Thesis (M.A. in National Security Affairs)--Naval Postgraduate School, March 2005. / Thesis Advisor(s): Mikhail Tsypkin, Edward J. Laurance. Includes bibliographical references (p. 73-79). Also available online.

abstract: With recent advances in missile and hypersonic vehicle technologies, the need for being able to accurately simulate missile-target engagements has never been greater. Within this research, we examine a fully integrated missile-target engagement environment. A MATLAB based application is developed with 3D animation capabilities to study missile-target engagement and visualize them. The high fidelity environment is used to validate miss distance analysis with the results presented in relevant GNC textbooks and to examine how the kill zone varies with critical engagement parameters; e.g. initial engagement altitude, missile Mach, and missile maximum acceleration. A ray-based binary search algorithm is used to estimate the kill zone region; i.e. the set of initial target starting conditions such that it will be "killed". The results show what is expected. The kill zone increases with larger initial missile Mach and maximum acceleration & decreases with higher engagement altitude and higher target Mach. The environment is based on (1) a 6DOF bank-to-turn (BTT) missile, (2) a full aerodynamic-stability derivative look up tables ranging over Mach number, angle of attack and sideslip angle (3) a standard atmosphere model, (4) actuator dynamics for each of the four cruciform fins, (5) seeker dynamics, (6) a nonlinear autopilot, (7) a guidance system with three guidance algorithms (i.e. PNG, optimal, differential game theory), (8) a 3DOF target model with three maneuverability models (i.e. constant speed, Shelton Turn & Climb, Riggs-Vergaz Turn & Dive). Each of the subsystems are described within the research. The environment contains linearization, model analysis and control design features. A gain scheduled nonlinear BTT missile autopilot is presented here. Autopilot got sluggish as missile altitude increased and got aggressive as missile mach increased. In short, the environment is shown to be a very powerful tool for conducting missile-target engagement research - a research that could address multiple missiles and advanced targets. / Dissertation/Thesis / Masters Thesis Electrical Engineering 2016

International Telemetering Conference Proceedings / October 18-21, 2004 / Town & Country Resort, San Diego, California / The Compact Kinetic Energy Missile (CKEM) is currently being developed as the Army’s newest hypervelocity anti-tank missile. The project has recently transitioned from the Science and Technology Objective phase to the Advanced Technology Demonstration phase. Science and technology phase flight testing required the development of a miniature telemetry system for measuring the super sonic flight dynamics of the airframe, as well as, monitoring of the on board flight computer. Design challenges included a small mechanical envelope, limited power budget, numerous analog measurements, computer serial stream processing, and harsh launch and flight dynamics. Two versions of the system were developed in support of the partnership effort between the Army Missile Research, Development, and Engineering Center (AMRDEC) and industry. This paper will focus on the successful design, development, and flight tests of the CKEM telemetry system.

The aim of this dissertation is to show how counter missile tactics for a fast attack craft armed with missiles [FAC(M)] against a surface-to-surface, fireand- forget missile [SSM] can be optimised. As a result the ship and missile will be modelled as generic concepts while the environment will be a chosen area of operations. The applicable methodology is to simulate the ship, missile and environment as well as the interactions between them. At the same time, the ship will be carrying out combinations of five separate missile counter measures. The methodology is then to build a dynamic simulation model to optimise soft kill tactics by a generic F AC(M) against a generic SSM in the chosen environment and evaluate the outcome of the simulation by viewing the experiment as a 25 factorial design and to analyse it accordingly. / Operations Research / M.Sc. (Operations Research)

ITC/USA 2010 Conference Proceedings / The Forty-Sixth Annual International Telemetering Conference and Technical Exhibition / October 25-28, 2010 / Town and Country Resort & Convention Center, San Diego, California / Development is currently underway to produce a dual redundant Flight Termination System (FTS) capable Missile Telemetry Section. This FTS will mainly consist of a conformal wraparound antenna, two flight termination safe & arm (FTS&A) devices, two flight termination receivers (FTR), two explosive foil initiators (EFI) and destruct charge. This paper will discuss the current status of the development of these FTS components along with the process of obtaining the Flight Certification from Range and System Safety to fly this newly outfitted missile on a governmental test range.

International Telemetering Conference Proceedings / October 23-26, 2000 / Town & Country Hotel and Conference Center, San Diego, California / New Norwegian anti-ship missile program (NSM) has evaluated both the fixed format and the packet telemetry for its log/telemetry system. It is important that the NSM log system is easy to reconfigure, since the system shall be used during debugging, lab testing, system testing, test firings, and later on for operational evaluation firings. The packet telemetry standard has been selected because the packet telemetry provides dynamics and flexibility for changes, which are not easy to achieve with fixed format. Test results and system experience will be available before October and a summary will be presented at the ITC 2000 conference.

