English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Tools annual

Global: Zendy Free Plan

Global: Zendy Tools monthly

Global: Zendy Plus monthly

An analytical approach is developed for determining the spacecraft attitude response for stick-slip induced disturbances of a large extended structure with tension control mechanism (TCM). In this method, attitude dynamics with flexible appendage is formulated as a general constrained mode model, and coupling with the stick-slip induced oscillations is formulated as the transition of equilibrium states of modal parameters. Numerical calculations are presented for the flexible solar array on the Advanced Earth Observing Satellite (ADEOS), which caused unexpected attitude oscillations due to the stick slip on the orbit.

Attitude Stability Analysis for Stick-Slip Induced Disturbanes of Extended Structure with Tension Control Mechanism