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.
Nonlinear Methods for Spacecraft Attitude Maneuvers
1985
160 pages
Report
No indication
English
Astronautics , Attitude control systems , Flight maneuvers , Satellite attitude , Rotation , Nonlinear analysis , Mathematical models , Perturbations , Transformations(Mathematics) , Functions , Axes , Attitude(Inclination) , Spacecraft , Euler angles , Parameters , Frames , Inertial systems , Quadratic equations , Angles , Multiaxial rotational maneuvers
Optimal Spacecraft Attitude Maneuvers via Adjoint Method
Trans Tech Publications | 2013
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