Z. Wang , D. Sarhaddi , P.C. Chen
DOI Number: N/A
Conference number: IFASD-2019-102
In this paper, a discrete time state-space aeroservoelastic modeling technique using FUN3D is discussed. A subspace realization algorithm is utilized to identify the individual aerodynamic systems, i.e., due to the structural deformations (modal coordinates), control surface deflections and/or discrete gust, respectively. This subspace realization algorithm has been implemented in our flight test data processing application called ZAMS+ within IADS environment and proved to be an efficient and robust system identification tool in real time. The dataset needed for the aerodynamic system identifications are obtained by a wrapper program, called OVERFUN, driving the underlying FUN3D solver. The routines of the subspace realization algorithm are incorporated within the OVERFUN program to identify the individual aerodynamic sub-systems, and thereafter they are coupled with the structural equation of motion represented in modal space and the actuator model to yield the conventional state-space forms of aeroelastic model and plant model. The Benchmark Active Control Technology (BACT) wing is studied as the example case to demonstrate the presented methodology. The obtained state-space models are used to compute the frequency response of an accelerometer with respect to the trailing edge flap and the upper spoiler, and the results are compared to the test data and solutions by others.