유도무기의 공력형상 설계를 위한 최적화 기법

Abstract

In this study an optimization technique for aerodynamic configuration design of guided missile systems is developed. A parameter optimization problem is formulated, for which the locations and profiles of the wing and control surfaces are treated as the parameters to be optimized for the minimum wing/tail or wing/canard area. Constraints on the angle of attack, the deflection angle of control surface, the hinge moment of actuator servo, and the time constant of the acceleration control loop are also considered. Computer program R1307, based on NACA Report 1307, is used to predict aerodynamic coefficients and the classical root locus method is adopted for control design. An aerodynamic configuration optimization program(OMICON) based on the augmented Lagrangian method is finally developed and its validity is successfully tested by several applications to the aerodynamic design of various types of air-to-air missile.