Strain type orthopedic force sensor for aircraft panel assembly

Abstract

The invention discloses a strain type shape righting force sensor for aircraft panel assembly, and belongs to the technical field of tool installation and detection.The strain type shape righting force sensor comprises a first screw rod, a through hole penetrating through the two ends of the first screw rod is formed in the center of the first screw rod, and a sensing assembly is arranged at one end of the first screw rod; the sensing assembly comprises a first plate body connected with the end of the first screw, and a strain gauge is arranged between the first plate body and the first screw. According to the invention, the in-situ monitoring of the shape righting force is realized, the problem that the existing sensor cannot carry out accurate measurement under the working conditions of large force value and long-time static loading is solved, the real-time measurement requirements of shape righting tension and pressure of multiple loading points of a large aircraft component are met, and the assembly precision and efficiency are ensured.

Description

Technical Field

[0001] This invention relates to the field of tooling installation and testing technology, and specifically to a strain-type straightening force sensor for aircraft panel assembly. Background Technology

[0002] In the aerospace manufacturing field, composite materials, due to their advantages such as lightweight, high strength, and corrosion resistance, have been widely used in the manufacture of key components such as aircraft panels. However, during the curing process, composite components are prone to irreversible curing deformation due to the release of internal stress, leading to deviations between their actual dimensions and design specifications. Therefore, during the assembly stage of aircraft panels, precise corrective forces must be applied at multiple loading points to correct the composite components to the assembly requirements. In current assembly technologies, force sensors and corrective force loading devices are placed separately, posing a risk of relative movement and thus preventing accurate in-situ measurements. Furthermore, piezoelectric sensors are widely used in force measurement, but these are more suitable for small force values ​​and high dynamic range measurements. For long-term, static, or quasi-static tests, they suffer from low accuracy and large drift; for this reason, sensor calibration under static conditions is difficult. In addition, the area of ​​the corrective force loading points is generally small, making it difficult for piezoelectric sensors to achieve a large range in small areas or spaces. Moreover, piezoelectric sensors widely use semiconductor materials, resulting in high individual costs and making them unsuitable for assembling large components with a large number of loading points.

[0003] For existing problems, there are already relevant technical solutions, such as the prior art patent KR102571451B1, which discloses a method for manufacturing composite material pressure vessels. This composite material pressure vessel is equipped with sensors, particularly strain sensors, for monitoring the structural integrity of the pressure vessel. The method includes the following steps: preparing a bushing with an inlet portion; and forming an inner shell by winding at least one composite filament around the liner. In the step of forming the inner shell, by changing the starting position of each of the multiple enameled wire strain sensors manufactured in the form of filaments as they begin to be wound onto the liner, each enameled wire strain sensor can be simultaneously wound onto the liner together with the composite filament. Further manufacturing of composite material pressure vessels using the above method is possible, but currently, there is no existing technology suitable for applications with a large number of loading points and high measurement accuracy. Summary of the Invention

[0004] The purpose of this invention is to provide a strain-type orthopedic force sensor for aircraft panel assembly, which enables in-situ monitoring of orthopedic force, solves the problem that existing sensors cannot accurately measure under high force and long-term static loading conditions, meets the real-time measurement requirements of orthopedic tension and pressure at multiple loading points of large aircraft components, and ensures assembly accuracy and efficiency.

[0005] To solve the above-mentioned technical problems, the present invention specifically provides the following technical solution: a strain-type orthostatic force sensor for aircraft panel assembly, comprising a first screw, a through hole at the center of the first screw extending through both ends thereto, a sensing component at one end of the first screw, the sensing component comprising a first plate connected to the end of the first screw, and a strain gauge between the first plate and the first screw. The connection between the first plate and the first screw can be by welding, such as argon arc welding, or other connection methods. The first plate and the first screw are connected by high-strength methods such as argon arc welding, which can prevent relative movement between the two and solve the problem of inaccurate in-situ measurement of traditional split sensors. The central through hole of the first screw of this invention can be adapted to the connecting rod, which facilitates stable connection with the assembly tooling and ensures that the straightening force is transmitted along the screw axis, avoiding force loss. The strain gauge between the first plate and the first screw can directly sense the deformation of the component under force and efficiently convert the force value into an electrical signal. It is suitable for the static / quasi-static working conditions of aircraft panel assembly, with high measurement accuracy and no signal drift. At the same time, the overall structure has a high degree of integration and can be adapted to the compact assembly space with multiple loading points.

