A Dynamic Model of a Passive Magnetic Attitude Control System for the RAX Nanosatellite*

Park, Geeyong; Seagraves, Sheryl; McClamroch, N. Harris

doi:10.2514/6.2010-8154

Cited by 13 publications

(12 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…This approach is quite involved and computation intensive, therefore, not particularly suited for long-term attitude motion numerical propagation. A simplified model has been proposed in [24] and successfully applied for example in [17,18,29,30]. This model has been recently elaborated further, leading to an analytical solution for the hysteresis curves, given an initial condition [14].…”

Section: Numerical Simulation Of the Performance In Orbitmentioning

confidence: 99%

Optimal geometry and materials for nanospacecraft magnetic damping systems

Santoni

Battagliere

Fiorillo

et al. 2015

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

A magnetic damping system for nanospacecraft attitude stabilization is proposed, based on the use of thin strips of amorphous Fe-B-Si soft magnetic ribbons. The size, number, and location of the strips is optimized, and a predictive formulation is provided. The main result of ground tests, comparing the performance of several soft magnetic materials, is that suitably heat-treated amorphous ribbons provide the best loss performance in the whole range of magnetic fields expected in orbit.

show abstract

Section: Numerical Simulation Of the Performance In Orbitmentioning

confidence: 99%

Optimal geometry and materials for nanospacecraft magnetic damping systems

Santoni

Battagliere

Fiorillo

et al. 2015

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

show abstract

“…In this example, the satellite parameters from [24] are used. The spacecraft inertia matrix is given by I diagf2.91058; 0.59261; 2.91058g × 10 −2 kg · m 2 .…”

Section: A Small Hysteresis Rodsmentioning

confidence: 99%

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Ruiter¹,

Tran²,

Kumar³

et al. 2016

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

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.

show abstract

“…The attitude of a spacecraft in low-Earth orbit can be either passively stabilized or actively controlled. Passive methods exploit environmental torques to achieve a stable attitude [1]. However, the range of reachable attitudes is limited by the specific method utilized.…”

Section: Introductionmentioning

confidence: 99%

Retrospective Cost Adaptive Control of Spacecraft Attitude Using Magnetic Actuators

Cruz

Bernstein

2013

AIAA Guidance, Navigation, and Control (GNC) Conference

View full text Add to dashboard Cite

We apply retrospective cost adaptive control (RCAC) to spacecraft attitude control with magnetic actuators. We compare two approaches to address the rank deficiency and time-varying nature of the input matrix. The first approach utilizes an average of the magnetic field based on a-priori knowledge, whereas the second approach uses three multi-input, single-output controllers. RCAC uses no information about the spacecraft inertia, and model information is limited to the input-output relation given by the first Markov parameter, which is computed from an inertia-free linearization of Euler's and Poisson's equations. We examine two problems for each of the controllers. For both problems, the spacecraft has an arbitrary initial angular rate and initial attitude. The objective for the first problem is to bring the spacecraft to rest at a specified attitude, while the second problem seeks to bring the spacecraft to spin about an inertially pointed body axis.

show abstract

A Dynamic Model of a Passive Magnetic Attitude Control System for the RAX Nanosatellite*

Cited by 13 publications

References 5 publications

Optimal geometry and materials for nanospacecraft magnetic damping systems

Optimal geometry and materials for nanospacecraft magnetic damping systems

Sun Vector–Based Attitude Determination of Passively Magnetically Stabilized Spacecraft

Retrospective Cost Adaptive Control of Spacecraft Attitude Using Magnetic Actuators

Contact Info

Product

Resources

About