To solve the test problems caused by the statically fixed connection and high pillar structure of large amphibious aircraft landing gear
based on the stiffness equivalence theory
two models of landing gear connected with fuselage and connected with test device were analy-ed by numerical simulation method. By optimi-ing the structural form
si-e and thickness of the test device
the displacement of landing gear-device connection model in the main direction of deformation was simulated according to that of the landing gear-fuselage connection model. Based on the numerical simulation of mechanical boundary condition
the displacement at the center point of the main landing gear shaft under the maximum load was calculated
and the installation position of the loading point was adjusted in advance to ensure the loading accuracy under the maximum load. The results showed that under the maximum resilience load condition(the load ratio of inner wheel to outer wheel is 6:4)for the tail subsid
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