[0006] According to one embodiment of the present invention, a spring is provided in the middle of the first plate. When the spring in the middle of the first plate is subjected to force, it can produce controllable surface deformation, avoiding measurement deviation caused by overall rigid deformation of the first plate, and providing a deformation feedback basis for the strain gauge between the first plate and the first screw.

[0007] According to one embodiment of the present invention, the first plate has a positioning hole in the middle. The positioning hole in the middle of the first plate is adapted to loading components such as suction cup assembly and pressure assembly to prevent the components from shifting during loading, ensure that the straightening force acts perpendicularly on the spring in the middle of the first plate, avoid uneven deformation of the spring due to off-center loading, provide stable deformation feedback for the strain gauge between the first plate and the first screw, improve the accuracy of electrical signal conversion, and is suitable for static / quasi-static measurement of aircraft panels without drift.

[0008] According to one embodiment of the present invention, there are an even number of strain gauges between the first plate and the first screw, and the strain gauges are attached to the spring sheet. There are four strain gauges between the first plate and the first screw, and the strain gauges are arranged in groups of four to form a full-bridge circuit. The strain gauges are attached to the spring sheet with two 0° and two 90° angles. Specifically, two strain gauges are arranged on each side of the positioning hole, and these two strain gauges are arranged adjacently, with one at 0° and the other at 90°.

[0009] The four strain gauges between the first plate and the first screw form a full-bridge circuit, which can cancel out external interference such as temperature and vibration. Compared with single / half-bridge circuits, it greatly improves measurement stability, is suitable for static / quasi-static conditions in aircraft panel assembly, and has no signal drift. The strain gauges are attached to the spring in the middle of the first plate with two 0° and two 90° angles. The 0° strain gauge can capture the axial deformation of the spring, and the 90° strain gauge can simultaneously sense the lateral deformation, thus improving the accuracy of electrical signal conversion. In addition, there are two strain gauges on each side of the positioning hole, adjacent to each other at 0° and 90°. Together with the positioning hole, the positioning constraint of the loading component is used to ensure that the spring deforms uniformly after being stressed, avoiding local deformation deviation caused by off-center loading.

[0010] According to one embodiment of the present invention, a second hole is provided on the through hole at the end of the first screw where the sensing component is located, and a first hole is provided at the other end. The second hole is a smooth hole, and the first hole is a threaded hole. The first hole at the other end of the first screw is used to adapt to detachable components such as the first connector, flexibly docking with assembly fixtures, and can also adjust the connection length by thread to adapt to different aircraft panel assembly spaces. The second hole at the end where the sensing component is located helps to reduce force transmission jamming, ensuring that the corrective force is accurately transmitted to the first plate along the axial direction of the through hole, and then acts on the central spring, avoiding force loss.

[0011] According to one embodiment of the present invention, a first connector is detachably connected to the first hole. The first connector is a cylindrical structure with threads on its outer wall that are adapted to the threaded hole of the first hole. A light hole is correspondingly provided on the first screw and the first connector, and the light hole on the first screw and the light hole on the first connector are coaxial. A light rod or other component can be inserted into the light hole. The first hole and the first connector are detachably screwed together, allowing for flexible replacement of first connectors of different sizes according to the specifications of the traction unit of the aircraft panel assembly tooling, improving the sensor's adaptability to different tooling. Simultaneously, the first connector can be precisely controlled by adjusting the depth of its screwing into the first hole, in conjunction with the second hole of the first screw and the light rod inserted through the coaxial light hole, to adapt to the straightening requirements of panels of different thicknesses.

[0012] According to one embodiment of the present invention, the outer wall of the first screw is provided with an external thread. The external thread enables the first screw to be stably screwed to the assembly fixture, preventing relative movement between the sensor and the fixture when the corrective force is applied, thus solving the problem of inaccurate in-situ measurement of traditional split sensors; moreover, the screwing depth can be flexibly adjusted to adapt to the spacing between different aircraft panels and fixtures, improving spatial adaptability. At the same time, the external thread, in conjunction with the first connecting piece inside the first hole, can bidirectionally adjust the position of the force application, ensuring that the corrective force is accurately transmitted along the axial direction of the first screw to the first plate of the sensing component, and then acts on the central spring, ensuring uniform deformation of the spring.

