A bending test device and test method

Abstract

This invention relates to the field of aircraft manufacturing technology and discloses a bending test apparatus and method. The bending test apparatus includes: a fixing component, comprising a fixedly mounted first clamp; a connecting component, comprising a second clamp and a connecting rod, the top end of the connecting rod being rotatably connected to the second clamp about a rotation axis, the fuselage frame being in a test state where both ends are simultaneously clamped by the first and second clamps, and the test plane on the fuselage frame being located between the first and second clamps; the connecting component being located between a loading component and a fixing component; and a loading component, comprising a connecting rope, a driving component, and a roller, the roller being located below the connecting rod, one end of the connecting rope being connected to the bottom end of the connecting rod, and the other end of the connecting rope being wound around the roller and connected to the driving end of the driving component, the roller being movable along a first direction. This invention enables bending tests on irregular fuselage frames, ensuring the accuracy of test results, reducing test costs, simplifying the operation process, and improving test efficiency.

Description

Technical Field

[0001] This invention relates to the field of aircraft manufacturing technology, and in particular to a bending test apparatus and test method. Background Technology

[0002] The fuselage frame is the fundamental structure of a commercial aircraft, typically bearing circumferential and in-plane bending loads, and is a critical structure for the structural integrity of a commercial aircraft. Under aerodynamic loads, flight maneuvers, and other operating conditions, the aircraft fuselage will deform and experience circumferential bending moments. These bending moments and local shear loads are usually transferred by the fuselage frame, requiring bending tests to verify the safety of the fuselage design and the reliability of the analysis. Furthermore, due to the design requirements of passenger / cargo compartment structures in commercial aircraft and other transport aircraft, as well as the technological limitations of some advanced materials (such as composite materials), the planar shape of the fuselage frame is usually not a perfect circle, but rather an irregular structure with varying curvature and cross-section. Especially in sections such as the nose, mid- and aft fuselage, and rear fuselage, the structure of the fuselage frame needs to be designed with continuously varying curvature to follow the aerodynamic shape; therefore, these fuselage frames are typically irregular structures with continuously changing curvature.

[0003] In existing technologies, such as patent CN106769533B, a four-point bending test is typically used to test the fuselage frame. However, such testing equipment requires the test piece to have a symmetrical structure, with the bottom of the test piece clamped on two fixtures, and the two fixtures symmetrically positioned about the plane to be tested on the fuselage frame. Then, two loading heads simultaneously apply the same load to the top of the fuselage frame, with the loading positions of the loading heads symmetrically positioned about the plane to be tested on the fuselage frame.

[0004] Existing bending testing devices cannot meet the testing requirements for irregularly structured fuselage frames. Furthermore, to ensure the symmetry of the test specimen, the specimen's structure is usually inconsistent with the actual fuselage frame structure, compromising the accuracy of the bending test results. Additionally, the test specimen requires additional fabrication, increasing testing costs. Moreover, in existing technologies, if bending tests are needed on different test planes on the fuselage frame, different test heads and fixtures are typically required for loading and clamping the frame, resulting in high testing costs and increased operational complexity, thus impacting testing efficiency.

[0005] Therefore, there is an urgent need for a bending test device and test method to solve the problems mentioned above. Summary of the Invention

[0006] One objective of this invention is to provide a bending test apparatus to perform bending tests on irregular and asymmetrical fuselage frames, as well as to perform bending tests on actual fuselage frames, ensuring the accuracy of test results while reducing test costs, simplifying the test operation process, and improving test efficiency.

[0007] Another objective of this invention is to provide a bending test method that simplifies the test process, ensures the accuracy of the test results, and enables bending tests to be performed on different test planes on the fuselage frame in a single clamping, thereby improving test efficiency and reducing test costs.

[0008] To achieve this objective, the present invention adopts the following technical solution:

[0009] A bending test apparatus for performing a bending test on a fuselage frame, comprising:

[0010] The fixing component includes a first clamp that is fixedly positioned.

[0011] A connecting assembly, wherein the fixing assembly is disposed on one side of the connecting assembly along a first direction, the connecting assembly includes a second clamp and a connecting rod, the top end of the connecting rod is rotatably connected to the second clamp about a rotation axis, the rotation axis and the first direction are both horizontal and perpendicular to each other, the body frame has a test state in which both ends are simultaneously clamped by the first clamp and the second clamp, and when the body frame is in the test state, the test plane on the body frame is located between the first clamp and the second clamp;

[0012] A loading component is disposed on the other side of the connecting component along the first direction. The loading component includes a connecting rope, a driving member, and a roller. The roller is located below the connecting rod and its rolling axis is parallel to the rotation axis. One end of the connecting rope is connected to the bottom end of the connecting rod, and the other end of the connecting rope is wound around the roller and connected to the driving end of the driving member. The driving end is movable along the extension direction of the connecting rope, and the roller is movable along the first direction to drive the connecting rod to rotate around the rotation axis.

