Accession Number : ADA297796
Title : Small Satellite Attitude Control for Sun-Oriented Operations Utilizing a Momentum Bias With Magnetic Actuators.
Descriptive Note : Master's thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Wolfe, Scott M.
PDF Url : ADA297796
Report Date : MAR 1995
Pagination or Media Count : 118
Abstract : The feasibility of using a three axis control, momentum bias system with magnetic actuators for sun-oriented operations is explored. Relevant equations of motion are developed for a sun-oriented coordinate system and control laws are developed for: initial spacecraft capture after launch vehicle separation; reorientation from Earth oriented to a sun oriented operations mode; sun-oriented attitude control; and momentum wheel control. Simulations demonstrating the stability and time responsiveness of the system are performed. Sensor noise input tests are performed to investigate the systems susceptibility to imperfect conditions. Cross product of inertia effects are also input to test for system instability.
Descriptors : *ATTITUDE CONTROL SYSTEMS, *SATELLITE ATTITUDE, COMPUTERIZED SIMULATION, MAGNETIC FIELDS, INERTIA, EQUATIONS OF MOTION, DETECTORS, THESES, COORDINATES, ACTUATORS, CONTROL THEORY, AIMING, BIAS, INSTABILITY, MOMENTUM, SUN.
Subject Categories : Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE