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为了提高航天产品的抗振动环境能力,有必要对产品进行减振设计。用有限元分析法对航天某薄壳结构进行动态特性分析,进而进行减振器动态特性设计,并通过试验进行设计验证。根据产品特点及减振要求给定减振器基本结构形式,根据基本理论计算确定减振器初始参数,建立产品和减振器有限元模型,用仿真的方法进行减振器动态特性设计、结构尺寸优化,用振动台试验的方法对设计进行验证。试验结果表明,所设计的减振器实现了三个方向的减振,达到了减振目标要求,所采用的有限元分析方法是有效的。
In order to improve the ability of anti-vibration environment of aerospace products, it is necessary to design the vibration damping products. The finite element analysis is used to analyze the dynamic characteristics of a shell structure in aerospace and then the design of the dynamic characteristics of shock absorber is carried out. The design verification is carried out through experiments. According to the characteristics of the products and vibration reduction requirements, given the basic structure of the shock absorber, the initial parameters of the shock absorber are calculated and calculated according to the basic theory, the finite element model of the product and the shock absorber are established, the dynamic characteristics of the shock absorber are designed by the simulation method, Size optimization, the vibration table test method to verify the design. The experimental results show that the designed shock absorber achieves vibration reduction in three directions and achieves the target of vibration damping. The finite element analysis method is effective.