Method and Apparatus for Contingency Guidance of a CMG-Actuated Spacecraft

Thumbnail Image
Files
NPS 9038958.pdf (551.72 KB)
Authors
Ross, Isaac Michael
Lee, Donghun
Karpenko, Mark
Subjects
Advisors
Date of Issue
2015-05-26
Date
Publisher
United States Patent and Trademark Office (USPTO)
Language
Abstract
Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CM Gs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.
Type
Patent
Description
URI
https://hdl.handle.net/10945/45410
Series/Report No
Department
Organization
Identifiers
US 9,038,958 B1
NPS Report Number
Sponsors
Funding
Format
Citation
Distribution Statement
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
Publications