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.

Report Date : MAR 1994

Pagination or Media Count : 94

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, AIRSPEED INDICATORS, CENTER OF GRAVITY, CONFIDENCE LEVEL, CONTROL, DEFLECTION, DIRECTIONAL, TEST AND EVALUATION, UNMANNED, AERODYNAMIC STABILITY, MOMENT OF INERTIA, LIFT TO DRAG RATIO, DYNAMIC RESPONSE, WING BODY CONFIGURATIONS, ANGLE OF ATTACK, VELOCITY, THESES.

Subject Categories : Pilotless Aircraft
      Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE