CN110712763A - Single-spar crack propagation test device and test method - Google Patents
Single-spar crack propagation test device and test method Download PDFInfo
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Abstract
The invention provides a single-wing spar crack propagation test device which is used for carrying out a single-wing spar 2 crack propagation test and comprises a bearing wall 1, a plurality of instability-proof clamps 3, a shear force loading device 5 and a bending moment loading device 6, wherein the bearing wall 1 is used for clamping and fixing one end of the single-wing spar 2; the shear force loading device 5 is positioned on one side of the parallel single-wing spar 2 and is used for applying a web plate shear force parallel to the side face of the single-wing spar 2 to the single-wing spar 2; the bending moment loading device 6 comprises a bending moment loading clamp 60 and a bending moment loading assembly 61, and the bending moment loading clamp 60 is fixedly connected with two opposite side faces of the single-wing beam 2; the bending moment loading assembly 61 is fixedly connected with the bending moment loading clamp 60, and the bending moment loading assembly 61 applies acting force to the bending moment loading clamp 60 and is used for applying bending moment to the single-wing spar 2.
Description
Technical Field
The invention belongs to the technical field of spar tests, and relates to a crack propagation test method and a test device.
Background
The concept of damage tolerance is currently widely used in aircraft structural design, where the damage tolerance design recognizes the presence of undetected initial defects in the structure, requiring that the propagation of defects (cracks) be controlled within a certain range under the repeated action of the service loads. In the compliance methods of the airworthiness provisions of the CCAR23.573 and CCAR23.574, it is specifically stated that tests are selected or that a test-based supported analysis is used to indicate that the structure meets the airworthiness provisions. In aircraft structural damage tolerance design, damage to the wing spar can cause catastrophic damage, and crack propagation control of the wing spar is particularly important. The spar crack propagation test is also a damage tolerance test that must be performed by the aircraft to meet airworthiness requirements.
In practical engineering application, when a traditional test method is adopted for carrying out a spar crack propagation test, in order to truly simulate the actual stress boundary condition of a spar, the whole test is carried out by mostly adopting a wing box structure with the spacing length of 3 ribs. The test method for carrying out the crack propagation test by adopting the wing box structure has the advantages of high manufacturing cost of a test piece, large and heavy structure and low crack propagation test efficiency. In the crack propagation process of the wing beam, the whole wing box structure is complex, the load of the wing beam can be transferred along with the difference of the length of the crack, the crack propagation test scale performed by adopting the whole wing box structure is large, and the test cost is high. If the single-spar structure is adopted for testing, the boundary requirements of the test load and the constraint can be met, and the cost of the test can be greatly reduced.
Disclosure of Invention
The invention aims to design a single-wing spar crack propagation test device and a test method.
The invention provides a crack propagation test device for a single wing spar, which is simple and convenient, can effectively improve the efficiency of the crack propagation test of the single wing spar, can independently perform the crack propagation test on the wing spar, simulate the boundary support condition of a wing box on the single wing spar, and simulate the transfer of the whole wing box structure load of a wing web plate in the crack propagation process, and has simple structure form and low cost.
On one hand, the invention provides a single wing spar crack propagation test device which is used for carrying out a single wing spar 2 crack propagation test and comprises a bearing wall 1, a plurality of anti-instability clamps 3, a shear force loading device 5 and a bending moment loading device 6,
the bearing wall 1 is used for clamping and fixing one end of the single wing beam 2;
the anti-instability clamp 3 comprises a clamp connecting piece 30 and an anti-instability clamp 31, the clamp connecting piece 30 and the anti-instability clamp 31 are respectively positioned on two opposite side surfaces of the single wing beam 2, and the upper end and the lower end of the clamp connecting piece 30 and the upper end and the lower end of the anti-instability clamp 31 are correspondingly fixedly connected and used for clamping the single wing beam 2;
the shear force loading device 5 is positioned on one side of the parallel single-wing spar 2 and is used for applying a web plate shear force parallel to the side face of the single-wing spar 2 to the single-wing spar 2;
the bending moment loading device 6 comprises a bending moment loading clamp 60 and a bending moment loading assembly 61, the bending moment loading clamp 60 comprises a first bending moment loading clamp 601 and a second bending moment loading clamp 602, the first bending moment loading clamp 601 and the second bending moment loading clamp 602 are respectively positioned on two opposite side surfaces of the single-wing spar 2 and positioned at one end of the single-wing spar 2 far away from the bearing wall 1, and the first bending moment loading clamp 601 and the second bending moment loading clamp 602 clamp the single-wing spar 2 and are fixedly connected with the single-wing spar 2; the bending moment loading assembly 61 is fixedly connected with the bending moment loading clamp 60, and the bending moment loading assembly 61 applies acting force to the bending moment loading clamp 60 and is used for applying bending moment to the single-wing spar 2.
