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Welcome to the GMAT-6-Degree of Freedom Simulator wiki!

This is the repository for a project to add the capability to model and simulate the attitude control system for a 6-degree of freedom satellite using the NASA GMAT framework. Note that the attitude control system senses angular acceleration, and integrates sensed acceleration to angular rate in 3 body referenced Cartesian axes. The angular rate is used as input to determine the required torques which will achieve and hold some commanded pointing angle. Thus the satellite is said to be under 3-axis attitude control.

The 6-DOF Simulator product is intended as an extension to be integrated with GMAT, the resultant mission simulation will be able to calculate the effect of external disturbance torques resulting from GMAT force calculations, as well as apply control torques to point the GMAT spacecraft model in accordance with a scripted GMAT mission sequence.

GMAT provides a very simple implementation of a Spin Stabilization attitude control system, which may be used as a guide and example.

Please see the links at right to navigate this WIKI.