[0013] According to one embodiment of the present invention, a suction cup assembly is detachably connected to a sensing component at the bottom of the first screw. The suction cup assembly includes a suction cup body, a first connecting rod on the suction cup body, a first ball head at the end of the first connecting rod, and a suction cup at the bottom of the suction cup body. The sensing component at the bottom of the first screw is detachably connected to the suction cup assembly, thus allowing for the replacement of suction cups with different adsorption forces according to the material of the aircraft composite panel and the adsorption requirements, adapting to various assembly scenarios. Furthermore, partial damage does not require complete scrapping, reducing maintenance costs. When the first ball head at the end of the first connecting rod of the suction cup body penetrates the positioning hole of the first plate, it can adapt to small angular deviations, avoiding uneven loading and ensuring that the corrective force is vertically transmitted to the spring, guaranteeing uniform deformation of the spring. Simultaneously, the suction cup can firmly adsorb the panel, preventing it from falling off during static / quasi-static pulling. Combined with the stable connection between the external thread of the first screw, the first hole, and the first connecting member, this solves the problem of inaccurate in-situ measurements by traditional split-type sensors.

[0014] According to one embodiment of the present invention, a first screw hole is provided at the center of the upper end of the suction cup body, and a first connecting rod is threadedly connected to the first screw hole. In the assembled state, the first ball head is placed in the space between the first plate and the first screw, that is, the first connecting rod passes through the positioning hole and is connected to the first screw hole. The first screw hole at the center of the upper end of the suction cup body is threadedly connected to the first connecting rod, and the extension length of the first connecting rod can be adjusted by rotation to adapt to the spacing of different aircraft panels and sensing components. The threaded connection ensures that there is no loosening during pulling, and ensures that the pulling force is stably transmitted to the first ball head at the end of the first connecting rod. In the assembled state, the first ball head is placed between the first plate and the first screw. With the help of the positioning hole of the first plate, it can adapt to small angular deviations, avoid uneven loading, and allow the pulling force to act perpendicularly on the spring in the middle of the first plate, ensuring uniform deformation of the spring. At the same time, this structure facilitates the disassembly and replacement of the first connecting rod or the suction cup body. Local damage does not require the entire body to be scrapped, reducing maintenance costs.

[0015] According to one embodiment of the present invention, a pressure assembly is detachably connected to a sensing component at the bottom of the first screw. The pressure assembly includes a pressure column, and a protective sleeve is fitted over the bottom of the pressure column. The protective sleeve is a silicone protective sleeve that can cover the bottom surface and the bottom part of the side surface of the pressure column. The sensing component at the bottom of the first screw is detachably connected to the pressure assembly, so that the suction cup assembly and the pressure assembly can be switched according to usage requirements. The pressure column of the pressure assembly can be precisely positioned in conjunction with the positioning hole of the first plate to ensure that the orthopedic pressure is vertically transmitted to the spring in the middle of the first plate, avoiding uneven deformation of the spring due to off-center loading. In addition, the protective sleeve at the bottom of the pressure column can directly contact the composite wall panel to prevent scratches on the surface of the wall panel during pressurization and protect the integrity of the composite components.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: The first screw of the present invention, in cooperation with the sensing component and the suction cup / pressurization component, solves the problem of relative movement of the split sensor, realizing in-situ accurate measurement of the corrective force; and the external thread on the outer wall of the first screw allows for flexible adjustment of the screwing depth with the tooling, the detachable first connector in the first hole can adapt to different tooling traction units, and the pulling / pressurization stroke can be controlled by adjusting the screwing depth to adapt to different thicknesses of the wall plate, and the positioning hole of the first plate and the first ball head of the suction cup component can prevent load offset and adapt to small angles to avoid off-center loading. The solution of the present invention is more suitable for high force values ​​and long-term static or quasi-static testing, and its good linearity makes it easier to calibrate and adjust, which better meets the working conditions requirements of aircraft component assembly compared with the prior art. Attached Figure Description

