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

Ye Somov, S. Butyrin, H. Siguerdidjane, Ch Hajiyev, V. Fedosov

Araştırma sonucu: ???type-name???Konferans katkısıbilirkişi

13 Atıf (Scopus)

Özet

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.

Orijinal dilİngilizce
Ana bilgisayar yayını başlığı19th IFAC Symposium on Automatic Control in Aerospace, ACA 2013 - Proceedings
YayınlayanIFAC Secretariat
Sayfalar393-398
Sayfa sayısı6
BaskıPART 1
ISBN (Basılı)9783902823465
DOI'lar
Yayın durumuYayınlandı - 2013
Etkinlik19th IFAC Symposium on Automatic Control in Aerospace, ACA 2013 - Wurzburg, Germany
Süre: 2 Eyl 20136 Eyl 2013

Yayın serisi

AdıIFAC Proceedings Volumes (IFAC-PapersOnline)
SayıPART 1
Hacim19
ISSN (Basılı)1474-6670

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???event.eventtypes.event.conference???19th IFAC Symposium on Automatic Control in Aerospace, ACA 2013
Ülke/BölgeGermany
ŞehirWurzburg
Periyot2/09/136/09/13

Finansman

★ The work was supported by RFBR (Grants 11-08-01037, 13-08-97000) and by Division on EMMCP of the RAS (Program 14)

FinansörlerFinansör numarası
Division on EMMCP
Rochester Academy of Science
Russian Foundation for Basic Research13-08-97000, 11-08-01037

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