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Composite material viscoelastic damping rod

A technology of composite materials and damping rods, which is applied in the field of spacecraft structures, can solve the problems of more rigidity and strength drops of rods, and achieve the effects of overcoming more rigidity and strength drops, improving structural damping, and improving damping characteristics

Active Publication Date: 2012-01-18
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] At present, the existing damping rod design introduces viscoelastic damping material into the main force transmission path. Although the axial damping is improved, the stiffness and strength of the rod are greatly reduced, which limits its application.

Method used

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  • Composite material viscoelastic damping rod
  • Composite material viscoelastic damping rod
  • Composite material viscoelastic damping rod

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Embodiment Construction

[0017] The viscoelastic damping rod of composite material includes mounting flanges at both ends and a middle rod between the mounting flanges. The middle rod consists of three layers, which are rod body 1, viscoelastic damping layer 2 and constraining layer 3 from inside to outside. Material The design range of the length of the viscoelastic damping rod is 20-1000mm, and the design range of the inner wall diameter is 10-50mm. Lamination is the main layer, with a single layer thickness of 0.125mm. A layer of viscoelastic damping material is pasted outside the rod body. The thickness of damping layer 2 varies from 0.1 to 0.6mm. The material is used as the constrained layer 3, the thickness of which varies from 0.5 to 2.5 mm, and the lay-up design is based on 0° lay-up, with a single-layer thickness of 0.125 mm. The number of segments in the length direction of the rod is 3 to 12, and the segments are realized by designing U-shaped grooves in the circumferential direction of the...

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Abstract

The invention relates to a composite material viscoelastic damping rod which comprises mounting flanges at two ends and an intermediate rod between the mounting flanges, wherein the intermediate rod comprises three layers which are a rod body (1), a viscoelastic damping layer (2) and a restraint layer (3) of T series high-intensity carbon fiber composite materials from inside to outside sequentially, and the length of the intermediate rod is 200-1000mm; a damping rubber material with the dissipation factor greater than 1 is selected for the viscoelastic damping layer (2) to be pasted to the outer part of the rod body (1); M series high-modulus carbon fiber composite materials are selected for the restraint layer (3), and the damping layer (2) and the restraint layer (3) are molded by adopting a co-curing technology; and the intermediate section is divided through opening a U-shaped groove out of the restraint layer (3), and the number of the sections of the intermediate rod at the length direction is 3-12.

Description

technical field [0001] The invention belongs to the spacecraft structure technology, in particular to a viscoelastic damping rod of composite material with high axial damping ratio. Background technique [0002] So far, in the field of aerospace, bar (system) structures have been widely used for their high load-bearing efficiency, free configuration, and simple design and analysis, especially for long-span and high-stability composite truss structures. Although the damping of composite trusses is better than that of traditional metal materials, it is still relatively low in applications. For the purpose of reducing vibration and improving structural stability, it is necessary to do further processing to improve its structural damping. [0003] The conventional constraint damping treatment method can only improve the bending modal damping of the bar, but cannot effectively improve the axial damping of the bar. In the truss structure, the rods generally bear tension and compr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16F1/38B32B1/08B32B27/04B32B9/04
Inventor 张少辉杨宝宁张晓莉王耀兵阮剑华钱志英马凯
Owner BEIJING INST OF SPACECRAFT SYST ENG
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