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在空间飞行器结构设计中,为改善仪器设备的振动环境,基于结构模态特性和动力学响应的关系,以某型号空间飞行器为例开展阻尼减振设计.通过仿真分析及地面试验,对减振设计的有效性进行验证.结果表明:在结构模态中的最大应变部位周围附加阻尼层可有效降低结构振动.结构测点在共振峰附近的放大倍数显著降低,最大降低幅度超过90%;结构测点的随机振动响应量级降至设备耐受能力范围之内,阻尼减振设计达到预期目的.
In the design of spacecraft structure, in order to improve the vibration environment of instrument and equipment, based on the relationship between structural modal characteristics and dynamic response, taking a model spacecraft as an example, damping damping design is carried out. Through the simulation analysis and ground test, The validity of the design is verified.The results show that the addition of damping layer around the maximum strain in the modal structure can effectively reduce the structural vibration.The magnification of the structure measuring point near the resonance peak is significantly reduced with the maximum reduction more than 90% The random vibration response of measuring point falls to the range of equipment tolerance, damping damping design to achieve the desired purpose.