NONLINEAR TRACKING ATTITUDE CONTROL OF SPACECRAFT ON TIME DEPENDENT TRAJECTORIES

TEKİNALP O., Gomroki M. M., Atas O.

AAS/AIAA Astrodynamics Specialist Conference, Colorado, Amerika Birleşik Devletleri, 11 - 13 Ağustos 2015, cilt.156, ss.1585-1597 identifier identifier

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Cilt numarası: 156
  • Basıldığı Şehir: Colorado
  • Basıldığı Ülke: Amerika Birleşik Devletleri
  • Sayfa Sayıları: ss.1585-1597
  • Orta Doğu Teknik Üniversitesi Adresli: Evet

Özet

The spacecraft attitude control is carried out using the to-go quatemion. A derivative of the to-go quaternion is derived where the desired attitude is a time dependent function. Based on this new attitude formulation, a proper state dependent coefficient matrix expression is obtained. Then the nonlinear tracking attitude control is realized using the state dependent Riccati equation method. The simulation results are given and discussed.