Radial compression test loading structure for single ear joint axle hole of vertical tail wall plate root

Abstract

The application belongs to the technical field of strength test of single lug joint of vertical tail wall plate root of an airplane, and particularly relates to a radial compression test loading structure of a single lug joint shaft hole of a vertical tail wall plate root of an airplane, when strength test is performed by using the radial compression test loading structure, a test machine can apply a pressure load on a wall surface of a loading pressure platform, the pressure load can be transmitted to a shaft hole of a single lug joint of a single lug joint test piece through a support bushing and a loading shaft, a radial compression load is applied in the shaft hole of the single lug joint, in the process, two support bushings can support the single lug joint of the single lug joint test piece from two sides, two support plates can support a transition section of the single lug joint test piece from two sides, lateral deviation of the single lug joint test piece is prevented, and the two support bushings and the support plates can follow the loading pressure platform to follow the support, the stress environment of the single lug joint can be well ensured, and the accuracy of a test result can be ensured.

Description

Technical Field

[0001] This application belongs to the technical field of strength testing of single-ear joint at the root of aircraft vertical tail panel, specifically relating to a radial compression test loading structure for the shaft hole of a single-ear joint at the root of aircraft vertical tail panel. Background Technology

[0002] A single-ear connector extends from the base of the aircraft's vertical tail panel and connects with a double-ear connector, resulting in high connection efficiency.

[0003] To assess the stability and strength of the single-ear joint at the root of the aircraft vertical tail panel under axial compression, a single-ear joint test piece was designed for radial compression testing of the shaft hole. The single-ear joint test piece includes a single-ear joint, a transition section formed at the root of the single-ear joint, and a support section formed below the transition section. During the radial compression test of the shaft hole, the support section is used for support. A radial compressive load needs to be applied to the shaft hole of the single-ear joint, and the single-ear joint and its transition section need to be supported to prevent lateral displacement and to reproduce the actual stress on the single-ear joint on the aircraft.

[0004] Currently, when conducting radial compression tests on the shaft hole of the single-ear joint at the root of the aircraft vertical tail panel, it is difficult to ensure the follow-up support of the single-ear joint and its transition section of the single-ear joint test piece, which can easily have a significant impact on the test load and make it difficult to guarantee the accuracy of the test results.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a radial compression test loading structure for the single-ear joint shaft hole at the root of an aircraft vertical tail panel, in order to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A radial compression test loading structure for a single-ear joint shaft hole at the root of an aircraft vertical tail panel includes:

[0010] Base plate;

[0011] Two positioning clamps are connected to the base plate and clamped on both sides of the support section of the single-ear joint test piece to provide reliable support for the single-ear joint test piece;

[0012] Two guide supports are connected to the base plate;

[0013] Two sets of guide rods are connected to two guide supports;

[0014] The loading platform has a through-hole and two sets of guide holes between its upper and lower walls, and loading holes on its two side walls. The limiting hole is located between the two sets of guide holes and is fitted onto the outer periphery of the single-ear joint of the single-ear joint test piece. The two sets of guide holes are fitted onto two sets of guide rods.

[0015] Two support bushings are provided in two loading holes, supporting both sides of the single-ear joint of the single-ear joint test piece;

[0016] The loading shaft passes through the shaft hole of the single-ear joint of the single-ear joint test piece, and two support bushings are provided.

[0017] Two limit strips are installed through the side walls at both ends of the loading shaft and connected to the side walls of the loading pressure table to press the two support bushings.

[0018] Two support plates are set inside the limiting holes and are located on both sides of the transition section of the single-ear joint test piece. The outer wall of the plate has multiple blind support holes.

[0019] Two sets of support bolts are screwed onto the two side walls of the loading platform. The top of the bolts extends into the blind holes of the two support plates, so that the two support plates support the two sides of the transition section of the single-ear joint test piece.

[0020] According to at least one embodiment of this application, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, two positioning clamps are connected to the support section of the single-ear joint test piece by bolts.

[0021] The base plate has two T-shaped clamp positioning grooves and a T-shaped support positioning groove.

[0022] Two positioning clamps are connected to the base plate by bolts through the connecting edge. The corresponding bolt holes on the connecting edge are racetrack-shaped. The head of the bolt connecting the base plate on each positioning clamp is stuck in a T-shaped clamp positioning groove.

[0023] Each guide support is connected to the base plate via two sets of bolts on the connecting edge. The heads of the two sets of bolts are engaged in the positioning grooves of the two T-shaped supports, and the corresponding bolt holes on the connecting edge of the two guide supports are in the shape of a racetrack.

[0024] According to at least one embodiment of this application, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, two sets of guide rods are threadedly connected to two guide supports.

[0025] The radial compression test loading structure for the single-ear joint shaft hole at the root of the aircraft vertical tail panel also includes:

[0026] Two sets of linear bearings are installed in two sets of guide holes using bearing retaining rings and are fitted onto two sets of guide rods.

[0027] According to at least one embodiment of this application, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, the two support bushings are stepped at one end on the outside and are embedded in the two loading holes.

[0028] The outer end of each of the two support bushings has a limiting groove that engages with the two limiting strips.

[0029] The two ends of the two limit bars are bolted to the side wall of the loading platform.

[0030] This application has at least the following beneficial technical effects:

[0031] A radial compression test loading structure for the shaft hole of a single-ear joint at the root of an aircraft vertical tail panel is provided. During strength testing, a compressive load is applied to the wall surface of the loading platform by a testing machine. This compressive load is transmitted to the shaft hole of the single-ear joint test piece via support bushings and a loading shaft, applying a radial compression load within the shaft hole. During this process, two support bushings support the single-ear joint test piece from both sides, and two support plates support the transition section of the single-ear joint test piece from both sides, preventing lateral displacement of the single-ear joint test piece. Furthermore, the two support bushings and support plates can move with the loading platform, effectively ensuring the stress environment of the single-ear joint and guaranteeing the accuracy of the test results. In addition, two guide supports and guide rods, in conjunction with the guide hole on the loading platform, ensure that the loading platform can only undergo vertical displacement under the action of the testing machine during the test, preventing horizontal deflection and ensuring the accurate application of the radial compression load within the shaft hole of the single-ear joint. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel provided in the embodiments of this application;

[0033] Figure 2 This is a schematic diagram of the base plate provided in an embodiment of this application;

[0034] Figure 3 This is a schematic diagram of the positioning clamp provided in an embodiment of this application;

[0035] Figure 4 This is a schematic diagram of the guide support and its guide rod provided in the embodiments of this application;

[0036] Figure 5 yes Figure 4 A sectional view;

[0037] Figure 6This is a schematic diagram of the loading stage provided in an embodiment of this application;

[0038] Figure 7 yes Figure 6 Sectional view along axis AA;

[0039] Figure 8 This is a schematic diagram of the support bushing and its limiting strip provided in an embodiment of this application;

[0040] Figure 9 yes Figure 8 A sectional view;

[0041] Figure 10 This is a schematic diagram of the single-ear connector test piece and its support plate and support bolts provided in the embodiments of this application;

[0042] in:

[0043] 1-Base plate; 2-Positioning clamp; 3-Single-ear joint test piece; 4-Guide support; 5-Guide rod; 6-Loading pressure table; 7-Support bushing; 8-Loading shaft; 9-Limiting strip; 10-Support plate; 11-Support bolt; 12-Linear bearing.

[0044] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0045] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0046] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0047] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0048] The following is in conjunction with the appendix Figures 1 to 10 This application will be described in further detail.

[0049] A radial compression test loading structure for a single-ear joint shaft hole at the root of an aircraft vertical tail panel includes:

[0050] Base plate 1;

[0051] Two positioning clamps 2 are connected to the base plate 1 and clamped on both sides of the support section of the single-ear joint test piece 3;

[0052] Two guide supports 4 are connected to the base plate 1;

[0053] Two sets of guide rods 5 are connected to two guide supports 4;

[0054] The loading platform 6 has a through-hole and two sets of guide holes between its upper and lower walls, and loading holes on its two side walls. The limiting hole is located between the two sets of guide holes and is fitted onto the outer periphery of the single-ear joint of the single-ear joint test piece 3. The two sets of guide holes are fitted onto the two sets of guide rods 5.

[0055] Two support bushings 7 are set in two loading holes and support both sides of the single-ear connector of the single-ear connector test piece 3;

[0056] Loading shaft 8, through the shaft hole of the single-ear joint of the single-ear joint test piece 3, and two support bushings 7 are provided;

[0057] Two limiting strips 9 are installed through the side walls at both ends of the loading shaft 8 and connected to the side walls of the loading pressure table 6 to press the two support bushings 7.

[0058] Two support plates 10 are set in the limiting hole and located on both sides of the transition section of the single-ear joint test piece 3. Multiple support blind holes are provided on the outer wall.

[0059] Two sets of support bolts 11 are screwed onto the two side walls of the loading platform 6. The top of the bolts extends into the blind holes of the two support plates 10, so that the two support plates 10 support the two sides of the transition section of the single-ear joint test piece 3 and can eliminate the influence of the gravity of the support plates 10 on the single-ear joint test piece 3.

[0060] Using the radial compression test loading structure for the single-ear joint shaft hole at the root of the aircraft vertical tail panel disclosed in the above embodiment, a strength test is conducted. A testing machine applies a compressive load to the wall surface of the loading platform 6. This compressive load is transmitted through the support bushings 7 and the loading shaft 8 to the shaft hole of the single-ear joint test piece 3, applying a radial compression load within the shaft hole. During this process, the two support bushings 7 support the single-ear joint test piece 3 from both sides, and the two support plates 10 support the transition section of the single-ear joint test piece 3 from both sides. To prevent lateral displacement of the single-ear joint test piece 3, and with the two support bushings 7 and support plate 10 able to move with the loading platform 6, the stress environment of the single-ear joint can be well guaranteed, ensuring the accuracy of the test results. In addition, the two guide supports 4 and guide rods 5, in conjunction with the guide holes on the loading platform 6, can ensure that the loading platform 6 can only move vertically under the action of the testing machine during the test, preventing horizontal deflection and ensuring the accurate application of radial compressive load to the shaft hole of the single-ear joint.

[0061] In some optional embodiments, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, two positioning clamps 2 are bolted to the support section of the single-ear joint test piece 3.

[0062] The base plate 1 has two T-shaped clamp positioning grooves and a T-shaped support positioning groove;

[0063] Two positioning clamps 2 are connected to the base plate 1 by bolts through the connecting edge. The corresponding bolt holes on the connecting edge are racetrack-shaped, with a margin of movement to facilitate the adjustment of the pressure core of the single-ear joint test piece 3. The bolt head of each positioning clamp 2 connected to the base plate 1 is locked in a T-shaped clamp positioning groove, and the position of the positioning clamp 2 can be slidably adjusted according to the actual situation.

[0064] Each guide support 4 is connected to the base plate 1 by two sets of bolts through the connecting edge. The heads of the two sets of bolts are locked in the positioning grooves of the two T-shaped supports. The position of the guide support 4 can be slidably adjusted according to the actual situation. The corresponding bolt holes on the connecting edge of the two guide supports 4 are racetrack-shaped, with a margin of movement to facilitate assembly with the single-ear joint test piece 3.

[0065] In some optional embodiments, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, two sets of guide rods 5 are threadedly connected to two guide supports 4.

[0066] The radial compression test loading structure for the single-ear joint shaft hole at the root of the aircraft vertical tail panel also includes:

[0067] Two sets of linear bearings 12 are installed in two sets of guide holes using bearing retaining rings and are fitted onto two sets of guide rods 5 to reduce the sliding friction between the loading platform 6 and the guide rods 5, thereby avoiding a large additional load on the test and affecting the accuracy of the test results.

