Optimal Control of Spinning Axisymmetric Spacecraft: A Pseudospectral Approach
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Authors
Fleming, Andrew
Ross, I. Michael
Subjects
cascaded computational scheme
ax symmetric rigid body
Pseudospectral method
ax symmetric rigid body
Pseudospectral method
Advisors
Date of Issue
2008-08-18
Date
August 18-21, 2008
Publisher
The American Institute of Aeronautics and Astronautics (AIAA)
Language
Abstract
Shen and Tsiotras considered the case where the ax symmetric rigid body was subject to only two control torques which spanned the plane perpendicular to the axis of symmetry. They used a cascaded computational scheme which involved both direct and indirect methods of optimization. Additionally, their method required initial costate guesses which further complicated numerical results. They concluded that two torques were sufficient to achieve a time-optimal maneuver. In this work the Legendre Pseudospectral method will be used to solve the two-torque problem with only a two-point guess to demonstrate the method's superiority. Additionally, it will be demonstrated that while reorientation of the spin axis is possible with two control torques spanning the plane perpendicular to the spin axis, the addition of a third control torque about the axis of symmetry further reduces the objective function. It will be shown that this new solution has significantly different characteristics form the previously published work.
Type
Conference Paper
Description
The article of record as published may be located at http://dx.doi.org/10.2514/6.2008-7164
AIAA Guidance, Navigation and Control Conference and Exhibit Paper no. AIAA-2008-7164, Honolulu, Hawaii, 2008
AIAA Guidance, Navigation and Control Conference and Exhibit Paper no. AIAA-2008-7164, Honolulu, Hawaii, 2008
Series/Report No
Department
Mechanical & Astronautical Engineering
Organization
Naval Postgraduate School (U.S.)
American Institute of Aeronautics and Astronautics (AIAA)
Identifiers
NPS Report Number
Sponsors
Funder
NA
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
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.