Reference: Sobieski, I.P., Kroo, I.M., 2000, “Collaborative optimization Using response Surface Estimation”, AIAA Journal, Vol 38, No 10, pp 1931-1938
Description: The problem is to design a 454-kg (1000 lb), propeller-powered, tailless aircraft for maximum range. The planform, gross weight, and engine performance parameters are fixed, whereas jig twist, spanwise skin thickness, elevon deflection angle, maneuver angle of attack, and the mass of wing tip and wing root ballasts are free design variables. The optimizer uses these free design variables to meet trim constraints during cruise and a 4-g maneuver. It also adjusts these variables to satisfy the structural stress constraints while maximizing the computed range.
Design Structure Matrix (DSM):
Unmanned Aerial Vehicle (UAV) Fixed parameters: