Large aircraft small component high cantilever static test loading device

Abstract

This utility model discloses a high-cantilever static test loading device for small components of a large aircraft. It includes an APU loading component (1), which includes a cuboid main body structure (101). The front end of the cuboid main body structure (101) is provided with a front connecting piece (102). The bottom surface of the cuboid main body structure (101) behind the front connecting piece (102) is connected with a rear connecting piece (103). The bottom ends of the front and rear connecting pieces are respectively provided with a front connecting groove (104) and a rear connecting groove (105). The front connecting piece (102) around the front connecting groove (104) has three front connecting holes (106) distributed in a triangular pattern. The side wall of the rear connecting groove (105) is provided with a through rear connecting hole (107). The upper surface of the cuboid main body structure (101) is provided with a vertical loading hole (108), and the rear end face is provided with a horizontal loading hole (109). The axes of the vertical loading hole (108) and the horizontal loading hole (109) intersect at the center of gravity of the APU component (9). This invention can accurately perform static cantilever tests on small components of large aircraft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft structural strength testing technology, and in particular to a high-cantilever static test loading device for small components of large aircraft. Background Technology

[0002] Currently, static load tests primarily rely on actuators mounted on the factory beams to apply the loads specified in the test outline in stages, verifying the aircraft structure's load-bearing capacity under static loads. To accommodate more test space in the factory, beams are often arranged around the factory walls and ceiling, typically in a U-shape to improve their strength, stiffness, and stability. However, for small components installed in the nooks and crannies of large aircraft, the significant difference in volume between the small component and the overall aircraft, coupled with the numerous surrounding structures, makes the conventional U-shaped beam method difficult to implement. Furthermore, the U-shaped beam supports are prone to interfering with the aircraft's main load-bearing components, making static loading of small components on large aircraft quite challenging.

[0003] APU (Auxiliary Power Unit) is an auxiliary power unit for aircraft. When the main power source fails, the auxiliary power source takes over to provide electrical power to the aircraft. The APU of a certain large amphibious aircraft (35.8m in length and 38.8m in wingspan) is mounted on the upper side of the mid-fuselage using a bracket. The APU is relatively heavy (approximately 250kg). The APU mounting bracket is located near wing components, and the surrounding area consists of the wing trailing edge, mid-fuselage panels, and other main load-bearing structures (see...). Figure 1 If the APU mounting bracket deforms or fails, it will inevitably affect the APU device and the main load-bearing structure. Therefore, a static test is required to analyze the load-bearing capacity of the APU mounting bracket. The test conditions are in two directions: vertically downward and horizontally. However, the actual APU is quite large (approximately 1620mm long x 600mm wide x 600mm high), making direct testing inconvenient. Therefore, a dummy APU with matching stiffness needs to be installed on the bracket to replace the actual APU for testing (see [link to relevant documentation]). Figure 2Due to the small size of the APU dummy (approximately 800mm long x 600mm wide x 1200mm high), and the change in the overall layout from mounting the APU on the outer side of the rear fuselage panel to the upper side of the mid-fuselage panel, the loading joint position of the dummy APU is not at the center of gravity of the actual APU, significantly affecting the accuracy of the test. Furthermore, since the APU is mounted on the upper side of the mid-fuselage, its ability to withstand vertically downward loads needs to be assessed. The method of applying loads by arranging the actuator on the roof beam of the factory building has problems such as the beam being extremely high and low vertical loading accuracy for the APU, failing to meet the requirements of the test specifications. Specifically, the APU mounting bracket partially overlaps with the trailing edge of the wing in the vertical direction, and a conventional U-shaped beam arrangement would cause interference between the vertical support beam and the wing. Therefore, applying static load in the vertical direction to a small APU mounting bracket (approximately 800mm long, 600mm wide, and 1200mm high) on the upper side of the mid-fuselage of a large aircraft (35.8m long x 38.8m wingspan) is a challenge. Utility Model Content

[0004] The purpose of this invention is to provide a loading device for static testing of small components of large aircraft using a high cantilever design. This invention can accurately perform static testing of small components of large aircraft using a high cantilever design.

[0005] The technical solution of this utility model is: a high-cantilever static test loading device for small components of large aircraft, including an APU loading component. The APU loading component includes a cuboid main body structure. The front end face of the cuboid main body structure is provided with a front connecting piece. The bottom face of the cuboid main body structure behind the front connecting piece is connected with a rear connecting piece. The bottom ends of the front and rear connecting pieces are respectively provided with a front connecting groove and a rear connecting groove. Three front connecting holes are triangularly distributed on the front connecting piece around the front connecting groove. The side wall of the rear connecting groove is provided with a through rear connecting hole. The upper surface of the cuboid main body structure is provided with a vertical loading hole, and the rear end face is provided with a horizontal loading hole. The axes of the vertical loading hole and the horizontal loading hole intersect at the center of gravity of the APU component.