[0017] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the assembly of the first screw and suction cup assembly of the present invention; Figure 2 This is a schematic diagram of the suction cup assembly of the present invention; Figure 3 This is a cross-sectional view of the first screw of the present invention in a first direction; Figure 4 This is a cross-sectional view of the first screw of the present invention in a second direction; Figure 5 This is a schematic diagram of the sensing component scheme of the present invention; Figure 6 This is the wiring diagram of the strain gauge of the present invention; Figure 7 This is a cross-sectional view of the suction cup assembly of the present invention; Figure 8 This is a schematic diagram of the second connecting rod scheme of the present invention; Figure 9 This is a schematic diagram of the assembly of the first screw and the pressurizing component of the present invention; Figure 10 This is a schematic diagram of the connection scheme between the pressure column and the protective sleeve of the present invention; Figure 11 This is a cross-sectional view of the pressurization component of the present invention.

[0019] Explanation of reference numerals in the attached drawings: 10. First screw; 11. External thread; 12. First hole; 13. Through hole; 14. Second hole; 20. Sensing component; 21. First plate; 22. Spring; 23. Positioning hole; 24. Strain gauge; 30. First connector; 40. Suction cup assembly; 41. Suction cup body; 42. First connecting rod; 43. First ball head; 44. Suction cup; 45. First screw hole; 46. Second connecting rod; 50. Pressurizing component; 51. Pressurizing column; 52. Protective sleeve. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] The concepts involved in this application will first be described with reference to the accompanying drawings. It should be noted that the following descriptions of various concepts are only for the purpose of making the content of this application easier to understand and do not constitute a limitation on the scope of protection of this application; furthermore, the embodiments and features in the embodiments of this application can be combined with each other unless otherwise specified. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] Example 1: As shown in the attached figure Figure 1 - Appendix Figure 7 and appendix Figure 9 - Appendix Figure 11 As shown, a strain gauge-type orthotic force sensor for aircraft panel assembly includes a first screw 10 with a through hole at its center extending through both ends. A sensing assembly 20 is located at one end of the first screw 10. The sensing assembly 20 includes a first plate 21 connected to the end of the first screw 10, and a strain gauge 24 is positioned between the first plate 21 and the first screw 10. The connection between the first plate 21 and the first screw 10 can be achieved by welding, such as argon arc welding, or by other connection methods. The first plate 21 and the first screw 10 are connected by high-strength methods such as argon arc welding, which can prevent relative movement between the two and solve the problem of inaccurate in-situ measurement of traditional split sensors. The central through hole of the first screw 10 of this invention can be adapted to the connecting rod, which facilitates stable connection with the assembly tooling and ensures that the straightening force is transmitted along the screw axis, avoiding force loss. Among them, the strain gauge 24 between the first plate 21 and the first screw 10 can directly sense the deformation of the component under force and efficiently convert the force value into an electrical signal, which is suitable for the static / quasi-static working conditions of aircraft panel assembly. It has high measurement accuracy and no signal drift. At the same time, the overall structure has high integration and can be adapted to the compact assembly space with multiple loading points.

[0023] This invention features a simple structure and is easy to manufacture. The main components can be machined by turning, wire cutting, and welding, requiring minimal assembly. Similar products applicable to aircraft assembly typically cost 500 yuan or more, while the cost of this invention is estimated to be only 10% to 20% of other similar products. The sensing component 20 can deform in both directions under tension or pressure, thus a single element can output pressure or tension signals. Furthermore, it includes tension and pressure loading components, which are non-rigidly connected to the sensor body, facilitating disassembly, replacement, and adjustment according to operating conditions.

[0024] This invention employs the principle of a strain gauge sensor, whose measurement range is solely dependent on the material of the sensing component 20. A higher elastic modulus results in a larger measurement range, and its creep is negligible. It exhibits almost no drift under prolonged loading, thus meeting the requirements for large range and long-term loading during assembly. Furthermore, this invention combines the first screw 10 and the sensing component 20, and incorporates a built-in positioning function, enabling in-situ measurement of corrective forces during assembly without the need for external sensors or accessories. It also ensures that the position of tensile and compressive loads does not shift.

