Methodology for aero-structural analysis of a missile attached to a maneuvering aircraft

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Methodology for aero-structural analysis of a missile attached to a maneuvering aircraft

Dillenius, M.F. / Lesieutre, D.J. / Perkins, S.C. jun. / Jeter, E.L. / Schulz, J.C.

A description is given of a unique aero-structural capability aimed at estimating the design (inertial plus aerodynamic) loads acting on a missile attached to the wing tip (or other location) of an aircraft. This paper focuses on the aerodynamic contributions calculated by prediction methods designed to compute efficiently the aerodynamic force distributions on the body and the fins of a missile for a multitude of cases. In this process, the missile is immersed in the nonuniform flow field induced by the aircraft as calculated by modified versions of the NEAR store separation programs. Summarized descriptions of the aerodynamic methodology and the structural model are given. Comparisons with aerodynamic data for missiles in free stream are described. Calculative examples are provided which demonstrate the severe effects of the nonuniform aircraft-induced flow on the tail fin aerodynamic loads. Based on preliminary comparisons of calculated tail fin loads with flight test data, the present aerodynamic methods predict the same trends indicated by the tests.