Nonlinear attitude dynamics of satellitesA study of predicting the rotational motion of a rigid body satellite orbiting the earth under the influence of external torques is presented. The attitude motion in response to external torques is formulated as a perturbation from a nominal torque-free case; the equations of motion are parameterized by the ratio of the orbital and attitude frequencies. The independent variable time is extended into a space of higher dimension by using new fast and slow scales. The theory is applied for predicting the attitude dynamics of an asymmetric rigid-body satellite.
Document ID
19800069528
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Ramnath, R. V. (Charles Stark Draper Laboratory, Inc.; MIT, Cambridge, Mass., United States)
Tao, Y.-C. (Charles Stark Draper Laboratory, Inc. Cambridge, Mass., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: New approaches to nonlinear problems in dynamics