[0025] The first plate 21 has a spring 22 in its middle. When subjected to force, the spring 22 in the middle of the first plate 21 can produce controllable surface deformation, avoiding measurement deviation caused by the overall rigid deformation of the first plate 21, and providing a deformation feedback basis for the strain gauge 24 between the first plate 21 and the first screw 10. The first plate 21 is made of a metal with high elastic modulus and good linearity, and can be directly calibrated using equipment such as a spring scale for force-voltage signal calibration.

[0026] The first plate 21 has a positioning hole 23 in the middle. The diameter of the positioning hole 23 can be φ5mm, or other sizes. The positioning hole 23 in the middle of the first plate 21 is adapted to loading components such as the suction cup assembly 40 and the pressure assembly 50 to prevent the components from shifting during loading, ensuring that the straightening force acts perpendicularly on the spring 22 in the middle of the first plate 21, avoiding uneven deformation of the spring 22 due to off-center loading, providing stable deformation feedback for the strain gauge 24 between the first plate 21 and the first screw 10, improving the accuracy of electrical signal conversion, and adapting to static / quasi-static measurement of aircraft panels without drift.

[0027] There are an even number of strain gauges 24 between the first plate 21 and the first screw 10, and the strain gauges 24 are attached to the spring sheet 22. There are four strain gauges 24 between the first plate 21 and the first screw 10. The four strain gauges 24 form a full-bridge circuit, which can cancel out external interference such as temperature and vibration. Compared with single / half-bridge circuits, it greatly improves measurement stability, is suitable for static / quasi-static conditions of aircraft panel assembly, and has no signal drift.

[0028] The first screw 10 has a second hole 14 on the through hole at the end with the sensing component 20, and a first hole 12 at the other end. The second hole 14 is a smooth hole, and the first hole 12 is a threaded hole. The first hole 12 at the other end of the first screw 10 is used to adapt to detachable components such as the first connector 30, flexibly docking with assembly fixtures. It can also adjust the connection length through the thread to adapt to different aircraft panel assembly spaces. The second hole 14 at the end with the sensing component 20 helps to reduce force transmission jamming, ensuring that the corrective force is accurately transmitted along the axis of the through hole to the first plate 21, and then acts on the central spring 22, avoiding force loss.

[0029] A first connector 30 is detachably connected within the first bore 12. The first connector 30 is a cylindrical structure with threads on its outer wall that match the threaded hole of the first bore 12. A light hole 13 is correspondingly provided on the first screw 10 and the first connector 30, and the light holes 13 on the first screw 10 and the first connector 30 are coaxial. A light rod or other components can be inserted into the light hole 13. The first bore 12 and the first connector 30 are detachably screwed together, allowing for flexible replacement of different sizes of the first connector 30 according to the specifications of the traction unit of the aircraft panel assembly tooling. This improves the sensor's adaptability to different tooling. Furthermore, by adjusting the depth of the first connector 30 screwed into the first bore 12, in conjunction with the second bore 14 of the first screw 10 and the light rod inserted into the light hole 13, the pulling or pressing stroke can be precisely controlled to adapt to the straightening requirements of panels of different thicknesses.

[0030] The outer wall of the first screw 10 is provided with an external thread 11. The external thread 11 enables the first screw 10 to be stably screwed into the assembly fixture, preventing relative movement between the sensor and the fixture when the corrective force is applied, thus solving the problem of inaccurate in-situ measurement of traditional split sensors; moreover, the screwing depth can be flexibly adjusted to adapt to the spacing between different aircraft panels and fixtures, improving spatial adaptability. At the same time, the external thread 11, in conjunction with the first connector 30 in the first hole 12, can adjust the position of the force value in both directions, ensuring that the corrective force is accurately transmitted along the axial direction of the first screw 10 to the first plate 21 of the sensing assembly 20, and then acts on the central spring 22, ensuring uniform deformation of the spring 22.

