Integrated Attitude interface generates an external attitude file for a satellite by numerically integrating Euler's equations for the current satellite.

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.

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.