Uniformed Aeroelastic ROM Realization Across Flight Parameter Space for Dynamic Flight Simulation

ABSTRACT: The proposed effort will focus on the development of the parameterized Navier-Stokes (NS) based ROM for the Dynamic Flight Simulation (DFS) framework. The F/A-18 Active Aeroelastic Wing (AAW) aircraft will be used as the test case to investigate and validate the proposed methods.The background flow solutions under various Mach number and angle-of-attack grid points are first obtained by the FUN3D NS solver, thereafter the generalized aerodynamic forces around such nonlinear background flow at various frequencies are obtained by ZULUS using the linearized Euler solver. The computed aerodynamic solutions related to rigid-body modes will be corrected by flight-test or wind-tunnel derived data using the Lagrange multiplier technique. The three methods of achieving the parameterized ROM will be evaluated and compared to one another and conclusions and recommendations will be drawn upon based on the results. The Phase I effort will pave the way for the final integration of ROMs into the DFS framework for flight simulation and prediction.; BENEFIT: The DFS system, once developed, can be utilized for a number of purposes, including control law development, maneuvering flight simulations, flutter simulations and testing, flight loads testing, and handling quality assessments.A uniformed aeroelastic Reduced Order Modeling (ROM) technique across various flight conditions serves as the key component of the DFS framework which can rapidly solve the flight dynamic equations of motion with flexible effects in real-time.This technology has the potential of providing more accurate dynamic flight simulations for better situational awareness, system understanding for aircraft systems under test as well as being a useful tool for training engineers and test pilots.