국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	FLIGHT TEST OF THE X-29A AT HIGH ANGLE OF ATTACK: FLIGHT DYNAMICS AND CONTROLS
저자	Jeffrey E. Bauer,, Robert Clarke and John J. Burken
Keyword	Digital flight controls; Flight test; Flying qualit;Unstable
URL	http://www.dfrc.nasa.gov/DTRS/1995/PDF/H-1984.pdf
보고서번호	NASA-TP-3537
발행년도	1995
출처	NASA Dryden Flight Research Center
ABSTRACT	The NASA Dryden Flight Research Center has flight tested two X-29A aircraft at low and high angles of attack. The high-angle-of-attack tests evaluate the feasibility of integrated X-29A technologies. More specific objectives focus on evaluating the high-angle-of-attack flying qualities, defining multiaxis controllability limits, and determining the maximum pitch-pointing capability. A pilot-selectable gain system allows examination of tradeoffs in airplane stability and maneuverability. Basic fighter maneuvers provide qualitative evaluation. Bank angle captures permit qualitative data analysis. This paper discusses the design goals and approach for high-angle-of-attack control laws and provides results from the envelope expansion and handling qualities testing at intermediate angles of attack. Comparisons of the flight test results to the predictions are made where appropriate. The pitch rate command structure of the longi-tudinal control system is shown to be a valid design for high-angle-of-attack control laws. Flight test results show that wing rock amplitude was overpredicted and aileron and rudder effectiveness were underpredicted. Flight tests show the X-29A airplane to be a good aircraft up to 40* angle of attack.