[0013] As an optional technical solution for a bending test device, the loading assembly further includes an adjusting seat and a roller seat. The adjusting seat has a roller strip hole that extends along the first direction. The roller is rotatably disposed on the roller seat, and the roller seat can move along the roller strip hole.

[0014] As an optional technical solution for a bending test device, the fixing assembly further includes a fixed base with a clamping strip hole. The first clamp includes two first clamping members, which are detachably connected and can move closer or further apart from each other along the clamping strip hole to clamp or release the frame located between the two first clamping members.

[0015] As an optional technical solution for a bending test device, the second clamp includes two second clamping members, which are detachably connected and capable of clamping or releasing the body frame located between the two second clamping members.

[0016] As an optional technical solution for the bending test device, the loading component further includes a measuring element connected between the driving end of the driving element and the connecting rope.

[0017] As an optional technical solution for a bending test device, the bending test device further includes an anti-torsion component, which includes two limiting members that are spaced apart along a second direction. The rotation axis extends along the second direction, and when the frame is in the test state, the frame is located between the two limiting members.

[0018] As an optional technical solution for a bending test device, the anti-torsion assembly further includes two fixedly mounted brackets, and two limiting members are respectively configured corresponding to the two fixed brackets. The limiting members have limiting strip holes that extend along the second direction. Bolts pass through the limiting strip holes and are connected to the corresponding fixed brackets. The bolts can slide along the limiting strip holes.

[0019] As an optional technical solution for a bending test device, the limiting member is connected to a contact plate on the side facing the second fixture. The contact plate is perpendicular to the second direction, and the contact plate can contact the side of the second fixture. The surface of the contact plate used to contact the second fixture is coated with a lubricating layer.

[0020] A bending test method, applied in the bending test apparatus described above, the method comprising:

[0021] S1. Install the fuselage frame to be tested onto the bending test device to put the fuselage frame into the test state;

[0022] S2. Measure the angle α between the connecting rope and the vertical plane passing through the axis of rotation of the connecting rod;

[0023] S3. Determine the position of the plane to be measured on the fuselage frame, make a reference plane perpendicular to the plane to be measured, make a first loading direction perpendicular to the reference plane and intersecting the rotation axis, and measure the angle b between the first loading direction and the vertical plane.

[0024] S4. Move the roller along the first direction until the degree of the included angle a is the same as the degree of the included angle b, and the end of the connecting rope connected to the connecting rod extends along the first loading direction;

[0025] S5. The drive end of the drive component moves and drives the connecting rope to apply a load to the fuselage frame that reaches the target value.

[0026] S6. Measure the test result parameters of the fuselage frame located on the plane to be tested.

[0027] As an optional technical solution for the bending test method, step S6 further includes:

[0028] S7. Determine the position of the additional plane to be measured on the fuselage frame. The additional plane to be measured is not parallel to the plane to be measured. Make an additional reference plane perpendicular to the additional plane to be measured. Make a second loading direction perpendicular to the additional reference plane and intersecting the rotation axis. Measure the angle c between the second loading direction and the vertical plane.

[0029] S8. Move the roller along the first direction until the degree of the included angle a is the same as the degree of the included angle c, and the end of the connecting rope connected to the connecting rod extends along the second loading direction;

[0030] S9. The driving end of the driving component moves and drives the connecting rope to apply a load to the fuselage frame that reaches the target value.

[0031] S10. Measure the additional test result parameters of the fuselage frame located at the additional test plane.

[0032] The beneficial effects of this invention are:

[0033] This invention provides a bending test apparatus, comprising a fixing component, a connecting component, and a loading component. The fixing component is used to fix one end of the fuselage frame, a second clamp can hold the other end of the fuselage frame, and the driving end of the driving component can pull the connecting rope to apply a load to the fuselage frame, thereby realizing a bending test on the fuselage frame and measuring the test results at the test plane. This bending test apparatus has a simple structure, realizes bending tests on irregular and asymmetrical fuselage frames, reduces the shape restrictions of the fuselage frames that can be bent, expands the applicability range of the bending test apparatus to fuselage frame shapes, improves practicality, and can use actual fuselage frame structures for bending tests, further ensuring the accuracy of test results, improving the safety of aircraft products, avoiding the production of dedicated test pieces, reducing test costs, and improving test efficiency. Furthermore, when the roller moves along the first direction, the connecting rope can drive the connecting rod to rotate relative to the second clamp, thereby adjusting the direction of the load applied by the driving component to the frame. This allows bending tests to be performed on different test planes on the frame with a single clamping of the frame, and the bending test results at different test planes can be obtained. This simplifies the test operation process, further improving test efficiency, ease of use, and practicality. It also avoids the need to use different loading heads and clamps to apply loads and clamp the frame, further reducing test costs.

