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Abstract
The paper describes the methodology of contact problem solving that is used for simulation of aircraft assembly process. The dimension of the problem is reduced after eliminating the unknowns outside the contact zone and the initial problem transforms into the problem of quadratic programming with linear constraints. The special computer code ASRP (Assembly Simulation of Riveting Process) was developed on the base of presented methodology. Now this code is utilized by Airbus. Some results of application of developed code are given in this paper.
Highlights
The components of the airframe are produced in different plants and joined together in Final Assembly Line (FAL) (Figure )
Reduced rigidity matrix is computed once for considered junction during data preparation stage. This matrix is stored and can be used for series of computations because changes of initial gap or applied loads do not affect KC. This computational decomposition is relevant for simulation of riveting process as it is aimed at solving variety of problems with different fastener configurations and different relative positions of joined parts
Most of the research work devoted to simulation of riveting process is done for the case when the contact problem is solved only in the neighborhood of one or several fasteners, i.e. local modeling is performed
Summary
The components of the airframe (fuselage sections, wings etc.) are produced in different plants and joined together in Final Assembly Line (FAL) (Figure ). The system ( ), ( ) is supplemented with following restriction to avoid interpenetration of the panels: (A · U)j ≤ G(xj), xj ∈ Ch. Here A is linear operator determining the relative displacement of parts in normal direction, G(xj) is a function of normal initial gap in the node xj; Ch is junction area that is the set of nodes that can come into contact. We need to compute only normal displacements of nodes in junction area.
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