I was wondering if it is possible to estimate the torque provided by actuators, given satellite attitude measurements (w & q)?
We only have access to measurements from satellite attitude (w and q) and we need to figure out what is the applied torque to the spacecraft (excluding disturbance) to the satellite at each time step.
Assume the satellite is not controlled and is under a pre-defined input voltage to its actuators.
Yes. You can calculate the torque to be provided by the actuators. If you have the attitude parameters of the satellite over a period of time (min 2), you can get the momentum it has in each axis. Then, based on the orientation you need and the specifications of your actuators you can calculate the torque to be produced.
Thank you Peeyush,
I am looking at it in case of fault/failure so the calculations based on pre-defined EOM may not be applicable in this case. Do you have any references or articles that have dealt with this before?
-Afshin
But you said you have access to measurements from satellite attitude ?
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