卫星星箭耦合力学分析模型二次缩聚方法

卫星的星箭耦合力学分析模型是利用模态综合法，从卫星有限元模型上直接缩聚得到的。目前的缩聚方法为一次缩聚方法，要求卫星本体以及天线、太阳电池阵等大部件的有限元模型都必须是未经缩聚的纯物理模型。为在无法获得大部件物理模型的情况下得到整星的星箭耦合力学分析模型，文章提出卫星星箭耦合分析模型的二次缩聚方法，可将由卫星本体物理模型和天线一次缩聚模型组成的混合模型二次缩聚为满足运载格式的星箭耦合分析出口模型，并与火箭研制方联合开展星箭耦合分析及结果校验，验证了该方法的有效性。

Second-time condensation for establishing coupled load dynamic model of satellite with launch vehicle

The dynamic model for analyzing the coupled load of satellite with the launch vehicle is condensed from the satellite’s unreduced finite element model by the component mode synthesis method. With the current condensation method, the condensation is only made once, thus all the finite element models of the satellite sub-structures are required to be unreduced, including the antennas, the solar arrays, and other parts. While sometimes the physical model of the satellite is not available from the manufacturers for the sake of the technical security, which brings about difficulties in implementing the " one-time condensation method”. This paper, in view of this limitation, proposes a method to achieve a second-time condensed dynamic model of a spacecraft when the initial model is composed of unreduced finite element sub-structures and reduced ones. Finally, the satellite/launch vehicle coupled load analysis is carried out jointly with the manufacturer of the launch vehicle, with a desirable result to prove the effectiveness of the method.