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 �lter, guidance based upon modi�ed Apollo methods, an attitude control system, and several di�erent 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 e�ects of sensor errors and the number of navigation states on total fuel use.
| Identifer | oai:union.ndltd.org:UTAHS/oai:digitalcommons.usu.edu:etd-3007 |
| Date | 01 May 2013 |
| Creators | Anderson, Jessica Thornley |
| Publisher | DigitalCommons@USU |
| Source Sets | Utah State University |
| Detected Language | English |
| Type | text |
| Format | application/pdf |
| Source | All Graduate Theses and Dissertations |
| Rights | Copyright for this work is held by the author. Transmission or reproduction of materials protected by copyright beyond that allowed by fair use requires the written permission of the copyright owners. Works not in the public domain cannot be commercially exploited without permission of the copyright owner. Responsibility for any use rests exclusively with the user. For more information contact Andrew Wesolek (andrew.wesolek@usu.edu). |
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