Accession Number : ADA282651

Title :   Flight Dynamics of an Unmanned Aerial Vehicle

Descriptive Note : Master's thesis

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Watkiss, Eric J

PDF Url : ADA282651

Report Date : Mar 1994

Pagination or Media Count : 105

Abstract : 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. Unmanned Aerial Vehicle, UAV, Flight test, Flight dynamics

Descriptors :   *FLIGHT TESTING, *REMOTELY PILOTED VEHICLES, AERODYNAMIC STABILITY, AIRSPEED INDICATORS, ANGLE OF ATTACK, CENTER OF GRAVITY, CONFIDENCE LEVEL, CONTROL, DEFLECTION, DIRECTIONAL, DYNAMIC RESPONSE, LIFT TO DRAG RATIO, MOMENT OF INERTIA, TEST AND EVALUATION, THESES, UNMANNED, VELOCITY, WING BODY CONFIGURATIONS

Subject Categories : Aerodynamics
      Pilotless Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE