Computer Science
Scientific paper
Dec 1986
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986aifo.repts....t&link_type=abstract
M.S. Thesis Air Force Inst. of Tech., Wright-Patterson AFB, OH. School of Engineering.
Computer Science
Autonomous Navigation, Celestial Navigation, Kinematics, Satellite Attitude Control, Spin Dynamics, Star Trackers, Synchronous Satellites, Algorithms, Computer Programs, Ephemerides, Least Squares Method, Scanners
Scientific paper
A fine attitude determination model is developed for a spinning geosynchronous satellite, based upon stellar observations from a V-slit star scanner and ground supplied satellite ephemerides. A true attitude model is determined through numerical integration of Euler's moment equations for a torque-free, rigid, axisymmetric body, and kinematic relations which consist of pitch, roll, yaw, orientation angles. Next, the closed form solutions to the Euler equations are coupled with first-order approximate solutions of the kinematic relations to develop a second order kinematics model. Observation relations, relating stellar slit-plane crossing times, (a priori star identification assumed), to attitude states, are then developed. Finally, a nonlinear least-squares estimation algorithm is used to identify the full satellite attitude state. Simulation is tested for single scan and multiple-scan capability using exact and noise ridden data.
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