[0031] The sensing component 20 at the bottom of the first screw 10 is detachably connected to a suction cup assembly 40. The suction cup assembly 40 includes a suction cup body 41, a first connecting rod 42 on the suction cup body 41, a first ball head 43 at the end of the first connecting rod 42, and a suction cup 44 at the bottom of the suction cup body 41. The sensing component 20 at the bottom of the first screw 10 is detachably connected to the suction cup assembly 40, so that suction cups 44 with different adsorption forces can be replaced according to the material of the aircraft composite panel and the adsorption requirements, adapting to various assembly scenarios. Moreover, in case of partial damage, the entire assembly does not need to be scrapped, reducing maintenance costs. When the first ball head 43 at the end of the first connecting rod 42 of the suction cup body 41 enters the positioning hole 23 of the first plate 21, it can adapt to small angular deviations, avoid uneven loading, and ensure that the corrective force is transmitted vertically to the spring 22, ensuring uniform deformation of the spring 22. Meanwhile, the suction cup 44 can firmly adhere to the wall panel, preventing it from falling off during static / quasi-static pulling. Combined with the stable connection between the external thread 11 of the first screw 10, the first hole 12 and the first connector 30, it solves the problem of inaccurate in-situ measurement of traditional split-type sensors.

[0032] A first screw hole 45 is provided at the center of the upper end of the suction cup body 41, and the first connecting rod 42 is threadedly connected to the first screw hole 45. In the assembled state, the first ball head 43 is placed in the space between the first plate 21 and the first screw 10, that is, the first connecting rod 42 passes through the positioning hole 23 and is connected to the first screw hole 45. The first screw hole 45 at the center of the upper end of the suction cup body 41 is threadedly connected to the first connecting rod 42, and the extension length of the first connecting rod 42 can be adjusted by rotation to adapt to the spacing between different aircraft panels and sensing components 20. The threaded connection ensures that there is no loosening during pulling, and ensures that the pulling force is stably transmitted to the first ball head 43 at the end of the first connecting rod 42. In the assembled state, the first ball head 43 is placed between the first plate 21 and the first screw 10. With the help of the positioning hole 23 of the first plate 21, it can adapt to small angular deviations, avoid uneven loading, and allow the pulling force to act perpendicularly on the spring 22 in the middle of the first plate 21, ensuring that the spring 22 deforms uniformly. Meanwhile, this structure facilitates the disassembly and replacement of the first connecting rod 42 or the suction cup body 41, eliminating the need for complete scrapping if only a part is damaged, thus reducing maintenance costs.

[0033] During the application of tension, the suction cup 44 adheres to the workpiece to provide tension, while the tension sensing component 20 undergoes elastic deformation, thereby generating a voltage signal in the full-bridge circuit that reflects the tension.

[0034] A pressure assembly 50 is detachably connected to the sensing component 20 at the bottom of the first screw 10. The pressure assembly 50 includes a pressure column 51, and a protective sleeve 52 is fitted over the bottom of the pressure column 51. The protective sleeve 52 is a silicone protective sleeve that covers the bottom surface and part of the bottom side of the pressure column 51. The pressure column 51 is a magnetic column or has a magnetic end. The pressure column 51 is detachably connected to the sensing component 20 at the bottom of the first screw 10. Specifically, the positioning hole 23 of the pressure column 51 and the sensing component 20 has a ball-head structure, and this ball-head structure has magnetic attraction that can attract and partially engage with the positioning hole 23 of the first plate 21. The diameter of the ball-head portion of the pressure column 51 can be φ8mm, or other sizes.

[0035] The sensing component 20 at the bottom of the first screw 10 is detachably connected to the pressure component 50, so that the suction cup component 40 and the pressure component 50 can be switched according to the usage requirements. The pressure column 51 of the pressure component 50 can be precisely positioned in conjunction with the positioning hole 23 of the first plate 21 to ensure that the orthopedic pressure is vertically transmitted to the spring 22 in the middle of the first plate 21, avoiding uneven deformation of the spring 22 due to off-center loading. In addition, the protective sleeve 52 at the bottom of the pressure column 51 can directly contact the composite wall panel to prevent scratches on the surface of the wall panel during pressure application and protect the integrity of the composite components.

