국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	AN APPROACH FOR EVALUATING THE DYNAMIC RESPONSE OF IN-FLIGHT THRUST CALIBRATION TECHNIQUES DURING THROTTLE TRANSIENTS
저자	Ronald J. Ray
Keyword	Aircraft engine simulation; Aircraft engine testing; Aircraft flight test; Dynamic thrust; Performance; Thnrust; Thrust Validation; Unsteady Flow
URL	http://www.dfrc.nasa.gov/DTRS/1994/PDF/H-1990.pdf
보고서번호	NASA-TM-4591
발행년도	1994
출처	NASA Dryden Flight Research Center
ABSTRACT	New fight test maneuvers and analysis techniques for evaluating the dynamic response of in-fight thrust models during throttle transient have been developed and validated. The approach is based on the aircraft and engine performance relationship between thrust and drag. Two fight test maneuvers, a throttle step and a throttle frequency sweep, were developed and used in the study. Graphical analysis techniques, including a frequency domain analysis method, were also developed and evaluated. They provide quantitative and qualitative results. Four thrust calculation methods were used to demonstrate and validate the test technique. Flight test applications on two high-performance aircraft confrmed the test methods as valid and accurate. These maneuvers and analysis techniques were easy to implement and use. Flight test results indicate the analysis techniques can identify the combined effects of model error and instrumentation response limitations on the calculated thrust value. The methods developed in this report provide an accurate approach for evaluating, validating, or comparing thrust calculation methods for dynamic fight applications.