ATTITUDE CONTROL OF THREE-AXES STABILISED SPACECRAFT WITH FLEXIBLE APPENDAGES RIDER NO. 1 - FINAL REPORT Volume I

摘要

This Report describes the results obtained during a Rider to a Study carried out under ESTEC Contract No. 2312/74 AK, being "The Attitude Control of three axes stabilized Spacecraft with Flexible Appendages."nThe work reported continues the investigation into the flexure satellite attitude interaction due to two uniform beam arrays on a three axis stabilized spacecraft. Four tasks have been defined. The first is an extension of the parametric study to/determine the applicability of a control scheme, designed neglecting flexure, to a reaction wheel stabilized flexible satellite. Charts are derived which show stability boundaries and attitude response magnitudes to a torque impulse. These provide a quantitative indication as to the extent of flexure interaction over a wide parameter range.