Dissertation/Thesis Abstract

Navigation algorithm for spacecraft lunar landing
by Paturi, Sasikanth Venkata Sai, M.S., Mississippi State University, 2010, 124; 1479262
Abstract (Summary)

A detailed analysis and design of a navigation algorithm for a spacecraft to achieve precision lunar descent and landing is presented. The Inertial Navigation System (INS) was employed as the primary navigation system. To increase the accuracy and precision of the navigation system, the INS was integrated with aiding sensors - a star camera, an altimeter and a terrain camera. An unscented Kalman filter was developed to integrate the aiding sensor measurements with the INS measurements, and to estimate the current position, velocity and attitude of the spacecraft. The errors associated with the accelerometer and gyro measurements are also estimated as part of the navigation filter. An STK scenario was utilized to simulate the truth data for the navigation system. The navigation filter developed was tested and simulated, and from the results obtained, the position, velocity and attitude of the spacecraft were observed to be well estimated.

Indexing (document details)
Advisor: Cheng, Yang
Commitee: Cinnella, Pasqualle, Xin, Ming
School: Mississippi State University
Department: Aerospace Engineering
School Location: United States -- Mississippi
Source: MAI 49/01M, Masters Abstracts International
Source Type: DISSERTATION
Subjects: Aerospace engineering
Keywords: Inertial navigation system, Lunar landings, Unscented Kalman filter
Publication Number: 1479262
ISBN: 978-1-124-11694-5
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