Loading device for preventing fatigue wear of steel wire rope
By designing a loading device including arc-shaped loading plate and guide groove, the problem of wire rope wear and loading error in the aircraft rudder surface fatigue test is solved, and the efficient wear and loading accuracy of wire rope is improved.
Patent Information
- Application Number
- CN202411599654.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-11
- Publication Date
- 2025-02-25
AI Technical Summary
In the existing aircraft rudder fatigue test, the wire rope is prone to fatigue and wear during repeated retraction and release, resulting in breakage, causing test safety risks, and large loading errors, affecting the test results.
A loading device including a fixed bracket, a rotatable lever, a small and large arc-shaped loading plate, a first and second loading wire rope, and a hand-crank hoist is designed. The small arc and large arc loading plates have arc guide grooves, and the first and second loading wire ropes are partially overlapped in the arc guide groove. The arc guide groove design makes the wire rope always vertically down along the outer edge of the arc, reducing wear, and improving loading accuracy through a single-ear base design and joint bearings.
It effectively prevents fatigue and wear of the wire rope, reduces the frequency of wire rope replacement, improves loading accuracy, avoids safety hazards in the test, and ensures the accuracy of the test results.
Smart Images
Figure CN119503152A_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of aircraft structure testing, and in particular relates to a loading device for preventing fatigue wear of steel wire ropes. Background Art
[0002] The moving control surface in the aircraft structure is a key component to control the flight attitude and ensure the aircraft's maneuverability. Therefore, the functional fatigue test of the control surface mechanism is an important test item in aircraft fatigue.
[0003] The aircraft control surfaces will be installed on the corresponding stabilizer, for example, the horizontal tail elevator will be installed on the horizontal tail stabilizer, and the flaps will be installed on the wing surface. In order to ensure the real boundary conditions of the control surface during the flight of the aircraft, a 1g load will be applied to the corresponding stabilizer to simulate the deformation of the stabilizer when the control surface is loaded. Since the load on the stabilizer is a constant load, in order to reduce the test cost and reduce the loading control equipment, a counterweight loading composed of a lead block and a pulley wire rope is used.
[0004] During the fatigue test, changes in the direction and size of the rudder load will cause the stabilizer to deform. In the existing lever-and-wire-rope loading solution, the lever will swing up and down with the wing, causing the heading position to change and resulting in loading errors. The pulley-and-wire-rope solution will cause fatigue wear of the counterweight cable due to repeated retraction and extension in the pulley groove. If the cable is worn and broken without being inspected in time, once the cable breaks, it will cause a series of safety accidents such as test protection. How to load accurately while preventing fatigue wear of the loading wire rope and avoiding safety hazards are technical difficulties faced by the test and problems that need to be solved. Summary of the invention
[0005] In order to solve the above problems, the present application provides a loading device for preventing fatigue wear of a steel wire rope, comprising:
[0006] A fixed bracket, a lever rotatably suspended below the fixed bracket, a small arc loading plate and a large arc loading plate located at both ends of the lever, a first loading wire rope connected to the small arc loading plate and the wing lever, a second loading wire rope connected to the large arc loading plate and the counterweight, and a hand-cranked hoist for adjusting the length of the second loading wire rope;
[0007] The small arc loading plate and the large arc loading plate both have vertical arc guide grooves, and the first loading steel wire rope and the second loading steel wire rope are partially overlapped in the arc guide grooves.
[0008] Preferably, the fixed bracket comprises: a loading beam fixed on the aircraft frame, a supporting column fixed below the loading beam, and a lower end of the supporting column is hinged to the lever through a single ear base.
[0009] Preferably, the arc guide grooves of the small arc loading plate and the large arc loading plate are located in the rotation plane of the lever.
[0010] Preferably, the centers of the arc guide grooves of the small arc loading plate and the large arc loading plate are located on the straight line where the lever is located.
[0011] Preferably, the arc length of the small arc loading plate is smaller than the arc length of the large arc loading plate.
[0012] Preferably, a spherical bearing is arranged in the single-ear base.
[0013] Advantages of this application include:
[0014] 1) Solve the problem of accurate application of aircraft movable wing surface, avoid wire rope wear, and complete the fatigue test of aircraft movable wing surface;
[0015] 2) Use arc-shaped levers combined with steel wire ropes to load variable wing loads, avoid steel wire rope wear, and reduce the frequency of steel wire rope replacement;
[0016] 3) The arc-shaped loading plate guide groove design allows the loading wire rope at the wing end to always move vertically downward along the outer edge of the arc, eliminating the loading error caused by the change of the heading coordinates during the up and down swing of the lever;
[0017] 4) The single-ear base is designed with a spherical bearing. The lever can not only rotate with the deformation of the wing surface, but also rotate laterally to follow the displacement of the wing surface loading point in the span direction caused by the wing surface deformation, thereby improving the loading accuracy. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 This is a schematic diagram of a loading device for preventing fatigue wear of a steel wire rope in a preferred embodiment of the present application;
[0019] Figure 2 It is a schematic diagram of a single-ear base in a preferred embodiment of the present application. DETAILED DESCRIPTION
[0020] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.
[0021] The present application provides a loading device for preventing fatigue wear of a steel wire rope, comprising:
[0022] A fixed bracket, a lever 6 rotatably suspended below the fixed bracket, a small arc loading plate 9 and a large arc loading plate 13 located at both ends of the lever 6, a first loading steel wire rope 7 connected to the small arc loading plate 9 and the wing lever 8, a second loading steel wire rope 10 connected to the large arc loading plate 13 and the counterweight 12, and a hand-cranked hoist 11 for adjusting the length of the second loading steel wire rope 10;
[0023] The small arc loading plate 9 and the large arc loading plate 13 both have vertical arc guide grooves, and the first loading steel wire rope 7 and the second loading steel wire rope 10 are partially overlapped in the arc guide grooves.
