Optimal Sensor Placement for On-orbit Assembly Structures
During the on-orbit assembly of large space structures,the configuration and dynamic characteristics continuously change,making a sensor layout optimized for one structure configu-ration unsuitable for others.To address this issue,a novel sensor placement algorithm,termed the Assembled Effective Independence(AEFI)method,is proposed.This method derives the as-sembly effective independence vector by weighted summation of the effective independent vectors for each structure configuration.The weighting coefficient is determined based on the number of target mode shapes.The optimal sensor layout is then determined using a backward sequential sensor placement algorithm.The proposed method is validated through a case study involving an on-orbit assembly space truss structure,considering three classical assembly stages:the"I"type,"I"type and"H"type truss structure.The modal assurance criterion and the condition number are employed to assess the sensor placement.The results demonstrate that the proposed method effectively enhances modal identification accuracy of structure configurations across all as-sembly stages.
optimal sensor placementon-orbit assemblyAssembly Effective Independence Methodstructural health monitoring
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