Dual attitude and parameter estimation of passively magnetically stabilized nano satellites

Burton, Roland; Rock, Stephen M.; Springmann, John C.; Cutler, James

doi:10.1016/j.actaastro.2013.08.017

Cited by 14 publications

(13 citation statements)

References 6 publications

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“…Formulating an accurate attitude dynamics model is non-trivial due to the large uncertainties in inertia properties and external torques [3]. Recent work [5], however, has shown that an attitude dynamics model can be reconstructed using a batch parameter estimation process. Reformulating the MEKF to incorporate an attitude dynamics model is presented in this paper.…”

Section: Introductionmentioning

confidence: 99%

Online attitude determination of a passively magnetically stabilized spacecraft

et al. 2017

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An online attitude determination filter is developed for a nano satellite that has no onboard attitude sensors or gyros. Specifically, the attitude of NASA Ames Research Center's O/OREOS, a passively magnetically stabilized 3U CubeSat, is determined using only an estimate of the solar vector obtained from solar panel currents. The filter is based upon the existing multiplicative extended Kalman filter (MEKF) but instead of relying on gyros to drive the motion model, the filter instead incorporates a model of the spacecraft's attitude dynamics in the motion model. An attitude determination accuracy of five degrees is demonstrated, a performance verified using flight data from the University of Michigan's RAX-1. Although the filter was designed for the specific problem of a satellite without gyros or attitude determination it could also be used to provide smoothing of noisy gyro signals or to provide a backup in the event of gyro failures.

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Section: Introductionmentioning

confidence: 99%

Online attitude determination of a passively magnetically stabilized spacecraft

et al. 2017

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“…where C ϕ;sI cos ϕ1 3 1 − cos ϕs I s T I − sin ϕs × I (15) for some fixed ϕ ∈ R. It is straightforward to show that C bI t; ω bI t is indeed a solution of Eqs. (3) and (4).…”

Section: A Indistinguishability For a Torque-free Spacecraftmentioning

confidence: 99%

“…It was demonstrated with numerical examples based on real flight data in [6,15] that it is indeed possible to estimate attitude and angular velocity for such spacecraft using only sun-vector measurements. In [15], a constrained batch optimization optimization problem is proposed to determine the entire history of attitude and angular velocity, as well as identifying the permanent magnet and hysteresis rod parameters. The purpose of this optimization procedure is primarily to estimate these magnetic parameters for calibration purposes.…”

Section: Introductionmentioning

confidence: 97%

“…In addition, as demonstrated numerically in the present paper, neglecting the hysteresis rods (when applicable) comes with a penalty of reduced attitude estimation accuracy. Finally, neither [15] nor [6] present any analytical study of observability of the states and parameters to be estimated. By contrast, a significant portion of this paper is devoted to observability analyses.…”

Section: Introductionmentioning

confidence: 99%

“…The purpose of this optimization procedure is primarily to estimate these magnetic parameters for calibration purposes. The determination of attitude and angular velocity in [15] is a byproduct of the batch optimization needed to determine the magnetic parameters. This constrained batch optimization procedure is suitable for offline implementation.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Ruiter¹,

Tran²,

Kumar³

et al. 2016

Journal of Guidance, Control, and Dynamics

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This paper examines the problem of attitude estimation for passively magnetically stabilized spacecraft using only sun-vector measurements. An analytical investigation of local observability is performed in the case where the spacecraft magnetic dipole is constant. This is relevant because for passively stabilized spacecraft using permanent magnets and magnetic hysteresis rods, the hysteresis rod dipole moments are nearly constant at steady state. It is shown that under reasonable assumptions on the Earth's magnetic field, not only are the attitude and angular velocity locally observable, but if one component of the magnetic dipole moment is known, then the remaining two components of the magnetic dipole moment are locally observable also. Numerical examples of three attitude estimation schemes are presented, demonstrating successful state estimation of passively magnetically stabilized spacecraft.

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Multiple-Model Adaptive Estimation of Time-Varying Residual Magnetic Moment for Small Satellites

Söken

Sakai

2015

Advances in Aerospace Guidance, Navigation and Control

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Dual attitude and parameter estimation of passively magnetically stabilized nano satellites

Cited by 14 publications

References 6 publications

Online attitude determination of a passively magnetically stabilized spacecraft

Online attitude determination of a passively magnetically stabilized spacecraft

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Multiple-Model Adaptive Estimation of Time-Varying Residual Magnetic Moment for Small Satellites

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