mating surfaces of parts. This is especially important for long strip parts, easily deformable sheet metal or composite parts, and large areas where such quick clamping tools using holes are needed.

[0003] Currently available clamping tools such as through-hole clamps and spring pins lack a fixed force requirement. Typical through-hole clamps have very high clamping force, and the specific axial clamping force cannot be determined. During use, the clamping force relies entirely on the operator's intuition. If the clamping force is too low, gaps will exist between parts, or parts will not be in the correct positioning. If the clamping force is too high, stress assembly, deformation, or damage to parts may occur during assembly. When multiple clamping tools are used together, inconsistent clamping forces may lead to uneven thickness of sealant and adhesive on the mating surfaces. All of these situations will affect product manufacturing quality. Existing clamping methods, using through-hole clamps or C-clamps, rely on operators to fully tighten them using a wrench or by observing gaps between parts or their wobbling, making it difficult to visualize and maintain a fixed clamping force. Tightening generally involves axial rotation, converting the rotational force into axial tension / clamping force. Since axial rotational force and axial tension are not directly related, this can result in unsuitable axial tension / clamping force.

[0004] The existing technology has the following drawbacks: 1) The existing clamping mechanism cannot display the clamping force. 2) Manual tightening of the clamp results in uncontrollable clamping force; 3) The clamping force is first applied along the axis of rotation, which is then converted into an axial tension force. Since the two are not directly related, the magnitude of the axial clamping force cannot be controlled. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a mandrel with adjustable clamping force for riveting or screwing positioning assembly of aircraft parts, which can precisely control the clamping force and effectively control the magnitude of the axial clamping force.

[0006] The technical solution adopted to solve the above-mentioned technical problems is: a fixed-force adjustable through-hole clamp for positioning and assembling aircraft parts by riveting or screwing. The fixed-force adjustable through-hole clamp includes a positioning through-hole clamping assembly, a through-hole clamp operating frame, and a fixed-force adjustment mounting assembly. The positioning through-hole clamping assembly is movably arranged on the through-hole clamp operating frame through the fixed-force adjustment mounting assembly. During the riveting or screwing positioning and assembling of aircraft parts, the clamping end of the positioning through-hole clamping assembly is inserted into the riveting or screwing holes of two adjacent aircraft parts that need to be connected. The positioning clamping force is adjustablely supplied to the positioning through-hole clamping assembly from the other end through the fixed-force adjustment mounting assembly in cooperation with the through-hole clamp operating frame to clamp the two adjacent aircraft parts.

[0007] Furthermore, the mandrel operating frame consists of a mounting housing, which has mounting clamping through holes and mounting adjustment structures. The positioning mandrel clamping component and the force adjustment mounting component are respectively arranged on the mandrel operating frame in a mutually adaptive manner through the mounting clamping through holes and the mounting adjustment structures.

[0008] The preferred embodiment of the above scheme is that the mounting housing is a cylindrical mounting housing, the mounting clamping through hole is formed by the through cavity of the cylindrical mounting housing, and the mounting adjustment structure is provided at both ends of the cylindrical mounting housing; the positioning through-hole clamping assembly that penetrates the through cavity along the axial direction is arranged on the cylindrical mounting housing with adjustable clamping force under the cooperation of the constant force adjustment mounting assembly and the mounting adjustment structure.

[0009] Furthermore, the positioning through-hole clamping assembly includes at least a tongue core and a main shaft. A clamping structure is provided on the clamping end of the main shaft. The positioning through-hole clamping assembly is inserted into the through-cavity with adjustable clamping force through the main shaft in cooperation with the constant force adjustment mounting assembly and the mounting adjustment structure. The clamping structure extending out of the through-cavity is engaged with the rivet holes or screw holes of two adjacent aircraft parts in cooperation with the tongue core.

[0010] The preferred embodiment of the above scheme is that the constant force adjustment mounting assembly includes at least a mounting component group and a clamping force adjustment component group. A support section adapted to the shape and size of the through cavity is provided in the middle of the spindle. A clamping force adjustment mounting structure is provided on the spindle at the other end of the support section and in the through cavity at the corresponding position. The spindle is arranged in the through cavity through the support section. The two ends of the spindle extending out of the through cavity are respectively limited by the mounting component group and the mounting adjustment structure. The clamping force adjustment component group is arranged between the spindle at the other end of the support section and the through cavity at the corresponding position through the clamping force adjustment mounting structure.

[0011] Furthermore, the mounting assembly includes an internally threaded end cap and an internally threaded tail cap. The mounting and adjustment structure consists of connecting external threads on the outer walls of both ends of the cylindrical mounting housing. The two ends of the spindle extending through the inner cavity are respectively limited by the internally threaded end cap and the internally threaded tail cap in cooperation with the corresponding connecting external threads.

[0012] The preferred embodiment of the above scheme is that the clamping force adjustment assembly includes a shim, a constant force spring, and an indicator nut. The clamping force adjustment mounting structure includes a reduced section disposed on the main shaft at the other end of the support section, an adjustment thread disposed outside the reduced section, and an enlarged section adjustment step hole disposed in the corresponding position through the inner cavity. The shim is arranged at the bottom of the enlarged section adjustment step hole. The indicator nut, with one end extending out of the internal thread end cap, is screwed onto the main shaft outside the reduced section through the adjustment thread. The constant force spring is abutted between the shim and the indicator nut.

[0013] Furthermore, the constant force adjustment mounting assembly also includes a reset support assembly. The main shaft and the through inner cavity between the support section and the internal threaded tail cap are provided with mutually adapted reset support mounting structures. After the aircraft parts are assembled and the force is released, at least the main shaft is reset by the reset support assembly arranged in the reset support mounting structure.

[0014] The preferred embodiment of the above scheme is that the reset support assembly consists of a set of reset springs. The reset support mounting structure includes a reduced section on the main shaft and an enlarged section reset step hole at the corresponding position of the inner cavity. The reduced section is set on the main shaft between the support section and the internal threaded tail cap. The reset spring arranged in the reset step hole of the enlarged section is abutted between the step of the reduced section and the internal threaded tail cap.

[0015] Furthermore, the clamping structure includes two sets of elastic tongues and two sets of locking protrusions. The projection of each set of elastic tongues in its cross-section is arc-shaped. The two sets of locking protrusions are respectively arranged on the outer side of the free end of the two sets of elastic tongues. The clamping end of the spindle forms an arrangement hole through the two sets of elastic tongues arranged elastically inward along the circumference. The tongue core is a T-shaped push rod. The vertical side of the T-shaped push rod is located in the arrangement hole, and the horizontal side of the T-shaped push rod is located between the internal threaded end cap and one end of the return spring. One end of the return spring is abutted against the internal threaded end cap through the horizontal side. The clamping structure passing through the riveting hole or screw hole is clamped on the edge of the riveting hole or screw hole by the tongue core in cooperation with the clamping force adjustment assembly. After clamping, the clamping structure retracts and unloads by the return spring in cooperation with the tongue core.

[0016] The beneficial effects of this invention are as follows: The technical solution provided in this application sets up a fixed-force adjustable through-hole clamp, including a positioning through-hole clamping assembly, a through-hole clamp operating frame, and a fixed-force adjustment mounting assembly. The positioning through-hole clamping assembly is movably arranged on the through-hole clamp operating frame through the fixed-force adjustment mounting assembly. Then, during the positioning and assembly of aircraft parts by riveting or screwing, the clamping end of the positioning through-hole clamping assembly is fitted into the riveting or screwing holes of two adjacent aircraft parts that need to be connected. The positioning clamping force is then adjustablely delivered from the other end to the positioning through-hole clamping assembly through the fixed-force adjustment mounting assembly in cooperation with the through-hole clamp operating frame to clamp the two adjacent aircraft parts. In this way, when using the adjustable-force through-hole clamp of this application to fix two adjacent aircraft parts, the clamping force can be adjusted and determined as needed or based on the clamping force determined by prior testing through the cooperation of the fixed-force adjustment mounting component and the positioning through-hole clamping component. This effectively solves the technical problems in the prior art where the clamping force can only be judged by the operator's experience, resulting in uneven and unreliable force on the clamped parts, as well as the inability to guarantee the clamping quality. This allows for precise control of the clamping force, effectively controlling the axial clamping force, ensuring assembly quality, and ultimately reducing the risk of part deformation and damage. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the axial cross-sectional structure of the adjustable through-hole clamp for riveting or screwing positioning assembly of aircraft parts according to the present invention. Figure 2 This is a partial sectional view of the clamping part of the adjustable through-hole clamp for riveting or screwing positioning assembly of aircraft parts according to the present invention.

