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The Attitude Determination and Control Subsystem (ADCS) essentially consists of two separate unconnected systems: an Attitude Determination System (ADS), which is not connected to the Attitude Control System (ACS). ADS The sun vector is determined by two angles alpha and beta, or at least by the incidence angle of the sun light on each solar panel. We use for that: - The data given by the four photodiodes (one on each side of the satellite, on the solar panels,
- The currents by each of the sensors of the AWSS.
The algorithm that we have to create must work without AWSS data since the device is part of the payload of the mission. So as inputs of the algorithm we only have: - Currents from the photodiodes
We are constructing a logical algorithm which uses an optimization method. ACS The ACS is designed as a completely passive system, so it will never act on an input. The spacecraft will not have any active attitude control and is free to rotate about all its axes. However, in order to limit the rotation rates of the satellite to about two rotations per minute, magnetic hysteresis material will be employed to limit rotation rates using the Earth's magnetic field. This document gives a detailed description about the ACS: ACS description
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