Attitude control of tethered spacecraftProcedures for achieving attitude control of single-body and multibody, tethered spacecraft are examined. The design considerations for attitude control and the generation of control torques are described. Two dimensional tether attach point motion is utilized to produce torque about two axes and the third axis is controlled with either a control moment gyro or a reaction wheel. The ability to perform attitude control of a tethered spacecraft is evaluated in the Kinetic Isolation Tether Experiment (KITE). It is observed that the KITE/SPARTAN design bandwidth is adequate to fully utilize the capability of attitude sensors with accuracies in the 1-arcsec range.
Document ID
19870026788
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lemke, L. G. (NASA Ames Research Center Moffett Field, CA, United States)
Powell, J. D. (NASA Ames Research Center Moffett Field, CA, United States)