[0018] The markings in the diagram are as follows: 1. Through-hole clamp operating frame; 2. Aircraft part; 3. Tongue core; 4. Main shaft; 5. Support section; 6. Internal thread end cap; 7. Internal thread tail cap; 8. Washer; 9. Constant force spring; 10. Indicator nut; 11. Reduction section; 12. Enlargement section adjustment step hole; 13. Reset support assembly; 14. Elastic tongue; 15. Snap-fit ​​protrusion; 16. Arrangement hole. Detailed Implementation

[0019] like Figure 1 , Figure 2The invention illustrates a force-adjustable through-hole clamping fixture for riveting or screwing positioning assembly of aircraft parts, where the clamping force can be precisely controlled and the axial clamping force can be effectively controlled. The force-adjustable through-hole clamping fixture includes a positioning through-hole clamping assembly, a through-hole clamping operating frame 1, and a force-adjusting mounting assembly. The positioning through-hole clamping assembly is movably arranged on the through-hole clamping operating frame 1 via the force-adjusting mounting assembly. During the riveting or screwing positioning assembly of aircraft parts 2, the clamping end of the positioning through-hole clamping assembly is inserted into the riveting or screwing holes of two adjacent aircraft parts 2 that need to be connected. The positioning clamping force, through the force-adjusting mounting assembly in cooperation with the through-hole clamping operating frame 1, is adjustablely supplied from the other end to the positioning through-hole clamping assembly to clamp the two adjacent aircraft parts 2. The technical solution provided in this application involves setting up a force-adjustable through-hole clamping fixture, including a positioning through-hole clamping assembly, a through-hole clamping operating frame, and a force-adjusting mounting assembly. The positioning through-hole clamping assembly is movably arranged on the through-hole clamping operating frame through the force-adjusting mounting assembly. Then, during the positioning and assembly of aircraft parts through riveting or screwing, the clamping end of the positioning through-hole clamping assembly is fitted into the riveting or screwing holes of two adjacent aircraft parts that need to be connected. The positioning clamping force is then adjustablely supplied from the other end to the positioning through-hole clamping assembly through the force-adjusting mounting assembly in cooperation with the through-hole clamping operating frame to clamp the two adjacent aircraft parts. Thus, when using the adjustable-force through-hole clamp of this application to fix two adjacent aircraft parts, the clamping force can be adjusted and determined as needed or based on the magnitude determined by prior testing, through the cooperation of the fixed-force adjustment mounting component and the positioning through-hole clamping component. This effectively solves the technical problems in the prior art where the clamping force can only be judged based on the operator's experience, resulting in uneven and unreliable force on the clamped parts, and the inability to guarantee clamping quality. Furthermore, it allows for precise control of the clamping force, effectively controlling the magnitude of the axial clamping force, ensuring assembly quality, and ultimately reducing the risk of part deformation and damage. Correspondingly, for ease of manufacturing, structural fit, installation, and subsequent use, the through-hole clamping operating frame 1 of this application consists of a mounting shell. The mounting shell is provided with mounting clamping through holes and mounting adjustment structures. The positioning through-hole clamping component and the fixed-force adjustment mounting component are respectively arranged on the through-hole clamping operating frame 1 in a mutually adaptive manner through the mounting clamping through holes and mounting adjustment structures. The preferred embodiment is that the mounting housing is a cylindrical mounting housing, the mounting clamping through hole is formed by the through cavity of the cylindrical mounting housing, and the mounting adjustment structure is provided at both ends of the cylindrical mounting housing; the positioning through-hole clamping assembly that penetrates the through cavity along the axial direction is arranged on the cylindrical mounting housing with adjustable clamping force under the cooperation of the constant force adjustment mounting assembly and the mounting adjustment structure.