When hostile missile raids are launched, protecting allied assets requires that many targets be tracked simultaneously. In these raids, it is possible that the number of missiles could outnumber the sensors available to measure them. In these situations, communication between sensors can be utilized along with dynamic task planning to increase the amount of knowledge available concerning these missiles. Since any allied decisions must depend on the knowledge available from the sensors, it follows that improving the overall knowledge will improve the ability of allies to protect their assets through improved decision making. The goal of the this research effort is to create a Sensor Resource Management (SRM) algorithm to optimize the information available during these missile raids, as well as strengthening the simulation framework required to evaluate the performance of the SRM. The SRM must be capable of near-real-time run time so that it could potentially be deployed in a real-world system. The SRM must be capable of providing time-varying assignments to sensors, allowing more than one target to be observed by a single sensor. The SRM must predict measurements based on sensor models to assess the potential information gain by each assignment. Using these predictions, an optimal allocation of all sensors must be constructed. The initial simulation, upon which this work was built, was capable of simulating a set number of missiles launched simultaneously, providing appropriate charts to display the accuracy of knowledge on each target as well as their predicted impact locations. Communication delays are implemented within the simulation, and sensor models are refined. In refining the sensor models, they are given geometric limitations such as range and viewing angles. Additionally, simulated measurements incorporate geometric considerations to provide more realistic values. The SRM is also improved to account for the details added to the simulation. These improvements include creating assignment schedules and allowing a time-varying numbers of targets. The resulting simulation and SRM are presented, and potential future work is discussed. / text

Approved for public release; distribution is unlimited / In the boost phase interception of ballistic missiles, determining the exact position of a ballistic missile has a significant importance. Several sensors are used to detect and track the missile. These sensors differ from each other in many different aspects. The outputs of radars give range, elevation and azimuth information of the target while space based infrared sensors give elevation and azimuth information. These outputs have to be combined (fused) achieve better position information for the missile. The architecture that is used in this thesis is decision level fusion architecture. This thesis examines four algorithms to fuse the results of radar sensors and space based infrared sensors. An averaging technique, a weighted averaging technique, a Kalman filtering approach and a Bayesian technique are compared. The ballistic missile boost phase segment and the sensors are modeled in MATLAB. The missile vector and dynamics are based upon Newton's laws and the simulation uses an earth-centered coordinate system. The Bayesian algorithm has the best performance resulting in a rms missile position error of less than 20 m. / 1st Lieutenant, Turkish Air Force

Approved for public release; distribution is unlimited / The flowfield downstream of a vertically-launched surface-to-air missile model at an angle of attack of 50° and a Reynolds number of 1.1 x 10(5) was investigated in a wind tunnel of the Naval Postgraduate School. The goal of this thesis is to experimentally validate the pressure measurement system for flowfield variables with elevated levels of turbulence; to determine the location and intensity of the asymmetric vortices in the wake of the VLSAM model at a raised level of freestream turbulence; and to display the asymmetric vortices by velocity mapping and pressure contours. The purpose is to correlate the results with the force measurements of Rabang to provide a greater understanding of the vortex flowfield. The body-only configuration was tested. Two flowfield conditions were treated: the nominal ambient wind tunnel condition, and a condition with grid­ generated turbulence of 3.8% turbulence intensity and a dissipation length scale of 1.7 inches. The following conclusions were reached: 1) The relative strengths of the asymmetric vortices can be noted by the sharp spike shape in the ambient condition; this condition becomes diffused and becomes fatter in the turbulent condition; 2) The right side vortex has greater strength than the left side one as seen by the diffusion in the total pressure coefficient and static pressure coefficient contours with and without a turbulent condition; 3) an increase in turbulence intensity tends to reduce the strength of the asymmetric nose-generated vortices; also pushes the two asymmetric vortices closer together; 4) and crossflow velocities were examined and were found to indicate the behavior denoted by the pressure contours. / http://archive.org/details/flowfieldmeasure00lung / Lieutenant, Republic of China Navy

Approved for public release; distribution is unlimited / The Tomahawk Land-Attack Missile (TLAM) is the long-range precision weapon of choice in strike warfare against strategic targets for U.S. military forces. Predesignation is the process of determining which ship or submarine will fire which TLAM missiles in support of an authorized attack upon specified targets. This thesis revisits the mathematical models and algorithms developed by previous NPS faculty and students to optimally conduct the allocation of TLAMs to firing units. We incorporate all the problem specifications addressed by previous heuristic algorithms for the problem, and compare our results to those in publicly available test cases. We show that our models can be solved optimally in affordable time for most of the cases and make provisions to establish accurate bounds in the other cases. / First Lieutenant, Turkish Army