A wing-body-joiner fatigue test piece

Abstract

The application belongs to the field of aircraft structure strength test, and particularly relates to a wing-body connection-body joint fatigue test piece. The test piece comprises: a test evaluation part which is consistent with the real structure of an aircraft, and the test evaluation part has a first support inclined surface; a bottom plate which is provided with bolt holes for cooperating with bolts to realize installation and positioning of the test piece; an outer edge strip and an inner edge strip which are connected with each other, and the outer edge strip and the inner edge strip are connected with the bottom plate, and a triangular support structure is formed between the outer edge strip, the inner edge strip and the bottom plate, the outer edge strip has a second support inclined surface, and the second support inclined surface of the outer edge strip is connected with the first support inclined surface of the test evaluation part; a vertical rib which comprises a first vertical rib part and a second vertical rib part, two ends of the first vertical rib part are connected with the outer edge strip and the inner edge strip respectively, and two ends of the second vertical rib part are connected with the outer edge strip and the bottom plate respectively; and a vertical rib diagonal brace which comprises a first vertical rib diagonal brace and a second vertical rib diagonal brace, the first vertical rib diagonal brace is connected with the outer edge strip and the bottom plate, and the second vertical rib diagonal brace is connected with the inner edge strip and the bottom plate.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing, and specifically relates to a wing-body connection-fuselage joint fatigue test piece. Background Technology

[0002] In aircraft structural strength testing, fatigue testing of the wing-fuselage junction area (hereinafter referred to as wing-fuselage junction) is one of the most important tests, as it determines the fatigue life of the entire aircraft.

[0003] Existing wing-fuselage joint fatigue test specimens typically only reinforce the bottom of the specimen, which easily leads to failure in non-test areas, resulting in fatigue test failure. Therefore, the key to solving this problem lies in designing a wing-fuselage joint test specimen that ensures a realistic structure and the highest stress level in the test area, so that test failure occurs within the test area.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Utility Model Content

[0005] The purpose of this application is to provide a wing-body connection-fuselage joint fatigue test specimen to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A wing-fuselage joint fatigue test specimen includes:

[0008] The test and assessment unit is consistent with the actual structure of the aircraft and has a first supporting inclined surface.

[0009] A base plate, wherein bolt holes are provided on the base plate for mounting and positioning the test piece with bolts;

[0010] The edging strip includes an outer edging strip and an inner edging strip, the outer edging strip and the inner edging strip are connected to each other, and both the outer edging strip and the inner edging strip are connected to the base plate. The outer edging strip, the inner edging strip and the base plate form a triangular support structure. The outer edging strip has a second support slope, and the second support slope of the outer edging strip is connected to the first support slope of the test and evaluation part.

[0011] The vertical rib includes an L-shaped first vertical rib portion and a second vertical rib portion. The two ends of the first vertical rib portion are respectively connected to the outer edge strip and the inner edge strip, and the two ends of the second vertical rib portion are respectively connected to the outer edge strip and the bottom plate.

[0012] The vertical bracing includes a first vertical bracing and a second vertical bracing. The first vertical bracing connects the outer edge strip and the bottom plate, and the second vertical bracing connects the inner edge strip and the bottom plate.

[0013] In at least one embodiment of this application, the test evaluation section is a single-ear connector with a weight reduction hole.

[0014] In at least one embodiment of this application, the connection between the test assessment section and the outer edge strip is widened and thickened.

[0015] In at least one embodiment of this application, the radius (R) at the bend between the test assessment section and the outer edge strip is greater than 30 mm.

[0016] In at least one embodiment of this application, the maximum tensile stress of the bolt is less than 1 / 3 of the bolt failure load, and the distance between the bolt hollow and the boundary is greater than twice the bolt diameter.

[0017] In at least one embodiment of this application, the connection between the outer edge strip and the inner edge strip and the base plate is widened and thickened.

