Wing body joint testing device

Abstract

The invention belongs to the technical field of aircraft structural strength ground tests, and particularly relates to a wing body joint test device. The device comprises a T-shaped joint (7), a lower web plate (105) and a supporting base (8), wherein the lower web plate (105) is used for connecting a wing body joint; the upper part of a horizontal rib plate (102) fixed on the wing body joint is connected with the supporting base (8) through a first long bolt (12); the upper butt-joint plate (3) is fixed on an upper web (104) of the wing body joint, and the end part of the upper butt-joint plate (3) is connected with a hollow square column (9); the vertical butt-joint plate (4) is attached and fixed to the vertical rib plate (103), and the other end of the vertical butt-joint plate (4) is fixedly connected with a hollow square column (9); the hollow square columns (9) are connected with the supporting base (8) through second long bolts (11), and strain gauges (15) are arranged on the first long bolts (12), the second long bolts (11) and the T-shaped connector (7) respectively. The wing body joint testing device is convenient to manufacture and low in cost.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure strength ground testing, and in particular to a wing-body joint testing device. Background Art

[0002] The wings and fuselage of transport aircraft are assembled together through wing-to-fuselage joints, such as Figure 1 As shown, the ear piece 101 at the upper end of the wing-to-body joint is connected to the wing, and the other parts of the wing-to-body joint are connected to the fuselage. The wing-to-body joint is a particularly important component of the aircraft structure. The wing-to-body joint mainly bears the tensile load of the wing. The ground strength test is the most reliable means to grasp its load-bearing and force-transmission characteristics. The ground strength test of the wing-to-body joint test includes static tests under different load distribution conditions, as well as fatigue tests under different load distributions and different stress ratios. The ability to adjust the load ratio under each condition is the difficulty of this test. At present, the wing-to-body joint test device is designed according to the stiffness distribution characteristics of the fuselage. The device is particularly large in size and weight. Some loads are applied by means of pressure on the actuator. The stability of the test device is poor, and the test operation risks are high. Not only the load transfer ratio cannot be adjusted, but also the wing-to-body joint has cracks many times before the target life during the fatigue test, which makes it difficult to meet the requirements of structural design selection. Summary of the invention

[0003] In order to solve at least one of the above technical problems, the present application provides a wing-body joint test device, wherein the wing-body joint comprises an ear piece located at the upper section, an upper web plate located at the middle section, and a lower web plate located at the lower section, a horizontal rib plate is arranged between the upper web plate and the ear piece, and a vertical rib plate is arranged on the side of the upper web plate, wherein the test device comprises:

[0004] A T-joint, one end of which is connected to the lower belly plate, and the other end is connected to a support base, and the support base is fixed on the test bench;

[0005] A horizontal butt plate is fixed to the horizontal rib plate, and the end thereof is connected to the supporting base through a first long bolt;

[0006] The upper butt plate has a middle plate surface fixed to the side of the upper web plate away from the vertical rib plate, and two ends are respectively fixedly connected to a hollow square column;

[0007] A vertical butt plate, one end of which is fitted and fixed on the vertical rib plate, and the other end is fixedly connected to a hollow square column;

[0008] Wherein, each hollow square column is connected to the supporting base through the second long bolt, each first long bolt, each second long bolt and the T-shaped joint are respectively provided with a strain gauge, and the ear piece is connected to the load applying mechanism.

[0009] Preferably, the vertical plate of the T-joint is connected to the two lower butt plates by bolts, the other ends of the two lower butt plates clamp the lower end surface of the lower belly plate and are connected to the lower belly plate by bolts, and the horizontal plate of the T-joint is connected to the support base by bolts.

[0010] Preferably, each end of the horizontal docking plate is provided with four through holes, wherein the two through holes in the middle are used to connect the four-hole square plate above the horizontal docking plate by bolts, and the two through holes on the two sides and the through holes on both sides of the four-hole square plate are aligned for installing the first long bolt.

[0011] Preferably, the hollow square column is a cube with square holes passing through it from top to bottom, a vertical through hole is opened on one side of the square hole to connect the upper docking plate or the vertical docking plate by bolts, and a parallel through hole is opened on the other side of the square hole to install the second long bolt.