[0020] Furthermore, as a major component of this application, in order to simplify the structure to the greatest extent, facilitate manufacturing, and maximize the convenience of operation and the reliability of the constant force adjustment, the positioning through-hole clamping assembly of this application includes at least a tongue core 3 and a main shaft 4. A clamping structure is provided on the clamping end of the main shaft 4. The positioning through-hole clamping assembly is inserted into the through-cavity with adjustable clamping force through the main shaft 4 in cooperation with the constant force adjustment mounting assembly and the mounting adjustment structure. The clamping structure extending out of the through-cavity is clamped into the rivet holes or screw holes of two adjacent aircraft parts 2 in cooperation with the tongue core 3. At this time, the constant force adjustment mounting assembly includes at least a mounting component group and a clamping force adjustment component group. A support section 5 adapted to the shape and size of the through-cavity is provided in the middle of the main shaft 4. A clamping force adjustment mounting structure is provided on the main shaft at the other end of the support section and in the through-cavity at the corresponding position. The main shaft 4 is arranged in the through-cavity through the support section 5. The two ends of the main shaft 4 extending out of the through-cavity are respectively limited by the mounting component group and the mounting adjustment structure. The clamping force adjustment component group is arranged between the main shaft 4 at the other end of the support section and the through-cavity at the corresponding position through the clamping force adjustment mounting structure. More specifically, the mounting component group of this application includes an internal thread end cap 6 and an internal thread tail cap 7. The mounting adjustment structure is a connecting external thread provided on the outer wall of both ends of the cylindrical mounting housing. The two ends of the main shaft 4 extending out of the through-cavity are respectively limited by the internal thread end cap 6 and the internal thread tail cap 7 under the cooperation of the corresponding connecting external threads.

[0021] As another major improvement in this application, as described above, to maximize structural simplification, ease of manufacturing, and operational convenience and reliability of force adjustment, the clamping force adjustment assembly of this application includes a shim 8, a force spring 9, and an indicator nut 10. The clamping force adjustment mounting structure includes a reduced section 11 located on the main shaft at the other end of the support section, an adjustment thread located outside the reduced section, and an enlarged section adjustment step hole 12 located in the corresponding position through the inner cavity. The shim 8 is arranged at the bottom of the enlarged section adjustment step hole 12. The indicator nut 10, with one end extending out of the internal thread end cap 6, is screwed onto the main shaft 4 outside the reduced section 11 via the adjustment thread. The force spring 9 is abutted between the shim 8 and the indicator nut 10. At this time, the force adjustment mounting assembly also includes a reset support assembly 13. A mutually compatible reset support mounting structure is provided on the main shaft 4 between the support section 5 and the internal thread end cap 7 and on the through inner cavity. After the aircraft part 2 is assembled and the force is released, at least the main shaft 4 is reset by the reset support assembly 13 arranged in the reset support mounting structure. More specifically, the reset support assembly 13 of this application consists of a set of reset springs. The reset support mounting structure includes a reduced section 11 on the main shaft 4 and an enlarged section reset step hole at the corresponding position of the inner cavity. The reduced section 11 is disposed on the main shaft 4 between the support section 5 and the internal threaded tail cap 7. The reset spring arranged in the reset step hole of the enlarged section is abutted between the step of the reduced section 11 and the internal threaded tail cap 7.

