Date of Award:

2013

Document Type:

Thesis

Degree Name:

Master of Science (MS)

Department:

Mechanical and Aerospace Engineering

Advisor/Chair:

David K. Geller

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 􏰄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.