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Flight results from the gravity-gradient-controlled RAE-1 satelliteThe in-orbit dynamics of a large, flexible spacecraft has been modeled with a computer simulation, which was used for designing the control system, developing a deployment and gravity-gradient capture procedure, predicting the steady-state behavior, and designing a series of dynamics experiments for the Radio Astronomy Explorer (RAE) satellite. This flexible body dynamics simulator permits three-dimensional, large-angle rotation of the total spacecraft and includes effects of orbit eccentricity, thermal bending, solar pressure, gravitational accelerations, and the damper system. Flight results are consistent with the simulator predictions and are presented for the deployment and capture phases, the steady-state mission, and the dynamics experiments.
Document ID
19860062715
Document Type
Conference Paper
Authors
Blanchard, D. L. (NASA Goddard Space Flight Center Greenbelt; Ford Aerospace and Communications Corp., College Park, MD, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 86-2140
Distribution Limits
Public
Copyright
Other