Abstract
Aircraft structural design requires lightweight design on the premise of meeting various performances. The number of hinge ribs in the aircraft trailing edge compartment is large, so it is very important to optimize the structure to achieve lightweight design. In this paper, the topology optimization algorithm is used to optimize the hinge ribs of the trailing edge cabin, and the secondary design is carried out according to the topology optimization results to achieve lightweight. The optimized rear edge cabin hinge rib can meet the requirements of strength, rigidity, process, manufacturing, etc., and the weight is greatly reduced compared with before optimization.
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