Device for testing influence of tightening torque of aircraft cantilever conduit on installation stress

Abstract

The utility model relates to the field of aviation cantilever conduit installation testing, and particularly discloses a device for testing the influence of aircraft cantilever conduit tightening torque on installation stress, which comprises an installation base, movable supports are detachably installed at the two ends of the installation base, and a cantilever conduit to be tested is installed between the two movable supports. And the end part of the cantilever guide pipe is detachably mounted with the end part of the movable support through a connecting mechanism. The problems of installation and fixation of aircraft cantilever guide pipes of any configuration and research on influence of tightening torque on installation stress at the two ends can be solved. The device is not limited to aviation cantilever conduits, and the device can be used for experimental tests in installation and fixation experimental studies of all similar cantilever structures. The device can achieve the functions of installation and fixation of cantilever conduits of any different configurations and research of the influence of tightening torque on installation stress, meets the test requirements, and is wide in adaptability.

Description

TECHNICAL FIELD

[0001] The utility model relates to a kind of test devices, more specifically to a kind of test device of the influence of aircraft cantilever duct tightening torque on installation stress, belong to aviation cantilever duct installation test field. BACKGROUND

[0002] The cantilever duct of aircraft is generally small in pipe diameter and thin in pipe wall, and is usually installed in aircraft wheel compartment, vertical tail and other parts. The cantilever duct is sensitive to the size of tightening torque due to its small rigidity, and improper tightening torque can easily generate large installation stress at both ends of the cantilever duct. In addition to the harsh installation site environment, vibration fatigue cracks and other failure problems are likely to occur, which can cause flight safety problems. Therefore, a test device for studying the influence of aircraft cantilever duct tightening torque on installation stress is designed to realize the study of the influence of tightening torque on installation stress at both ends of the cantilever duct, so as to determine the appropriate tightening torque of the aircraft cantilever duct to minimize the installation stress of the cantilever duct, thereby improving the service reliability and having important economic value. SUMMARY

[0003] In view of the problems in the prior art, the utility model provides a test device for studying the influence of aircraft cantilever duct tightening torque on installation stress.

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

[0005] A test device for studying the influence of aircraft cantilever duct tightening torque on installation stress, comprising a mounting base, the mounting base is detachably mounted with a movable support at both ends, the cantilever duct to be tested is installed between the two movable supports, and the end of the cantilever duct is detachably mounted with the end of the movable support through a connecting mechanism.

[0006] Optionally, the mounting base is arranged in a "concave" shape, and an "L"-shaped sliding groove is formed through the two side walls of the mounting base, a scale line is arranged on the outer edge of the sliding groove, and the sliding groove is used for mounting the movable support.

[0007] Optionally, the movable support comprises a stop block, two connecting pipes are connected to the two ends of the stop block, the two connecting pipes are arranged in a through manner inside, and the ends of the two connecting pipes away from the stop block are arranged in a conical shape.

[0008] Optionally, a limiting block is arranged at the connection between the side of the stop block and the connecting pipe, two threaded segments are connected to the outer wall of the connecting pipe, and a nut is connected to the threaded segment close to the limiting block.

[0009] Optionally, the connecting mechanism comprises a nut, a threaded cylinder for threaded connection with the connecting pipe is integrally connected to one end of the nut, and the inner diameter of the threaded cylinder is larger than the inner diameter of the nut.

[0010] Optionally, the inside of the threaded cylinder is sleeved with a flat nozzle, 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 inside of the limiting ring and the guide pipe is through, the diameter of the limiting ring is matched with the inner diameter of the threaded cylinder, 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 inside of the nut to the outside.

[0011] Optionally, a plurality of screw holes are further formed through the bottom of the mounting base.

[0012] The utility model discloses the beneficial effect that:

[0013] The device can solve the installation and fixation of arbitrary configuration aircraft cantilever duct and the research problem of tightening torque influence on both end installation stress. The device is not limited to aviation cantilever duct, and all similar cantilever structure installation and fixation experimental research can use the device to carry out experimental test. The device can realize the installation and fixation of arbitrary different configuration cantilever duct and the function of tightening torque influence on installation stress research, meets the test demand, and is widely adaptable. BRIEF DESCRIPTION OF DRAWINGS

[0014] In order to facilitate the person skilled in the art to understand, the utility model is further explained below in combination with the drawings.