[0034] This invention provides a bending test method applied to a bending test apparatus. By utilizing the movement of rollers, the connecting rope drives the connecting rod to rotate relative to the second clamp, making the load application direction parallel to the plane to be tested. This simplifies the operation process of adjusting the load direction applied to the frame by the driving component, ensuring the accuracy of the test results. Moreover, the load application direction can be changed by moving the rollers, thereby enabling bending tests to be performed at different planes to be tested on the frame with a single clamping of the frame, obtaining bending test results at different planes to be tested, further improving test efficiency and reducing test costs. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the bending test device provided in an embodiment of the present invention;

[0036] Figure 2 This is a first-view structural schematic diagram of a portion of the bending test device provided in an embodiment of the present invention;

[0037] Figure 3 This is a second-view structural schematic diagram of a portion of the bending test device provided in an embodiment of the present invention;

[0038] Figure 4 This is a structural schematic diagram of the fixing component, connecting component, and loading component provided in an embodiment of the present invention;

[0039] Figure 5 This is a schematic diagram of the anti-torsion component provided in an embodiment of the present invention;

[0040] Figure 6 This is a schematic diagram of the bending test method using the bending test apparatus provided in this embodiment of the invention.

[0041] In the picture:

[0042] 10. Fuselage frame; 101. Plane to be measured; 101'. Additional plane to be measured; 102. Reference plane; 102'. Additional reference plane; 103. First loading direction; 104. Second loading direction; 20. Vertical plane;

[0043] 1. Fixing component; 11. First clamp; 111. First clamping element; 112. Outer edge; 12. Fixing base; 121. Clamping strip hole;

[0044] 2. Connecting assembly; 21. Second clamp; 211. Second clamping element; 22. Connecting rod;

[0045] 3. Loading component; 31. Connecting rope; 32. Driving component; 33. Roller; 34. Adjusting seat; 341. Roller slot; 35. Roller seat; 36. Measuring component; 37. Loading fixing seat;

[0046] 4. Anti-torsion assembly; 41. Limiting component; 411. Limiting strip hole; 412. Bolt; 42. Fixing bracket; 421. First connecting hole; 43. Contact plate; 44. Anti-torsion fixing seat. Detailed Implementation

[0047] To make the technical problems solved by the present invention, the technical solutions adopted, and the technical effects achieved clearer, the technical solutions of the embodiments of the present invention will be further described in detail 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.

[0048] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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 of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0049] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0050] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0051] This embodiment provides a bending test apparatus for performing a bending test on the fuselage frame 10. Specifically, as shown... Figures 1-6 As shown, the bending test device includes a fixing component 1, a connecting component 2, and a loading component 3. The fixing component 1 includes a first clamp 11 fixedly mounted; the fixing component 1 is disposed on one side of the connecting component 2 along a first direction. The connecting component 2 includes a second clamp 21 and a connecting rod 22. The top end of the connecting rod 22 is rotatably connected to the second clamp 21 about a rotation axis. The rotation axis and the first direction are both horizontal and perpendicular to each other. The frame 10 has a test state in which both ends are simultaneously clamped by the first clamp 11 and the second clamp 21. When the frame 10 is in the test state, the test plane 101 on the frame 10 is located between the first clamp 11 and the second clamp. Between 21; the loading component 3 is disposed on the other side of the connecting component 2 along the first direction. The loading component 3 includes a connecting rope 31, a driving member 32 and a roller 33. The roller 33 is located below the connecting rod 22. The rolling axis of the roller 33 is parallel to the rotation axis. One end of the connecting rope 31 is connected to the bottom end of the connecting rod 22. The other end of the connecting rope 31 is wrapped around the roller 33 and connected to the driving end of the driving member 32. The driving end can move along the extension direction of the connecting rope 31. The roller 33 can move along the first direction to drive the connecting rod 22 to rotate around the rotation axis.

[0052] This embodiment provides a bending test device, which includes a fixing component 1, a connecting component 2, and a loading component 3. The fixing component 1 is used to fix one end of the fuselage frame 10, the second clamp 21 can clamp the other end of the fuselage frame 10, and the driving end of the driving component 32 can pull the connecting rope 31 to apply a load to the fuselage frame 10, thereby realizing a bending test on the fuselage frame 10 and measuring the test results at the test plane 101. This bending test device has a simple structure, realizes bending tests on irregular and asymmetrical fuselage frames 10, reduces the shape restrictions of the fuselage frame 10 that can be bent, expands the applicability range of the bending test device to the shape of the fuselage frame 10, improves practicality, and can use the actual fuselage frame 10 structure to perform bending tests, further ensuring the accuracy of the test results, improving the safety of aircraft products, avoiding the production of special test parts, reducing test costs, and improving test efficiency. Furthermore, when the roller 33 moves along the first direction, the connecting rope 31 can drive the connecting rod 22 to rotate relative to the second clamp 21, thereby adjusting the direction of the load applied by the drive component 32 to the frame 10. This allows bending tests to be performed at different test planes 101 on the frame 10 with a single clamping of the frame 10, and the bending test results at different test planes 101 can be obtained. This simplifies the test operation process, further improves test efficiency, ease of use, and practicality, and avoids the need to use different loading heads and clamps to apply loads and clamp the frame 10, further reducing test costs.