[0036] Example 2: See appendix Figure 5 Appendix Figure 6 As shown, strain gauges 24 are attached to the spring sheet 22 with two 0° angles and two 90° angles. Specifically, two strain gauges 24 are arranged on each side of the positioning hole 23, adjacent to each other, with one at 0° and the other at 90°. See Appendix Figure 6 The diagram shown is the wiring diagram of strain gauge 24, where U in As the excitation signal, U out For output signal. Strain gauges 24 are attached to the spring sheet 22 in the middle of the first plate 21 with two 0° and two 90° angles. The 0° strain gauge 24 can capture the axial deformation of the spring sheet 22, and the 90° strain gauge 24 can simultaneously sense the lateral deformation, thus improving the accuracy of electrical signal conversion. In addition, there are two strain gauges 24 on each side of the positioning hole 23, adjacent to each other at 0° and 90°. Together with the positioning hole 23, the positioning constraint of the loading component is ensured to ensure that the spring sheet 22 deforms uniformly after being subjected to force, avoiding local deformation deviation caused by off-center loading.

[0037] Example 3: See appendix Figure 8 As shown, in application scenarios where the length of the first connecting rod 42 is insufficient, see Appendix Figure 7 Appendix Figure 8As shown, the problem is solved by adding a second connecting rod 46. A screw hole is opened at the center of the bottom of the first connecting rod 42. One end of the second connecting rod 46 is connected to the screw hole at the bottom of the first connecting rod 42, and the other end is connected to the first screw hole 45.

[0038] It should also be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application 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, and therefore should not be construed as a limitation on this application. Unless otherwise expressly specified and limited, the terms "installed," "connected," "linked," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0039] The embodiments and / or implementation methods described above are merely preferred embodiments and / or implementation methods for implementing the technology of the present invention, and are not intended to limit the implementation methods of the technology of the present invention in any way. Any person skilled in the art can make some modifications or alterations to other equivalent embodiments without departing from the scope of the technical means disclosed in the content of the present invention, but they should still be regarded as the technology or embodiments that are substantially the same as the present invention.

[0040] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A strain type orthopaedic force sensor for aircraft panel assembly comprising a first screw (10) having a through hole in its center passing through both ends thereof, characterized in that, The first screw (10) has a sensing component (20) at one end. The sensing component (20) includes a first plate (21) connected to the end of the first screw (10). A strain gauge (24) is located between the first plate (21) and the first screw (10).

2. A strain gauge orthotic force sensor for use in the assembly of aircraft panels according to claim 1, wherein, The first plate (21) has a spring (22) in the middle.

3. A strain gauge orthotic force sensor for use in the assembly of aircraft panels according to claim 1, wherein, The first plate (21) has a positioning hole (23) in the middle.

4. A strain gauge orthotic force sensor for use in the assembly of aircraft panels according to claim 2, wherein, The number of strain gauges (24) between the first plate (21) and the first screw (10) is even, and the strain gauges (24) are attached to the spring sheet (22).

5. A strain gauge orthotic force sensor for use in the assembly of aircraft panels according to claim 1, wherein, The first screw (10) has a second hole (14) on the through hole at the end of the sensing component (20) and a first hole (12) at the other end.

6. A strain gauge orthotic force sensor for use in the assembly of aircraft panels according to claim 5, wherein, The first connector (30) is detachably connected inside the first hole (12).

7. A strain-type corrective force sensor for aircraft panel assembly according to claim 1, characterized in that, The outer wall of the first screw (10) is provided with an external thread (11).

8. A strain-type corrective force sensor for aircraft panel assembly according to claim 1, characterized in that, The sensing component (20) at the end of the first screw (10) is detachably connected to a suction cup assembly (40). The suction cup assembly (40) includes a suction cup body (41), a first connecting rod (42) is provided on the suction cup body (41), a first ball head (43) is provided at the end of the first connecting rod (42), and a suction cup (44) is provided at the bottom of the suction cup body (41).

9. A strain-type corrective force sensor for aircraft panel assembly according to claim 8, characterized in that, The suction cup body (41) has a first screw hole (45) at the center of its upper end, and the first connecting rod (42) is threadedly connected to the first screw hole (45).

10. A strain-type corrective force sensor for aircraft panel assembly according to claim 1, characterized in that, The sensing component (20) at the end of the first screw (10) is detachably connected to a pressurizing component (50), which includes a pressurizing column (51) and a protective sleeve (52) is fitted at the bottom of the pressurizing column (51).

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