Further, the shear force loading device 5 is a first actuator cylinder, one end of the first actuator cylinder, which is close to the single-wing spar 2, is provided with a first load cell 50, and the first load cell 50 is located between the first actuator cylinder and the single-wing spar 2 and is used for measuring the web shear force applied by the first actuator cylinder.
Further, the bending moment loading assembly 61 includes a first bending moment loading plate 610, a second bending moment loading plate 612 and two second actuators 611, the first bending moment loading plate 610 is fixedly connected to the first bending moment loading fixture 601, the second bending moment loading plate 612 is fixedly connected to the first bending moment loading fixture 601,
the first bending moment loading plate 610 and the second bending moment loading plate 612 respectively include two loading rods extending in parallel, and the two second actuators 611 are respectively and fixedly connected to the two loading rods of the first bending moment loading plate 610 and the second bending moment loading plate 612, and are configured to apply an acting force to the loading rods.
Further, a second load cell 51 is disposed at one end of the two second actuators 611 close to the loading rod, and the second load cell 51 is located between the second actuators and the loading rod and is used for measuring the acting force applied to the loading rod by the second actuators.
Further, the test apparatus comprises at least 3 anti-buckling clamps 3, each located at a position where a single spar is supported by a rib in the aircraft structure.
Further, the single spar 2 comprises a lug 20, and one end of the shear loading device 5 is fixedly connected with the lug 20.
In another aspect, there is provided a single spar crack propagation test method, using a test apparatus as described above, characterised in that the method comprises,
one end of a single wing beam 2 is clamped and fixed by a bearing wall 1; the anti-instability clamp 3 clamps two opposite side surfaces of the single wing beam 2; the bending moment loading clamp 60 clamps and fixes the two opposite side surfaces at the other end of the single-wing beam 2 and is fixedly connected with the single-wing beam 2, and the bending moment loading assembly 61 is fixedly connected with the bending moment loading clamp 60;
the two second actuating cylinders 611 respectively apply acting forces in different directions or different magnitudes to one ends of two loading rods extending in parallel of the first bending moment loading plate 610 and the second bending moment loading plate 612, so that bending moment loading on the single-wing spar 2 is realized, and the two second actuating cylinders are used for simulating expansion crack propagation;
the directions of the forces applied by the two second rams 611 are parallel.
Further, the method may further comprise,
applying a web plate shearing force parallel to the side surface of the single wing beam 2 to the single wing beam 2 by using a shearing force loading device 5; meanwhile, the two second actuators 611 respectively apply acting forces in different directions or different magnitudes to one ends of two loading rods extending in parallel of the first bending moment loading plate 610 and the second bending moment loading plate 612, and simultaneously realize shear loading and bending moment loading on the single-wing spar 2, so as to simulate composite crack propagation.
Further, the method includes, prior to performing the crack propagation test, performing a pre-crack of an initial crack of the single spar structure, the pre-crack being performed at a crack tip of the single spar lower rail.
The invention has the technical effects that:
the single wing spar crack propagation test device is simple in structure, can effectively improve the efficiency of a wing spar crack propagation test, can independently perform the crack propagation test on a wing spar, simulate the boundary support condition of a wing box on the single wing spar, and simulate the transfer of the structural load of the whole wing box of a wing web in the crack propagation process, and the test assembly is simple in structural form and low in cost.
The test device combines two groups of loading systems, and realizes I-type (open type) crack propagation and II-type (slip type) crack propagation simulating crack propagation and a single-wing beam composite crack propagation test with two crack configurations existing simultaneously by adjusting the proportion of the shear loading systems. The single-wing spar crack propagation test method is designed based on a simple and practical principle, the test piece is easy to install and disassemble, the boundary constraint and loading condition of the single-wing spar are easy to simulate, the scale of the test piece is reduced, and the cost of a test tool and a test is controlled.
Drawings
FIG. 1 is a schematic diagram of the test apparatus of the present invention;
FIG. 2 is a disassembled schematic view of the test apparatus of the present invention.
Detailed Description
Example one
Fig. 1 is a schematic structural diagram of a testing apparatus of the present invention, fig. 2 is a schematic disassembly diagram of the testing apparatus of the present invention, and as shown in fig. 1 and fig. 2, in this embodiment, a single spar crack propagation testing apparatus is provided for performing a single spar 2 crack propagation test, and the testing apparatus includes a load-bearing wall 1, a plurality of instability-proof clamps 3, a shear loading apparatus 5, and a bending moment loading apparatus 6.
