Detumbling and nutation canceling maneuvers with complete analytic reduction for axially symmetric spacecraft
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Authors
Romano, Marcello
Subjects
Rigid-body dynamics and kinematics
Artificial satellites
Rotation
Integrable cases of motion
Artificial satellites
Rotation
Integrable cases of motion
Advisors
Date of Issue
2010
Date
Publisher
Language
Abstract
A new method is introduced to control and analyze the rotational motion of anaxially
symmetric rigid-body spacecraft. In particular, this motion is seen as the combination of
the rotation of a virtual sphere with respect to the inertial frame, and the rotation of the
body, about its symmetry axis, with respect to this sphere. Two new exact solutions are
introduced for the motion of axially symmetric rigid bodies subjected to a constant
external torque in the following cases: (1) torque parallel to the angular momentum and
(2) torque parallel to the vectorial component of the angular momentum on the plane
perpendicular to the symmetry axis. By building upon these results, two rotational
maneuvers are proposed for axially symmetric spacecraft: a detumbling maneuver and
a nutation canceling maneuver. The two maneuvers are the minimum time maneuvers
for spherically constrained maximum torque. These maneuvers are simple and elegant,
as they reduce the control of the three degrees-of-freedom nonlinear rotational motion
to a single degree-of-freedom linear problem. Furthermore, the complete (both for the
dynamics and for the kinematics) and exact analytic solutions are found for the two
maneuvers. An extended survey is reported in the introduction of the paper of the few
cases where the rotation of a rigid body is fully reduced to an exact analytic solution in
closed form.
Type
Article
Description
The article of record as published may be located at http://dx.doi.org/10.1016/j.actaastro.2009.09.015
Series/Report No
Department
Mechanical and Astronautical Engineering
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NPS Report Number
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Citation
Acta Astronautica, Vol. 6, 2010, pp. 989-998
Distribution Statement
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.