Vibration reduction lug for airplane brake system

Abstract

The utility model relates to the technical field of vibration reduction supports, in particular to a vibration reduction lug for an aircraft brake system, which comprises a mounting block and a vibration reduction block, the mounting block and the vibration reduction block are made of vibration suppression alloy, the vibration reduction block is vertically connected with the mounting block, the mounting block is provided with a mounting hole connected with an aircraft landing gear, and the mounting hole is communicated with the vibration reduction block. And a vibration reduction groove or a vibration reduction hole is formed in the vibration reduction block. The mounting block and the vibration reduction block are made of vibration suppression alloy, so that vibration on an undercarriage of an aircraft brake system can be absorbed; the vibration damping blocks are provided with vibration damping grooves or vibration damping holes, the weight of the vibration blocks can be reduced, the rigidity of the vibration blocks is reduced, and the deformation amount is increased to absorb vibration.

Description

Technical Field

[0001] The utility model relates to the technical field of damping brackets, and specifically relates to a damping lug for an aircraft braking system. Background Art

[0002] The wheel braking system is one of the most important systems of an aircraft and plays an important role in the take-off and landing processes of the aircraft. The high-frequency vibration caused by the wheel braking system is accompanied by the shimmy of the landing gear and the difficulty in turning. The difficulty in turning is because the braking vibration causes a wheel speed difference between the two wheels, activates the inter-wheel protection, causes the inner wheel to release pressure during turning, and increases the turning radius. In the prior art, when designing the wheel braking system, the braking efficiency is mainly considered, and there is a lack of an active suppression design method for the landing gear resonance problem existing in the braking process. Content of the Utility Model

[0003] The purpose of the utility model is to provide a damping lug for an aircraft braking system to solve the problems existing in the prior art.

[0004] To solve the above technical problems, the utility model provides the following technical solution: a damping lug for an aircraft braking system, the lug includes a mounting block and a damping block, the mounting block and the damping block are made of vibration suppression alloy, the damping block is vertically connected to the mounting block, the mounting block is provided with mounting holes for connecting with the aircraft landing gear, and the damping block is provided with damping grooves or damping holes.

[0005] Further, the width of the mounting block is greater than the width of the damping block, and the two mounting holes on the mounting block are located at the lower parts on both sides of the damping block.

[0006] Further, the total length of the lug is 40 mm.

[0007] Further, the height of the mounting block is 16 mm and the thickness is 3 mm.

[0008] Further, the height of the damping block is 6 mm and the length is 37 mm.

[0009] Further, a first damping groove is formed in the damping block along its length direction.

[0010] Further, a first damping groove is formed in the damping block along its length direction.

[0011] Further, a plurality of uniformly distributed second damping holes are formed in the damping block along its length direction, and the second damping holes are circular.

[0012] Further, a plurality of uniformly distributed third damping holes are formed in the damping block along its length direction, and the third damping holes are horizontally or vertically elliptical.

[0013] Further, a plurality of uniformly distributed fourth damping holes are formed in the damping block along its length direction, and the fourth damping holes are inclined holes.

[0014] Further, a plurality of uniformly distributed fifth damping grooves are provided on the lower surface of the damping block. The cross-section of the fifth damping groove is semicircular; the number of the fifth damping grooves is 4, the radius of the fifth damping groove is 1.6 mm, and the center distance between the fifth damping grooves is 7 mm.

[0015] Compared with the prior art, the beneficial effects achieved by the present utility model are as follows: The mounting block and the damping block of the present utility model are made of vibration damping alloy, which can absorb the vibration on the landing gear of the aircraft braking system; the damping block is provided with damping grooves or damping holes, which can reduce the weight of the vibration block, reduce its stiffness, and increase the deformation amount to absorb vibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings are used to provide a further understanding of the present utility model and constitute a part of the specification. They are used together with the embodiments of the present utility model to explain the present utility model and do not constitute a limitation to the present utility model. In the drawings:

[0017] Figure 1 is a schematic structural diagram of the damping lug in Embodiment 1;

[0018] Figure 2 is a schematic structural diagram of the damping lug in Embodiment 2;

[0019] Figure 3 is a schematic structural diagram of the damping lug in Embodiment 3;

[0020] Figure 4 is a schematic structural diagram of the damping lug in Embodiment 4;

[0021] Figure 5 is a schematic structural diagram of the damping lug in Embodiment 5;

[0022] Figure 6 is an analysis result diagram of the vibration acceleration in Test Example 1.

[0023] In the figures, 1, mounting block; 11, mounting hole; 2, damping block; 21, first damping groove; 22, second damping hole; 23, third damping hole; 24, fourth damping hole; 25, fifth damping groove. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0024] Next, in combination with the embodiments of the present utility model, the technical solutions in the embodiments of the present utility model will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0025] Embodiment 1

[0026] As Figure 1 shown, Embodiment 1 of the present disclosure discloses a vibration damping lug for an aircraft braking system, which includes a mounting block 1 and a vibration damping block 2, and the vibration damping block 2 is perpendicularly mounted to the mounting block 1. Two mounting holes 11 are provided on the mounting block 1 for connecting with the landing gear of the aircraft braking system.

[0027] The above-mentioned mounting block 1 and vibration damping block 2 are made of vibration damping alloy, and the vibration damping alloy can absorb the vibration energy on the landing gear. In order to increase the deformation amount to absorb vibration, a vibration damping groove or a vibration damping hole is further provided on the vibration damping block 2. In Embodiment 1 of the present disclosure, a first vibration damping groove 21 is provided along the length direction of the vibration damping block 2, and the first vibration damping groove 21 is a through groove, which can absorb and convert the vibration force received on the upper surface of the vibration damping block 2, making the vibration damping effect better.

