Abstract
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 language | English |
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Title of host publication | Proceedings 19th European Conference on Modelling and Simulation |
Place of Publication | Nottingham |
Publisher | European Council for Modelling and Simulation (ECMS) |
Pages | 691-696 |
ISBN (Electronic) | 1-84233-113-2 |
ISBN (Print) | 1-84233-112-4 |
Publication status | Published - 2005 |
MoE publication type | A4 Article in a conference publication |
Event | 19th European Conference on Modelling and Simulation, ECMS 2005 - Riga, Latvia Duration: 1 Jun 2005 → 4 Jun 2005 |
Conference
Conference | 19th European Conference on Modelling and Simulation, ECMS 2005 |
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Country/Territory | Latvia |
City | Riga |
Period | 1/06/05 → 4/06/05 |
Keywords
- simulation model
- satellite
- FDIR
- Quaternion