[0022] At this time, the clamping structure includes two sets of elastic tongues 14 and two sets of locking protrusions 15. The projection of each set of elastic tongues 14 in its cross-section is arc-shaped. The two sets of locking protrusions 15 are respectively arranged on the outer side of the free end of the two sets of elastic tongues 14. The clamping end of the spindle 4 forms an arrangement hole 16 through the two sets of elastic tongues 14 arranged inwardly along the circumference. The tongue core 3 is a T-shaped top rod. The vertical side of the T-shaped top rod is located in the arrangement hole 16. The horizontal side of the T-shaped top rod is located between the internal threaded tail cap 7 and one end of the return spring. One end of the return spring is abutted on the internal threaded tail cap 7 through the horizontal side. The clamping structure passing through the rivet hole or screw hole is clamped on the edge of the rivet hole or screw hole by the tongue core 3 in cooperation with the clamping force adjustment component group. After clamping, the clamping structure is retracted and unloaded by the return spring in cooperation with the tongue core 3.

[0023] In summary, the technical solution provided in this application also has the following advantages: 1. It can improve the readability of force values ​​when positioning and clamping objects, control the magnitude of the applied force, and thus improve product quality; 2. Compared to the fixed-force C-clamp, this tool method is not limited by the clamping width; 3. Improve assembly efficiency, shorten assembly cycle, and reduce costs.

[0024] The technical solution of this application will be further described below through specific embodiments: Terminology Explanation Indicator nut: A type of nut with force values ​​marked on its surface for reading.

[0025] The technical problem to be solved by this invention is as follows: 1) When clamping an object, the magnitude of the clamping force is visualized; 2) The clamping force can be controlled when clamping an object; 3) The clamping tool is suitable for different clamping thicknesses and is efficient, convenient and universal to use.

[0026] The complete technical solution provided by this invention is as follows: 1) The principle of this invention is to utilize the elastic deformation of materials and the action and reaction forces of Newton's third law to achieve visualization of the clamping force and the functions of force setting and positioning in a hole-based clamping device. Figure 1 As shown.

[0027] 2) The usage process of this invention is the same as that of a conventional positioning pin, as illustrated below: 1. Determine the positions of the coordination holes for each part and align the holes that need to be coordinated; 2. Press the spindle with the fixed housing so that the tail end extends beyond the tongue, and pass the tail end of the spindle through the matching hole; 3. Release the spindle, reset the tail end, the tongue core supports the tail end of the spindle, and the stepped protrusion at the tail end of the spindle locks the object being supported; 4. Rotate the nut to compress the constant force spring, which in turn pushes the tail end of the housing to press against the object being clamped, applying a clamping force; 5. Once the end cap reaches the scale indicating the expected force value on the nut, stop rotating the nut to achieve the expected clamping force; 6. Fixed force clamping completed.

Claims

1. A mandrel clamp with adjustable force for riveting or screwing positioning assembly of aircraft parts, characterized in that: The adjustable-force mandrel includes a positioning mandrel clamping assembly, a mandrel operating frame (1), and a force adjustment mounting assembly. The positioning mandrel clamping assembly is movably arranged on the mandrel operating frame (1) through the force adjustment mounting assembly. The positioning through-hole clamping assembly includes at least a tongue core (3) and a main shaft (4). A clamping structure is provided on the clamping end of the main shaft (4). The positioning through-hole clamping assembly is inserted into the through-cavity with adjustable clamping force through the main shaft (4) in cooperation with the constant force adjustment mounting assembly and the mounting adjustment structure. The clamping structure extending out of the through-cavity is clamped into the rivet holes or screw holes of two adjacent aircraft parts (2) in cooperation with the tongue core (3). The constant force adjustment mounting assembly includes at least a mounting component group and a clamping force adjustment component group. A support section (5) adapted to the shape and size of the through cavity is provided in the middle of the main shaft (4). A clamping force adjustment mounting structure is provided on the main shaft at the other end of the support section and in the through cavity at the corresponding position. The main shaft (4) is arranged in the through cavity through the support section (5). The two ends of the main shaft (4) extending out of the through cavity are respectively limited by the mounting component group and the mounting adjustment structure. The clamping force adjustment component group is arranged between the main shaft (4) at the other end of the support section and the through cavity at the corresponding position, with adjustable clamping force through the clamping force adjustment mounting structure. The mounting assembly includes an internally threaded end cap (6) and an internally threaded tail cap (7). The mounting and adjustment structure consists of connecting external threads on the outer walls of both ends of the cylindrical mounting housing. The two ends of the main shaft (4) extending through the inner cavity are respectively limited by the internally threaded end cap (6) and the internally threaded tail cap (7) under the engagement of the corresponding connecting external threads. The clamping force adjustment assembly includes a shim (8), a constant force spring (9), and an indicator nut (10). The clamping force adjustment mounting structure includes a reduced section (11) located on the main shaft at the other end of the support section, an adjustment thread located outside the reduced section, and an enlarged section adjustment step hole (12) located in the corresponding position and penetrating the inner cavity. The shim (8) is arranged at the bottom of the enlarged section adjustment step hole (12). The indicator nut (10), with one end extending out of the internal thread end cap (6), is screwed onto the main shaft (4) outside the reduced section (11) through the adjustment thread. The constant force spring (9) is abutted between the shim (8) and the indicator nut (10). The constant force adjustment mounting assembly also includes a reset support assembly (13). A mutually compatible reset support mounting structure is provided on the main shaft (4) between the support section (5) and the internal threaded tail cap (7) and on the through-cavity. After the aircraft part (2) is assembled and the force is released, at least the main shaft (4) is reset by the reset support assembly (13) arranged in the reset support mounting structure. The clamping structure includes two sets of elastic tongues (14) and two sets of locking protrusions (15). The projection of each set of elastic tongues (14) in its cross-section is arc-shaped. The two sets of locking protrusions (15) are respectively arranged on the outer side of the free end of the two sets of elastic tongues (14). The clamping end of the spindle (4) forms an arrangement hole (16) through the two sets of elastic tongues (14) arranged elastically inward along the circumference. The tongue core (3) is a T-shaped top rod. The vertical edge of the rod is located in the arrangement hole (16), and the horizontal edge of the T-shaped top rod is located between the internal thread tail cap (7) and one end of the return spring. One end of the return spring is abutted on the internal thread tail cap (7) through the horizontal edge. The clamping structure passing through the rivet hole or screw hole is clamped on the edge of the rivet hole or screw hole by the tongue core (3) in cooperation with the clamping force adjustment assembly. After clamping, the clamping structure retracts and unloads by the return spring in cooperation with the tongue core (3).

2. The adjustable-force through-hole clamp for riveting or screwing positioning assembly of aircraft parts according to claim 1, characterized in that: The through-hole clamp operating frame (1) consists of a mounting housing. The mounting housing is provided with mounting clamping through holes and mounting adjustment structures. The positioning through-hole clamping component and the force adjustment mounting component are respectively arranged on the through-hole clamp operating frame (1) in a mutually adaptive manner through the mounting clamping through holes and the mounting adjustment structures.

3. The adjustable-force through-hole clamp for riveting or screwing positioning assembly of aircraft parts according to claim 2, characterized in that: The mounting housing is a cylindrical mounting housing. The mounting clamping through hole is formed by the through cavity of the cylindrical mounting housing. Mounting adjustment structures are respectively provided at both ends of the cylindrical mounting housing. The positioning through-hole clamping assembly that runs through the through cavity along the axial direction is arranged on the cylindrical mounting housing with adjustable clamping force under the cooperation of the fixed force adjustment mounting assembly and the mounting adjustment structure.

4. The adjustable-force through-hole clamp for riveting or screwing positioning assembly of aircraft parts according to any one of claims 1 to 3, characterized in that: The reset support assembly (13) consists of a set of reset springs. The reset support mounting structure includes a reduced section (11) on the main shaft (4) and an enlarged section reset step hole at the corresponding position of the inner cavity. The reduced section (11) is set on the main shaft (4) between the support section (5) and the internal threaded tail cap (7). The reset spring arranged in the reset step hole of the enlarged section is abutted between the step of the reduced section (11) and the internal threaded tail cap (7).

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