[0018] In at least one embodiment of this application, the radius (R) at the bend between the outer edge strip and the inner edge strip and the base plate is greater than 30 mm.

[0019] In at least one embodiment of this application, the connection points between the vertical rib and the outer edge strip, the inner edge strip, and the base plate are all widened and thickened.

[0020] In at least one embodiment of this application, the radius (R) at the bends of the vertical rib, the outer edge strip, the inner edge strip, and the base plate is greater than 30 mm.

[0021] The utility model has at least the following beneficial technical effects:

[0022] The wing-fuselage joint fatigue test specimen of this application can ensure that the test area is real and the stress is maximum. The stress in the transition section and the fixed support plate is less than the stress in the test area. At the same time, the bolt load is not high, ensuring that the test failure occurs in the test area, so that the test results of the fuselage joint test area are real and reliable. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of a wing-body connection-fuselage joint fatigue test specimen according to one embodiment of this application.

[0024] in:

[0025] 1-Outer edge strip; 2-Vertical reinforcement; 3-Inner edge strip; 4-Vertical reinforcement diagonal brace; 5-Base plate. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0027] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0028] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0029] This application provides a wing-body connection-fuselage joint fatigue test piece, including: a test and assessment section, a base plate 5, a flange, a vertical rib 2, and a vertical rib diagonal brace 4.

[0030] like Figure 1 As shown, the test assessment section is determined according to the test and assessment requirements, and adopts a test assessment section consistent with the actual structure of the aircraft. This test assessment section has a first supporting inclined surface. In this embodiment, the test assessment section is a single-ear connector with weight reduction holes.

[0031] The base plate 5 serves as the support and positioning structure for the test specimen. Multiple bolt holes are provided on the base plate 5 for mounting and positioning the test specimen using bolts. In this embodiment, the base plate 5 is rectangular. The overall dimensions of the base plate 5 are based on the horizontal projection of the first supporting inclined plane onto the horizontal plane, with an additional 75mm on each side in the length direction and an additional 20mm on each side in the width direction. During installation, bolts are pre-positioned on the base plate 5. The maximum tensile stress of the bolts on the base plate 5 is less than 1 / 3 of the bolt failure load, and the distance between the bolt hollow and the boundary is greater than twice the bolt diameter.

[0032] The edging strip includes an outer edging strip 1 and an inner edging strip 3. The outer edging strip 1 and the inner edging strip 3 are connected to each other, and both the outer edging strip 1 and the inner edging strip 3 are connected to the base plate 5. The outer edging strip 1, the inner edging strip 3 and the base plate 5 form a triangular support structure. The outer edging strip 1 has a second support slope, and the second support slope of the outer edging strip 1 is connected to the first support slope of the test and evaluation section.

[0033] The vertical rib 2 includes an L-shaped first vertical rib section and a second vertical rib section. The two ends of the first vertical rib section are respectively connected to the outer edge strip 1 and the inner edge strip 3, and the two ends of the second vertical rib section are respectively connected to the outer edge strip 1 and the bottom plate 5.

[0034] The vertical bracing 4 includes a first vertical bracing and a second vertical bracing. The first vertical bracing connects the outer edge strip 1 and the base plate 5, and the second vertical bracing connects the inner edge strip 3 and the base plate 5.

[0035] In a preferred embodiment of this application, the connection between the test and evaluation section and the outer edge strip 1 is widened and thickened, and the radius (R) at the bend between the test and evaluation section and the outer edge strip 1 is greater than 30 mm.

[0036] In a preferred embodiment of this application, the connection between the outer edge strip 1 and the inner edge strip 3 and the base plate 5 is widened and thickened, and the radius (R) at the bend between the outer edge strip 1 and the inner edge strip 3 and the base plate 5 is greater than 30mm.

[0037] In the preferred embodiment of this application, the connection between the vertical rib 2 and the outer edge strip 1, the inner edge strip 3 and the bottom plate 5 is widened and thickened, and the radius (R) at the bend of the vertical rib 2 and the outer edge strip 1, the inner edge strip 3 and the bottom plate 5 is greater than 30mm.

[0038] The wing-fuselage joint fatigue test specimen of this application is designed for fatigue testing of the fuselage joint structure of the wing-fuselage connection. The core features are three points: 1. The structure of the test area is consistent with the actual structure of the aircraft to ensure the effectiveness of the test area; 2. The transition section (edge ​​strip and vertical rib 2) is reinforced to ensure that the stress level is lower than that of the test area; 3. The connection structure with the test fixture (base plate 5) is reinforced to ensure that the stress level is lower than that of the test area and the transition section.

[0039] If the test specimen is designed according to existing technology, it is prone to failure at the transition section or the base plate, making it impossible to conduct a true test and verification of the test area. According to the test specimen design in this application, the stress gradually decreases from the test area to the transition section and then to the base plate. The stress measured in each area during the test is consistent with the design stress and matches the finite element analysis results. The test results are authentic and reliable, proving the feasibility of the test specimen in this application.

[0040] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A fatigue test specimen for a wing-fuselage joint, characterized in that, include: The test and assessment unit is consistent with the actual structure of the aircraft and has a first supporting inclined surface. The base plate (5) has bolt holes for mounting and positioning the test piece with bolts. The rim strip includes an outer rim strip (1) and an inner rim strip (3). The outer rim strip (1) and the inner rim strip (3) are connected to each other, and both the outer rim strip (1) and the inner rim strip (3) are connected to the base plate (5). A triangular support structure is formed between the outer rim strip (1), the inner rim strip (3), and the base plate (5). The outer rim strip (1) has a second support slope, and the second support slope of the outer rim strip (1) is connected to the first support slope of the test and evaluation section. The vertical rib (2) includes an L-shaped first vertical rib section and a second vertical rib section. The two ends of the first vertical rib section are respectively connected to the outer edge strip (1) and the inner edge strip (3), and the two ends of the second vertical rib section are respectively connected to the outer edge strip (1) and the bottom plate (5). The vertical bracing (4) includes a first vertical bracing and a second vertical bracing. The first vertical bracing connects the outer edge strip (1) and the bottom plate (5), and the second vertical bracing connects the inner edge strip (3) and the bottom plate (5).

2. The wing-fuselage joint fatigue test specimen according to claim 1, characterized in that, The test and evaluation section is a single-ear connector with a weight reduction hole.

3. The wing-fuselage joint fatigue test specimen according to claim 2, characterized in that, The connection between the test and evaluation section and the outer edge strip (1) is widened and thickened.

4. The wing-fuselage joint fatigue test specimen according to claim 3, characterized in that, The radius (R) at the bend between the test section and the outer edge strip (1) is greater than 30 mm.

5. The wing-fuselage joint fatigue test specimen according to claim 1, characterized in that, The maximum tensile stress of the bolt is less than 1 / 3 of the bolt failure load, and the distance between the bolt hollow and the boundary is greater than twice the bolt diameter.

6. The wing-fuselage joint fatigue test specimen according to claim 1, characterized in that, The connection between the outer edge strip (1) and the inner edge strip (3) and the base plate (5) is widened and thickened.

7. The wing-fuselage joint fatigue test specimen according to claim 6, characterized in that, The radius (R) at the bend between the outer edge strip (1) and the inner edge strip (3) and the base plate (5) is greater than 30 mm.

8. The wing-fuselage joint fatigue test specimen according to claim 1, characterized in that, The connection points between the vertical rib (2) and the outer edge strip (1), the inner edge strip (3) and the bottom plate (5) are all widened and thickened.

9. The wing-fuselage joint fatigue test specimen according to claim 8, characterized in that, The radius (R) at the bends of the vertical rib (2) with the outer edge strip (1), the inner edge strip (3), and the bottom plate (5) is greater than 30 mm.

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