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 - Sep 1 2013 |
| Externally published | Yes |
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ASJC Scopus subject areas
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Applied Mathematics
- Electrical and Electronic Engineering
Cite this
Inertia-free spacecraft attitude control using reaction wheels. / Weiss, Avishai; Kolmanovsky, Ilya; Bernstein, Dennis S.; Sanyal, Amit.
In: Journal of Guidance, Control, and Dynamics, Vol. 36, No. 5, 01.09.2013, p. 1425-1439.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Inertia-free spacecraft attitude control using reaction wheels
AU - Weiss, Avishai
AU - Kolmanovsky, Ilya
AU - Bernstein, Dennis S.
AU - Sanyal, Amit
PY - 2013/9/1
Y1 - 2013/9/1
N2 - 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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=84885098049&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84885098049&partnerID=8YFLogxK
U2 - 10.2514/1.58363
DO - 10.2514/1.58363
M3 - Article
AN - SCOPUS:84885098049
VL - 36
SP - 1425
EP - 1439
JO - Journal of Guidance, Control, and Dynamics
JF - Journal of Guidance, Control, and Dynamics
SN - 0731-5090
IS - 5
ER -