Call number: LD2668 .T4 1965 D227 / Master of Science

Angles measurements from optical systems are the primary source of data for maintaining the orbits of high altitude satellites. Radar measurements are used primarily for low Earth orbit (LEO) satellites. Recently it has been shown that the accuracy of the orbit updates using only optical system angles-only data is just as good, if not better, than the performance from radar systems for LEO satellites. The purpose of this thesis is to investigate the use of optical angles data with and without laser ranging data in determining the trajectories of missiles. Analytical Graphics, Inc. Satellite Tool Kit is used to model the trajectory of a ballistic missile. Several scenarios are developed for determining the orbit when acquired by sensors providing various combinations of range, range rate and angles data. It is found that the combination of range, azimuth and elevation sensor data yields an orbit determination that has enough merit to be called accurate. The error of the orbit determined by the angles-only data is two orders of magnitude larger than the error of the range and angles measurement. Additionally completed was an analysis of what would happen if the sensors could only track to the maximum altitude of the orbit. As was assumed, the known position of the object drifts ranged from minimal to significant predicated on the final known position. This is indicated by the error ellipsoid. It was again found that the combination of range, azimuth and elevation sensor data until the maximum altitude yields an orbit determination that has enough merit to be called accurate. Also considered was the addition of a second sensor that had the capacity to always track range, azimuth and elevation to increase the time that is afforded to track the object, increasing the overall accuracy of the orbit determination. It is found that the addition of a second sensor increases the fidelity of the angles-only measurement such that the combination of azimuth and elevation sensor data yields an orbit determination that has enough merit to be called accurate.

We describe major enhancements to the missile defense planning aid "JOINT DEFENDER" (JDEF). JDEF is the first system that shows how to evaluate and exploit new and anticipated improvements in interceptors, long-range surveillance and tracking capabilities, networked communications, and the ability of detecting platforms to cue intercepting ones downrange. We want to improve system-wide effectiveness, gauged here by the reduction of expected damage inflicted. We defend an asset list (DAL) of targets, characterized by their locations and values to us. Our defenders include pure "LOOKERs," radars and sensors of enemy missile launches, and "SHOOTERs," platforms with means to both detect and intercept enemy launches. JDEF optimally positions platforms that can be moved, and prescribes what each platform should do. JDEF can estimate the value to either opponent of secrecy, deception, or intelligence. JDEF is the only missile defense planning system using formal optimization. Among many advantages this conveys, JDEF is able to unambiguously quantify the difference among disparate plans. Although the JDEF planner can manually control any detail, the planner is well advised to let optimization suggest where to start.

A near-optimal guidance law has been developed using the direct method of calculus of variations that maximizes the kinetic energy transfer from a surface-launched missile upon interception to a ballistic missile target during the boost phase of flight. Mathematical models of a North Korean Taep'o-dong II (TD-2) medium-range ballistic missile and a Raytheon Standard Missile 6 (SM-6) interceptor are used to demonstrate the guidance lawâ s performance. This law will utilize the SM-6â s onboard computer and active radar sensors to independently predict an intercept point, solve the two-point boundary value problem, and determine a near-optimal flight path to that point. Determining a truly optimal flight path would require significant computing power and time, while a near-optimal flight path can be calculated onboard the interceptor and updated in real time without significant changes to the interceptorâ s hardware. That near-optimal guidance path is then converted into a set of command functions and fed back into the control computer of the interceptor. By modifying the second and third derivatives of the two-point boundary value problem, the intercept conditions can be varied to study their effects upon the optimal flight path regarding the maximization of kinetic energy upon impact. / US Navy (USN) author.

Thesis. 1975. Sc.D.--Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics. / Vita. / Bibliography: leaves 318-319. / Sc.D.

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Thesis (M.S.)--Ohio University, August, 1999. / Title from PDF t.p.

Thesis (M.Eng.Sc.) - Dept. of Electrical and Electronic Engineering, University of Adelaide, 1983. / AR-003-687. Originally his Thesis (M.Eng.Sc.) - Dept. of Electrical and Electronic Engineering, University of Adelaide, 1980. Photostat. Includes bibliographical references (p. 66-67).

Thesis (Ph. D.)--RAND Graduate School, 1991. / Includes bibliographical references.