국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	RESULTS FROM F-18B STABILITY AND CONTROL PARAMETER ESTIMATION FLIGHT TESTS AT HIGH DYNAMIC PRESSURES.
저자	Timothy R. Moes, Gregory K. Noffz and Kenneth W. Iliff
Keyword	Active aeroelastic wing; Control derivatives; Maximum likelihood estimates; Parameter identification; Stability derivatives
URL	http://www.dfrc.nasa.gov/DTRS/2000/PDF/H-2424.pdf
보고서번호	NASA-TP-2000-209033
발행년도	2000
출처	NASA Dryden Flight Research Center
ABSTRACT	A maximum-likelihood output-error parameter estimation technique has been used to obtain stability and control derivatives for the NASA F-18B Systems Research Aircraft. This work has been performed to support flight testing of the active aeroelastic wing (AAW) F-18A project. The goal of this research is to obtain baseline F-18 stability and control derivatives that will form the foundation of the aerodynamic model for the AAW aircraft configuration. Flight data have been obtained at Mach numbers between 0.85 and 1.30 and at dynamic pressures ranging between 600 and 1500 lbf/ft2. At each test condition, longitudinal and lateral-directional doublets have been performed using an automated onboard excitation system. The doublet maneuver consists of a series of single-surface inputs so that individual control-surface motions cannot be correlated with other control-surface motions. Flight test results have shown that several stability and control derivatives are significantly different than prescribed by the F-18B aerodynamic model. This report defines the parameter estimation technique used, presents stability and control derivative results, compares the results with predictions based on the current F-18B aerodynamic model, and shows improvements to the nonlinear simulation using updated derivatives from this research.