Mechanism and test device for eliminating rotation bending eccentric torque of aircraft duct

Abstract

The utility model discloses a mechanism for eliminating rotation bending eccentric torque of an airplane conduit and a test device. Comprising a fixed end seat (1), the fixed end seat (1) is connected with an installation disc universal joint (3) through a cross joint (2), the installation disc universal joint (3) is in sliding connection with an eccentric disc universal joint (4) in the axial direction, and the eccentric disc universal joint (4) is connected with an eccentric disc fixing seat (5) through the cross joint (2). The eccentric stress adjustment of the guide pipe is not influenced, the generation of eccentric torque can be controlled, and the strength and the stability of the whole eccentric structure are ensured.

Description

Technical Field

[0001] This utility model relates to the field of fuel duct bending fatigue testing technology, and in particular to a mechanism and testing device for eliminating the eccentric moment of rotational bending of aircraft ducts. Background Technology

[0002] Rotational bending fatigue testing apparatus, see Figure 1 This is a tubing rotational bending fatigue test bench that simultaneously assesses the bending fatigue characteristics of a single tubing or multiple tubing of the same specifications. When multiple tubings undergo planar eccentric oscillation, the eccentric coil of the fixed tubing rotates around its own axis, generating an eccentric moment relative to the central axis. This eccentric moment will exert an additional load on the test tubing, causing unnecessary stress deformation and thus affecting the test results. Utility Model Content

[0003] The purpose of this invention is to provide a mechanism and testing device for eliminating the eccentric moment caused by the rotational bending of aircraft ducts. This invention can both adjust the eccentric stress of the duct and control the generation of the eccentric moment, thus ensuring the strength and stability of the entire eccentric structure.

[0004] Technical solution. A mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts in a rotational bending fatigue testing device includes a fixed end seat, which is connected to a mounting plate universal joint via a cross joint. The mounting plate universal joint and the eccentric plate universal joint are slidably connected axially, and the eccentric plate universal joint is connected to an eccentric plate fixed seat via a cross joint.

[0005] In the aforementioned mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts, the axial limit between the mounting plate universal joint and the eccentric plate universal joint is achieved by a set screw.

[0006] In the aforementioned mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts, the sliding connection structure between the mounting plate universal joint and the eccentric plate universal joint is a slide rod sleeve structure.

[0007] In the aforementioned mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts, the mounting plate universal joint and the eccentric plate universal joint are made of stainless steel.

[0008] A rotational bending fatigue testing device equipped with a mechanism for eliminating the eccentric moment of rotational bending of an aircraft duct as described above includes a mounting plate and an eccentric plate arranged opposite each other. The middle part of the inner side of the mounting plate is connected to a fixed end seat, and the middle part of the inner side of the eccentric plate is connected to an eccentric plate fixed seat.

[0009] In the aforementioned rotating bending fatigue testing device, one or more guide tubes to be tested are installed between the mounting plate and the eccentric plate.

[0010] Beneficial Effects: This utility model adopts a structure of universal joint + ten-joint + sliding sleeve to connect the mounting plate and the eccentric plate. The middle section uses an adjustable length sliding sleeve structure, and the two ends of the sliding sleeve structure adopt a ten-joint structure. The universal joints at both ends are connected to the sliding sleeve through the ten-joint, forming a set of eccentric torque anti-rotation structure. When the eccentric plate revolves around the central axis when it is not eccentric after eccentricity, its own rotation is restricted, eliminating the eccentric torque and improving the test accuracy. Specifically, the following beneficial effects are achieved:

[0011] 1. Low processing cost;

[0012] 2. The process requirements are simple;

[0013] 3. Compact size and high space utilization. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a traditional rotary bending fatigue testing device;

[0015] Figure 2 This is a schematic diagram of the mechanism of this utility model;

[0016] Figure 3 This is a schematic diagram of the rotary bending fatigue testing device of this utility model;

[0017] Figure 4 This is a schematic diagram of the test state of this utility model. Detailed Implementation

[0018] Example 1. A mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts in a rotational bending fatigue testing device, see [link to example]. Figures 2-4 It includes a fixed end seat 1, which is connected to the mounting plate universal joint 3 via a cross 2. The mounting plate universal joint 3 is axially slidably connected to the eccentric plate universal joint 4, and the eccentric plate universal joint 4 is connected to the eccentric plate fixed seat 5 via a cross 2.

[0019] The aforementioned mounting plate universal joint 3 and eccentric plate universal joint 4 are axially limited by set screws.

[0020] The sliding connection structure between the aforementioned mounting plate universal joint 3 and the eccentric plate universal joint 4 is a sliding rod sleeve structure.

[0021] The aforementioned mounting plate universal joint 3 and eccentric plate universal joint 4 are made of stainless steel.

[0022] A rotational bending fatigue testing device equipped with a mechanism for eliminating the eccentric moment of rotational bending of an aircraft duct as described above includes a mounting plate 6 and an eccentric plate 7 arranged opposite to each other. The middle of the inner side of the mounting plate 6 is connected to a fixed end seat 1, and the middle of the inner side of the eccentric plate 7 is connected to an eccentric plate fixed seat 5.

[0023] One or more test conduits 8 are installed between the aforementioned mounting plate 6 and eccentric plate 7.

[0024] During the test, the guide tube 8 to be tested is installed between the mounting plate 6 and the eccentric plate 7. The eccentric plate 7 is moved a preset distance (generally 3 mm) upwards / downwards / leftwards / rightwards from the central axis 9 of the test device. The eccentric plate 7 is then driven to revolve around the central axis 9 of the test device at a speed generally of 1500–3000 rad / min to conduct a fatigue test on the guide tube 8. During the test, the eccentric plate 7 cannot rotate around its own center under the constraint of the mechanism, thus eliminating the eccentric torque.

[0025] Taking a certain type of machine rotational bending fatigue test bench as an example, the anti-deflection adjustment mechanism has been tested and proven to be simple, small and flexible, and can effectively limit the rotation of the eccentric disk itself, thus improving the test accuracy.

Claims

1. A mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts, characterized in that, It includes a fixed end seat (1), which is connected to the mounting plate universal joint (3) via a cross (2). The mounting plate universal joint (3) and the eccentric plate universal joint (4) are axially slidably connected. The eccentric plate universal joint (4) is connected to the eccentric plate fixed seat (5) via a cross (2).

2. The mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts according to claim 1, characterized in that, Axial positioning is achieved between the mounting plate universal joint (3) and the eccentric plate universal joint (4) via set screws.

3. The mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts according to claim 1, characterized in that, The sliding connection structure between the mounting plate universal joint (3) and the eccentric plate universal joint (4) is a sliding rod sleeve structure.

4. The mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts according to claim 1, characterized in that, The mounting plate universal joint (3) and the eccentric plate universal joint (4) are made of stainless steel.

5. A test apparatus equipped with a mechanism for eliminating the eccentric moment of rotational bending of aircraft ducts as described in any one of claims 1-4, characterized in that, It includes a mounting plate (6) and an eccentric plate (7) that are set opposite to each other. The middle part of the inner side of the mounting plate (6) is connected to the fixed end seat (1), and the middle part of the inner side of the eccentric plate (7) is connected to the eccentric plate fixed seat (5).

6. The experimental apparatus according to claim 5, characterized in that, One or more test tubes (8) are installed between the mounting plate (6) and the eccentric plate (7).

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