Flight dynamics of an unmanned aerial vehicle
By:  Eric John Watkiss
Publisher: Naval Postgraduate School; Available from National Technical Information Service
Published: 1994
Place of publication: Monterey, Calif; Springfield, Va
Language: eng
Number of pages: 81
Description: Moments of inertia were experimentally determined and longitudinal and lateral/directional static and dynamic stability and control derivatives were estimated for a fixed wing Unmanned Air Vehicle (UAV). Dynamic responses to various inputs were predicted based upon the estimated derivatives. A divergent spiral mode was revealed, but no particularly hazardous dynamics were predicted. The aircraft was then instrumented with an airspeed indicator, which when combined with the ability to determine elevator deflection through trim setting on the flight control transmitter, allowed for the determination of the aircraft's neutral point through flight test. The neutral point determined experimentally corresponded well to the theoretical neutral point. However, further flight testing with improved instrumentation is planned to raise the confidence level in the neutral point location. Further flight testing will also include dynamic studies in order to refine the estimated stability and control derivatives.
Notes: Thesis advisor(s):Richard M. Howard.

"March 1994."

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1994.

Includes bibliographical references.

Approved for public release; distribution unlimited.