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Observing Mode Attitude Controller for the Lunar Reconnaissance OrbiterThe Lunar Reconnaissance Orbiter (LRO) mission is the first of a series of lunar robotic spacecraft scheduled for launch in Fall 2008. LRO will spend at least one year in a low altitude polar orbit around the Moon, collecting lunar environment science and mapping data to enable future human exploration. The LRO employs a 3-axis stabilized attitude control system (ACS) whose primary control mode, the "Observing mode", provides Lunar Nadir, off-Nadir, and Inertial fine pointing for the science data collection and instrument calibration. The controller combines the capability of fine pointing with that of on-demand large angle full-sky attitude reorientation into a single ACS mode, providing simplicity of spacecraft operation as well as maximum flexibility for science data collection. A conventional suite of ACS components is employed in this mode to meet the pointing and control objectives. This paper describes the design and analysis of the primary LRO fine pointing and attitude re-orientation controller function, known as the "Observing mode" of the ACS subsystem. The control design utilizes quaternion feedback, augmented with a unique algorithm that ensures accurate Nadir tracking during large angle yaw maneuvers in the presence of high system momentum and/or maneuver rates. Results of system stability analysis and Monte Carlo simulations demonstrate that the observing mode controller can meet fine pointing and maneuver performance requirements.
Document ID
20080012716
Document Type
Conference Paper
Authors
Calhoun, Philip C. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Garrick, Joseph C. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 24, 2013
Publication Date
September 24, 2007
Publication Information
Publication: Proceedings of the 20th International Symposium on Space Flight Dynamics
Subject Category
Spacecraft Design, Testing and Performance
Distribution Limits
Public
Copyright
Public Use Permitted.

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IDRelationTitle20080012629Analytic PrimaryProceedings of the 20th International Symposium on Space Flight Dynamics