Advisor

Cheng, Yang

Committee Member

Xin, Ming

Committee Member

Cinnella, Pasquale

Date of Degree

1-1-2010

Document Type

Graduate Thesis - Open Access

Major

Aerospace Engineering

Degree Name

Master of Science

College

College of Engineering

Department

Department of Aerospace Engineering

Abstract

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.

URI

https://hdl.handle.net/11668/15521

Comments

Estimation||Inertial Navigation System||Lunar Landing||Unscented Kalman Filter

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