[0012] Preferably, a gasket is installed at one end of the bolt head of the first long bolt and the second long bolt during assembly, and the nut end is assembled in the order of gasket, spring washer, gasket, spring washer and nut during assembly.

[0013] Preferably, the bolts connected to the wing-body joint are high-lock bolts.

[0014] The present application provides multiple load transfer paths, and the load on each path can be adjusted by connecting bolts. The wing-body joint test device of the present application is easy to manufacture, low in cost, and safe and reliable to assemble. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the wing-fuselage joint structure.

[0016] Figure 2 This is a schematic diagram of the connection between the wing-to-fuselage joint and each mounting plate and the supporting base of the wing-to-fuselage joint test device of this application.

[0017] Figure 3 For this application Figure 2 Schematic diagram of the connection between each mounting plate and the supporting base in the illustrated embodiment.

[0018] Among them, 1-wing-fuselage joint, 101-ear plate, 102-horizontal rib plate, 103-vertical rib plate, 104-upper belly plate, 105-lower belly plate, 2-horizontal docking plate, 3-upper docking plate, 4-vertical docking plate, 5-high locking bolt, 6-lower docking plate, 7-T-joint, 8-support base, 9-hollow square column, 10-stud, 11-second long bolt, 12-first long bolt, 13 is 60# bolt, 14-four-hole square plate, 15-strain gauge, 16 is 50# bolt, and 17 is 300# bolt. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0020] The present application provides a wing-body joint test device, such as Figure 1 As shown, the wing-body joint 1 includes an ear piece 101 located at the upper section, an upper web 104 located at the middle section, and a lower web 105 located at the lower section. A horizontal rib 102 is provided between the upper web 104 and the ear piece 101, and a vertical rib 103 is provided on the side of the upper web 104. It is characterized in that the test device includes:

[0021] A T-shaped connector 7, one end of which is connected to the lower belly plate 105, and the other end is connected to a support base 8, and the support base 8 is fixed on the test bench;

[0022] The horizontal butt plate 2 is fixed on the horizontal rib plate 102, and the end thereof is connected to the support base 8 via the first long bolt 12;

[0023] The upper butt plate 3, wherein the middle plate surface is fixed to the side of the upper web plate 104 away from the vertical rib plate 103, and the two ends are respectively fixedly connected to a hollow square column 9;

[0024] A vertical butt plate 4, one end of which is fitted and fixed on the vertical rib plate 103, and the other end is fixedly connected to a hollow square column 9;

[0025] Each hollow square column 9 is connected to the support base 8 via a second long bolt 11 , each first long bolt 12 , each second long bolt 11 and the T-joint 7 are provided with a strain gauge 15 , and the ear piece 101 is connected to the load applying mechanism.

[0026] In some optional embodiments, the vertical plate of the T-joint 7 is connected to the two lower docking plates 6 by bolts, the other ends of the two lower docking plates 6 clamp the lower end surface of the lower belly plate 105 and are connected to the lower belly plate 105 by bolts, and the horizontal plate of the T-joint 7 is connected to the support base 8 by bolts.

[0027] In some optional embodiments, four through holes are provided at each end of the horizontal docking plate 2, wherein the two through holes in the middle are used to connect the four-hole square plate 14 located above the horizontal docking plate 2 through bolts, and the two through holes on the two sides and the through holes on both sides of the four-hole square plate 14 are aligned for installing the first long bolt 12.

[0028] The wing-fuselage joint test device of the present application applies an upward load to the ear 101 of the wing-fuselage joint 1, and the load is transmitted to the support base 8 in four ways: the first load starts from the ear 101, passes through the horizontal rib plate 102, the horizontal docking plate 2, the four-hole square plate 14, and the first long bolt 12 to be transmitted to the support base 8; the second load starts from the ear 101, passes through two vertical rib plates 103, two vertical docking plates 4, two hollow square columns 9, and the second long bolt 11 to be transmitted to the support base 8; the third load starts from the ear 101, passes through the upper belly plate 104, the upper docking plate 3, two hollow square columns 9, and the second long bolt 11 to be transmitted to the support base 8; the fourth load starts from the ear 101, passes through the lower belly plate 105, two lower docking plates 6, and the T-joint 7 to be transmitted to the support base 8.

