4
$\begingroup$

A typical controller generally gives control torques which should be applied about the axis of a satellite. How exactly is this torque applied using a reaction wheel?

For example if control torques are a,b,c then will equating a,b,c to $I(\omega_{cur}-\omega_{prev})/step$ (where $I$ is moment of inertia, $\omega_{prev}$ and $\omega_{cur}$ are previous and current angular velocities) give me the new angular rate at which the wheel should rotate, or should I equate it with -a,-b,-c?

And also if I want continuous attitude control while dumping the momentum of reaction wheel using a magnetorquer, is it required that the net torque from magnetorquer and reaction wheel be equal to control torque?

Improve this question
$\endgroup$
5
  • $\begingroup$ I don't quite understand your question. Are you asking for the equation of motion of angular momentum? $\endgroup$
    – ChrisR
    Commented May 29, 2017 at 4:00
  • $\begingroup$ Usually any control system gives a torque which needs to be applied on the system and not directly the angular velocity of reaction wheel which needs to be set. So i wanted to know if the equation above will get me the required conversion. $\endgroup$
    – user97213
    Commented May 29, 2017 at 5:01
  • $\begingroup$ Right. Wouldn't that depend on the set of wheels you're using and the mass of your spacecraft? $\endgroup$
    – ChrisR
    Commented May 29, 2017 at 5:05
  • $\begingroup$ Yeah consider for 3 reaction wheels on 3 orthogonal axis and it does depend on Moment of Inertia (indirectly on mass). $\endgroup$
    – user97213
    Commented May 29, 2017 at 10:22
  • 1
    $\begingroup$ You shouldn't try to base the control on the torque as values of torques involved will be so small that your problem will be ill-conditioned numerically. Your control variables should be angles and angular velocities (0th and 1st derivative) and only use angular acceleration, and torque (2nd derivative) where you can't get away with lower derivatives (say, power supply to the RW motor) deriving these ad-hoc from φ,ω for immediate use. $\endgroup$
    – SF.
    Commented May 29, 2017 at 12:48

1 Answer 1

Reset to default
2
$\begingroup$

Some reaction wheels provide "torque mode control", which means the interface of the reaction wheel admits a torque command to be performed by the wheel, then non such concern is needed by the AOCS designer.

Some reaction wheels provide only "speed control", in which the interface admits only the speed that the wheel needs to track. If the AOCS designed a controller that would output torque, then the command to the wheel would need to be converted somehow, one possibility being similar to your suggestion, but with $\omega_{next}$ and $\omega_{cur}$ instead of the previous spin rate. A designer could also build the control under the premise that it will not control wheels in torque mode.

As for the last part of your question, that would likely not be "required", but it is a good practice, since it reduces the effect of momentum damping torque in the atitude of the spacecraft. Care should be taken if the magnetic field is poorly known tough.

Improve this answer
$\endgroup$

Your Answer

By clicking “Post Your Answer”, you agree to our terms of service and acknowledge you have read our privacy policy.