Date of Award:
5-2013
Document Type:
Thesis
Degree Name:
Master of Science (MS)
Department:
Mechanical and Aerospace Engineering
Committee Chair(s)
David K. Geller
Committee
David K. Geller
Committee
R. Rees Fullmer
Committee
Stephen A. Whitmore
Abstract
A Monte Carlo simulation is developed to study the performance of the closed-loop guidance, navigation, and control (GN&C) system of a lunar lander in powered descent. The simulation includes six-degrees-of-freedom dynamics, an extended Kalman filter, guidance based upon modified Apollo methods, an attitude control system, and several different types of sensors. Sensors included in the sensor suite include accelerometers, gyroscopes, a star camera, an altimeter, a velocimeter, and a radio navigation system. The simulation is used to examine the effects of sensor errors and the number of navigation states on total fuel use.
Checksum
e8c51972a1cef32b35de6beada4a6963
Recommended Citation
Anderson, Jessica Thornley, "The Effect of Navigation State Selection on Fuel Dispersions for Powered Lunar Descent" (2013). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 2004.
https://digitalcommons.usu.edu/etd/2004
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