Date of Award

Spring 2015

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Aerospace Engineering

Committee Director

Brett Newman

Committee Member

Thomas Alberts

Committee Member

Kishore Pamadi

Call Number for Print

Special Collections; LD4331.E56 J67 2015

Abstract

This thesis describes the derivation and implementation of an Extended Kalman Filter for the purpose of estimating the line of sight rates between a non-thrusting, guided projectile and a ground target. Line of sight rates are required signals to implement the proportional navigation guidance scheme. Using low-cost strapdown sensors, the line of sight rate is not directly measurable but is observable as shown in this thesis. The line of sight signal generated by strapdown seekers inherently includes projectile body motion, but with the use of a global positioning system and a strapdown inertial sensor suite, the seeker signal is transformed to the inertial frame and the required guidance signals are generated. Limited laser seeker update rates also preclude direct discrete derivative formulation of the line of sight rates in a spinning airframe. The various update rates of the sensors onboard the guided projectile are handled within the Kalman filter by use of a Sequential Update. The derived filter is simulated using a six degree of freedom simulation to provide the necessary signal inputs to the filter. The simulation also serves to close the guidance, navigation, and control loops and evaluate the entire system architecture. Additionally, the robustness of the filter is analyzed using a Monte Carlo simulation. The simulation results are examined to show the successful implementation of the Kalman filter and the utility of a strapdown seeker.

Rights

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DOI

10.25777/dxfp-rh74

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