The primary objective of the present SBIR proposal is to develop a new design methodology and applying it to demonstrate the feasibility of rendering minimized missile fin hinge moment covering all possible critical flight conditions while satisfying maneuverability requirements by passive or active profile control means. The final goal is aimed at the achievability of a significant reduction in the feasible minimum hinge moment such that a sizeable payoff in cost and performance of the total missile system can be ascertained. We propose a global design strategy (consisting of three design loops) which adopts the techniques of aeroelastic/aeroservoelastic tailoring on a selected composite fin structure utilizing a multidiscilplinary design optimization (MDO) software.

Served as the inner loop of the design strategy, the MDO software is a well proven technology called ASTROS* (an enhancement of the Automated STRuctural Optimization System), currently under further development at ZONA Technology. The outer loop is the parametric study, which governs the shape and hinge moment study which imposes an active constraint to ASTROS* in each design cycle.