Orbit selection and EKV guidance for space-based ICBM intercept
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Authors
Aydin, Ahmet Tarik
Subjects
Advisors
Pace, Phillip E.
Tummala, Murali
Date of Issue
2006-09
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Boost-phase intercept of a threat intercontinental ballistic missile (ICBM) is the first layer of a multilayer defense. This thesis investigates the requirements and limitations of the U.S. space-based ICBM defense against North Korea, Iran and China by introducing an ICBM trajectory prediction, selecting an orbit for exoatmospheric kill vehicles (EKV) and developing a hybrid guidance algorithm. The prediction of the ICBM trajectory takes the rotation of the earth and the atmospheric drag into account along with the gravitational forces and thrust. The threat ICBM locations, specifications and capabilities of the EKV and EKV carrier, and the capabilities of the space launch vehicle are analyzed to determine an appropriate orbit for the space-based intercept. The pursuit guidance, proportional navigation guidance and bang-bang guidance rules and their performances are investigated and simulated for three example ICBM threats in three-dimensional environment. The simulation results performances are compared and analyzed for minimum miss distance, intercept time and total command effort. The guidance rules are combined to meet the mission requirements, resulting in a hybrid guidance algorithm, which uses different guidance rules for different stages of a boost-phase intercept scenario.
Type
Thesis
Description
Series/Report No
Organization
Graduate School of Engineering and Applied Science (GSEAS)
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
xvi, 118 p. : col. ill., col. maps ;
Citation
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.