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Dynamic coupling on the design of space structures

机译：空间结构设计中的动力耦合

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For the design of space structures, the dynamic coupling between equipment and the satellite (or between a satellite and the launcher) is usually avoided due to negative effects like high stresses produced by structural resonance. The usual procedure to assure the dynamic decoupling is by limiting the minimum value of natural frequency of the secondary structure to a value high enough above the main natural frequencies of the main structure. However, in some spacecraft configurations, it is unavoidable that some parts or equipment present natural frequencies close to the main natural frequencies of the spacecraft because these parts may be massive or may have a special interface design with low stiffness. This dynamic coupling provokes modifications on the modal behavior of the satellite, which can lead to a significant decrease in the first natural frequency of the entire satellite. To analyze this phenomenon, a representative but simple mathematical model is studied to evaluate the influence of the design parameters of space structures. Analytical expressions are obtained that can help to highlight the influence of the parameters. The results are demonstrated with the example of the UPMSat-2 satellite design. (C) 2018 Elsevier Masson SAS. All rights reserved.
机译：对于空间结构的设计，通常会由于诸如结构共振产生的高应力等负面影响而避免设备与卫星之间（或卫星与发射器之间）的动态耦合。保证动态去耦的常用程序是将二级结构的固有频率的最小值限制在足够高的值上，该值要比主结构的主要固有频率足够高。但是，在某些航天器配置中，不可避免的是某些零件或设备的固有频率接近航天器的主要固有频率，因为这些零件可能很重，或者具有低刚度的特殊接口设计。这种动态耦合引起了卫星模态特性的改变，这可能导致整个卫星的第一自然频率的显着降低。为了分析这种现象，研究了一个代表性但简单的数学模型来评估空间结构设计参数的影响。获得的分析表达式可以帮助突出显示参数的影响。结果以UPMSat-2卫星设计为例。 （C）2018 Elsevier Masson SAS。版权所有。

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