OPTIMAL ATTITUDE MANEUVERS FOR THE KEPLER K2 MISSION

Loading...
Thumbnail Image
Authors
Argenziano, Matthew R.
Subjects
Kepler
K2
Optimal Control
Momentum Dumping
Momentum Management
Pontryagin’s Principle
Advisors
Karpenko, Mark
Ross, Isaac M.
Date of Issue
2014-12
Date
December 2014
Publisher
Monterey, California. Naval Postgraduate School
Language
Abstract
The Kepler satellite was designed to detect stars with planets capable of supporting life. After completing its primary mission, two of the satellite’s four reaction wheels failed, severely degrading the spacecraft attitude control system. In order to continue providing useful data to the scientific community, NASA has arranged a new mission for the Kepler satellite known as the K2 mission. The K2 mission currently uses a hybrid control approach for rotating the satellite that relies on thrusters for augmenting the authority of the remaining wheels. This thesis explores the application of optimal control for minimizing fuel consumption in support of the K2 mission. Such an approach is useful not only for momentum management during pointing but also for large angle slews needed to support non-science operation. Reducing fuel consumption will further extend the life of the K2 mission. Optimal control was shown in this thesis to reduce fuel consumption by as much as 28 percent during momentum management and 30 percent for large angle maneuvers. The results of this thesis are also applicable to other missions where it is desired to operate an underactuated spacecraft in the most fuel-efficient manner possible.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Organization
Identifiers
NPS Report Number
Sponsors
Funder
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.
Collections