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Mixed-integer sequential approximate optimization method for stiffened cylindrical shells in large launch vehicles
王志祥 雷勇军 张大鹏 崔辉如
Acta Aeronautica et Astronautica Sinica . 0, (): 0 -0 .  DOI: 10.7527/S1000-6893.2024.31089

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Total visits: 6658907 Today visits: 1341All copyright © editorial office of Chinese Journal of Aeronautics

All copyright © editorial office of Chinese Journal of Aeronautics

Total visits: 6658907 Today visits: 1341