Nonlinear Methods for Spacecraft Attitude Maneuvers.
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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. Additional keywords Perturbations Transformations.
- Theoretical Mathematics