The bearing wall 1 is used for clamping and fixing one end of the single wing beam 2, and specifically, the bearing wall 1 clamps two side faces of one end of the single wing beam 2 and fixes the single wing beam 2.
The anti-instability clamp 3 comprises a clamp connecting piece 30 and an anti-instability clamp 31, the clamp connecting piece 30 and the anti-instability clamp 31 are respectively located on two opposite side faces of the single wing beam 2, and the upper end and the lower end of the clamp connecting piece 30 and the upper end and the lower end of the anti-instability clamp 31 are correspondingly fixedly connected and used for clamping the single wing beam 2. During the actual test, the clamp connection 30 is constrained to the fixed ground rail. The upper end and the lower end of the clamp connecting piece 30 and the anti-instability clamp 31 are fixedly connected through bolts respectively and clamp the single-wing spar 2.
The shear loading device 5 is positioned on one side of the parallel single-wing spar 2 and is used for applying a web shear force of the side surface of the parallel single-wing spar 2 to the single-wing spar 2. In this embodiment, the shear loading device 5 is a first actuator cylinder, the first actuator cylinder is located near one end of the single wing spar 2 and between the first actuator cylinder and the single wing spar 2, and a first force sensor 50 is disposed for measuring a web shear force applied by the first actuator cylinder.
Referring to fig. 1 and 2, the bending moment loading device 6 includes a bending moment loading fixture 60 and a bending moment loading assembly 61, the bending moment loading fixture 60 includes a first bending moment loading fixture 601 and a second bending moment loading fixture 602, and the first bending moment loading fixture 601 and the second bending moment loading fixture 602 are respectively located at the two opposite side surfaces at the other end of the single-wing spar 2 and are fixedly connected to the single-wing spar 2. The bending moment loading assembly 61 is fixedly connected with the bending moment loading clamp 60, and the bending moment loading assembly 61 applies acting force to the bending moment loading clamp 60 and is used for applying bending moment to the single-wing spar 2.
The test device of the embodiment has a simple structure, can effectively improve the efficiency of the single-wing spar crack propagation test, and can carry out the crack propagation test on the single-wing spar independently. By arranging the shear force loading device 5 and the bending moment loading device 6 and adjusting different proportional values of the force applied by the two sets of loading devices, the pure I-type (opening type) crack expansion process, the pure II-type (sliding type) crack expansion process or the composite crack expansion of the wing web plate of the airplane structure is realized, the transfer condition of the load borne by the whole single-wing spar in a wing box in the crack expansion process is simulated really and approximately, and the crack expansion process of the single-wing spar is simulated really. And simulating the boundary supporting condition of the wing box to the wing beam through the restraint of the bearing wall 1 and the simulated instability clamp 4.
Further, as shown in fig. 2, the bending moment loading assembly 61 includes a first bending moment loading plate 610, a second bending moment loading plate 612, and two second actuators 611, wherein the first bending moment loading plate 610 is fixedly connected to the first bending moment loading fixture 601, and the second bending moment loading plate 612 is fixedly connected to the second bending moment loading fixture 602. The bending moment loading plate 610 and the second bending moment loading plate 612 include two loading rods extending in parallel, and the two second actuators 611 are respectively and fixedly connected to one ends of the two loading rods of the first bending moment loading plate 610 and the second bending moment loading plate 612, and are configured to apply an acting force to the loading rods.
Further, in this embodiment, two second actuators 611 are disposed near one end of the loading rod and between the second actuators 611 and the loading rod, and each second load cell 51 is configured to measure the acting force applied to the loading rod by the second actuator.
Further, the test apparatus of the present embodiment comprises at least 3 anti-buckling clamps 3, each located at a position where the single spar is supported by a rib in the aircraft structure. In the embodiment, a plurality of anti-instability clamps 3 are adopted, and the support of a rib structure and a skin structure in a wing box to a single-wing spar structure is simulated through the anti-instability clamps.
Further, the single spar 2 comprises a lug 20, and one end of the shear loading device 5 is fixedly connected with the lug 20. In the crack propagation test of the single-spar structure, the center of the shear-loaded lug is positioned near the shear center of the spar structure, so that the torsion of the single-spar structure caused by the load eccentricity of a loading system is avoided.
Example two
In this embodiment, a single spar crack propagation test method is provided, using the test apparatus described above, the method comprising,
the first step is as follows: the initial crack of the spar structure was pre-cracked prior to crack propagation testing, at the crack tip of the lower cap of the spar, and the crack length was about 1.3 mm. Care should be taken to prevent residual stresses from occurring when the cracks are preformed.
