In-flight calibration of attitude determination systems for information mini-satellites?

Somov Y., Butyrin S., Siguerdidjane H., Hacızade C., Fedosov V.

19th IFAC Symposium on Automatic Control in Aerospace, ACA 2013, Würzburg, Germany, 2 - 06 September 2013, vol.19, pp.393-398 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume: 19
  • Doi Number: 10.3182/20130902-5-de-2040.00025
  • City: Würzburg
  • Country: Germany
  • Page Numbers: pp.393-398
  • Keywords: Attitude determination, In-ight calibration, Spacecraft
  • Istanbul Technical University Affiliated: Yes


Contemporary information mini-satellites have general mass up to 500 kg and are placed onto the orbit altitudes from 500 up to 1500 km. For such spacecraft some principle problems on precise attitude determination and in-ight calibration are considered and elaborated methods are presented for their solving. Original multiple discrete algorithms for filtering, integration and calibration of a strapped-down inertial navigation system for precise determining the spacecraft attitude, are presented. This system contains electrostatic microaccelerometer, an inertial measurement unit based on the gyro sensors, an astronomical system based on star trackers, multi-head Sun sensor and magnetic sensor, the that are fixed to the spacecraft body. © IFAC.