[0006] The aforementioned high-cantilever static test loading device for small components of large aircraft also includes a loading support assembly. The loading support assembly includes a column with a long base beam and a short base beam at the lower end, which are arranged in a cross pattern. During vertical loading, a single loading support assembly is placed within the angle range between the left / right wing and the fuselage of the large aircraft. The upper end of the column is connected to the vertical loading crossbeam. The long base beam and the vertical loading crossbeam are located on both sides of the column and are parallel to each other. The vertical loading crossbeam is connected to the vertical loading hole via the vertical loading actuator assembly.

[0007] In the aforementioned high-cantilever static test loading device for small components of large aircraft, a top diagonal bracing beam is provided between the vertical loading beam and the column; and a bottom diagonal bracing beam is provided between the long and short base beams and the column.

[0008] In the aforementioned high-cantilever static test loading device for small components of large aircraft, during horizontal loading, two loading support components are arranged in the angle range between the left and right wings of the large aircraft and the fuselage, respectively. The upper ends of the two columns are connected by a horizontal loading beam, and the horizontal loading beam is connected to the horizontal loading hole through the horizontal loading actuator assembly.

[0009] In the aforementioned high-cantilever static test loading device for small components of large aircraft, the APU loading component is composed of 30CrMnSiA.

[0010] In the aforementioned large aircraft small component high cantilever static test loading device, the APU loading component is an integrally machined structure.

[0011] The advantages of this utility model are: this utility model can match the APU dummy by setting a loading component, and at the same time set a vertical loading hole and a horizontal loading hole with the axis intersecting the center of gravity of the APU real part in the loading component; this structure effectively overcomes the problem of the center of gravity of the APU dummy and the APU real part shifting due to changes in the overall layout scheme, and the loading component has a simple structure and is easy to process and manufacture.

[0012] This invention designs a loading support assembly and positions it within the angle range between the left / right wings and fuselage of a large aircraft. During vertical loading, the entire vertical loading support system is formed by fixing a vertical loading beam to the upper end of the column, followed by arranging the vertical loading actuator assembly on the vertical loading beam. Compared to traditional vertical loading support systems that utilize roof beams to apply loads, this structure significantly reduces the beam height, minimizes load loss during loading, and improves vertical loading accuracy, effectively meeting the requirements of the test specifications. Furthermore, the loading support assembly is supported at its bottom by intersecting long and short base beams, with the long base beam and the vertical loading beam positioned parallel to each other on opposite sides of the column; this structure effectively ensures support rigidity during loading.

[0013] The loading support component of this utility model can also be combined with the horizontal loading beam to form a horizontal loading support system, allowing for flexible arrangement. Attached Figure Description

[0014] Figure 1 This is a schematic diagram showing the installation location of the APU component; Figure 2 This is a diagram showing the installation of an APU dummy component; Figure 3 This is a schematic diagram of the APU loading component structure; Figure 4 This is a schematic diagram of the connection structure between the APU loading component and the APU dummy component; Figure 5 This is a schematic diagram of a vertical loading system; Figure 6 This is a schematic diagram of vertical loading; Figure 7 This is a schematic diagram of the vertical loading system layout; Figure 8 This is a schematic diagram of horizontal loading; Figure 9 This is a schematic diagram of a horizontal loading support system. Detailed Implementation

[0015] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.

[0016] Example 1. A loading device for static testing of small components of a large aircraft using a high cantilever, see [link to example]. Figures 1-9 The APU loading component 1 includes a cuboid main body structure 101. The front end of the cuboid main body structure 101 is provided with a front connecting piece 102. The bottom surface of the cuboid main body structure 101 behind the front connecting piece 102 is connected to a rear connecting piece 103. The bottom ends of the front and rear connecting pieces are respectively provided with a front connecting groove 104 and a rear connecting groove 105. Three front connecting holes 106 are triangularly distributed on the front connecting piece 102 around the front connecting groove 104. The side wall of the rear connecting groove 105 is provided with a through rear connecting hole 107. The upper surface of the cuboid main body structure 101 is provided with a vertical loading hole 108, and the rear end face is provided with a horizontal loading hole 109. The axes of the vertical loading hole 108 and the horizontal loading hole 109 intersect at the center of gravity of the APU component 2.

[0017] It also includes a loading support assembly 3, which includes a column 31 with a long base beam 32 and a short base beam 33 at the lower end, and the long and short base beams are arranged in a cross pattern. During vertical loading, a single loading support assembly 3 is placed within the angle range between the left / right wings and the fuselage of the large aircraft. The upper end of the column 31 is connected to the vertical loading crossbeam 4. The long base beam 32 and the vertical loading crossbeam 4 are respectively located on both sides of the column 31 and are parallel to each other. The vertical loading crossbeam 4 is connected to the vertical loading hole 108 through the vertical loading actuator assembly 5.

[0018] The aforementioned vertical loading beam 4 and column 31 are provided with a top diagonal bracing beam 35; the long and short base beams and column 31 are both provided with a bottom diagonal bracing beam 34.

[0019] During horizontal loading, the two loading support components 3 are positioned within the angle range between the left and right wings of the large aircraft and the fuselage, respectively. The upper ends of the two columns 31 are connected by a horizontal loading beam 6, which is connected to the horizontal loading hole 109 via a horizontal loading actuator assembly 7.

[0020] The aforementioned APU loading component 1 is made of 30CrMnSiA.

[0021] The aforementioned APU loading component 1 is a one-piece structure machined as a whole.

[0022] Before loading, connect the APU dummy 8 to the mounting bracket 10 in the same way that the APU real component 9 is connected to the mounting bracket 10, see [link to previous section]. Figure 2 Align the front connecting hole 106 with the hole on the triangular piece 11 of the APU dummy 8 and secure it with bolts; the front connecting groove 104 is engaged with the yaw rod 12 of the APU dummy 8, and the rear connecting hole 107 at the rear connecting groove 105 is aligned with the rear connector 2 on the yaw rod 12 and secured with a pin, see [link to relevant documentation]. Figure 4 When vertically loaded, press Figures 5-7 Set up the vertical loading system and apply vertical loading; for horizontal loading, follow the instructions. Figures 8-9 Set up the horizontal loading system and perform horizontal loading.

Claims

1. A loading device for static cantilever testing of small components of a large aircraft, characterized in that, The APU loading component (1) includes a cuboid main body structure (101). The front end of the cuboid main body structure (101) is provided with a front connecting piece (102). The bottom surface of the cuboid main body structure (101) behind the front connecting piece (102) is connected with a rear connecting piece (103). The bottom ends of the front and rear connecting pieces are respectively provided with a front connecting groove (104) and a rear connecting groove (105). The front connecting piece (102) around the front connecting groove (104) has three front connecting holes (106) distributed in a triangular pattern. The side wall of the rear connecting groove (105) is provided with a through rear connecting hole (107). The upper surface of the cuboid main body structure (101) is provided with a vertical loading hole (108), and the rear end face is provided with a horizontal loading hole (109). The axes of the vertical loading hole (108) and the horizontal loading hole (109) intersect at the center of gravity of the APU component (9).

2. The loading device for static testing of small components of large aircraft with high cantilever as described in claim 1, characterized in that: It also includes a loading support assembly (3), which includes a column (31) with a long base beam (32) and a short base beam (33) at the lower end. The long and short base beams are arranged in a cross pattern. When loading vertically, a single loading support assembly (3) is placed within the angle range between the left / right large aircraft wing and the fuselage. The upper end of the column (31) is connected to the vertical loading crossbeam (4). The long base beam (32) and the vertical loading crossbeam (4) are respectively located on both sides of the column (31) and are parallel to each other. The vertical loading crossbeam (4) is connected to the vertical loading hole (108) through the vertical loading actuator assembly (5).

3. The loading device for static testing of small components of large aircraft using a high cantilever as described in claim 2, characterized in that: A top diagonal bracing beam (35) is provided between the vertical loading beam (4) and the column (31); a bottom diagonal bracing beam (34) is provided between the long and short base beams and the column (31).

4. The loading device for static testing of small components of large aircraft with high cantilever as described in claim 2, characterized in that: During horizontal loading, the two loading support components (3) are arranged in the angle range between the left and right wings of the large aircraft and the fuselage, respectively. The upper ends of the two columns (31) are connected by a horizontal loading beam (6), and the horizontal loading beam (6) is connected to the horizontal loading hole (109) through the horizontal loading actuator assembly (7).

5. The high-cantilever static test loading device for small components of large aircraft according to claim 1, characterized in that: The APU loading component (1) is made of 30CrMnSiA.

6. The loading device for static testing of small components of large aircraft with high cantilever as described in claim 1, characterized in that: The APU loading component (1) is a one-piece structure machined as a whole.

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