[0053] Understandably, in order to apply a moment about the bending center at the plane 101 to the fuselage frame 10, the direction of the load application needs to be parallel to the plane 101.

[0054] For ease of description, a first direction and a second direction are defined as horizontally positioned, with the first direction and the second direction being perpendicular to each other. The rolling axis of the roller 33 and the rotation axis of the connecting rod 22 both extend along the second direction.

[0055] In this embodiment, the driving component 32 and the connecting rod 22 are respectively arranged on opposite sides of the roller 33 along the first direction. The roller 33 can change the direction of the load transmitted through the connecting rope 31, which helps to shorten the vertical dimension of the bending test device and reduce the space occupied. The connecting rope 31 is a steel wire rope.

[0056] As a preferred embodiment, the loading assembly 3 also includes an adjusting seat 34, on which a roller slot 341 is provided. The roller slot 341 extends along a first direction, and the roller 33 can move along the roller slot 341. The adjusting seat 34 and the roller slot 341 help to limit the direction of movement of the roller 33, ensuring that when the roller 33 moves along the first direction, the connecting rope 31 can drive the connecting rod 22 to rotate relative to the second clamp 21. This allows bending test results to be measured at different test planes 101 on the machine frame 10, simplifying the operation of the bending test device, further improving test efficiency, ease of use, and practicality, and also further reducing test costs.

[0057] Furthermore, the loading component 3 also includes a roller seat 35, on which the roller 33 is rotatably disposed. The roller seat 35 is movable along the roller slot 341. The roller slot 341 can vertically penetrate the adjusting seat 34. The bottom of the roller seat 35 extends into the roller slot 341, and a locking bolt is provided at the bottom of the adjusting seat 34. The locking bolt extends from the bottom of the roller slot 341 into the roller slot 341 and is threadedly connected to the bottom of the roller seat 35. When the locking bolt is tightened, it can restrict the position of the roller seat 35 within the roller slot 341. When the locking bolt is not tightened, the roller seat 35 can move along the roller slot 341. In other embodiments, other structural forms can be provided to both allow the roller seat 35 to move along the roller slot 341 and restrict its position within the roller slot 341, which is not limited here.

[0058] In this embodiment, the adjusting seat 34 can be configured as a profile extending along a first direction, with a roller strip hole 341 formed on the profile. A limiting ring groove can be formed on the side wall of the roller 33, and the connecting rope 31 is located in the limiting ring groove to prevent the connecting rope 31 from detaching from the roller 33.

[0059] Preferably, the loading assembly 3 further includes a loading fixing seat 37, which is used to fix the driving component 32. The loading fixing seat 37 and the roller 33 are respectively disposed on opposite sides of the driving component 32 along a first direction. The driving component 32 is configured as a cylinder, the cylinder body of which is connected to the loading fixing seat 37. The piston rod of the cylinder is disposed on the side of the cylinder body facing the roller 33 and is connected to the connecting rope 31. The loading fixing seat 37 is fixedly disposed, and the cylinder body is rotatably connected to the side wall of the loading fixing seat 37 facing the roller 33. The cylinder body can rotate relative to the loading fixing seat 37 around a second direction, so that after the roller 33 moves to a position along the first direction, the cylinder body can rotate to adjust the angle of the piston rod and ensure that the piston rod can always tighten the connecting rope 31 and apply a load to the frame 10. In this embodiment, the structure of the loading fixing seat 37 can be constructed by metal rods, and the specific structural form is not limited.

[0060] Furthermore, the loading component 3 also includes a measuring element 36, which is connected between the driving end of the driving component 32 and the connecting rope 31. The measuring element 36 can measure the load transmitted to the frame 10 through the connecting rope 31, thereby helping to ensure the accuracy of the bending test results. In this embodiment, the measuring element 36 is a tension sensor, fixed to the end of the piston rod of the cylinder, with the measuring end connected to the connecting rope 31. The specific structure and measurement principle of the measuring element 36 can be found in the prior art, which is not the focus of this embodiment and will not be described in detail here.

[0061] As a preferred embodiment, the fixing assembly 1 further includes a fixed base 12, which has a clamping slot 121. The first clamp 11 includes two first clamping members 111, which are detachably connected and can move closer or further apart along the clamping slot 121 to clamp or release the fuselage frame 10 located between the two first clamping members 111. This structural arrangement facilitates the first clamp 11 clamping the first end of the fuselage frame 10 and also facilitates the removal of the fuselage frame 10 from the first clamp 11 after the test, further ensuring the convenience of the test operation and expanding the range of fuselage frame 10 sizes to which the first clamp 11 is applicable. Furthermore, the detachable connection between the two first clamping members 111 ensures that the first clamp 11 can reliably clamp the fuselage frame 10. The detachable connection between the two first clamping members 111 can be achieved through snap-fit ​​or other structures, which are not limited here.

[0062] In this embodiment, two clamping strip holes 121 are spaced apart on the top surface of the fixing base 12 along the second direction, and the clamping strip holes 121 extend along the second direction. Two first clamping members 111 are respectively disposed in the two clamping strip holes 121, so that the two first clamping members 111 can move closer or further away from each other along the second direction, avoiding interference between the first clamping members 111 and the connecting rope 31 and connecting rod 22 and other structures, ensuring the smooth conduct of the bending test, ensuring the efficiency of the test, and saving time and costs.

[0063] In this embodiment, the fixing base 12 can be configured as a profile extending along the second direction, with a clamping strip hole 121 formed on the profile. The bottom of the sidewalls of the two first clamping members 111, facing away from each other, can be bent outwards with outer extensions 112. The fixing base 12 has a fixing strip hole extending along the second direction. A locking bolt passes through the fixing strip hole and can be threadedly connected to the outer extension 112. When the locking bolt is tightened, the first clamping members 111 are fixed, thus restricting their position within the clamping strip hole 121. When the locking bolt is not tightened, the first clamping members 111 can move, allowing them to move along the clamping strip hole 121. In other embodiments, other structural forms can be used to both allow the first clamping members 111 to move along the clamping strip hole 121 and restrict their position within the clamping strip hole 121; these are not limited here.

[0064] Preferably, the first clamping member 111 is plate-shaped and perpendicular to the second direction. One of the first clamping members 111 has a first groove on its side facing the other, and the first groove penetrates the top surface of the first clamping member 111. When the two first clamping members 111 are engaged, a first space is formed between the first groove and the other first clamping member 111. The first end of the body frame 10 can be placed within the first space, and the sidewall of the first end of the body frame 10 is circumferentially fitted with the sidewall of the first space to ensure that the first clamp 11 can firmly clamp the first end of the body frame 10. In other embodiments, both first clamping members 111 may have first grooves, which are directly opposite each other. When the two first clamping members 111 are engaged, a first space is formed between the two first grooves. Alternatively, neither of the two first clamping members 111 may have a first groove; these are not limited in this respect.

[0065] In this embodiment, the top surface of the fixed seat 12 is higher than the top surface of the adjusting seat 34, which further facilitates the placement of the roller 33 below the connecting rod 22. This allows the loading direction to be adjusted by adjusting the position of the roller 33, ensuring ease of operation.

[0066] As a preferred embodiment, the second clamp 21 includes two second clamping members 211, which are detachably connected and capable of clamping or releasing the fuselage frame 10 located between the two clamping members 211. This structural arrangement facilitates the second clamp 21 clamping the second end of the fuselage frame 10 away from the first end, and also facilitates the removal of the fuselage frame 10 from the second clamp 21 after the test, further ensuring the convenience of the test operation and expanding the range of fuselage frame 10 sizes to which the second clamp 21 is applicable. Furthermore, the detachable connection between the two second clamping members 211 ensures that the second clamp 21 can reliably hold the fuselage frame 10. The detachable connection of the two second clamping members 211 can be achieved through snap-fits or other structures, which are not limited here.

[0067] Preferably, the second clamping member 211 is plate-shaped and perpendicular to the second direction. One of the second clamping members 211 has a second groove on its side facing the other, and the second groove penetrates the top surface of the second clamping member 211. When the two second clamping members 211 are engaged, a second space is formed between the second groove and the other second clamping member 211. The second end of the body frame 10 can be placed within the second space, and the sidewall of the second end of the body frame 10 is circumferentially fitted with the sidewall of the second space to ensure that the second clamp 21 can firmly clamp the second end of the body frame 10. In other embodiments, both second clamping members 211 may have second grooves, which are directly opposite each other. When the two second clamping members 211 are engaged, a second space is formed between the two second grooves. Alternatively, neither of the two second clamping members 211 may have second grooves; these are not limited in this respect.

[0068] In this embodiment, a rotating rod is fixed on the second clamp 21, extending along the second direction and passing through the two second clamping members 211. A connecting rod 22 is rotatably connected to the rotating rod, and the axis of rotation of the connecting rod 22 is the axis of the rotating rod.

[0069] As a preferred embodiment, the bending test apparatus further includes an anti-torsion component 4, which includes two limiting members 41 spaced apart along a second direction. When the fuselage frame 10 is in the test state, the fuselage frame 10 is located between the two limiting members 41. When the driving member 32 applies a load to the fuselage frame 10, the second end of the fuselage frame 10 may tilt towards the second direction. The two limiting members 41 can limit the fuselage frame 10, reducing the possibility of the second end of the fuselage frame 10 tilting along the second direction and ensuring the accuracy of the test results.

