국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	FLIGHT TEST OF AN ADAPTIVE CONFIGURATION OPTIMIZATION SYSTEM FOR TRANSPORT AIRCRAFT
저자	Glenn B. Gilyard, Jennifer Georgie and Joseph S. Barnicki
Keyword	Adaptive control; Ailerons; Aircraft performance; Cambered wings; Commercial aircraft; Drag reduction; Flight optimization; Fuel consumption; Optimization; Flaps (control surfaces); Wing camber
URL	http://www.dfrc.nasa.gov/DTRS/1999/PDF/H-2284.pdf
보고서번호	NASA-TM-1999-206569
발행년도	1999
출처	NASA Dryden Flight Research Center
ABSTRACT	A NASA Dryden Flight Research Center program explores the practical application of real-time adaptive configuration optimization for enhanced transport performance on an L-1011 aircraft. This approach is based on calculation of incremental drag from forced-response, symmetric, outboard aileron maneuvers. In real-time operation, the symmetric outboard aileron deflection is directly optimized, and the horizontal stabilator and angle of attack are indirectly optimized. A flight experiment has been conducted from an onboard research engineering test station, and flight research results are presented herein. The optimization system has demonstrated the capability of determining the minimum drag configuration of the aircraft in real time. The drag-minimization algorithm is capable of identifying drag to approximately a one-drag-count level. Optimizing the symmetric outboard aileron position realizes a drag reduction of 2? drag counts (approximately 1 percent). Algorithm analysis of maneuvers indicate that two-sided raised-cosine maneuvers improve definition of the symmetric outboard aileron drag effect, thereby improving analysis results and consistency. Ramp maneuvers provide a more even distribution of data collection as a function of excitation deflection than raised-cosine maneuvers provide. A commercial operational system would require airdata calculations and normal output of current inertial navigation systems; engine pressure ratio measurements would be optional.