Using coupled fluid/structure interaction code to predict fighter aircraft wing response to AAA damage

Abstract

This chapter describes a proposed hybrid analytical/experimental technique for dynamic live-fire ground testing. In this technique, an explicit, time-integrated, nonlinear structural finite element code is coupled with a linear aerodynamic code. This is used to predict the time response of a flying aircraft wing during damage infliction. In live-fire testing of aircraft wings, quasistatic ground loading techniques do not account for changes in structural stiffness and mass that occur during damage infliction. The modeling that was performed in this study illustrated the complexity of different conditions that must be addressed before an assessment regarding survivability can be made. The decision process must first start with a list of known factors and conditions, such as aircraft selection, stores, fuel load, flight conditions, shot location, and threat selection. Modeling plays a key role in determining appropriate loading methods for the determination of aircraft survivability.