NONLINEAR TRACKING ATTITUDE CONTROL OF SPACECRAFT ON TIME DEPENDENT TRAJECTORIES
AAS/AIAA Astrodynamics Specialist Conference, Colorado, Amerika Birleşik Devletleri, 11 - 13 Ağustos 2015, cilt.156, ss.1585-1597, (Tam Metin Bildiri)
- 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.