Experimental device for simultaneously loading bending and twisting combined loads of airplane hydraulic conduit

Abstract

The utility model relates to the field of aviation hydraulic conduit vibration fatigue experiments, and particularly discloses an experimental device for simultaneously loading bending and twisting combined loads of an airplane hydraulic conduit, which comprises a mounting base, a mounting cavity is arranged in the mounting base, a flange plate is mounted at one end of the mounting cavity, and a counterweight support is mounted at the other end of the mounting cavity. And the flared conduit to be tested is arranged between the flange plate and the counterweight support. The problems that bending / torsion loads of the aircraft hydraulic guide pipe are independently applied, and different amplitude proportions and different phase difference relations between the bending and torsion loads are loaded at the same time are solved. The experimental device is not limited to aviation hydraulic conduits, and the experimental device can be used for experimental testing in bending-torsion combined vibration fatigue experiments of all similar structures.

Description

TECHNICAL FIELD

[0001] The utility model relates to an experimental device, concretely relates to a kind of for the experimental device of bending torsion combined load of aircraft hydraulic conduit simultaneously loading, belong to aviation hydraulic conduit vibration fatigue experimental field. BACKGROUND

[0002] Aircraft hydraulic conduit is served in high level vibration environment for a long time, and large quality problems such as crack and oil leakage are prone to occur, which seriously affects the flight safety of aircraft. Therefore, an experimental device for simultaneously loading bending and torsion combined loads of aircraft hydraulic conduit is designed to simulate the actual service conditions of bending and torsion vibration fatigue loads of aircraft hydraulic conduit, which is of great significance for studying the vibration fatigue failure mechanism of aircraft hydraulic conduit and optimizing the layout of the conduit to improve the service reliability. SUMMARY

[0003] In view of the problems in the prior art, the utility model provides an experimental device for simultaneously loading bending and torsion combined loads of aircraft hydraulic conduit.

[0004] The purpose of the utility model can be achieved by the following technical solutions:

[0005] An experimental device for simultaneously loading bending and torsion combined loads of aircraft hydraulic conduit, comprising a mounting base, an installation cavity is provided in the mounting base, a flange plate is installed at one end of the installation cavity, and a counterweight support is installed at the other end.

[0006] Optionally, one end of the mounting base is open, the flange plate is installed on the end plate at the other end of the mounting base through a plurality of bolts, and the counterweight support is installed above the open end.

[0007] Optionally, one end of the flange plate towards the counterweight support is connected with a connecting pipe, the outer wall of the connecting pipe is provided with external threads, and the end of the connecting pipe away from the flange plate is conically arranged.

[0008] Optionally, the end of the connecting pipe is connected with a nut through external threads, one end of the nut is integrally connected with a threaded barrel for threaded connection with the connecting pipe, and the inner diameter of the threaded barrel is larger than the inner diameter of the nut.

[0009] Optionally, a flat nozzle is sleeved in the threaded barrel, the flat nozzle comprises a limiting ring and a guide pipe, the guide pipe is connected to one end of the limiting ring, and the interiors of the two are through, the diameter of the limiting ring is matched with the inner diameter of the threaded barrel, the diameter of the guide pipe is smaller than the diameter of the limiting ring, and one end of the guide pipe can extend from the interior of the nut to the exterior.

[0010] Optionally, the counterweight support comprises an upper support and a lower support, opposite sides of the upper support and the lower support are respectively provided with semicircular arc grooves, two through holes are respectively arranged at two ends of the upper support and the lower support, and the two ends of the upper support and the lower support are connected through fastening screws.

[0011] Optionally, a horizontal plate is further arranged at the connection between the two ends of the upper support and the lower support, and the other end of the horizontal plate is connected to the upper side of the end side wall of the mounting base.

[0012] Optionally, a groove is arranged at the connection between the upper side of the end side wall of the mounting base and the horizontal plate, the end of the horizontal plate is clamped in the groove, a gasket is further arranged above the groove, two through holes are respectively arranged at the two ends of the horizontal plate and the gasket, two screw holes corresponding to the through holes are arranged at the bottom of the groove, and screws are inserted into the two through holes of the gasket and connected to the screw holes after penetrating through the gasket and the horizontal plate.