[0028] In Embodiment 1 of the present disclosure, the width of the mounting block 1 is greater than the width of the vibration damping block 2, so that the two mounting holes 11 on the mounting block 1 exactly fall on the two side shoulders of the vibration damping block 2. When the vibration block receives the vibration force, the bolts in the mounting holes 11 can provide a more stable and firm connection for the lug.

[0029] In Embodiment 1 of the present disclosure, the total length of the lug is preferably 40 mm, the height of the mounting block 1 is preferably 16 mm, the thickness is preferably 3 mm, the height of the vibration damping block 2 is preferably 6 mm, and the length is preferably 37 mm.

[0030] The operating principle of Embodiment 1 is as follows: During assembly, the two mounting holes 11 on the mounting block 1 are fixedly connected to the pin shaft on the landing gear, and the vibration damping block 2 is placed on the upper surface of the landing gear. The resonance generated on the landing gear is simultaneously transmitted to the mounting block 1 and the vibration damping block 2, and is absorbed by the mounting block 1 and the vibration damping block 2 made of vibration damping alloy. The reasons are as follows: on the one hand, the shapes of the mounting block 1 and the vibration damping block 2 fit the shape of the lower part of the landing gear, which is convenient for sensing all the vibration forces of the landing gear; on the other hand, the interior of the mounting block 1 and the vibration damping block 2 is a twin crystal. When subjected to external vibration, the movement of the twin crystal will be caused. The twin crystal gradually undergoes elastic deformation and generates new twin crystals. The external vibration is eliminated due to the movement of the twin crystal; on the other hand, the first vibration damping groove 21 can provide a deformation amount for the vibration damping block 2 to absorb vibration, achieving the vibration damping effect.

[0031] Embodiment 2

[0032] As Figure 2 shown, the difference from Example 1 is that: a plurality of uniformly distributed second damping holes 22 are formed in the damping block 2 along its length direction, and the second damping holes are circular.

[0033] Example 3

[0034] As Figure 3 shown, the difference from Example 1 is that: a plurality of uniformly distributed third damping holes 23 are formed in the damping block 2 along its length direction, and the third damping holes are horizontally or vertically oval.

[0035] Example 4

[0036] As Figure 4 shown, the difference from Example 1 is that: a plurality of uniformly distributed fourth damping holes 24 are formed in the damping block 2 along its length direction, and the fourth damping holes 24 are inclined holes.

[0037] Example 5

[0038] As Figure 5 shown, the difference from Example 1 is that: a plurality of uniformly distributed fifth damping grooves 25 are provided on the lower surface of the damping block 2, and the cross section of the fifth damping groove 25 is semicircular. The number of the fifth damping grooves 25 is preferably 4, the radius of the fifth damping groove 25 is preferably 1.6 mm, and the center distance between the fifth damping grooves 25 is preferably 7 mm.

[0039] Test Example 1 Harmonic Response Vibration Acceleration Test

[0040] One group of comparative examples involving structural steel lugs and one group of test examples involving the lugs of Example 1 were used to conduct harmonic response vibration acceleration tests under the same test conditions. The results are shown in Figure 6 . The lugs not only have to bear a pressure of 350 kN, but also absorb high-frequency vibrations. Under the same conditions, when using the lugs made of the vibration damping alloy of Example 1, the peak acceleration of the structural steel lugs is reduced by up to 42.66%. It can be seen that the lugs made of the vibration damping alloy of Example 1 have good vibration damping effects.

[0041] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above-described exemplary embodiments, and without departing from the spirit or basic characteristics of the present invention, the present invention can be implemented in other specific forms. Therefore, in any aspect, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be construed as limiting the claimed rights.

Claims

1. A vibration-damping lug for an aircraft braking system, characterized in that: The ear piece comprises a mounting block (1) and a vibration damping block (2), the mounting block (1) and the vibration damping block (2) being made of a vibration damping alloy, the vibration damping block (2) being vertically connected to the mounting block (1), the mounting block (1) being provided with a mounting hole (11) connected to an aircraft landing gear, and the vibration damping block (2) being provided with a vibration damping groove or a vibration damping hole.

2. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The width of the mounting block (1) is greater than the width of the vibration-damping block (2), and the two mounting holes (11) on the mounting block (1) are located at the lower parts of both sides of the vibration-damping block (2).

3. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The total length of the ear piece is 40 mm.

4. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The mounting block (1) has a height of 16 mm and a thickness of 3 mm.

5. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The vibration damping block (2) has a height of 6 mm and a length of 37 mm.

6. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The vibration-damping block (2) is provided with a first vibration-damping groove (21) along its length direction.

7. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The vibration-damping block (2) is provided with a plurality of evenly distributed second vibration-damping holes (22) along its length direction, and the second vibration-damping holes (22) are circular.

8. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The vibration-damping block (2) is provided with a plurality of evenly distributed third vibration-damping holes (23) along its length direction, and the third vibration-damping holes (23) are elliptical in a horizontal or vertical direction.

9. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The vibration-damping block (2) is provided with a plurality of evenly distributed fourth vibration-damping holes (24) along its length direction, and the fourth vibration-damping holes (24) are inclined holes.

10. The vibration-damping ear piece for an aircraft brake system according to claim 1, characterized in that: The lower surface of the vibration damping block (2) is provided with a plurality of evenly distributed fifth vibration damping grooves (25), the cross section of the fifth vibration damping grooves (25) being semicircular; the number of the fifth vibration damping grooves (25) is 4, the radius of the fifth vibration damping grooves (25) is 1.6 mm, and the distance between the centers of the fifth vibration damping grooves (25) is 7 mm.

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