[0070] Furthermore, a contact plate 43 is connected to the side of the limiting member 41 facing the second clamp 21. The contact plate 43 is perpendicular to the second direction and can contact the side of the second clamp 21. A lubricating layer is coated on the surface of the contact plate 43 that contacts the second clamp 21. By contacting the limiting member 41 with the second clamp 21, the movement range of the second end of the fuselage frame 10 is further restricted, preventing the possibility of the second end of the fuselage frame 10 tilting along the second direction, and further ensuring the accuracy of the bending test results. It is understandable that, since the contact plate 43 is used to contact the second clamp 21, when a load is applied to the second end of the fuselage frame 10, the fuselage frame 10 may deform, i.e., there is friction between the second clamp 21 and the contact plate 43. Therefore, the lubricating layer coated on the contact plate 43 also reduces the friction between the second clamp 21 and the contact plate 43, reducing the load on the fuselage frame 10 in other directions and ensuring the accuracy of the bending test results.

[0071] In this embodiment, the contact plate 43 and the limiting member 41 are detachably connected, which facilitates the replacement of the contact plate 43 when it is worn.

[0072] As a preferred embodiment, the anti-torsion assembly 4 further includes two fixedly mounted brackets 42, with two limiting members 41 corresponding to the two fixed brackets 42 respectively. Each limiting member 41 has a limiting slot 411 extending along a second direction. A bolt 412 passes through the limiting slot 411 and connects to the corresponding fixed bracket 42, allowing the bolt 412 to slide along the limiting slot 411. This structural arrangement allows the two limiting members 41 to move closer or further apart, facilitating the removal or installation of the fuselage frame 10 at the second clamp 21, ensuring the smooth conduct of the bending test. Furthermore, by adjusting the distance between the two limiting members 41, bending tests can be performed on fuselage frames 10 of different sizes, expanding the applicability. In this embodiment, the two fixed brackets 42 are respectively connected to the bottom of the two limiting members 41.

[0073] Specifically, the anti-torsion assembly 4 also includes two anti-torsion fixing seats 44, which are fixedly installed and respectively fixedly connected to two fixing brackets 42. The two anti-torsion fixing seats 44 are respectively located on the opposite side of the two fixing brackets 42. The opposite side of the fixing brackets 42 has a first connecting hole 421, and the opposite side of the anti-torsion fixing seats 44 has a second connecting hole. The fixing brackets 42 and the anti-torsion fixing seats 44 can be detachably connected by threaded fasteners that pass through the first connecting hole 421 and the second connecting hole in sequence.

[0074] Furthermore, each anti-torsion fixing seat 44 is provided with multiple second connecting holes in the vertical direction. The first connecting hole 421 can be selectively set to face any one of the second connecting holes on the corresponding anti-torsion fixing seat 44, so as to realize the vertical adjustment of the position of the fixing frame 42 on the anti-torsion fixing seat 44. This further realizes that the anti-torsion component 4 is applicable to bending tests of the frame 10 of different sizes, thus expanding the scope of application.

[0075] This embodiment also provides a bending test method, applied to the bending test apparatus as described above. Specifically, as... Figures 1-6 As shown, the above bending test method includes:

[0076] S1. Install the fuselage frame 10 to be tested onto the bending test device to put the fuselage frame 10 into the test state;

[0077] S2. Measure the angle α between the connecting rope 31 and the vertical plane 20 that passes through the axis of rotation of the connecting rod 22;

[0078] S3. Determine the position of the plane to be measured 101 on the fuselage frame 10, make a reference plane 102 perpendicular to the plane to be measured 101, make a first loading direction 103 perpendicular to the reference plane 102 and intersecting the rotation axis, and measure the angle b between the first loading direction 103 and the vertical plane 20.

[0079] S4. Move the roller 33 along the first direction until the degree of included angle a is the same as the degree of included angle b, and the end of the connecting rope 31 connected to the connecting rod 22 extends along the first loading direction 103.

[0080] S5. The drive end of the drive unit 32 moves and drives the connecting rope 31 to apply a load to the fuselage frame 10 that reaches the target value.

[0081] S6. Measure the test result parameters of the fuselage frame 10 located at the test plane 101.

[0082] The bending test method provided in this embodiment utilizes the movement of the roller 33 to enable the connecting rope 31 to drive the connecting rod 22 to rotate relative to the second clamp 21, so that the load application direction is parallel to the test plane 101. This simplifies the operation process of adjusting the load direction applied by the drive component 32 to the fuselage frame 10, ensuring the accuracy of the test results. Moreover, the load application direction can be changed by the movement of the roller 33, thereby enabling bending tests to be performed at different test planes 101 on the fuselage frame 10 with a single clamping of the fuselage frame 10, and obtaining bending test results at different test planes 101, further improving test efficiency and reducing test costs.

[0083] The bending test method provided in this embodiment is described in detail below. The bending test method includes:

[0084] S1. Install the fuselage frame 10 to be tested onto the bending test device to put the fuselage frame 10 into the test state.

[0085] Specifically, the bending test apparatus is first assembled. The first end of the frame 10 to be tested is fixed to the first clamp 11, and the second end of the frame 10 is fixed to the second clamp 21. After the frame 10 is installed, the positions of the second clamp 21 and the connecting rod 22 can be determined. Then, the roller 33 can be fixed at any position on the side of the connecting rod 22 opposite to the frame 10. The drive end of the drive component 32 is adjusted to make the connecting rope 31 taut.

