Secondary Development Of Integral Panel Developing Software

Integral panel is a kind of integrated sheet metal parts made from frame elements andskin in traditional aircraft structure. Because of the advantage of high intensity, low weightand good air-tightness, integral panel is widely applied in main stress area instead of rivetingpanel or thin skin integral panel as the typical structure unit of modern aircraft. Moreover,with the increasing demand of the aerospace vehicle, it has become a trend to employmajority of integral panels which is optimized designed and have good performance.Therefore, the level of integral panel manufacturing directly affects the performance ofaircraft. It is badly necessary to carry out research on the accurate and efficientintegral-panel-forming technology.The thesis is to further study the blank development project of panel parts in a aircraftmanufacturing company. In the developing process, according to deforming characteristic andexisting documents, some related parameters of the strain neutral layer after peen forming andthe function expressions are obtained. Through the optimizing of geometric simulationalgorithm, taking the selected surface as the benchmark, integral panel parts are meshed.The top points are selected and their coordinates are determined successively. By means ofspline fitting and lines joining together, boundary lines of panel outer contour are described.In Windows XP system, CATIA V5is combined with Visual Basic to conduct secondarydevelopment of integral panel developing software. The purpose is to improve the developingprecision of blank shape and reduce the production cost.The software is applied in the project of integral panel developing in laboratory and hasreached expected purpose. Meanwhile, secondary development of software lays foundationfor further study of the development of integral panel.