Geometric parametric modeling method and device for aircraft fuselage frame structure

Abstract

The invention belongs to the technical field of geometric modeling, and particularly relates to a geometric parametric modeling method and device for an aircraft fuselage frame structure. The method comprises the steps: intercepting a curve on the inner profile geometry and the outer profile geometry of a fuselage frame according to a frame position plane, and obtaining a first inner profile geometry curve and a first outer profile geometry curve; constructing a first characteristic equation of the inner shape surface and the outer shape surface, intercepting discrete point coordinates on thefirst inner shape surface geometric curve and the first outer shape surface geometric curve, and performing curve reconstruction according to the first characteristic equation to obtain a second innershape surface geometric curve and a second outer shape surface geometric curve; constructing a coefficient control equation, respectively adjusting the second inner surface geometric curve and the second outer surface geometric curve, and obtaining a contour curve of the fuselage frame according to the two adjusted curves; and constructing a second characteristic equation, intercepting nodes on the contour curve of the fuselage frame according to the second characteristic equation, and taking the nodes as positions for arranging frame reinforcing ribs.

Description

technical field [0001] The present application belongs to the technical field of geometric modeling, and in particular relates to a geometric parametric modeling method and device for an aircraft fuselage frame structure. Background technique [0002] Due to the high performance requirements of military aircraft on aerodynamics, stealth, and propulsion, the geometry of the external aerodynamic surface and the internal air intake surface is complex, which makes the geometry of the internal supporting fuselage frame structure difficult to regularize. [0003] The traditional method needs to build a geometric model by manually taking points and building a line: Step 1: Intercept the plane of the frame position on the inside and outside of the plane to obtain two curves; Step 2: Manually adjust the points in the curve Breakpoints make each curve closed; Step 3: Use two closed curves in the plane to establish the outline geometric model of the frame structure; Step 4: Take points...

AI Technical Summary

Problems solved by technology

When using the traditional method to intercept the curve geometrically, due to the accuracy of the model, it may be necessary to manually connect the curve to close it; after the adjustment of the inner and outer surfaces of the aircraft, it needs to be manually intercepted again, and all work is restarted; the traditional spline point adjustment is used There are too many variables to be adjusted in this way, and it is difficult to meet the specific shape and surface requirements of the aircraft; manual modeling cannot be associated with subsequent finite element modeling analysis, which greatly reduces the efficiency of structural design analysis

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