[0086] S2. Measure the angle α between the connecting rope 31 and the vertical plane 20 that passes through the rotation axis of the connecting rod 22.

[0087] Specifically, when the connecting rope 31 is taut, the length direction of the connecting rod 22 and the connecting rope 31 on the side of the roller 33 facing the connecting rod 22 can be considered to be on the same straight line G. At this time, the direction of the straight line G is the preload direction.

[0088] S3. Determine the position of the plane to be measured 101 on the fuselage frame 10, make a reference plane 102 perpendicular to the plane to be measured 101, make a first loading direction 103 perpendicular to the reference plane 102 and intersecting the rotation axis, and measure the angle b between the first loading direction 103 and the vertical plane 20.

[0089] Understandably, the first loading direction 103 is parallel to the plane to be tested 101. When performing step S1, a model of the bending test apparatus can be created in CATIA or other CAD software; steps S2 and S3 can also be performed in CATIA or other CAD software.

[0090] S4. Move the roller 33 along the first direction until the degree of included angle a is the same as the degree of included angle b, and the end of the connecting rope 31 connected to the connecting rod 22 extends along the first loading direction 103.

[0091] Specifically, the position of the roller 33 is determined in the CAD software when the connecting rope 31 extends along the first loading direction 103. Based on the aforementioned position of the roller 33 on the CAD software model, the roller 33 is moved on the bending test device until the degree of included angle α is the same as that of included angle b, so that the end of the connecting rope 31 connected to the connecting rod 22 extends along the first loading direction 103. When the straight line G coincides with the first loading direction 103, the degree of included angle α is the same as that of included angle b.

[0092] S5, the drive end of the drive unit 32 moves and drives the connecting rope 31 to apply a load to the fuselage frame 10 that reaches the target value.

[0093] Specifically, the load magnitude is measured using measuring element 36. The target value is determined based on the actual operating conditions of the fuselage frame 10 and is not limited here.

[0094] S6. Measure the test result parameters of the fuselage frame 10 located at the test plane 101.

[0095] In other words, in step S6, when the fuselage frame 10 is subjected to a load of the target value, the test result parameters of the fuselage frame 10 located at the plane to be measured 101 are measured.

[0096] Typically, the test result parameters include the strain at the test plane 101 and the breaking load. When the drive component 32 applies a load to the fuselage frame 10, and the fuselage frame 10 breaks, the magnitude of the load at the time of breakage is the breaking load.

[0097] Step S6 is followed by: S7, determining the position of the additional test plane 101' on the fuselage frame 10, the additional test plane 101' is not parallel to the test plane 101, an additional reference plane 102' is made perpendicular to the additional test plane 101', a second loading direction 104 is made perpendicular to the additional reference plane 102' and intersects the rotation axis, and the included angle c between the second loading direction 104 and the vertical plane 20 is measured.

[0098] The test plane 101 in step S3 is set as the first test section, and the additional test plane 101' in step S7 is set as the second test section. Since this bending test device can perform bending tests on multiple test planes 101 in one clamping, by applying loads at different angles (first loading direction 103 and second loading direction 104) to the fuselage frame 10, bending tests can be performed on different test planes 101 (first test section and second test section), which helps to simplify the bending test process of the fuselage frame 10.

[0099] S8. Move the roller 33 along the first direction until the degree of included angle a is the same as the degree of included angle c, and the end of the connecting rope 31 connected to the connecting rod 22 extends along the second loading direction 104.

[0100] Specifically, the position of the roller 33 is determined within the CAD software when the connecting rope 31 extends along the second loading direction 104. Based on the aforementioned position of the roller 33 on the CAD software model, the roller 33 is moved on the bending test device until the angle α is the same as the angle c, so that the end of the connecting rope 31 connected to the connecting rod 22 extends along the second loading direction 104. When the straight line G coincides with the second loading direction 104, the angle α is the same as the angle c.

[0101] S9, the drive end of the drive member 32 moves and drives the connecting rope 31 to apply a load to the fuselage frame 10 that reaches the target value.

[0102] Specifically, the load magnitude is measured using measuring element 36. The target value here can be the same as or different from the target value in S5. The magnitude of this target value is determined based on the actual operating conditions of the fuselage frame 10 and is not limited here.

[0103] S10, Measure the additional test result parameters of the body frame 10 located at the additional test plane 101'.

[0104] Additional test result parameters include the strain at the additional test plane 101' and the destructive load.

[0105] It is understandable that after step S10, the positions of other test planes 101 to be tested can be determined on the frame 10, and the position of the roller 33 can be changed to realize the bending test of other test planes 101.

