Design of a Guidance System for an Airlaunch Rocket Using Iterative Guidance Mode

Yanık T., Söken H. E.

10th International Conference on Recent Advances in Air and Space Technologies, RAST 2023, İstanbul, Türkiye, 7 - 09 Haziran 2023 identifier identifier

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Doi Numarası: 10.1109/rast57548.2023.10197935
  • Basıldığı Şehir: İstanbul
  • Basıldığı Ülke: Türkiye
  • Anahtar Kelimeler: air-launch, ascent guidance, IGM, launch vehicle
  • Orta Doğu Teknik Üniversitesi Adresli: Evet

Özet

The use of satellites in small sizes has increased in the last decades thanks to improvements in electronics and materials technology. However, the problem arises from their smaller size is the way of launching them into the operating orbit. Thus, dedicated vehicles launched in the air are now of great interest. In this paper, Iterative Guidance Mode (IGM) is applied to a hypothetical air launch rocket which can be used to insert a micro satellite into a Low Earth Orbit (LEO) orbit. The results are compared with the optimal trajectories obtained. Unlike traditional launchers, these types of vehicles can be launched from different initial conditions and the target might be different for each use. In this paper, the guidance algorithm is applied to an airlaunch rocket and its performance tested considering the specifications.