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)

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