Source: http://space-scitechjournal.org.ua/en/archive/2015/1/1
Timestamp: 2019-04-24 14:07:55+00:00

Document:
The work is devoted to the adaptation of robust ellipsoidal state estimation methods for dynamic systems to the changes of attitude control of small spacecrafts. Software and hardware implementation of these methods at the problem-oriented processors in FPGAs element basis is established. Its effectiveness is illustrated by the example of the attitude control system of small spacecraft, when a three-axis magnetometer is using as a measuring device.
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