| For shortenning the airplane design period,speeding the optimization progress of the airplane conceptual design. This research work aims at the structure layout optimization problem for stiffened shell structure of fuselage. Firstly,it proposes a kind of parametric method of building model based on quadratic curve to build fuselage model. Sencondly,it brings up a kind of method which simplify model based on the equivalent model. Lastly,it realizes the rapid layout optimization of stiffened shell structure. This research work mainly includes the following several aspects:1) Aiming at fuselage structure,it proposes a kind of method,which can descript the shape of fuselage by setting parameters. It combines the secondary development technology of Patran and develops a rapidly automaticly building model module. This module can use the setted parameters of fuselage shape and structure,and rapidly bulid the FEM model for computing.2) According to stiffened shell load and deformation’s relation,it sufficiently considers the load characteristic of stiffened and deducts stiffened stiffness and weight equivalent formula,then it use the equivalent formula to build equivalent model. It takes two typical buckling style of semimonocoque for example,and builds equivalent model and high precision model to carry out buckling analysis. From the analysis results of the two kinds of model we can see,the equivalent model has very high creditability.3) It takes the setted shape parameters of stiffened shell structure of fuselage for example. It uses the equivalent model to finish the structure layout optimization of global buckling. Then it uses the result of optimization to build high precision model for verifying precision. It takes the variable shape parameters of fuselage structure for example. It uses the parametric equivalent model to finish the structure layout optimization of global buckling. Lastly,we conclude the influence of the shape parameters on the structure weight. |
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