Model and Control Problem for Space Vehicles with Propellant Slosh

Sahin M., CİHAN M., Kaya M. O.

7th International Conference on Recent Advances in Space Technologies (RAST), İstanbul, Türkiye, 16 - 19 Haziran 2015, ss.461-466 identifier identifier

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Doi Numarası: 10.1109/rast.2015.7208389
  • Basıldığı Şehir: İstanbul
  • Basıldığı Ülke: Türkiye
  • Sayfa Sayıları: ss.461-466
  • Anahtar Kelimeler: propellant slosh, equivalent mechanical model, nonlinear dynamics, Lagrange equations
  • Anadolu Üniversitesi Adresli: Evet

Özet

This paper contains calculations about propellant slosh for an upper stage rocket. The liquid fuel is modeled by using an equivalent mechanical model, from this point of view the stability of this rocket is examined by means of mass-spring model. In theory, a nonlinear mathematical model is derived and nonlinear feedback control laws are used. Specifications of the Attitude Vernier Upper Module (AVUM) upper stage rocket Vega are chosen for simulations. The results of this study are obtained for first four slosh modes.