Aeroelastic Analysis Of Plate And Shell Structures In Subsonic Airflow

In order to take advantage of the aeroelastic characteristic of the plate and shellstructures, the aeroelasticity stability of open cylindrical shells and trianglesandwich plates is studied in this work.According to the Donnell theory, the aeroelastic equation of open cylindricalshell with four edges simply supported is established. In this model, one surface issubjected to the subsonic airflow. Based on the Galerkin discretization method andthe assumed-mode method, the physical coordinates can be transformed to modalcoordinates. Then the partial differential equations can be discretized to ordinarydifferential ones. The aeroelastic characteristic of open cylindrical shell is analyzedby solving its natural frequencies.The open cylindrical shell model with four edges simply supported can beestablished by using the finite element analysis software ANSYS. The responses ofthe structure in the time domain can be calculated in subsonic airflow (at the criticalinstability speed calculated theoretically) by using the CFD/CSD two-wayfluid-structure coupling method. The responses obtained by the CFD/CSD arecompared with those calculated by the theoretical method. It can be seen that thetwo results are agree well. Considering the cantilever open cylindrical shell model,the responses of the non-ribbed structures in the time domain can be calculated andcompared with those of the ribbed ones. Three-dimensional open cylindrical shellswith simply supported and clamped boundary conditions are considered. Theaeroelasticity stability influences of different boundary conditions on the shellstructure are analyzed.The responses of the points on the free edge of cantilever triangle sandwichplate are calculated. Meanwhile, the responses of a cantilever plate which has thesame length, width and volume with the cantilever triangle sandwich plate wasdiscussed and the results are compared with each other. The results present that thetriangle sandwich plate has better aeroelasticity stability characteristics. Then theinfluences of different boundary conditions and material parameters on theaeroelastic characteristics are studied.In this work, the results calculated by the CFD/CSD software and thetheoretical method get mutual authentication. The aeroelasticity stabilitycharacteristics are analyzed by this software, which has widened the applicationfields of the CFD/CSD software. The studies in this work are expected helpful forthe active aeroelastic design of subsonic plate and shell structures. Theoretical exploration of the flutter problem of plates and shells is discussed by theinvestigation of the different material and structural parameters.