[0106] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A bending test apparatus for performing a bending test on a fuselage frame (10), characterized in that, include: The fixing component (1) includes a first clamp (11) that is fixedly set; The connecting component (2) includes a fixing component (1) disposed on one side of the connecting component (2) along a first direction. The connecting component (2) includes a second clamp (21) and a connecting rod (22). The top end of the connecting rod (22) is rotatably connected to the second clamp (21) about a rotation axis. The rotation axis and the first direction are both horizontal and perpendicular to each other. The body frame (10) has a test state in which both ends are clamped by the first clamp (11) and the second clamp (21) at the same time. When the body frame (10) is in the test state, the test plane (101) on the body frame (10) is located between the first clamp (11) and the second clamp (21). A loading component (3) is disposed on the other side of the connecting component (2) along the first direction. The loading component (3) includes a connecting rope (31), a driving member (32), and a roller (33). The roller (33) is located below the connecting rod (22) and its rolling axis is parallel to the rotation axis. One end of the connecting rope (31) is connected to the bottom end of the connecting rod (22), and the other end of the connecting rope (31) is wound around the roller (33) and connected to the driving end of the driving member (32). The driving end can move along the extension direction of the connecting rope (31), and the roller (33) can move along the first direction to drive the connecting rod (22) to rotate around the rotation axis.

2. The bending test apparatus according to claim 1, characterized in that, The loading component (3) further includes an adjusting seat (34) and a roller seat (35). The adjusting seat (34) has a roller slot (341) extending along the first direction. The roller (33) is rotatably disposed on the roller seat (35), and the roller seat (35) can move along the roller slot (341).

3. The bending test apparatus according to claim 1, characterized in that, The fixing component (1) further includes a fixing seat (12) fixedly disposed thereon. The fixing seat (12) has a clamping strip hole (121). The first clamp (11) includes two first clamping members (111). The two first clamping members (111) are detachably connected and can move closer or further away from each other along the clamping strip hole (121) to clamp or release the body frame (10) located between the two first clamping members (111).

4. The bending test apparatus according to claim 1, characterized in that, The second clamp (21) includes two second clamping members (211) which are detachably connected and capable of clamping or releasing the fuselage frame (10) located between the two second clamping members (211).

5. The bending test apparatus according to claim 1, characterized in that, The loading component (3) further includes a measuring element (36), which is connected between the driving end of the driving element (32) and the connecting rope (31).

6. The bending test apparatus according to any one of claims 1-5, characterized in that, The bending test device further includes an anti-torsion component (4), which includes two limiting members (41) that are spaced apart along a second direction. The rotation axis extends along the second direction. When the body frame (10) is in the test state, the body frame (10) is located between the two limiting members (41).

7. The bending test apparatus according to claim 6, characterized in that, The anti-torsion assembly (4) also includes two fixed brackets (42), and two limiting members (41) are respectively provided corresponding to the two fixed brackets (42). The limiting member (41) has a limiting strip hole (411) which extends along the second direction. The bolt (412) passes through the limiting strip hole (411) and is connected to the corresponding fixed bracket (42). The bolt (412) can slide along the limiting strip hole (411).

8. The bending test apparatus according to claim 6, characterized in that, The limiting member (41) is connected to a contact plate (43) on the side facing the second clamp (21). The contact plate (43) is perpendicular to the second direction. The contact plate (43) can contact the side of the second clamp (21), and the surface of the contact plate (43) used to contact the second clamp (21) is coated with a lubricating layer.

9. A bending test method, characterized in that, Applied in the bending test apparatus as described in any one of claims 1-8, the method comprises: S1. Install the fuselage frame (10) to be tested onto the bending test device, so that the fuselage frame (10) is in the test state; S2. Measure the angle α between the connecting rope (31) and the vertical plane (20) that passes through the axis of rotation of the connecting rod (22); S3. Determine the position of the plane to be measured (101) on the fuselage frame (10), make a reference plane (102) perpendicular to the plane to be measured (101), make a first loading direction (103) perpendicular to the reference plane (102) and intersecting the rotation axis, and measure the angle b between the first loading direction (103) and the vertical plane (20); S4. Move the roller (33) along the first direction until the degree of the included angle a is the same as the degree of the included angle b, and the end of the connecting rope (31) connected to the connecting rod (22) extends along the first loading direction (103). S5. The drive end of the drive unit (32) moves and drives the connecting rope (31) to apply a load to the fuselage frame (10) to the target value. S6. Measure the test result parameters of the fuselage frame (10) located on the test plane (101).

10. The bending test method according to claim 9, characterized in that, Step S6 is followed by: S7. Determine the position of the additional test plane (101') on the fuselage frame (10). The additional test plane (101') is not parallel to the test plane (101). Make an additional reference plane (102') perpendicular to the additional test plane (101'). Make a second loading direction (104) perpendicular to the additional reference plane (102') and intersecting the rotation axis. Measure the angle c between the second loading direction (104) and the vertical plane (20). S8. Move the roller (33) along the first direction until the degree of the included angle a is the same as the degree of the included angle c, and the end of the connecting rope (31) connected to the connecting rod (22) extends along the second loading direction (104). S9. The driving end of the driving member (32) moves and drives the connecting rope (31) to apply a load to the fuselage frame (10) that reaches the target value. S10. Measure additional test result parameters of the fuselage frame (10) located at the additional test plane (101').

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