This thesis looks at the development of Canadian satellite policy between 1960 and 1980 through a study of the policy decisions relating to Telesat Canada, its specific corporate structure, and mandates and ownership patterns. The analysis draws upon a modified "interplay" model, which examines public policy as an amalgam of interacting ideas, interests and institutions. On the basis of available documents, supplemented by interviews, and supporting secondary analyses, the sometimes contradictory decisions made by the DOC and the CRTC with regards to Telesat's Agreement with the Trans Canada Telephone system during this period are argued to reflect a policy process driven by the interplay of competing views of Telesat's primary purpose and, by extension, competing visions of what constitutes the public interest.

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Thesis (M.S. in Electrical Engineering)--University of Virginia, March 1968. / "June 1970." Submitted in partial fulfillment of the requirements for the degree Master of Electrical Engineering, University of Virginia, Charlottesville, Virginia, March 1968.--Report documentation page. "NASA TN D-5829." "L-6988." Includes bibliographical references (p. 17). Also available online in PDF from NASA Technical Reports Server Web site.

Thesis (Ph. D.)--University of Texas at Austin, 1998. / Vita. Includes bibliographical references (leaves 226-231). Available also in a digital version from Dissertation Abstracts.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1993. / Vita. Abstract. Includes bibliographical references (leaves 85-88). Also available via the Internet.

Thesis (Ph.D.)--School of Mechanical Engineering, Georgia Institute of Technology, 2005. / Singhose, William, Committee Chair ; Banerjee, Arun, Committee Member ; Chen, Ye-Hwa, Committee Member ; Ebert-Uphoff, Imme, Committee Member ; Olds, John, Committee Member. Includes bibliographical references.

Thesis (M.S.)--University of Wisconsin, 1967. / eContent provider-neutral record in process. Description based on print version record. Includes bibliographical references (leaf 39).

Thesis (M.S.)--Montana State University--Bozeman, 2005. / Typescript. Chairperson, Graduate Committee: David M. Klumpar. Includes bibliographical references (leaves 220-221).

The thesis identifies several limitations in the modelling and attitude stability analysis of two classes of spacecraft: rigid and flexible satellites. Attractive methods are proposed which promise to have far reaching consequences in spacecraft dynamics. These alternatives, developed based on techniques of differential equations, classical mechanics, and differential topology, are indicated below. (a) An Alternate Transition from the Lagrangian of a Satellite to Equations of Motion The classical procedure requires the Lagrangian to be expressed in terms of the corresponding generalized coordinates of the problem. This requirement significantly complicates the derivation of the equations of motion through an introduction of a set of librational generalized coordinates, which is strictly not a part of the dynamical system. Using the Lagrangian in the natural variables (angular velocity, direction cosines, and vibrational coordinates), one develops a procedure for derivation of equations of motion without an a priori choice of rotational generalized coordinates. For the case of a satellite with two flexible plate-type appendages, for example, the approach reduced the formulation time to one-third. (b) Synthesis and Depiction of Rotational Motion of Satellites and Robots The rotational coordinates in use for numerical prediction of orientation of a satellite are either singular or redundant. Furthermore, they lack a convenient visual interpretation. A new set of coordinates is proposed and an associated representation is developed which avoids these limitations. The procedure is applied to represent and integrate numerically the librational response of the flexible satellite mentioned in (a). (c) Resolution of Attitude Stability of Delp Satellites The development here tackles a long outstanding problem in the area of attitude stability of satellites. The resolution of this problem through normalization of the Hamiltonian leads to a better appreciation of stability associated with the class of gravity gradient structures such as the proposed Space Station. / Applied Science, Faculty of / Mechanical Engineering, Department of / Graduate