see document / Master of Science

A ramjet inlet duct structure has been designed using nonlinear structural analysis to allow local plastic deformations which result in structural weight reduction. To establish the feasibility of reduced shell thickness, the Lower-Bound Theorem of limit analysis has been applied using an existing finite element analysis computer code intended for elastic analysis. The results of the analysis were verified by structural testing. Predicted stresses and deflections showed good correlation with measured values up to the point of failure. This work was supported by the U.S. Air Force Aero Propulsion Laboratory, Wright-Patterson Air Force Base, Ohio, under Contract No. F33615-72-C-1366.

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The United States-Japanese missile defense cooperation signals yet another step in Japan's continuing trend of "normalization" and official acknowledgement that Japan has a significant military force. This thesis analyzes the current status of the Japanese missile defense debate and assesses factors shaping the Japanese commitment to joint missile defense with the United States. Three major inter-related trends mark the course of Japanese post- Cold War SDF evolution, relations with the United States and the missile defense debate. These include a willingness to relax legal considerations on the use of military force, the expansion of the roles for the JSDF, and the responsiveness of Japanese decision makers to external factors, notably the requirement to improve relations with the United States and the threat perceived from North Korea. This represents a shift to a more military-based security outlook away from the traditional notion of "comprehensive security." These trends point invariably to the amendment of Article 9 of the Japanese Constitution. To maximize U.S. interests, Washington must pursue a balanced and limited missile defense in East Asia and actively undertake measures to avoid the perception of a threat to Chinese nuclear deterrence.

Thesis--School of Advanced Airpower Studies, Maxwell Air Force Base, Ala., 1993-94. / Title from title screen (viewed Nov. 5, 2003). "October 1995." Includes bibliographical references.

Dissertation (Ph.D.)--Auburn University, 2006. / Abstract. Vita. Includes bibliographic references.

Thesis -- University of Adelaide, 1966. / [Typescript].

Thesis (M.S. in Electrical Engineering)--Naval Postgraduate School, December 1990. / Thesis Advisor(s): Titus, Harold A. Second Reader: Powell, James R. "December 1990." Description based on title screen as viewed on April 1, 2010. DTIC Descriptor(s): Guided Missiles, Simulation, Forward Areas, Optimization, Transfer Functions, Guided Missile Warheads, Dynamics, Two Dimensional, Theses, Targets, Time, Three Dimensional, Solutions (General), Homing Devices, Maneuvers, Evasion, Simplification, Proportional Navigation, Automatic Pilots, Guided Missile Components, Miss Distance. DTIC Identifier(s): Proportional Navigation, Guided Missile Targets, Evasion, Flight Maneuvers, Intercept Trajectories, Guided Missile Trajectories, Antiaircraft Missiles, Aircraft Defense Systems, Miss Distance, Optimization, Adjoint Models, Survivability, Barrel Roll Maneuver, Split S Maneuver, Scenarios, Computer Programs, Theses. Author(s) subject terms: Proportional Navigation, Miss Distance, Adjoint. Includes bibliographical references (p. 111). Also available in print.

Texte remanié de: Th. Ph. D.--Law--University of Oxford, 1995. / Bibliogr. p. 217-240. Index.

The engagement between an antiship missile and a ship’s defense system is investigated. The missile is equipped with proportional navigation guidance for homing in on its ship target. The ship’s defense system consists of a radar, an estimation system (the extended Kalman filter and the “jump filter” are used), and a gun system. The performance index is defined as the estimated number of hits (EHITS) of projectiles on the missile. The main objective of this dissertation is to determine maneuvering periods for the missile which minimize the EHITS to evade the ship’s gunfire under different engagement conditions. The maneuvering periods are design parameters in the missile’s controls of both the vertical and the horizontal planes. The engagement conditions are the follows: the maximum amplitude of the maneuvering functions, the homing in position of the missile on the ship, the measurement noise condition of the ship’s radar, and the missile’s model assumed in the ship’s filters. The missile’s control functions considered are periodic and of specific types (sinusoidal, square and sawtooth waveforms); therefore, the periods which minimize the EHITS in this study are suboptimal for the general engagement problem. Two methods are used to obtain the suboptimal periods: one is the ”brute force" method of computing the EHITS for certain equally spaced periods, the other uses an optimization software to search for the minimum point. The results show that the curve of EHITS vs. period is monotonically decreasing until it reaches a minimum point. The optimal period increases with an increase in measurement noise. Among the three waveforms used, the square wave gives the smallest optimal period and the sawtooth wave gives the largest one. The sinusoidal waveform with the period of 1.9 seconds is recommended. We consider the missile's performance against a perfect radar, a modern radar, and an earlier model radar. The optimum EHITS resulting from the optimal periods are between two and three EHITS for all three radars considered. / Ph. D.