by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor in Edwards, Calif, [Springfield, Va .
Written in English
|Statement||Glenn B. Gilyard, Jennifer Georgie, and Joseph S. Barnicki.|
|Series||NASA/TM -- 1999-206569., NASA technical memorandum -- 206569.|
|Contributions||Georgie, Jennifer., Barnicki, Joseph S., NASA Dryden Flight Research Center.|
|The Physical Object|
Adaptive Performance Optimization Patent 5,, Gilyard’s L flight test results in “Optimizing the symmetric outboard aileron position realizes a drag reduction of drag counts (approximately 1 percent).” Flight Test of an Adaptive Configuration Optimization System for Transport Aircraft. Mission Adaptive Wing System for Tactical Aircraft. William W. Gilbert ; William W. Gilbert. Simultaneous Configuration Optimization of Multistate Reconfigurable Aerostructures. Matthew P. Snyder and The design and flight test of a new smart wing by: Evolution of aircraft flight control system and fly-by-light flight control system Article (PDF Available) December with 7, Reads How we measure 'reads'. Flight Test Techniques Series – Volume 14 system level operational needs. The scope of the Panel covers a multidisciplinary range of theoretical Volume 1 and 2 of the original Flight Test Manual, including the flight testing of aircraft systems. The monographs in this series (with the exception of AG , which was separately numbered.
FLIGHT TRAJECTORY OPTIMIZATION FOR AN EFFICIENT AIR TRANSPORTATION SYSTEM is an assumed sphere with radius R and the aircraft’s position is located by latitude I, longitude T 1and altitude H ¨in a polar coordinate frame XYZ. The Great Circle Route (GCR) defined as . For these flight tests the baseline configuration was used. These flight tests proved that: (i) the predictions regarding takeoff and landing runway distance had less than 10% divergence from the actual test flights, (ii) the control surfaces provided an aircraft response exactly as calculated in flight mechanics analysis, (iii) the flight test. Stability and Control Analysis for an Unmanned Aircraft Configuration Using System-Identification Techniques. FLIGHT TEST PROTOCOL OPTIMIZATION USING GENETIC ALGORITHMS. IFAC Proceedings Volumes, Vol. 39, No. 1 Transport Aircraft System Identification from Wind Tunnel Data. The Transport Airplane and Engine Issues Group is pleased to submit the following as a recommendation to the FAA in accordance with the reference tasking. This information has been prepared by the Flight Guidance Harmonization Working Group. • FGHWG report - , Automatic Pilot System • Proposed NPRM - , Automatic Pilot System.
The Intelligent Flight Control System team is currently in the process of implementing a second generation control scheme, collectively known as “Generation 2” or “Gen 2,” for flight testing on the NASA F aircraft. This report describes the Gen 2 system as implemented by the team for flight test . American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA A NASA Dryden Flight Research Center program explores the practical application of real-time adaptive configuration optimization for enhanced transport performance on an L aircraft. This approach is based on calculation of incremental drag from forcedresponse, symmetric, . aircraft has been tested in flight for a post-design performance optimization and for the assessment of flight qualities. These experiences have led to the application of two winglets to the original wing. The final configuration has beenextensively tested for the achievement of CS certification.