Abstract
In aircraft assembly, frames are usually used as the skeleton shape benchmarks of a fuselage panel to locate other parts accurately, thereby coordinating the relative position relationships between each part. In order to guarantee the assembly quality, a methodology for analyzing the effect of positioning errors of frames on fuselage panel assembly deformation is proposed. A finite element model of the fuselage panel is established first and then a mathematical model for representing the assembly deformation is derived. To contain more assembly deformation information, the optimal measurement point placement method is adopted to extract a set of finite element nodes as the measurement point locations from a large candidate set. Meanwhile, the mathematical relationship between the position errors of measurement points and the positioning errors of frames is also determined, which is then combined with the Monte Carlo simulation and the grey relational analysis to quantitatively analyze the impacts of the positioning error(s) generated by single or multiple frames on fuselage panel assembly deformation.
Highlights
In aircraft assembly, a fuselage panel is generally assembled by numerous parts according to the design criteria and technical requirements, and factors such as the environmental temperature, the non-nominal shape of parts, the non-nominal location, and deteriorated condition of tooling can cause the fuselage panel assembly deformation
In the large aircraft assembly process, one of the most important preconditions to guarantee the assembly accuracy is to control the fuselage panel assembly deformation, while in the subassembly processes, frames are usually used as the skeleton shape benchmarks of the fuselage panel to locate other parts accurately, so their positioning errors are the primary factors that affect the fuselage panel assembly deformation, and the impacts of the positioning error(s) generated by single or multiple frames on the overall assembly deformation of the fuselage panel are quantitatively analyzed in this article
Since the fuselage panel assembly deformation is usually represented by the position errors of measurement points, the mathematical relationship between the position errors of measurement points and the positioning errors of frames is established
Summary
A fuselage panel is generally assembled by numerous parts according to the design criteria and technical requirements, and factors such as the environmental temperature, the non-nominal shape of parts, the non-nominal location, and deteriorated condition of tooling can cause the fuselage panel assembly deformation. Keywords Frame, fuselage panel, assembly deformation, optimal placement, measurement point, positioning error
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