[0013] Optionally, two sliding rail grooves are arranged at the bottom of the mounting base.

[0014] The present application has the following beneficial effects:

[0015] The experimental device is not limited to the aviation hydraulic conduit, and can be used for experimental testing of vibration fatigue experiments of all similar structures in combination with bending and torsion. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to facilitate the understanding of those skilled in the art, the present application will be further described below with reference to the drawings.

[0017] Figure 1 It is a schematic diagram of the overall structure of the present application.

[0018] Figure 2 It is a schematic diagram of the mounting base structure of the present application.

[0019] Figure 3 It is a schematic diagram of the flange structure of the present application.

[0020] Figure 4 It is a schematic diagram of the flared conduit structure of the present application.

[0021] Figure 5 It is a schematic diagram of the flat nozzle structure of the present application.

[0022] Figure 6 It is a schematic diagram of the nut structure of the present application.

[0023] Figure 7 It is a left view of the present application. Figure 6 ​

[0024] Figure 8 It is the counterweight support structure schematic view of the utility model.

[0025] Figure 9 It is the cross plate structure schematic view of the utility model.

[0026] Figure 10 It is the cushion block structure schematic view of the utility model.

[0027] Figure 11 It is the fastening screw structure schematic view of the utility model.

[0028] In the drawing: 1, mounting base;2, flange plate;3, flared conduit;4, flat pipe nozzle;5, nut;6, counterweight support;7, cross plate;8, cushion block;9, fastening screw;10, screw;11, slide rail groove;12, groove;13, connecting pipe;14, limiting ring;15, guide pipe;16, threaded cylinder;601, upper support;602, lower support. DETAILED DESCRIPTION

[0029] The technical scheme of the utility model will be described clearly and completely below in combination with embodiments. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0030] Please refer to Figures 1-11 As shown in the figure, an experimental device for simultaneously loading the bending and torsion combined load of the aircraft hydraulic conduit, comprising a mounting base 1, the inside of the mounting base 1 is provided with a mounting cavity, one end of the mounting cavity is provided with a flange plate 2, the other end is provided with a counterweight support 6, and the flared conduit 3 to be tested is installed between the flange plate 2 and the counterweight support 6.

[0031] Specifically, one end of the mounting base 1 is open, the flange plate 2 is installed on the end plate at the other end of the mounting base 1 through a plurality of bolts, and the counterweight support 6 is installed above the open end. The open end facilitates the installation and removal of the counterweight support 6, and the installation and removal process is not affected by the end plate.

[0032] Specifically, one end of the mounting base 1 is open, the flange plate 2 is installed on the end plate at the other end of the mounting base 1 through a plurality of bolts, and the counterweight support 6 is installed above the open end. The open end facilitates the installation and removal of the counterweight support 6, and the installation and removal process is not affected by the end plate.

[0033] Specifically, the end of the connecting pipe 13 is connected with the screw cap 5 through external thread, one end of the screw cap 5 is integrally connected with the threaded cylinder 16 for thread connection with the connecting pipe 13, the inner diameter of the threaded cylinder 16 is larger than that of the screw cap 5. The inside of the threaded cylinder 16 is sleeved with the flat nozzle 4, the flat nozzle 4 comprises a limiting ring 14 and a guide pipe 15, the guide pipe 15 is connected to one end of the limiting ring 14, and the inside of the two is through, the diameter of the limiting ring 14 is matched with the inner diameter of the threaded cylinder 16, the diameter of the guide pipe 15 is smaller than that of the limiting ring 14, and one end of the guide pipe 15 can extend from the inside of the screw cap 5 to the outside. When the flared guide pipe 3 is installed, the cylindrical end of the flared guide pipe 3 extends from the inside of the flat nozzle 4 to the outside, and the trumpet-shaped end is clamped in the inside of the limiting ring 14. The trumpet-shaped small-diameter end abuts at the connection of the limiting ring 14 and the guide pipe 15, and the large-diameter end is flush with the end of the limiting ring 14 away from the guide pipe 15. After the limiting ring 14 is sleeved in the inside of the threaded cylinder 16, the bottom thereof abuts with the end of the screw cap 5, and then the threaded cylinder 16 is connected with the connecting pipe 13, the trumpet-shaped end of the flared guide pipe 3 is sleeved outside the tapered end of the connecting pipe 13, which is used to simulate the on-board installation state of the aircraft hydraulic guide pipe. The screw cap 5 is convenient to use with wrench, and then drives the threaded cylinder 16 to rotate, the threaded cylinder 16 is convenient for the installation and fixation of the flat nozzle 4, the flat nozzle 4 is convenient for the stability of the flared guide pipe 3 and the connecting pipe 13 during connection, and the end contact is more sufficient.

