Simulation of spacecraft attitude and orbit dynamics

Pasi Riihimäki, Jean-Peter Ylén

Research output: Chapter in Book/Report/Conference proceedingConference article in proceedingsScientificpeer-review

4 Citations (Scopus)


In this paper, the simulation model of satellite attitude and orbit dynamics is discussed. The satellite attitude model has been represented in term of a quaternion and a ordinary differential equation is used to describe the satellite orbital motion. The different actuators and sensors have been modeled with suitable faults and failures. The simulation model enables us to consider the satellite motion under different environmental perturbations (for example aerodynamic drag, external celestial body etc.) and failure in actuators and sensors. The simulation model is utilized in the development of attitude and orbit control algorithms or fault detection, isolation and recovery (FDIR) technologies. Simulation results are also given.
Original languageEnglish
Title of host publicationProceedings 19th European Conference on Modelling and Simulation
Place of PublicationNottingham
PublisherEuropean Council for Modelling and Simulation (ECMS)
ISBN (Electronic)1-84233-113-2
ISBN (Print)1-84233-112-4
Publication statusPublished - 2005
MoE publication typeA4 Article in a conference publication
Event19th European Conference on Modelling and Simulation, ECMS 2005 - Riga, Latvia
Duration: 1 Jun 20054 Jun 2005


Conference19th European Conference on Modelling and Simulation, ECMS 2005


  • simulation model
  • satellite
  • FDIR
  • Quaternion


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