Description
Integrated Attitude interface generates an external attitude file for a satellite by numerically integrating Euler's equations for the current satellite.
Public Methods
 InitFromAtt | Initializes the parameters using a satellite's attitude. |
| SaveToFile | Generates an external attitude file for a satellite by numerically integrating Euler's equations for the current satellite and save results to the specified file. |
Public Properties
 Epoch | Epoch of the attitude file. Uses DateFormat Dimension. |
| Orientation | Get the initial orientation of the satellite in the Earth Inertial (ECI) frame. |
| StartTime | Start time for the attitude file. Uses DateFormat Dimension. |
| StopTime | Stop time for the attitude file. Uses DateFormat Dimension. |
| Torque | Get the external torque data. |
| Wx | Body fixed wx rate: initial angular velocity rate about the satellite's X axis. Uses AngleRate Dimension. |
| Wy | Body fixed wy rate: initial angular velocity rate about the satellite's Y axis. Uses AngleRate Dimension. |
| Wz | Body fixed wz rate: initial angular velocity rate about the satellite's Z axis. Uses AngleRate Dimension. |