Parameter optimization and optimal attitude response of a passive environmentally controlled space system

Details Parameter optimization and optimal attitude response of a passive environmentally controlled space system Parameter optimization and optimal attitude response of a passive environmentally controlled space system

Sep 1975

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1975cemec..12..231r&link_type=abstract

Celestial Mechanics, vol. 12, Sept. 1975, p. 231-249. National Research Council of Canada

Computer Science

Performance

Aerodynamic Characteristics, Gravity Gradient Satellites, Optimal Control, Satellite Attitude Control, Spacecraft Stability, Aerodynamic Drag, Environmental Control, Roots Of Equations, Satellite Orbits, Torque

Scientific paper

Optimal response criteria are developed for the passive attitude control of a composite spacecraft. The physical structure is uniquely different from multibody systems in that the components are independently and passively stabilized. The primary body is gravity oriented while the auxiliary body, through geometry selection, is aerodynamically controlled. The Routh-Hurwitz stability criterion is used to obtain the parameter bounds for stability about the preferred dynamic equilibrium position. Further, the least-damped-mode concept with respect to the roots of the characteristic equation is used to predict conditions for optimum performance. Numerically generated optimal response curves for a satellite in circular orbit show very rapid damping rates for large disturbances up to ten degrees. Under these conditions and in the absence of external disturbances, course alignment was reached within several orbits, and fine pointing accuracy was attainable up to altitudes of 650 kilometers.

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