[0029] In the present application, strain gauges 15 are attached to the center of the first long bolt 12, the second long bolt 11, and the center of the vertical rib plate of the T-joint 7. The strain values ​​measured by the strain gauges 15 can be converted to obtain the magnitude of the four-way load. During the test, the magnitude of the four-way load can be adjusted by rotating the nuts of the first long bolt 12, the nuts of the second long bolt 11, and the nuts of the bolts between the T-joint 7 and the supporting base 8, so that the downward load of the fuselage is passively applied proportionally to the horizontal rib plate 102, the vertical rib plate 103, the upper belly plate 104, and the lower belly plate 105. This method has a clear mechanical state and an accurate load transmission ratio, which meets the requirements of the wing-body joint structure selection test.

[0030] In some optional embodiments, the bolts connected to the wing-body joint 1 are high-lock bolts 5. The high-lock bolts 5 are a type of bolt and are standard aviation fasteners. After assembly, they produce a higher preload force and have significantly higher fatigue performance than ordinary bolts. In the wing-body joint test device of the application, the bolts connected to the wing-body joint 1 of the test piece are all high-lock bolts 5.

[0031] The horizontal docking plate 2 of the present application is a long strip steel plate, preferably 10 mm thick, made of Q345 steel, with a central square hole for placing the ear piece 101 of the wing-body joint 1, a central small hole connected to the horizontal rib plate 102 of the wing-body joint 1 through a high locking bolt 5, four large holes at the central position of the two ends for installing the four-hole square plate 14, and four large holes at the two sides of the two ends for installing the first long bolt 12. The upper docking plate 3 is a rectangular steel plate, preferably 10 mm thick, made of 30CrMnSiA steel, heat treatment level 1000MPa, a central small hole connected to the upper belly plate 104 of the wing-body joint 1 through a high locking bolt 5, and six large holes at each end for installing the hollow square column 9. The vertical docking plate 4 is a rectangular steel plate, a total of two pieces, preferably 10 mm thick, made of 30CrMnSiA steel, heat treatment level 1000MPa, a small hole at one end connected to the vertical rib plate 103 of the wing-body joint 1 through a high locking bolt 5, and six large holes at the other end for installing the hollow square column 9. The lower docking plate 6 is a rectangular steel plate with an optimal thickness of 10 mm. The material is 30CrMnSiA steel with a heat treatment level of 1000MPa. There are two pieces in total, which are respectively installed in front and behind the lower belly plate 105 of the wing-body joint 1. The upper small hole is connected to the lower belly plate 105 of the wing-body joint 1 through the high locking bolt 5, and the four large holes in the lower part are used to install the vertical rib plate of the T-joint 7. The T-joint 7 is an integral machined part, made of 30CrMnSiA steel with a heat treatment level of 1000MPa. The thickness of the vertical rib plate is the same as that of the lower belly plate 105 of the wing-body joint 1. The thickness of the horizontal bottom plate is usually 40 mm. The T-joint 7 is installed between the two lower docking plates 6 through the four through holes on the vertical rib plate.

[0032] The supporting base 8 of the present application is a rectangular thick steel plate made of Q345. The large holes around it are connected to the load-bearing floor of the laboratory through bolts equipped in the laboratory. The small hole in the middle is a fisheye hole and is connected to the second long bolt 11, the first long bolt 12 and other bolts. The bolt heads of each bolt are placed in the fisheye hole.

[0033] In some optional embodiments, the hollow square column 9 is a cube with square holes passing through the top and bottom, a vertical through hole is opened on one side of the square hole to connect the upper docking plate 3 or the vertical docking plate 4 by bolts, and a parallel through hole is opened on the other side of the square hole to install the second long bolt 11.

[0034] In this embodiment, the hollow square column is made of Q345 steel, with a square hole in the middle, six vertical through holes on the side that can be assembled and connected with the upper docking plate 3 and the vertical docking plate 4, and two through holes that penetrate the upper and lower surfaces can be respectively installed with the second long bolt 11. The vertical through hole here means that the axis of the through hole is perpendicular to the axis of the square hole, and the parallel through hole means that the axis of the through hole is parallel to the axis of the square hole. The stud 10 is installed in the vertical through hole. The stud 10 is a standard part, made of 30CrMnSiA steel, with a heat treatment level of 1000MPa. Its two ends are used in conjunction with two washers and two nuts to install the hollow square column 9 at both ends of the upper docking plate 3 and one end of the vertical docking plate 4.

[0035] In some optional embodiments, a gasket is installed at one end of the bolt head of the first long bolt 12 and the second long bolt 11 during assembly, and the nut end is assembled in the order of gasket, spring washer, gasket, spring washer and nut during assembly.

[0036] The first long bolt 12 of the present application is a 1400# bolt, made of 30CrMnSiA steel, with a heat treatment level of 1000MPa, and is used in conjunction with three washers, two spring washers and a nut. A washer needs to be installed at one end of the bolt head during assembly, and the nut end is assembled in the order of washer, spring washer, washer, spring washer, and nut during assembly and connection. The second long bolt 11 has the same structure and usage as the first long bolt 12, but is slightly shorter in length and is a 1350# bolt.

[0037] The bolts used to connect the horizontal docking plate 2 and the four-hole square plate 14 in this application are 60# bolts 13, which are standard parts and can be made of Q345 steel. The four-hole square plate 14 is a rectangular steel plate with a thickness of 50mm. The bolts used to connect the lower docking plate 6 and the T-joint 7 in this application are 50# bolts 16, which are standard parts and made of 30CrMnSiA steel with a heat treatment level of 1000MPa. The bolts used to connect the T-joint 7 and the support base 8 in this application are 300# bolts 17.

[0038] The wing-fuselage joint test device of the present application is easy to manufacture, low in cost, safe and reliable in assembly, and has a high fatigue test frequency.

[0039] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A wing-body joint test device, the wing-body joint (1) comprising an ear piece (101) located at an upper section, an upper web (104) located at a middle section, and a lower web (105) located at a lower section, a horizontal rib plate (102) being arranged between the upper web (104) and the ear piece (101), and a vertical rib plate (103) being arranged on the side of the upper web (104), characterized in that: The test device comprises: A T-shaped joint (7), one end of which is connected to the lower belly plate (105), and the other end of which is connected to a support base (8), and the support base (8) is fixed on the test bench; A horizontal butt joint plate (2) is fixed on the horizontal rib plate (102), and an end portion thereof is connected to a support base (8) via a first long bolt (12); An upper butt joint plate (3), wherein the middle plate surface is fixed to the side of the upper web plate (104) away from the vertical rib plate (103), and the two ends are respectively fixedly connected to a hollow square column (9); A vertical butt joint plate (4), one end of which is fitted and fixed on the vertical rib plate (103), and the other end of which is fixedly connected to a hollow square column (9); Each hollow square column (9) is connected to a supporting base (8) via a second long bolt (11), each first long bolt (12), each second long bolt (11) and the T-shaped joint (7) are respectively provided with a strain gauge (15), and the ear piece (101) is connected to a load applying mechanism.

2. The wing-fuselage joint test device according to claim 1, characterized in that: The vertical plate of the T-joint (7) is connected to the two lower butt plates (6) by bolts, the other ends of the two lower butt plates (6) clamp the lower end surface of the lower belly plate (105) and are connected to the lower belly plate (105) by bolts, and the horizontal plate of the T-joint (7) is connected to the support base (8) by bolts.

3. The wing-fuselage joint test device according to claim 1, characterized in that: Each end of the horizontal docking plate (2) is provided with four through holes, wherein the two through holes in the middle are used to connect the four-hole square plate (14) located above the horizontal docking plate (2) through bolts, and the two through holes on the two sides and the through holes on the two sides of the four-hole square plate (14) are aligned and used to install the first long bolt (12).

4. The wing-fuselage joint test device according to claim 1, characterized in that: The hollow square column (9) is a cube with square holes passing through it from top to bottom. A vertical through hole is opened on one side of the square hole so as to connect the upper docking plate (3) or the vertical docking plate (4) by bolts. A parallel through hole is opened on the other side of the square hole so as to install the second long bolt (11).

5. The wing-fuselage joint test device according to claim 1, characterized in that: A gasket is installed at one end of the bolt head of the first long bolt (12) and the second long bolt (11) during assembly, and the nut end is assembled in the order of gasket, spring washer, gasket, spring washer and nut during assembly.

6. The wing-fuselage joint test device according to claim 1, characterized in that: The bolts connected to the wing-body joint (1) are high-locking bolts (5).

Images