INTEGRATED DESIGN METHOD FOR AIRPLANE NOSE HAVING SINGLE CURVED SURFACE WINDSHIELD

摘要

An integrated design method for an airplane nose having a single curved surface windshield, comprising the following steps: extracting a Catia forming parameter according to an airplane nose design constraint; establishing an airplane nose parameterized curved surface model, and generating a curved surface in the following order: generating an upper main curved surface (ICLJ) on one side of the airplane nose; cutting a windshield area on the upper main curved surface; firstly generating a main windshield curved surface (CERM) and then generating a lateral windshield curved surface (MRFD) in the windshield area; generating a transition curved surface (ACDB) between the main windshield curved surface and the remaining upper main curved surface (IABHJ) after the windshield area is cut; generating an upper front curved surface (EGHF) on one side of the airplane nose; and sequentially generating the remaining curved surfaces on one side of the airplane nose: a lower main curved surface (OPQN), a lower back curved surface (NOKJ), and a lower front curved surface (GPO); and symmetrically generating curved surfaces on the other side of the airplane nose. The upper main curved surface integrally generated with the cutting method ensures the curvature of the upper main curved surface to have high level continuity, thus facilitating integrated manufacturing; and ensures that the airplane nose has good aerodynamic characteristics and flow performance, thus reducing fuel consumption.