[0015] Figure 1 It is the whole structure schematic diagram of the utility model.

[0016] Figure 2 It is the mounting base structure schematic diagram of the utility model.

[0017] Figure 3 It is the movable support structure schematic diagram of the utility model.

[0018] Figure 4 It is the cantilever duct structure schematic diagram of the utility model.

[0019] Figure 5 It is the flat nozzle structure schematic diagram of the utility model.

[0020] Figure 6 It is the nut structure schematic diagram of the utility model.

[0021] Figure 7 It is the left view of the utility model. Figure 6

[0022] Figure 8 It is the nut structure schematic diagram of the utility model.

[0023] Figure 9 It is the strain gauge structure schematic diagram of the utility model.

[0024] ​In the figure: 1, mounting base; 2, movable support; 3, cantilever conduit; 4, nut; 5, nut; 6, strain gauge; 7, flat nozzle; 8, sliding groove; 9, threaded section; 10, connecting pipe; 11, stop block; 12, guide pipe; 13, limit ring; 14, threaded cylinder. DETAILED DESCRIPTION

[0025] The technical solutions of the utility model will be described clearly and completely in combination with examples below, obviously, the described examples are only part of the examples of the utility model, not all the examples. Based on the examples in the utility model, all other examples obtained by the ordinary skilled in the art without creative labor belong to the protection scope of the utility model.

[0026] Please refer to Figures 1-9 As shown in the figure, a kind of testing device of the influence of aircraft cantilever conduit tightening torque on installation stress, including mounting base 1, the both ends of mounting base 1 are detachably installed with movable support 2, the cantilever conduit 3 to be tested is installed between two movable supports 2, and the end of cantilever conduit 3 is detachably installed with the end of movable support 2 by connecting mechanism.

[0027] Specifically, mounting base 1 is arranged in a "concave" shape, and "L"-shaped sliding grooves 8 are formed through the two side walls of mounting base 1, and scale lines are arranged on the outer edges of the sliding grooves 8, which are used for the installation of movable support 2. The movable support 2 can be adjusted and installed in the sliding grooves 8, which can adapt to different testing requirements. The scale lines are helpful to improve the accuracy of the position adjustment of the movable support 2.

[0028] Specifically, the movable support 2 includes a stop block 11, the two ends of the stop block 11 are connected with connecting pipes 10, the interiors of the two connecting pipes 10 are arranged in a through manner, and the ends of the two connecting pipes 10 away from the stop block 11 are arranged in a conical shape. The conical shape is convenient for adapting to the flared end of the cantilever conduit 3. The stop block 11 can play a limiting role when installed, and the nut 5 on one side is omitted. The two connecting pipes 10 are through, which is convenient for subsequent oil supply and pressure test.

[0029] Specifically, a limiting block is arranged at the connection between one side of the stop block 11 and the connecting pipe 10, the outer wall of the connecting pipe 10 is connected with two threaded sections 9, and the threaded section 9 close to the limiting block is connected with a nut 5.

[0030] Specifically, the connecting mechanism includes a nut 4, one end of the nut 4 is integrally connected with a threaded cylinder 14 for threaded connection with the connecting pipe 10, and the inner diameter of the threaded cylinder 14 is larger than that of the nut 4.

