Simultaneous spacecraft attitude and orbit estimation using magnetic field vector measurements
Based on magnetometer measurements only, three-axis attitude, rate, and orbit estimation are successfully achieved. A single Augmented Dynamics Extended Kalman Filter (ADEKF) is configured by combining the spacecraft nonlinear attitude dynamics and quaternion kinematics with orbital mechanics. The...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
Elsevier Masson SAS
2011
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/ http://irep.iium.edu.my/8582/1/b6111107506111847812c6c0b8b87987.pdf |
| Summary: | Based on magnetometer measurements only, three-axis attitude, rate, and orbit estimation are successfully
achieved. A single Augmented Dynamics Extended Kalman Filter (ADEKF) is configured by combining the
spacecraft nonlinear attitude dynamics and quaternion kinematics with orbital mechanics. The filter
design is adopted for three-axis stabilized spacecraft in low Earth orbits where the aerodynamic drag
is the dominant source of disturbances in addition to the spacecraft magnetic residuals. To reduce
the computational burden, another Interlaced Extended Kalman Filter (IEKF) is developed to uncouple
the attitude/rate from the orbit dynamics. Both filters are implemented using the magnetometer
measurements and their corresponding time derivatives. As a part of EgyptSat-1 flight scenario,
detumbling and standby modes are used for performance testing of the ADEKF. The concept of local
observability is applied to the basic filter and the stability is investigated by incorporating extensive
Monte Carlo simulations with uniformly distributed initial conditions. The filter shows the capability of
estimating the attitude better than 5 deg and rate of order 0.03 deg/s in each axis. In orbit estimation,
the filter is capable of estimating the position with accuracy less than 8 km and velocity upto 5 m/s in
each axis.
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