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Problem Details
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Classification: II B 1 |
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Reference: Sobieski, I.P., Kroo, I.M., 2000, “Collaborative optimization Using response Surface Estimation”, AIAA Journal, Vol 38, No 10, pp 1931-1938 |
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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. |
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Design Structure Matrix (DSM): |
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Analysis: |
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Aerodynamic Analysis
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Structural Analysis |
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Performance_Analysis |
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Unmanned Aerial Vehicle (UAV) Fixed parameters: |
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Behavior Variables: |
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Design Variables: |
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System Optimization: |
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