The second step is that: mounting a test piece, and clamping and fixing one end of a single-wing beam 2 by using a bearing wall 1; the anti-instability clamp 3 clamps two opposite side surfaces of the single wing beam 2; the bending moment loading clamp 60 clamps and fixes the two opposite side faces at the other end of the single-wing beam 2 and is fixedly connected with the single-wing beam 2, and the bending moment loading assembly 61 is fixedly connected with the bending moment loading clamp 60. The shear loading device 5 is installed, and the lug end is connected and loaded with the first actuating cylinder through the bolt, so that the shear loading of the single-wing spar is realized.
The third step:
and in the simulation of the open crack propagation test, the two second actuating cylinders 611 respectively apply acting forces in different directions or different magnitudes to one ends of the two loading rods of the first bending moment loading plate 610 and the second bending moment loading plate 612, which extend parallel to each other, so as to realize bending moment loading on the single-wing spar 2. The two second actuators 611 respectively apply acting forces to one ends of the two loading rods extending in parallel, and the directions of the acting forces are parallel.
Performing composite crack propagation simulation, namely applying a web plate shearing force parallel to the side surface of the single-wing beam 2 to the single-wing beam 2 by using a shearing force loading device 5; meanwhile, the two second actuators 611 respectively apply acting forces in different directions or different magnitudes to one ends of the two loading rods of the first bending moment loading plate 610 and the second bending moment loading plate 612, which extend in parallel to each other, and simultaneously realize shear loading and bending moment loading on the single-wing spar 2, so as to simulate composite crack propagation.
The fourth step: when an open crack propagation test was conducted, the number of cycles N was recorded every 5mm of crack propagationiAnd corresponding spar crack tip position coordinates (x)i，yi). When a single-spar composite type crack propagation test is performed, cracks are generated and rotatedAnd folding while recording the crack propagation angle.
The test principle of the invention is as follows:
when the single-wing-beam test piece is installed, the single-wing-beam test piece is connected to a force bearing wall of a test room and is fixedly restrained on the root of the single-wing beam. The lug end of the single-wing beam assembly is connected with the first actuating cylinder through a bolt, so that the shear force loading on the single-wing beam is realized. The bending moment loading plates are connected to the bending moment loading clamp through bolts, and the connected bending moment loading plates are symmetrically connected to two sides of a web plate of the single-wing beam crack propagation test piece through bolts. In the actual structure of an aircraft, the wing box is a closed structure, and the wing beam can not be twisted due to the support of the wing beam structure by the skin and the wing ribs. In the crack propagation test of the single-wing spar structure, the bending moment loading plates are symmetrically arranged on two sides of the web plate of the single-wing spar, and the centers of the lugs of the single-wing spar are positioned near the shear center of the single-wing spar structure, so that the torsion of the single-wing spar structure caused by the load eccentricity of a shear loading system and a bending moment loading system is avoided. The shear force loading device and the bending moment loading device are provided with three loading actuating cylinders in total, the three loading actuating cylinders are provided with force transducers, and the three loading actuating cylinders are respectively connected to the lug structure and the two sides of the loading rod to realize shear force and bending moment loading. And measuring and outputting the force while loading through a force sensor, and monitoring the acting load of the whole wing spar of the airplane in the crack propagation process.
According to the actual structural size of the wing beam of the airplane, a group of buckling-simulating clamps are arranged at intervals of 330mm in the length direction of the wing beam. And (3) recording the cycle times and the position coordinates of the crack tip corresponding to the spar structure once the crack expands 5mm in the machine type spar crack expansion test. When a composite crack propagation test is carried out, the crack is bent, the bending angle of crack propagation needs to be recorded while the length and the cycle number of the crack are recorded, and the process curve of the crack propagation test of the spar is really recorded.
Claims (9)
1. A single wing beam crack propagation test device is used for carrying out a single wing beam (2) crack propagation test and is characterized by comprising a bearing wall (1), a plurality of anti-instability clamps (3), a shear force loading device (5) and a bending moment loading device (6),
the bearing wall (1) is used for clamping and fixing one end of the single wing beam (2);
the anti-instability clamp (3) comprises a clamp connecting piece (30) and an anti-instability clamp (31), the clamp connecting piece (30) and the anti-instability clamp (31) are respectively positioned on two opposite side surfaces of the single wing beam (2), and the upper end and the lower end of the clamp connecting piece (30) and the upper end and the lower end of the anti-instability clamp (31) are correspondingly and fixedly connected; the clamp connecting piece (30) is matched with the anti-instability clamp (31) to clamp the single wing beam (2);
the shear force loading device (5) is positioned on one side of the parallel single-wing beam (2) and is used for applying a web plate shear force parallel to the side face of the single-wing beam (2) to the single-wing beam (2);
the bending moment loading device (6) comprises a bending moment loading clamp (60) and a bending moment loading assembly (61), the bending moment loading clamp (60) comprises a first bending moment loading clamp (601) and a second bending moment loading clamp (602), the first bending moment loading clamp (601) and the second bending moment loading clamp (602) are respectively located on two opposite side faces of the single wing beam (2) and located at one end, far away from the bearing wall (1), of the single wing beam (2), and the first bending moment loading clamp (601) and the second bending moment loading clamp (602) are matched to clamp the single wing beam (2) and are fixedly connected with the single wing beam (2); the bending moment loading assembly (61) is fixedly connected with the bending moment loading clamp (60), and the bending moment loading assembly (61) applies acting force to the bending moment loading clamp (60) and is used for applying bending moment to the single wing beam (2).
2. A test device according to claim 1, wherein the shear loading device (5) is a first ram having a first load cell (50) disposed at an end of the first ram adjacent the spar (2), the first load cell (50) being located between the first ram and the spar (2) for measuring the web shear force applied by the first ram.
3. The test rig according to claim 1, wherein the bending moment loading assembly (61) comprises a first bending moment loading plate (610), a second bending moment loading plate (612) and two second rams (611), the first bending moment loading plate (610) being fixedly connected with the first bending moment loading clamp (601), the second bending moment loading plate (612) being fixedly connected with the first bending moment loading clamp (601),
the first bending moment loading plate (610) and the second bending moment loading plate (612) respectively comprise two loading rods extending in parallel, and the two second actuating cylinders (611) are respectively and correspondingly fixedly connected with the two loading rods of the first bending moment loading plate (610) and the second bending moment loading plate (612) and used for applying acting force to the loading rods.
4. A test device according to claim 3, wherein the second actuator cylinder (611) is provided with a second load cell (51) at an end thereof adjacent the load bar, the second load cell (51) being located between the second actuator cylinder (611) and the load bar for measuring the force applied to the load bar by the second actuator cylinder (611).
5. Test rig according to claim 1, characterized in that the test rig comprises at least 3 anti-buckling clamps (3), which 3 anti-buckling clamps (3) are each located at a position where a single spar is supported by a rib in the aircraft structure for simulating the bracing of the rib structure, the skin structure, to the single spar structure in a wing box.
6. Testing device according to claim 1, characterized in that the single spar (2) comprises a tab (20), one end of the shear loading device (5) being fixedly connected with the tab (20).
7. A single spar crack propagation test method using a test apparatus according to any of claims 1 to 6, the method comprising,
one end of the single wing beam (2) is clamped and fixed by a bearing wall (1); the anti-destabilization clamp (3) clamps two opposite side surfaces of the single wing beam (2); the bending moment loading clamp (60) clamps and fixes the two opposite side surfaces at the other end of the single wing beam (2) and is fixedly connected with the single wing beam (2), and the bending moment loading assembly (61) is fixedly connected with the bending moment loading clamp (60);
the two second actuating cylinders (611) respectively apply acting forces in different directions or different magnitudes to the two loading rods extending in parallel of the first bending moment loading plate (610) and the second bending moment loading plate (612), so that bending moment loading on the single-wing beam (2) is realized, and the two second actuating cylinders are used for simulating expansion crack propagation;
the directions of the forces exerted by the two second rams (611) are parallel.
8. The crack propagation test method of claim 7, further comprising,
applying a web plate shearing force parallel to the side surface of the single wing beam (2) to the single wing beam (2) by using a shearing force loading device (5); meanwhile, the two second actuating cylinders (611) respectively apply acting forces in different directions or different magnitudes to the two loading rods extending in parallel of the first bending moment loading plate (610) and the second bending moment loading plate (612), and meanwhile, the shear loading and bending moment loading of the single-wing spar (2) are achieved, and the composite crack propagation simulation device is used for simulating composite crack propagation.
9. The crack propagation test method of claim 8, further comprising, prior to performing the crack propagation test, performing a pre-crack of an initial crack of the single spar structure, the pre-crack being performed at a crack tip of a lower cap of the single spar.
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| CN114235375A (en) * | 2021-12-22 | 2022-03-25 | 中国飞机强度研究所 | Unmanned aerial vehicle wing girder strength test structure |
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