[0034] Specifically, the counterweight support 6 comprises an upper support 601 and a lower support 602, and the opposite sides of the upper support 601 and the lower support 602 are provided with semicircular arc grooves. Two through holes are arranged at the two ends of the upper support 601 and the lower support 602, and the two ends of the upper support 601 and the lower support 602 are connected by fastening screws 9.

[0035] Specifically, the connecting part of the upper support 601 and the lower support 602 is also provided with a horizontal plate 7, and the other end of the horizontal plate 7 is connected to the upper side of the end side wall of the mounting base 1.

[0036] Specifically, the connecting part of the upper support 601 and the lower support 602 is also provided with a horizontal plate 7, and the other end of the horizontal plate 7 is connected to the upper side of the end side wall of the mounting base 1.

[0037] The split counterweight support 6 is convenient for dismounting and mounting the flared guide pipe 3 to be tested, and the two lateral horizontal plates 7 can support the counterweight support 6 during measurement, so that the counterweight support 6 can work stably after installation. The pad 8 on the horizontal plate 7 makes the horizontal plate 7 more fixed after being clamped and installed in the recess 12, and is not easy to deform in use.

[0038] Specifically, two slide rail grooves 11 are formed through the bottom of the mounting base 1. The slide rail grooves 11 are used for connecting the mounting base 1 to the multi-axial vibration test bench. During installation, multiple fixing bolts are threaded through the slide rail grooves 11 and connected to the bolt holes on the surface of the multi-axial vibration test bench. Washers are fitted on the outside of the fixing bolts and are pressed against the top of the slide rail grooves 11, so that the mounting base 1 is not easy to shake after it is fixed.

[0039] In use, the mounting base 1 is fixed to the surface of the multi-axial vibration test bench via the slide rail groove 11 at the bottom, and the flange 2 is installed at one end of the mounting base 1. Then, two horizontal plates 7 are respectively snapped into the inside of the groove 12, and pressed together at the top with a pad 8. Then, two screws 10 are used to pass through the pad 8 and the horizontal plate 7 and connect to the threaded hole, so that the horizontal plate 7 is installed on the end side wall of the mounting base 1.

[0040] Next, connect one end of the flared conduit 3 to the connecting tube 13. The flared conduit 3 is a type of hydraulic conduit commonly used in aircraft. The specific connection method is as follows:

[0041] First, use a wrench to tighten the nut 5, which will cause the threaded cylinder 16 to rotate until it disengages from the connecting pipe 13. The flared conduit 3 has a trumpet-shaped end and a cylindrical end. Pass the cylindrical end of the flared conduit 3 through the inside of the flat nozzle 4 and extend it to the outside. The trumpet-shaped end is engaged inside the limiting ring 14. The smaller diameter end of the trumpet-shaped conduit abuts against the connection between the limiting ring 14 and the guide pipe 15, while the larger diameter end is flush with the end of the limiting ring 14 furthest from the guide pipe 15. After the limiting ring 14 is fitted inside the threaded cylinder 16, its bottom abuts against the end of the nut 5. Then, using the connection between the threaded cylinder 16 and the connecting pipe 13, the trumpet-shaped end of the flared conduit 3 is fitted over the tapered end of the connecting pipe 13, simulating the onboard installation of the flared conduit 3 as an aircraft hydraulic conduit.

[0042] After the flared end of the conduit 3 is fixed, the other end extends between the two horizontal plates 7. The upper support 601 is placed above the two horizontal plates 7, and the lower support 602 is placed below them. The cylindrical end of the conduit 3 fits snugly into the arc-shaped groove formed by the splicing of the ends of the upper and lower supports 601 and 602. Then, two fastening screws 9 are inserted through holes at both ends of the upper support 601, passing through the upper support 601, the horizontal plates 7, and the lower support 602, respectively. The nuts on the fastening screws 9 are tightened to ensure a stable connection between the upper support 601, the horizontal plates 7, and the lower support 602. This completes the assembly of the conduit 3 to be tested on the experimental apparatus.

[0043] The experimental setup can be used for the following operations during testing:

[0044] The first type: Under the vertical vibration condition of the multi-axial vibration test bench, under the action of the counterweight support 6, only the root of the flared guide tube 3 generates bending stress load.

[0045] The second type: Under the horizontal vibration condition of the multi-axial vibration test bench, in the direction parallel to the plane of the horizontal plate 7, under the restraint of the counterweight support 6 and the horizontal plate 7, only torsional stress load is generated at the root of the flared guide tube 3.

[0046] The third type: Under the condition of simultaneous vertical and horizontal vibration on the multi-axial vibration test bench, the root of the flared guide tube 3 is simultaneously subjected to bending and torsional stress loads.

[0047] Furthermore, the arbitrary setting of simultaneously loading different amplitude ratios and phase differences between the bending and torsional stress loads at the root of the flared guide tube 3 can be achieved by varying the amplitude ratios and phase differences between the vibration loads in two directions on the multi-axial vibration test bench, thereby meeting experimental requirements. The root of the flared guide tube 3 is the trumpet-shaped end of the flared guide tube 3.

[0048] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. An experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits, comprising a mounting base (1), characterized in that, The mounting base (1) has an internal mounting cavity. A flange (2) is installed at one end of the mounting cavity and a counterweight support (6) is installed at the other end. The flared conduit (3) to be tested is installed between the flange (2) and the counterweight support (6).

2. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 1, characterized in that, One end of the mounting base (1) is open, and the flange (2) is mounted on the end plate of the other end of the mounting base (1) by multiple bolts. The counterweight support (6) is mounted above the open end.

3. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 2, characterized in that, The flange (2) is connected to a connecting pipe (13) at one end facing the counterweight support (6). The outer wall of the connecting pipe (13) is provided with external threads, and the end of the connecting pipe (13) away from the flange (2) is set in a conical shape.

4. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 3, characterized in that, The end of the connecting pipe (13) is connected to a nut (5) by an external thread. One end of the nut (5) is integrally connected to a threaded cylinder (16) for threaded connection with the connecting pipe (13). The inner diameter of the threaded cylinder (16) is larger than the inner diameter of the nut (5).

5. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 4, characterized in that, The threaded cylinder (16) is fitted with a flat nozzle (4), which includes a limiting ring (14) and a guide tube (15). The guide tube (15) is connected to one end of the limiting ring (14) and the two are internally connected. The diameter of the limiting ring (14) is adapted to the inner diameter of the threaded cylinder (16). The diameter of the guide tube (15) is smaller than the diameter of the limiting ring (14), and one end of the guide tube (15) can pass through the inside of the nut (5) and extend to the outside.

6. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 1, characterized in that, The counterweight support (6) includes an upper support (601) and a lower support (602). The upper support (601) and the lower support (602) are provided with semi-circular arc grooves on opposite sides. The upper support (601) and the lower support (602) are provided with two through holes at both ends. The upper support (601) and the lower support (602) are connected by fastening screws (9).

7. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 6, characterized in that, A horizontal plate (7) is also installed at the connection points of the upper support (601) and the lower support (602), and the other end of the horizontal plate (7) is connected to the upper side wall of the end of the mounting base (1).

8. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 7, characterized in that, A groove (12) is provided at the connection between the upper end side wall of the mounting base (1) and the horizontal plate (7). After the end of the horizontal plate (7) is engaged in the groove (12), a pad (8) is pressed on its upper part. Two through holes are provided at both ends of the horizontal plate (7) and on the pad (8). Two threaded holes corresponding to the through holes are provided at the bottom of the groove (12). Screws (10) are inserted into the two through holes on the pad (8). The screws (10) pass through the pad (8) and the horizontal plate (7) and are connected to the threaded holes.

9. The experimental apparatus for simultaneously applying combined bending and torsional loads to aircraft hydraulic conduits according to claim 1, characterized in that, The bottom of the mounting base (1) has two slide rail grooves (11) through it.

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