Aircraft engine damping system

Through the multi-stage shock absorption system and dynamic clamping mechanism, the problem of poor shock absorption effect of the aircraft engine is solved, and the multi-stage shock absorption and stable fixation of the engine is achieved, which improves the safety and comfort of the aircraft.

CN119705837AInactive Publication Date: 2025-03-28BEIJING ALL FORTUNE TECH CO LTD
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Patent Information

Application Number
CN202510221726.6
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-02-27
Publication Date
2025-03-28
Estimated Expiration
Not applicable · inactive patent

AI Technical Summary

Technical Problem

In the prior art, the shock absorption effect of aircraft engines is poor, especially in high-frequency vibration and large amplitudes, it is difficult to effectively deal with composite vibrations at different frequencies and directions, affecting the reliability and safety of the aircraft.

Method used

A multi-stage shock absorption system is adopted, including a first load bearing mechanism, a second load bearing mechanism and a third load bearing mechanism. Through the cooperation of the shock absorber pad, a shock absorber mechanism and a clamping mechanism, the first, second and third-stage shock absorption of the engine is realized, and the stable and fixed state of the engine is maintained through the clamping mechanism.

Benefits of technology

Effectively reduce the vibration transmission of the engine in different directions, improve the safety and comfort of aircraft operation, extend the service life of the engine, and enhance the overall shock resistance of the system.

✦ Generated by Eureka AI based on patent content.
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Abstract

The invention relates to an aircraft engine damping system, and belongs to the technical field of aircraft engine damping structures. The device comprises a first bearing mechanism, a second bearing mechanism, a third bearing mechanism, a damping mechanism and a clamping mechanism, the first bearing mechanism comprises a first bearing body and a damping pad, the first bearing body is provided with a mounting groove used for bearing an engine, and the damping pad is arranged on the inner circumference of the mounting groove to conduct primary damping on the engine; the second bearing mechanism bears the first bearing mechanism and conducts two-stage damping on the first bearing mechanism, and the third bearing mechanism is connected with the airplane. The third bearing mechanism supports the second bearing mechanism through the damping mechanism, and three-stage damping is conducted on the second bearing mechanism. The two clamping mechanisms are symmetrically arranged on the two sides of the engine, the two clamping mechanisms are in transmission connection with the damping mechanism, the damping mechanism can drive the two clamping mechanisms to move relatively so as to clamp the engine in the first direction, and vibration borne by the engine in the second direction is reduced. The damping effect of the aircraft engine can be improved.
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