The focus of this study is to be able to control the air-to-surface missile throughout the entire flight, with emphasis on the propulsion phase to increase the impact range of the missile. A major difficulty in controlling the missile during the propulsion phase is the important change in mass of the missile. This results in sliding the center of gravity (cg) point and changing inertias. Moreover, aerodynamic coefficients and stability derivatives are not assumed to be constant at predetermined ranges / conversely, they depend on Mach number, angle of attack, and side slip angle. Consequently, as the change of missile mass, cg point, inertia terms, and stability and aerodynamic coefficients come together apart from flight operation stages, a great number of points need to be taken into account when designing the controller. This makes controlling the missile all the more complicated. In this thesis, first the equations of motion are derived, in which, mass of the missile is not assumed constant. Thus, not only the variation of mass but also the variation of inertias is incorporated in the equations of motion. From the derived v equations of motion, a nonlinear inverse dynamics controller that can achieve desired guidance for a conceptually developed air-to-surface missile has been designed, tested and verified for a modeled missile with six degrees of freedom. For brevity of the study, conceptual design and aerodynamic calculations are not given in detail. Nevertheless, improvements for conceptual design are suggested. As a result, it is shown that the controller works efficiently: the missile is able to hit the target with less than 12 m circular error of probability (CEP). Finally, studies and improvements are proposed.

Varying missile configurations may create uncertainty for a missile control algorithm developed with linear control theory, for instance the control system performance requirements may not be satisfied anymore. Missile configuration may change during the missile design period due to variations in subsystem locations, subsystem weights and missile geometry. Likewise, burning propellant, deployment of aerodynamic surfaces and wings with varying sweep angle can be considered as in-flight missile configuration changes. This thesis study addresses development and analysis of an adaptive missile control algorithm to account for the uncertain effects caused by varying missile configuration. Control algorithms, designed using pole placement, are augmented with adaptive neural networks. The resulting controller is a type of model reference adaptive controller. Adaptation characteristics of the augmented control algorithms are investigated to changing center of pressure location and missile geometry. Analyses are performed for three different missile configurations using simulation.

This thesis analyzes the Western missile defense initiatives and their role in Russia&#039 / s relations with NATO and the U.S. The main question of this thesis is whether the Western missile defense initiatives have paved the way for a new era of cooperation between Russia and the West or not. The main argument of this thesis is that Russia has failed to collaborate with NATO in a meaningful manner on missile defense issue as Russia has not adjusted its security policies and nuclear strategy, which are still based on the Cold War thinking, to the changing conditions of global security in the post Cold War era. The missile defense initiatives have a negative impact on the relations between Russia and the West due to the intransigent stance of Russia on this issue. A robust cooperation can only be achieved between Russia and NATO if Moscow changes its Cold War mentality about global security issues.

Abstract Since being developed in 1956, no matter it¡¦s category, function or quantity, Chinese ballistic missiles have kept renewing and increasing. For example, the development of its strategic missiles has undergone the 1st through the 3rd generation with models from Dongfeng-1 to currently developing Dongfeng-41 Ballistic Missile, and its warhead has been gradually developed from carrier of single nuclear head to combination of both traditional and nuclear warheads and to multiple warheads now. Under such multiple developments, Chinese nuclear strategy according to their official speech has still adopted ¡§minimum deterrence¡¨ claimed by the 1960¡¦s and 1970¡¦s until now, and which has already led to external speculations. They think that Chinese has devoted to modernization of ballistic missiles lately, actively developed more land-based strategic missiles and sea-based nuclear submarines, techniques of multiple warheads and space-based weapons, and reinforced the practicality of tactical nuclear missiles etc. that such development has already exceeded the ¡§minimum deterrence¡¨ strategy, which even develops towards the ¡§limited deterrence¡¨ strategy. Therefore, whether China¡¦s deterrence strategy is changing is one of the assumptions in this study. If China¡¦s deterrence strategy is no longer equipped with the minimum deterrence, then whether the most important features of the minimum deterrence by ¡§no use of nuclear weapons at first¡¨ and China¡¦s¡§three nos principle on nuclear weapons¡¨will be changed accordingly is the second assumption in this study. Chinese ballistic missiles apart from being used as deterrence can also be used to practice coercive and annihilative strategies. Especially in the issue of Taiwan, when Chinese deterrence strategy fails in terms of Taiwan, it may use coercive or annihilative strategies to achieve their political and military objectives. As the ability of Taiwan¡¦s anti-ballistic missile is obviously insufficient; so if Taiwan suffers the attack from Chinese missiles, the result will be unimaginable. Therefore, how to prevent the attack from its missiles is what I would like to discuss in this paper. For the probable battle by the two sides of the Taiwan Strait in the future, in order to quickly facilitate the victory, whether Chinese will use micro-kiloton nuclear warhead to destroy the important and stable military targets in Taiwan to help smooth the warfare and further crash the myth that Chinese will not use nuclear weapons against Taiwan is the 3rd assumption in this paper. Finally how to increase our defense against ballistic missiles and whether we should participate in the TMD (Theatre Missile Defense) provided by America, I will provide several suggestions for references of the related units, hoping to make certain contributions towards Taiwanese prevention against the threat from Chinese ballistic missile.

