中国空间科学技术（中英文）2025，Vol.45Issue(2)：70-78,9.DOI:10.16708/j.cnki.1000-758X.2025.0024
柔性航天器动力学方程一般形式的工程简化方法
Engineering simplified approach to the general formulation for the dynamics of flexible spacecraft
摘要
Abstract
An engineering simplified approach to the general formulation for the dynamics of flexible spacecraft is presented on the basis of the complete second-order differential equations.First,the integral items are simplified based on the translational lumped mass method,and the element inertia and rotational motions for shell element or beam element are omitted.Thus,the complex volume integral computation is transformed to the summation operation of variables multiplied by translational masses.Second,the nonlinear matrix coefficients are simplified to constant matrix based on"the small deformation assumption",while omitting the impact of the elastic displacements on the position vectors.Therefore,all the items of the general formulation for the dynamics of flexible spacecraft are well preserved,but their computation is remarkably simplified.The approach could be used for the analysis of flexible spacecraft with large-amplitude and complex motions,and further extended from single-body to multi-body in order to solve the dynamics of on-orbit construction structures or space robots/arms.Finally,the approach is verified by multiple numerical examples and an application case.关键词
柔性航天器/动力学/一般形式/工程简化方法/平动集中质量方法Key words
flexible spacecraft/dynamics/general formulation/engineering simplified approach/translational lumped mass method引用本文复制引用
邹元杰,邓润然,史纪鑫,葛东明..柔性航天器动力学方程一般形式的工程简化方法[J].中国空间科学技术（中英文）,2025,45(2):70-78,9.基金项目
民用航天预研项目(D020104) （D020104）
