Sunrise/sunset thermal shock disturbance analysis and simulation for the TOPEX satelliteIt is shown here that during normal on-orbit operations the TOPEX low-earth orbiting satellite is subjected to an impulsive disturbance torque caused by rapid heating of its solar array when entering and exiting the earth's shadow. Error budgets and simulation results are used to demonstrate that this sunrise/sunset torque disturbance is the dominant Normal Mission Mode (NMM) attitude error source. The detailed thermomechanical modeling, analysis, and simulation of this torque is described, and the predicted on-orbit performance of the NMM attitude control system in the face of the sunrise/sunset disturbance is presented. The disturbance results in temporary attitude perturbations that exceed NMM pointing requirements. However, they are below the maximum allowable pointing error which would cause the radar altimeter to break lock.
Document ID
19900032805
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dennehy, C. J. (Fairchild Space Co. Germantown, MD, United States)
Welch, R. V. (Fairchild Space Co. Germantown, MD, United States)
Zimbelman, D. F. (Fairchild Space Co. Germantown, MD, United States)