| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 713122 | IFAC-PapersOnLine | 2015 | 6 Pages |
Abstract
The 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.
Related Topics
Physical Sciences and Engineering
Engineering
Computational Mechanics
