A method based on a sequence of modified modal transformations for numerical simulation of the dynamics of flexible spacecraft equipped with actuators and sensors was developed. The spacecraft assembly is treated as a sampled data system, characterized by locally constant inputs and by outputs at discrete times. The result consists of a system of exact difference equations, which describes the transition of the spacecraft assembly state from one point in time to the next. In this manner, the usual numerical integration of the differential equations of the spacecraft assembly is replaced by exact, numerical, discrete propagation with difference equations. The associated time interval is determined mainly by measurement times, control update times, and measurement and system noise simulation requirements.
Towards Digital Computer Simulation of the Dynamics of Flexible Spacecraft
1983
90 pages
Report
No indication
English
Unmanned Spacecraft , Flexible spacecraft , Spacecraft models , Digital simulation , Dynamic models , Mathematical models , Actuators , Algorithms , Appendages , Coordinate transformations , Equations of motion , Finite element method , Guidance sensors , Infrared astronomy satellite , Parameterization , Quaternions , Satellite attitude control , State vectors , Foreign technology
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