Study on the eddy current damping of the spin dynamics of spatial debris from the Ariane launcher
Authors: Nicolas Praly, Nicolas Petit, Christophe Bonnal, Julien Laurent-Varin, 4TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES (EUCASS), July 4 2011, St Petersburg
This paper addresses the topic of damping of the spinning dynamics of a spatial debris orbiting around the Earth. Such debris, which can consists of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as the conducting non- ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important phenomenon which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we expose a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm’s law, we show how one can obtain a Neumann partial differential equations problem that, once solved, e.g. through a considered finite elements method, yields the value of induced currents and braking torques. The case of a spatial debris, being a part of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of orbits of interest are treated.
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BibTeX:
@Proceedings{,
author = {Nicolas Praly, Nicolas Petit, Christophe Bonnal and Julien Laurent-Varin},
editor = {},
title = {Study on the eddy current damping of the spin dynamics of spatial debris from the Ariane launcher},
booktitle = {4TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES},
volume = {},
publisher = {},
address = {St Petersburg},
pages = {1-11},
year = {2011},
abstract = {This paper addresses the topic of damping of the spinning dynamics of a spatial debris orbiting around the Earth. Such debris, which can consists of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as the conducting non- ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important phenomenon which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we expose a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm’s law, we show how one can obtain a Neumann partial differential equations problem that, once solved, e.g. through a considered finite elements method, yields the value of induced currents and braking torques. The case of a spatial debris, being a part of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of orbits of interest are treated.},
keywords = {}}
This paper addresses the topic of damping of the spinning dynamics of a spatial debris orbiting around the Earth. Such debris, which can consists of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as the conducting non- ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important phenomenon which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we expose a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm’s law, we show how one can obtain a Neumann partial differential equations problem that, once solved, e.g. through a considered finite elements method, yields the value of induced currents and braking torques. The case of a spatial debris, being a part of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of orbits of interest are treated.
Download PDF
BibTeX:
@Proceedings{,
author = {Nicolas Praly, Nicolas Petit, Christophe Bonnal and Julien Laurent-Varin},
editor = {},
title = {Study on the eddy current damping of the spin dynamics of spatial debris from the Ariane launcher},
booktitle = {4TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES},
volume = {},
publisher = {},
address = {St Petersburg},
pages = {1-11},
year = {2011},
abstract = {This paper addresses the topic of damping of the spinning dynamics of a spatial debris orbiting around the Earth. Such debris, which can consists of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as the conducting non- ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important phenomenon which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we expose a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm’s law, we show how one can obtain a Neumann partial differential equations problem that, once solved, e.g. through a considered finite elements method, yields the value of induced currents and braking torques. The case of a spatial debris, being a part of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of orbits of interest are treated.},
keywords = {}}