摘要：AbstractThe study presents and validates a flexible appendage model to be used in an integrated control/structure spacecraft design. The integrated design methodology needs an accurate LFT representation of spacecraft flexible appendages so that parametric variations can be included. This requirement can be met using the Interconnected Flexible Appendage model studied in Perez et al. (2015). The model suitability is validated through the modeling of a real deployable boom, obtaining the same frequency modes and dynamical behavior.
关键词：KeywordsIntegrated DesignStructured HœSynthesisFlexible StructuresAttitude Control System (ACS)Linear Fractional Representation (LFT)