[0031] Specifically, the inside of the threaded cylinder 14 is sleeved with the flat nozzle 7, the flat nozzle 7 comprises a limiting ring 13 and a guide pipe 12, the guide pipe 12 is connected to one end of the limiting ring 13, and the inside of the limiting ring 13 and the guide pipe 12 is through, the diameter of the limiting ring 13 is matched with the inner diameter of the threaded cylinder 14, the diameter of the guide pipe 12 is smaller than the diameter of the limiting ring 13, and one end of the guide pipe 12 can extend from the inside to the outside of the nut 4. The nut 4 facilitates the screwing of the threaded cylinder 14, and when the nut 4 is screwed during installation, the threaded cylinder 14 can be driven to rotate. The arrangement of the flat nozzle 7 can make the flared end of the cantilever guide pipe 3 be uniformly stressed after installation, and the threaded cylinder 14 will not directly contact the flared end of the cantilever guide pipe 3 during rotation, so that the deformation of the flared end of the cantilever guide pipe 3 is not easy to cause, and the subsequent test is more accurate.

[0032] Specifically, a plurality of screw holes are further provided in the bottom of the mounting base 1. During installation, the mounting base 1 is fixedly installed on the preset experiment table surface through the plurality of screw holes in the bottom and the matched fixing bolts.

[0033] In use, the mounting base 1 is fixedly installed on the preset experiment table surface through the plurality of screw holes in the bottom and the matched fixing bolts. Then, the two movable supports 2 are respectively installed on the two side walls of the mounting base 1. During installation of the movable support 2, the limiting clamping block is placed in the inside of the sliding groove 8, the blocking block 11 is placed outside the mounting base 1, then according to the actual installation requirement, the limiting clamping block is slid in the inside of the sliding groove 8 until it is moved to the preset installation position, then the nut 5 is installed on the connecting pipe 10 away from the blocking block 11, the nut 5 is screwed, the nut 5 and the blocking block 11 clamp the side wall of the mounting base 1, so that the movable support 2 is stably installed on the side wall of the mounting base 1.

[0034] Then, the cantilever guide pipe 3 to be tested is sleeved with a nut 4 and a flat nozzle 7 in sequence at both ends, and the flat nozzle 7 is sleeved in the inside of the threaded cylinder 14. The two ends of the cantilever guide pipe 3 are flared according to the conical size of the end of the connecting pipe 10, and the end of the cantilever guide pipe 3 is expanded into a horn shape by using the existing pipe flaring equipment, which can be matched with the conical shape of the end of the connecting pipe 10, as shown in Figure 4

[0035] The horn-shaped end of the cantilever guide pipe 3 is clamped in the inside of the limiting ring 13. The horn-shaped small-diameter end abuts at the connection of the limiting ring 13 and the guide pipe 12, and the large-diameter end is flush with the end of the limiting ring 13 away from the guide pipe 12. After the limiting ring 13 is sleeved in the inside of the threaded cylinder 14, the bottom of the limiting ring 13 abuts with the end of the nut 4, then the threaded cylinder 14 is threadedly connected with the threaded section 9 of the connecting pipe 10 away from the nut 5, the horn-shaped end of the cantilever guide pipe 3 is sleeved outside the conical end of the connecting pipe 10, which is used for simulating the on-board installation state of the aircraft cantilever guide pipe 3.

[0036] ​After the cantilever conduit 3 is initially installed, a strain gauge 6 is bonded at a position close to the nut 5 on the outer wall of each end of the cantilever conduit 3, the strain gauge 6 is connected to an external connecting wire by welding, and the connecting wire is connected to a strain collection device hardware interface.

[0037] Subsequently, the torque of each end of the cantilever conduit 3 is tested and adjusted separately. The testing and adjusting process of each end is as follows:

[0038] One wrench is used to fix the nut 4 at one end of the cantilever conduit 3 and keep it stationary. Another torque wrench is used to slowly rotate the nut 4 at the end to be tested to the minimum tightening torque required by the installation process of the cantilever conduit 3. At this time, the strain value of the test end of the cantilever conduit 3 is recorded. The tightening torque value is slowly increased, and the corresponding strain value is recorded until the maximum tightening torque value required by the process is reached.

[0039] The tightening torque corresponding to the minimum strain value of the test end of the cantilever conduit 3 is analyzed, and this tightening torque is the most suitable tightening torque for this end of the cantilever conduit 3.

