Satellites mostly rely on star trackers and gyros for precision attitude knowledge. Under impulsive thrust manoeuvres, I expect the star trackers to blur and provide no attitude knowledge. What is the strategy for precision attitude estimation in such a case? Open Loop gyro propagation? If you know the attitude during the manoeuvre, then you can use it as a fail-safe mechanism next to the accelerometer, for aborting thrust manoeuvre in the event of non-nominal rates, e.g. in case the thruster gets stuck.
This needs to be assessed on a case-by-case basis, with simulations, and with all hardware and algorithms properly modeled.
But to give an ideia of what is concerned and what is usual:
- Image blur on star trackers is a thing indeed, you may expect a star tracker to stop providing measurements while thrusting occurs.
- Some satellites such as geostationary ones in transfer orbit, which require long thrusting periods simply don't rely on star trackers, but rather on a coupling of gyros, sun-sensor and a spin stabilization strategy.
- For orbit maintenance, either in LEO or GEO, the duration of maneuvers can be very short, in the order of tens of milliseconds, such that one can afford to propagate attitude in open loop while maneuvering.
- Some activities might need to be interrupted during maneuvering, optical imaging for instance, telecom is not since it has less stringent requirements on pointing accuracy.
- Some agile satellites, specially those with control-moment gyros rely on gyro-based open loop attitude propagation while making fast maneuvers, as they expect star trackers to lose track due to angular rate alone.