Abstract
A new missile guidance law is proposed for the control of impact time which provides an improved time-to-go calculation by removing error due to trajectory curvature and also provides a family of trajectories for trajectory planning purposes. Unlike conventional optimal guidance laws, the proposed law is non explicit in time-to-go and the linearization of the engagement kinematics in order to gain a closed form solution is not necessary.
Notes
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Graduation Date
2016
Semester
Summer
Advisor
Qu, Zhihua
Degree
Doctor of Philosophy (Ph.D.)
College
College of Engineering and Computer Science
Department
Electrical Engineering and Computer Engineering
Degree Program
Electrical Engineering
Format
application/pdf
Identifier
CFE0006398
URL
http://purl.fcla.edu/fcla/etd/CFE0006398
Language
English
Release Date
August 2016
Length of Campus-only Access
None
Access Status
Doctoral Dissertation (Open Access)
STARS Citation
Snyder, Mark, "A New Path Planning Guidance Law For Improved Impact Time Control of Missiles and Precision Munitions" (2016). Electronic Theses and Dissertations. 5089.
https://stars.library.ucf.edu/etd/5089