Fig. 1. AIM-9L(Air-to-Air Missile)[2]
Fig. 2. AIM-9X(Air-to-Air Missile)[3]
Fig. 3. Model configuration
Fig. 4. Design space of faring
Fig. 5. Design variable and objective function area
Fig. 6. Valid space of variables A, B1, B2, C1, C2 at CASE 1,2
Fig. 8. Latin hypercube sampling for CASE 1
Fig. 9 Latin hypercube sampling for CASE 2
Fig. 10. Latin hypercube sampling for CASE 3
Fig. 11. Surface mesh configuration
Fig. 12. Grid dependency test
Fig. 13. Pressure contour of hanger
Fig. 14. Sensitivity of CASE 1,2,3
Fig. 15. Meta model of A vs. B2 vs. Cd (CASE 1)
Fig. 16. Meta model of A vs. B1 vs. Cd (CASE 2)
Fig. 19. Optimized hanger geometries
Fig. 7. Valid space of variables A, B1, C1 at CASE 3
Fig. 17. Meta model of A vs. B1 vs. Cd (CASE 3)
Fig. 18 Meta model of A vs. B2 vs. Cd (CASE 3)
Table 1. Optimization results
Table 2. Optimization results for mass limit
Table 3. Validation of results
참고문헌
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