This paper describes progress on a proposed hybrid analytical/experimental technique for dynamic live-fire ground testing which may remedy the shortcomings of current static ground testing methodologies. In this technique an explicit, time-integrated, non-linear structural finite element code is coupled with a linear aerodynamic code and used to predict the time response of a flying aircraft wing during damage infliction. The subsequent concept designs of the dynamic ground test are to be based on the predicted structural response. A representative fighter aircraft model is used. Model validation results (both static and dynamic) are presented. Damage representative of a current threat is instantaneously inflicted on the model. Results of wing response (displacements and load redistribution) in the time domain are presented.