Time-Optimal Magnetic Attitude Maneuvers Academic Article

abstract

• Time-optimal magnetic attitude maneuvers for near-Earth spin-stabilized spacecraft are treated using Pontryagins Principle. A nonlinear bang-bang switching function is derived for the electromagnets polarity. The approach is quite general, allowing user-prescribed orbit dynamics models and geomagnetic field models. For the case of a single electromagnet aligned with the nominal spin axis of a symmetric satellite, and retaining general orbit and geomagnetic models, the determination of time-optimal magnetic maneuvers reduces to a bounded one-dimensional search of an initial costate variable. The formulation is used to construct extremal field maps of typical optimal maneuvers and is further used to determine for example time-optimal maneuvers for the NOVA navigational satellite scheduled for launch in the spring of 1981. 1981 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

authors

• Junkins, John

published proceedings

• Journal of Guidance and Control

author list (cited authors)

• Junkins, J. L., Carrington, C. K., & Williams, C. E.

citation count

• 21

complete list of authors

• Junkins, JL||Carrington, CK||Williams, CE

publication date

• July 1981

publisher

• American Institute of Aeronautics and Astronautics (AIAA)  Publisher

published in

• Journal of guidance and control  Journal

Digital Object Identifier (DOI)

• 10.2514/3.56088

start page

• 363

end page

• 368

volume

• 4

issue

• 4

URL

• http://dx.doi.org/10.2514/3.56088