Nonlinear Methods for Spacecraft Attitude Maneuvers

摘要

Spacecraft attitude control is described by a nonlinear dynamic mathematical model. When Euler parameters are used to define the orientation of a spacecraft with respect to an inertial frame, the model takes a certain form where the components of one factor are quadratic or higher order functions of the state vehicles. Large-angle maneuvers have traditionally been accomplished as a succession of small-angle rotations from a sequence of defined operating points about which the model is linearized. Alternatively, a sequence off single axis rotations are performed. These processes are computationally burdensome and are unable to produce fast multi-axial rotational maneuvers.