Abstract
This paper extends the continuous inertia-free control law for spacecraft attitude tracking derived in prior work to the case of three axisymmetric reaction wheels. The wheels are assumed to be mounted in a known and linearly independent, but not necessarily orthogonal, configuration with an arbitrary and unknown orientation relative to the unknown spacecraft principal axes. Simulation results for slew and spin maneuvers are presented with torque and momentum saturation.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1425-1439 |
| Number of pages | 15 |
| Journal | Journal of Guidance, Control, and Dynamics |
| Volume | 36 |
| Issue number | 5 |
| DOIs | |
| State | Published - 2013 |
| Externally published | Yes |
ASJC Scopus subject areas
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics
Fingerprint Dive into the research topics of 'Inertia-free spacecraft attitude control using reaction wheels'. Together they form a unique fingerprint.
Cite this
Weiss, A., Kolmanovsky, I., Bernstein, D. S., & Sanyal, A. (2013). Inertia-free spacecraft attitude control using reaction wheels. Journal of Guidance, Control, and Dynamics, 36(5), 1425-1439. https://doi.org/10.2514/1.58363