
Accession Number : AD0282775
Title : SATELLITE INERTIAWHEEL ATTITUDE CONTROL ON ELLIPTICAL ORBITS
Corporate Author : DOUGLAS AIRCRAFT CO INC SANTA MONICA CALIF
Personal Author(s) : ABZUG,M.J.
Report Date : AUG 1962
Pagination or Media Count : 1
Abstract : An investigation is made of the attitudecontrol characteristics of a satellite on an elliptical orbit itudecon rol system consists of hree iner ia wheels in a closedloop arrangement. A twopart perturbation analysis of the system is made. First, a referencemotion solution is obt i ed. his i a particular solution of the no linear equations of motion in which body axes coincide with reference axes. Then, perturbations from the reference motio are analyzed. The reference otion solution is used to minimize the peak inertiawh l spee s incurred in follo ing onu iformly rotating ref re c o a ellip ical orbit. An unda p d oscillation of very long period that varies with position on orbit is found in the perturbation analysis. The existence of thi oscillation is verified in the solution of the complete equations of motion by numerical analysis. A comparison of the numerical results with perturbation theory predictio s show that the motions following realistic injection errors ar very little affected by no linearities in th equations of motion and coordi r formatio . ut or) D  * %! % +++Satellite in rtiawh el attitude control o lliptical orbits, twopart p rturb tion a alysis, referencemotion solution.
Descriptors : *CONTROL SYSTEMS, *SATELLITE ATTITUDE, EQUATIONS, MATHEMATICAL ANALYSIS, MOTION, NONLINEAR DIFFERENTIAL EQUATIONS, ORBITS, PERTURBATION THEORY, SATELLITES (ARTIFICIAL), STABILITY
Distribution Statement : APPROVED FOR PUBLIC RELEASE