Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990. / Thesis Advisor(s): Howard, Richard M. Second Reader: Pagenkopf, Eric L. "September 1990." Description based on title screen as viewed on December 18, 2009. DTIC Descriptor(s): Unmanned, Flight Testing, Angles, Steady State, Measurement, Vibration, Maneuverability, Marine Corps, Aircraft, Scale Models, Structural Properties, Tail Assemblies, Theses, Angle Of Attack, Estimates, Fuels, Endurance(General), Flight, Response, Scale, Weight, Airframes, Airspeed, Instrumentation, Recording Systems, Sideslip, Maneuvers, Behavior, Flow, Vehicles, Wings, Altitude, Failure(Mechanics), Radio Signals, Remote Control, Control Surfaces, Directional, Booms(Equipment), Propellers, Data Bases, Data Processing. DTIC Identifier(s): Remotely Piloted Vehicles, Unmanned Air Vehicles, Aerodynamic Control Surfaces, Aerodynamic Characteristics, Flight Testing, Pitch(Motion). Yaw, Flight Maneuvers, Theses. Includes bibliographical references (p. 55). Also available in print.

Thesis (Aeronautical and Astronautical Engineer)--Naval Postgraduate School, December 2002. / Thesis advisor(s): Kevin James, Max Platzer. Includes bibliographical references (p. 139). Also available online.

Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2009. / Source: Dissertation Abstracts International, Volume: 70-06, Section: B, page: 3590. Adviser: Jonathan B. Freund. Includes bibliographical references (leaves 95-98) Available on microfilm from Pro Quest Information and Learning.

Thesis (Ph.D.)--Lehigh University, 2009. / Adviser: Gary Harlow.

<p> A computer vision-based navigation feasibility study consisting of two navigation algorithms is presented to determine whether computer vision can be used to safely navigate a small semi-autonomous inspection satellite in proximity to the International Space Station. Using stereoscopic image-sensors and computer vision, the relative attitude determination and the relative distance determination algorithms estimate the inspection satellite's relative position in relation to its host spacecraft. An algorithm needed to calibrate the stereo camera system is presented, and this calibration method is discussed. These relative navigation algorithms are tested in NASA Johnson Space Center's simulation software, Engineering Dynamic On-board Ubiquitous Graphics (DOUG) Graphics for Exploration (EDGE), using a rendered model of the International Space Station to serve as the host spacecraft. Both vision-based algorithms proved to attain successful results, and the recommended future work is discussed. </p>

A large-scale model of a tiltrotor wing and flap was built and tested to determine how the size and spacing of fluidic actuators for active flow control should be scaled up from laboratory size models to aircraft size. Flow control was provided by sweeping jet actuators mounted in the flap follower. Chordwise pressure data was collected through pressure taps located along the model centerline. The maximum flap deflection to which the flow could be attached with actuation was compared to previous experiments on a 10% 3D model. An ideal actuator spacing was found and the momentum coefficient was comparable between the various sized models. These results were used in the design of an industrial wind tunnel-scale model of a wing built for cruise and tiltrotor-like download testing. These tests have shown that actuators located in the flap follower are effective in both the hover and cruise phases of flight.

<p> The design of control mixing algorithms for launch vehicles with multiple vectoring engines yields competing objectives for which no straightforward solution approach exists. The designer seeks to optimally allocate the effector degrees of freedom such that maneuvering capability is maximized subject to constraints on available control authority. In the present application, such algorithms are generally restricted to linear transformations so as to minimize adverse control-structure interaction and maintain compatibility with industry-standard methods for control gain design and stability analysis. Based on the application of the theory of ellipsoids, a complete, scalable, and extensible framework is developed to effect rapid analysis of launch vehicle capability. Furthermore, a control allocation scheme is proposed that simultaneously balances attainment of the maximum maneuvering capability with rejection of internal loads and performance losses resulting from thrust vectoring in the null region of the admissible controls. This novel approach leverages an optimal parametrization of the weighted least squares generalized inverse and exploits the analytic properties of the constraint geometry so as to enable recovery of more than ninety percent of the theoretical capability while maintaining linearity over the majority of the attainable set.</p>

Wind tunnel tests were conducted to investi gate t he effect of placing a propulsion fan behind the tip of a li.tting ring for the purpose of recovering the energy in the trailing vortex. Results indicated tha~ significant increase of thrust could be obtained as a result of vortex energy recovery. In addition, the pre-swirling effect provided b.r the vortex allowed the tan to absorb more power and develop more thrust at a lower rotational speed. / Thesis (M.S.)--Wichita State University, Dept. of Aeronautical Engineering.

<p> The purpose of this thesis is to ascertain the feasibility of using strain gauges attached to a Unmanned Aerial Vehicle (UAV) gripper to determine, upon impact, the hardness of a landing site. We design and fabricate a four finger gripper that uses a rotary component to convert the rotational motion of a servo to the linear motion of the finger assemblies. We functionally test a gripper prototype made from rapid-prototype material. We conduct three experiments to test the gripper's functionality. The first experiment tests the gripper's ability to grasp, lift, and release a centered payload, and the gripper performed with overall success rates of 91%, 100%, and 87% respectively. The second experiment tests the gripper's ability to self-align, lift and release the payload and the gripper performed with overall success rates of 99%, 100%, and 96% respectively. The third experiment tests the functional durability of the gripper, and it performed without error for 5000 open/close cycles. </p>

Due to the nature of today's competitive electronics market, the development of new electronic / Thesis (M.Sc.Eng.)-University of KwaZulu-Natal, 2007.