Thesis (M.A. in National Security Affairs)--Naval Postgraduate School, June 2003. / Thesis advisor(s): David S. Yost, James J. Wirtz. Includes bibliographical references. Also available online.

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President John F. Kennedy’s announcement, on Monday 22 October 1962, that there were offensive missiles on the island of Cuba began the public phase of what would be remembered as the Cuban missile crisis. This Cold War crisis had ramifications in many other countries than just the Soviet Union and the United States. Due to the danger involved in this nuclear confrontation, the entire globe was threatened. If either side lost control of negotiations, an atomic war could have broken out which would have decimated the planet. As the direct northern neighbors of the United States and partners in continental defence, Canadians experienced and understood the Cuban missile crisis in the context of larger issues. In many ways, Canadian and American reactions to the crisis were similar. Many citizens stocked up their pantries, read the newspapers, protested, or worried that the politicians would make a mistake and set off a war. However, this dissertation argues that English Canadians experienced the crisis on another level as well. In public debate and print sources, many debated what the crisis meant for Canadian-Cuban relations, Canadian-American relations and Canada’s place in the world. Examining these print and archival sources, this dissertation analyzes the contour of public debate during the crisis, uniting that debate with the actions of politicians. Prime Minister John G. Diefenbaker hesitated for two days before making a statement which fully committed Canada to a position which supported the American quarantine of Cuba, and shortly after the crisis, was defeated at the polls. This dissertation argues that understanding the Canadian reaction to and experience of the Cuban missile crisis necessitates an understanding of how different Canadians talked about and understood the actions of their leaders. The shifting terrain of memory also serves to demonstrate the manner in which this history is told and remembered in Canada. This dissertation, therefore, examines the intersections between this Cold War confrontation and Canadian identity in the postwar period. / Thesis (Ph.D, History) -- Queen's University, 2011-12-23 09:01:36.5

DYNAMIC MODELING, GUIDANCE, AND CONTROL OF HOMING MISSILES &Ouml / ZKAN, B&uuml / lent Ph. D., Department of Mechanical Engineering Supervisor: Prof. Dr. M. Kemal &Ouml / ZG&Ouml / REN Co-Supervisor: Dr. G&ouml / kmen MAHMUTYAZICIOgLU September 2005, 236 pages In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then, regarding the relative rotation between the bodies, the aerodynamic model of the missile is constructed by means of the Missile Datcom software available in T&Uuml / BiTAK-SAGE. After obtaining the required aerodynamic stability derivatives using the generated aerodynamic data, the necessary transfer functions are determined based on the equations of motion of the missile. Next, the guidance laws that are considered in this study are formulated. Here, the Linear Homing Guidance and the Parabolic Homing Guidance laws are introduced as alternatives to the Proportional Navigation Guidance law. On this occasion, the spatial derivation of the Proportional Navigation Guidance law is also done. Afterwards, the roll, pitch and yaw autopilots are designed using the determined transfer functions. As the roll autopilot is constructed to regulate the roll angle of the front body of the missile which is the controlled part, the pitch and yaw autopilots are designed to realize the command signals generated by the guidance laws. The guidance commands are in the form of either the lateral acceleration components or the flight path angles of the missile. Then, the target kinematics is modeled for a typical surface target. As a complementary part of the work, the design of a target state estimator is made as a first order fading memory filter. Finally, the entire guidance and control system is built by integrating all the models mentioned above. Using the entire system model, the computer simulations are carried out using the Matlab-Simulink software and the proposed guidance laws are compared with the Proportional Navigation Guidance law. The comparison is repeated for a selected single-body missile as well. Consequently, the simulation results are discussed and the study is evaluated.