A study to estimate control surface deflections from flight data

Abstract

This chapter describes a modified output error method, the application of which on Automatic Landing Flight Experiment (ALFLEX) data supplied by National Aerospace Laboratory/ National Space Development Agency of Japan is reported at the ISIP200L. The performance for high frequency characteristics on the flight data is also verified. The result of analysis, lift coefficient CL, drag coefficient CD, three axes aerodynamic moment coefficients Cl,t, Cm,t, and Cn,t are also estimated fairly good as well as the altitude, the total velocity, and the euler angles. Yanagihara et al. proposed aerodynamic model for estimating ALFLEX aerodynamic characteristics. The model is available for estimating control surface deflections. This aerodynamic model is available for estimating control surface deflections by combining this model into the proposed method, and to estimate control surface deflections. As a result, the control surface deflection can be precisely measured.