[0024] In some optional embodiments, the fixed bracket includes: a loading beam 2 fixed on the aircraft frame 3, a supporting column 4 fixed below the loading beam 2, and the lower end of the supporting column 4 is hinged to the lever 6 through a single ear base 5.
[0025] In some optional embodiments, the arc guide grooves of the small arc loading plate 9 and the large arc loading plate 13 are located in the rotation plane of the lever 6 .
[0026] In some optional embodiments, the centers of the arc guide grooves of the small arc loading plate 9 and the large arc loading plate 13 are located on the straight line where the lever 6 is located.
[0027] In some optional embodiments, the arc length of the small arc loading plate 9 is smaller than the arc length of the large arc loading plate 13 .
[0028] In some optional embodiments, a joint bearing is disposed in the single ear base 5 .
[0029] The invention is mainly achieved through the following steps:
[0030] The first step is to connect and fix the loading beam 2 to the aircraft frame 3 using anchor bolts 1;
[0031] Step 2: Fix the support column 4 to the loading beam 2 by screwing or welding. Then install the single-ear base 5 with a spherical bearing on the support column;
[0032] Step 3: Insert the single-ear base 5 into the lever 6, connect it with bolts, use it as the fulcrum of the rotating lever, and use the joint bearing to rotate it to prevent the bolts from being damaged by friction;
[0033] Step 4: Connect one end of the loading wire rope 7 to the lever 8 on the wing, and the other end to the bolt on the small arc loading plate 9. At the same time, connect one end of another loading wire rope 10 to the hand hoist 11, the hand hoist is connected to the counterweight 12, and one end is connected to the bolt on the large arc loading plate 13.
[0034] Step 5: Protect the steel wire rope 14 Figure 1The connection shown in the figure prevents the lever 6 from swinging out of control after the loading wire ropes 7 and 10 break accidentally, causing safety accidents such as damage to the test piece.
[0035] Step 6: Adjust the length by hand-cranked hoist 11 to suspend the counterweight 12 off the ground to apply wing load.
[0036] Preferably, a circular arc lever is designed to load the variable wing load in combination with a steel wire rope. In this way, in a fatigue test, the steel wire rope is prevented from being worn during tens of thousands of reciprocating deformations of the wing surface, and the replacement frequency of the steel wire rope is reduced.
[0037] Preferably, the arc-shaped guide groove design is used to make the loading wire rope at the wing end always move vertically downward along the outer edge of the arc, thereby preventing the change of the heading coordinates of the lever during the up and down swing, thereby causing loading errors;
[0038] Preferably, the single-ear base is designed with a joint bearing, so that while ensuring that the lever rotates due to the wing deformation, the lever can also rotate laterally to follow the displacement of the wing loading point in the span direction caused by the wing deformation, thereby improving the loading accuracy.
[0039] In the fatigue test of a certain type of aircraft flap, the device was applied, solved the key problem, and achieved significant results. Practice has proved that the device solves the problem of easy wear and tear of the counterweight loading wire in the fatigue test of the movable wing surface; fully considers the objective problem of easy wear of the counterweight loading wire rope, and connects the arc loading plate with the wire rope to avoid sliding wear of the wire rope during the wing movement, but instead fits and separates in the arc loading plate limit guide groove, so as to achieve wear-free load application during the test; the arc guide groove design is used to make the wing end loading wire rope always vertically downward along the outside of the arc, eliminating the change of the heading coordinate when the lever swings up and down with the wing surface, and reducing the loading error.
[0040] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.
Claims
1. A loading device for preventing fatigue wear of a steel wire rope, characterized in that: include: A fixed bracket, a lever (6) rotatably suspended below the fixed bracket, a small arc loading plate (9) and a large arc loading plate (13) located at both ends of the lever (6), a first loading steel wire rope (7) connected to the small arc loading plate (9) and the wing lever (8), a second loading steel wire rope (10) connected to the large arc loading plate (13) and the counterweight (12), and a hand-cranked hoist (11) for adjusting the length of the second loading steel wire rope (10); The small arc loading plate (9) and the large arc loading plate (13) both have vertical arc guide grooves, and the first loading steel wire rope (7) and the second loading steel wire rope (10) are partially overlapped in the arc guide grooves.
2. The loading device for preventing fatigue wear of steel wire rope according to claim 1, characterized in that: The fixed bracket comprises: a loading beam (2) fixed on an aircraft frame (3), a supporting column (4) fixed below the loading beam (2), and the lower end of the supporting column (4) is hinged to a lever (6) through a single ear base (5).
3. The loading device for preventing fatigue wear of steel wire rope according to claim 1, characterized in that: The arc-shaped guide grooves of the small arc-shaped loading plate (9) and the large arc-shaped loading plate (13) are located in the rotation plane of the lever (6).
4. The loading device for preventing fatigue wear of steel wire rope according to claim 1, characterized in that: The centers of the arc guide grooves of the small arc loading plate (9) and the large arc loading plate (13) are located on the straight line where the lever (6) is located.
5. The loading device for preventing fatigue wear of steel wire rope according to claim 1, characterized in that: The arc length of the small arc loading plate (9) is smaller than the arc length of the large arc loading plate (13).
6. The loading device for preventing fatigue wear of steel wire rope according to claim 1, characterized in that: A joint bearing is arranged inside the single-ear base (5).
Citation Information
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