[0068] In some optional embodiments, in the radial compression test loading structure of the single-ear joint shaft hole at the root of the aircraft vertical tail panel described above, the two support bushings 7 are stepped at the outer end and are embedded in the two loading holes.

[0069] The outer end of each of the two support bushings 7 has a limiting groove that engages with the two limiting strips 9.

[0070] The two ends of the two limit bars 9 are bolted to the side wall of the loading platform 6.

[0071] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0072] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An aircraft vertical tail wallboard root single ear joint shaft hole radial compression test loading structure, characterized in that, The utility model relates to a kind of loading structures of radial compression test of single ear joint shaft hole of aircraft vertical tail wallboard root, including: Bottom plate (1); Two positioning clamping plates (2) are connected on bottom plate (1), and are clamped on both sides of support section of single ear joint test piece (3); Two guide supports (4) are connected on bottom plate (1); Two groups of guide support rods (5) are connected on two guide supports (4); Loading pressure platform (6) has limiting hole and two groups of guide holes between upper and lower wall surfaces, and loading hole is formed on two side walls, wherein limiting hole is located between two groups of guide holes, and is sleeved on the outer periphery of single ear joint of single ear joint test piece (3);Two groups of guide holes are sleeved on two groups of guide support rods (5); Two support bushings (7) are arranged in two loading holes and are supported on both sides of single ear joint of single ear joint test piece (3); Loading shaft (8) penetrates the shaft hole of single ear joint of single ear joint test piece (3) and two support bushings (7) are arranged; Two limiting strips (9) are arranged in the end side wall of loading shaft (8) and are connected on both side walls of loading pressure platform (6), and two support bushings (7) are compressed; Two support plates (10) are arranged in limiting hole and are located on both sides of transition section of single ear joint test piece (3), and outer side wall has a plurality of support blind holes; Two groups of support bolts (11) are screwed on both side walls of loading pressure platform (6), and screw rod top end is inserted into each support blind hole on two support plates (10), so that two support plates (10) are supported on both sides of transition section of single ear joint test piece (3).

2. The loading structure of radial compression test of single ear joint shaft hole of aircraft vertical tail wallboard root according to claim 1, wherein: Two positioning clamping plates (2) are connected on support section of single ear joint test piece (3) by bolt connection; Bottom plate (1) has two T-shaped clamping plate positioning grooves and T-shaped support positioning grooves; Two positioning clamping plates (2) are connected on bottom plate (1) by connecting edge using bolt connection, and corresponding bolt holes on the connecting edge are runway-shaped, the bolt head of each positioning clamping plate (2) is clamped in a T-shaped clamping plate positioning groove when connecting bottom plate (1); Each guide support (4) is connected on bottom plate (1) by connecting edge using two groups of bolts, and the bolt head of two groups of bolts is clamped in two T-shaped support positioning grooves, and corresponding bolt holes on the connecting edge of two guide supports (4) are runway-shaped.

3. The loading structure of radial compression test of single ear joint shaft hole of aircraft vertical tail wallboard root according to claim 1, wherein: Two groups of guide support rods (5) are screwed on two guide supports (4); The loading structure of radial compression test of single ear joint shaft hole of aircraft vertical tail wallboard root further comprises: Two groups of linear bearings (12) are installed in two groups of guide holes using bearing retainer, and are sleeved on two groups of guide support rods (5).

4. The loading structure of radial compression test of single ear joint shaft hole of aircraft vertical tail wallboard root according to claim 1, wherein: One end of two support bushings (7) on the outer side is stepped and is sunk in two loading holes; One end of two support bushings (7) on the outer side has a limiting clamping groove, and is clamped on two limiting strips (9); Two ends of two limiting strips (9) are connected on the side wall of loading pressure platform (6) by bolt connection.

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