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X-29A Lateral-Directional Stability and Control Derivatives Extracted From High-Angle-of-Attack Flight DataThe lateral-directional stability and control derivatives of the X-29A number 2 are extracted from flight data over an angle-of-attack range of 4 degrees to 53 degrees using a parameter identification algorithm. The algorithm uses the linearized aircraft equations of motion and a maximum likelihood estimator in the presence of state and measurement noise. State noise is used to model the uncommanded forcing function caused by unsteady aerodynamics over the aircraft at angles of attack above 15 degrees. The results supported the flight-envelope-expansion phase of the X-29A number 2 by helping to update the aerodynamic mathematical model, to improve the real-time simulator, and to revise flight control system laws. Effects of the aircraft high gain flight control system on maneuver quality and the estimated derivatives are also discussed. The derivatives are plotted as functions of angle of attack and compared with the predicted aerodynamic database. Agreement between predicted and flight values is quite good for some derivatives such as the lateral force due to sideslip, the lateral force due to rudder deflection, and the rolling moment due to roll rate. The results also show significant differences in several important derivatives such as the rolling moment due to sideslip, the yawing moment due to sideslip, the yawing moment due to aileron deflection, and the yawing moment due to rudder deflection.
Document ID
19970004545
Document Type
Technical Publication (TP)
Authors
Iliff, Kenneth W. (NASA Dryden Flight Research Center Edwards, CA United States)
Wang, Kon-Sheng Charles Wang (Sparta, Inc. Lancaster, CA United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Aircraft Stability and Control
Report/Patent Number
NAS 1.60:3664
H-2118
NASA-TP-3664
Funding Number(s)
PROJECT: RTOP 505-68-50
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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