Abstract
This article introduces a design scheme for a distributed load follow-up loading system for large passenger aircraft flaps. The follow-up loading system includes tape lever components, follow-up pulley and drive components, force control actuators, fixed pulley and cable components, and support structures. At the same time, a loading control system was also designed. The dynamic loading system can simulate the deformation of flaps under distributed aerodynamic loads during the entire retraction and extension process, greatly improving the fidelity of the test environment and comprehensively assessing the interference between flaps and surrounding structures under all operating conditions.
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