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Bi-directional high load-bearing capacity wear-resistant mechanism

A high-load-bearing, wear-resistant lining technology, applied in the aviation field, can solve the problems of body structure wear and motion mechanism that cannot meet the design and use requirements, and achieve self-lubricating, large practical application value, and easy maintenance and replacement.

Active Publication Date: 2014-11-19
沈阳飞机设计研究所扬州协同创新研究院有限公司
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AI Technical Summary

Problems solved by technology

The suspension arm of the rudder surface is always in a relative sliding state under high-load conditions in the axial direction during flight, and the radial direction is always subject to large variable dynamic fatigue loads. The body structure is severely worn during use, while the existing None of the kinematic mechanisms can meet the design requirements

Method used

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  • Bi-directional high load-bearing capacity wear-resistant mechanism
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Embodiment Construction

[0014] The specific embodiments of the present invention will be further described below in conjunction with the drawings.

[0015] See figure 1 . The high-load-bearing double-sided self-lubricating composite gasket (1) used in the present invention is a composite structural product. The surface layer is a self-lubricating fabric (1-1), and the middle is a metal substrate (1-2). In the process, it plays a role of reducing friction and lubricating.

[0016] See figure 2 . The self-lubricating wear-resistant bushing (2) used in the present invention is a composite structural product, the inner surface of the shaft hole is self-lubricating fabric (2-1), the rest is metal substrate (2-2), and the self-lubricating fabric slides In the process, it plays a role of reducing friction and lubricating.

[0017] See image 3 . The deflection arm (6) used in the present invention has a double-ear structure, and the self-lubricating wear-resistant bushing (2) is press-fitted in the shaft hole...

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Abstract

The invention belongs to the technical field of aviation, and relates to a bi-directional high load-bearing capacity wear-resistant mechanism. The bi-directional high load-bearing capacity wear-resistant mechanism is characterized by adopting a two-sided self-lubricating composite gasket and a deflection rocker arm with a self-lubricating wear-resistant bush to realize a bi-directional high load-bearing capacity wear-resistant function of the mechanism. The bi-directional high load-bearing capacity wear-resistant mechanism has beneficial effects that a simple replaceable structure is arranged between two structures which can slide relative to each other under a high load, and a simple permanent wear-resistant structure is arranged between two structures which slide relative to each other under a secondary high load, so that not only can the self lubrication of the mechanism be realized, but also a replacing mechanism is convenient to maintain and replace, and the slide abrasion problem of an airplane body structure under the high load can be thoroughly solved.

Description

Technical field [0001] The invention belongs to the technical field of aviation, and relates to a bidirectional high-load wear-resistant mechanism. Background technique [0002] At present, the usual load-bearing capacity of civil self-lubricating products ranges from (20-50) MPa, and the existing aviation self-lubricating structural parts have a maximum sliding dynamic load capacity of 100 MPa, and they have a single-sided self-lubricating plate structure. The suspension arm on the rudder surface of the aircraft is always in a relative sliding state under high load conditions in the axial direction during flight, and always bears large and variable dynamic fatigue loads in the radial direction. The body structure is seriously worn during use, while the existing None of the motion mechanisms can meet the design and use requirements. Summary of the invention [0003] The technical problem to be solved by the present invention is: how to design a simple and practical movement mecha...

Claims

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Application Information

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IPC IPC(8): F16C11/04
Inventor 王彦红王明利周志强
Owner 沈阳飞机设计研究所扬州协同创新研究院有限公司
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