Thesis (M.S.)--Naval Postgraduate School, 2002. / Thesis advisor(s): Isaac I. Kaminer, Oleg A. Yakimenko. Includes bibliographical references (p. 103). Also available online.

Thesis (M.S.)--Brigham Young University. Dept. of Electrical and Computer Engineering, 2004. / Includes bibliographical references (p. 235-236).

Project report (M.S.)--Virginia Polytechnic Institute and State University, 1990. / Vita. Abstract. Includes bibliographical references (leaf 59). Also available via the Internet.

Thesis (MScIng)--University of Stellenbosch, 2005. / Bibliography. Also available via the Internet.

No description available.

An adaptive pitch axis autopilot design procedure is presented. The design procedure is applicable to both stable and unstable pitch axis models and to those having nonminimum phase. The design approach assumes the adaptive autopilot is activated after achieving level flight. It is shown a rate-feedback compensator can be designed to ensure stable level flight pitch axis operation for the entire desired flight regime. The adaptive control loop design utilizes a pole-placement algorithm. The closed-loop characteristic polynomial is designed to have dominant poles of that of an ideal second order system to obtain the desired transient response. The identification of the system uses a modified least-squares algorithm with a variable forgetting factor. The nonlinear pitch axis model is used in simulations to evaluate the design. Command response tests include the step response and the ramp command response. Simulation results indicate that the adaptive pitch axis autopilot is capable of tracking altitude commands after activation. The closed-loop system response is close to that of the ideal second order system having the dominant poles. / Graduation date: 1991

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

Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2005. / Bottasso, Carlo, Committee Chair ; Hodges, Dewey, Committee Member ; Bauchau, Olivier, Committee Member. Includes bibliographical references.

Thesis (M.S.)--Brigham Young University. Dept. of Mechanical Engineering, 2007. / Includes bibliographical references (p. 127-130).

Thesis (MScEng (Electrical and Electronic Engineering))--Stellenbosch University, 2005. / The successful development of a conventional flight autopilot for a model aircraft is presented. All aspects of the autopilot design are considered, from modeling to flight tests. A mathematical aircraft model, as a function of the aircraft’s physical parameters alone, is presented. A controller architecture capable of regulating the motion variables required for conventional flight using only low cost, off-the-shelf sensors is developed. The controller design complements the aircraft model development technique used, by reducing the sensitivity of the controller performance to the model accuracy. The avionics and ground station design is presented. The avionics includes a generic Inertial Measurement Unit (IMU). The total avionics cost is only R5000. Results from three days of flight tests demonstrate the autopilot’s success. Its rapid success can largely be attributed to the extensive simulations of the entire autopilot in the two non-linear simulators developed.