[0040] After the torque of one end of the cantilever conduit 3 is tested and adjusted, the testing and adjusting method of the other end is the same as that of the end, and the most suitable tightening torque of both ends of the cantilever conduit 3 is finally obtained. The testing process of the above two ends is to study the effect of the tightening torque of the cantilever conduit 3 on the installation stress and to determine the most suitable tightening torque.

[0041] Finally, the ports of the connecting pipes 10 outside the two side walls of the installation base 1 are externally connected to oil pipes, one end of each connecting pipe 10 is connected to an oil inlet pipe, and the other end is connected to an oil return pipe. An external oil supply device delivers hydraulic oil to the inside of the connecting pipe 10 from the oil inlet pipe, and the hydraulic oil flows through the cantilever conduit 3 and then flows out of the other end of the connecting pipe 10 to be collected from the oil return pipe, thereby simulating the normal oil delivery state of the cantilever conduit 3 and performing pressure supply testing. During the oil delivery process, it is observed whether there is oil leakage at the connection between the cantilever conduit 3 and the connecting pipe 10 to ensure that the most suitable tightening torque does not cause oil leakage during installation. If oil leakage occurs, the tightening torque needs to be retested and adjusted until no oil leakage occurs, and then the most suitable tightening torque is finally determined.

[0042] The preferred embodiments disclosed above are only used to help describe the utility model. The preferred embodiments do not describe all the details and do not limit the utility model to the specific implementation described. Obviously, many modifications and changes can be made according to the content of the specification. The specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the utility model, so that those skilled in the art can well understand and utilize the utility model. The utility model is limited by the claims and the entire scope and equivalents thereof.

Claims

1. A testing device for the effect of tightening torque on installation stress of aircraft cantilever guide tubes, comprising a mounting base (1), characterized in that, Both ends of the mounting base (1) are detachably mounted with movable supports (2). The cantilever conduit (3) to be tested is installed between the two movable supports (2). The end of the cantilever conduit (3) is detachably mounted to the end of the movable support (2) through a connecting mechanism.

2. The testing device for the influence of aircraft cantilever guide tightening torque on installation stress according to claim 1, characterized in that, The mounting base (1) is concave in shape. Both sides of the mounting base (1) are provided with L-shaped grooves (8). The outer edge of the grooves (8) is provided with scale lines. The grooves (8) are used for the installation of the movable support (2).

3. The testing device for the influence of aircraft cantilever guide tightening torque on installation stress according to claim 1, characterized in that, The movable support (2) includes a stop block (11), and both ends of the stop block (11) are connected to a connecting pipe (10). The interiors of the two connecting pipes (10) are connected, and the ends of the two connecting pipes (10) away from the stop block (11) are both conical.

4. The testing device for the influence of aircraft cantilever guide tightening torque on installation stress according to claim 3, characterized in that, A limit block is provided at the connection between one side of the stop (11) and the connecting pipe (10). The outer wall of the connecting pipe (10) is connected to two threaded sections (9), and a nut (5) is connected to the threaded section (9) near the limit block.

5. The testing device for the influence of aircraft cantilever duct tightening torque on installation stress according to claim 4, characterized in that, The connecting mechanism includes a nut (4), one end of which is integrally connected to a threaded cylinder (14) for threaded connection with the connecting pipe (10), the inner diameter of the threaded cylinder (14) being larger than the inner diameter of the nut (4).

6. The testing device for the influence of aircraft cantilever guide tightening torque on installation stress according to claim 5, characterized in that, The threaded cylinder (14) is fitted with a flat nozzle (7), which includes a limiting ring (13) and a guide tube (12). The guide tube (12) is connected to one end of the limiting ring (13), and the two are internally connected. The diameter of the limiting ring (13) is adapted to the inner diameter of the threaded cylinder (14). The diameter of the guide tube (12) is smaller than the diameter of the limiting ring (13), and one end of the guide tube (12) can pass through the inside of the nut (4) and extend to the outside.

7. The testing device for the influence of aircraft cantilever guide tightening torque on installation stress according to claim 1, characterized in that, The bottom of the mounting base (1) is also provided with multiple screw holes.

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