The purpose of this research was to investigate a method of determining an aircraft's airspeed in the event of total air data system failure. The process combined GPS-aided inertial velocity with a continuously estimated wind velocity. A velocity estimator (VEST) algorithm was developed to combine the inertial and wind velocities to provide an estimate of the aircraft's current true velocity to be used for command path gain scheduling and for display in the cockpit. The effort resulted in a flight test program as part of a Test Management Project at the United States Air Force Test Pilot School. The project consisted of two ground test and six flight test evaluation sorties. The average true airspeed error from the estimator algorithm during inflight maneuvers was determined to be 12 knots, nondivergent, and minimally variable. The results of this research clearly showed the potential of the algorithm to determine an aircraft's airspeed in the event of an air data system failure. Recommendations for future research and improvements to the operation of the velocity estimator algorithm are discussed.
Velocity Estimate Following Air Data System Failure
2008
307 pages
Report
Keine Angabe
Englisch
Aerodynamics , Avionics , Algebra, Analysis, Geometry, & Mathematical Logic , Algorithms , Scheduling , Estimates , Wind velocity , Airspeed , Gain , Flight control systems , Altitude , Flight simulation , Inertial guidance , Errors , Global positioning system , Theses , Kalman filtering , Information systems , Optimization , Ground speed , Flight testing , Velocity estimation , Gain scheduling , Air data system failure , Inertial velocity , Vest(Velocity estimator) , Airspeed estimation , Learjet simulator , Ground testing , Standby gain scheduling , Gain setting , Groundspeed
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