Abstract: An assembly platform configured to manipulate at least one aircraft lower shell without deforming it with a view to assembly of an aircraft fuselage barrel is disclosed including at least one rectangular chassis, at least two frames having an adjustable trim with respect to the rectangular chassis, at least two setting systems intended to adjust the trim of the frame and at least two cradles fixed onto the frames and intended to receive the lower shell and to hold the lower shell in a desired form. The cradles of the assembly platform make it possible to prevent a deformation of the lower shell during the assembly of the fuselage barrel.

Abstract: A system for handling a side shell of an aircraft with a view to assembling a fuselage barrel of the aircraft and method for assembling a fuselage barrel of an aircraft are disclosed. The handling system includes at least two fixing devices per side shell. Each of the fixing devices is configured to be fixed to a longitudinal end of the side shell. Each of the fixing devices has a fixing part configured to be fixed on the side shell, a fixing support is configured to mount the fixing device movably on a holding device of an assembly platform, and an elastic element connecting the fixing part to the fixing support.

Abstract: An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.

Abstract: A referential positioning device configured to position relative to each other at least one cabin floor grid and one side shell of an aircraft in order to assemble a fuselage barrel of the aircraft is disclosed having at least one fixing support for fixing the referential positioning device to the top of an alignment post of an assembly platform, and a partially spherical support having a spherical surface (S) intended to receive the V-shaped surface of an end of an arm of a transport system for a cabin floor grid of an aircraft. The referential positioning device makes it possible to arrange the cabin floor grid precisely on the assembly platform with respect to the other elements of the fuselage barrel.

Abstract: Methods, systems, and computer readable media for generating a nondestructive inspection model are provided, where such methods, systems and computer readable media are particularly suitable for use with aerospace parts or components. The method can include occurring at a computing platform with a memory and a processor, and analyzing, by the processor, a design model file stored in the memory to determine one or more properties of a composite part, the design model file describing one or more physical characteristics of the composite part. The method also can include generating, by the processor, a non-destructive inspection model for the composite part based on the one or more properties of the composite part determined by analyzing the design model file.

Abstract: A computer aided method is provided for coupling non-destructive inspection data for a material or structure to an analysis tool. The method includes receiving a voxel data representation of a damaged area of the material or structure, and generating a finite element mesh based on the voxel data representation. The finite element mesh includes a plurality of nodes, each node corresponding to one or more voxels of the voxel data representation. The method further includes integrating damage information from the voxel data representation into the finite element mesh by applying at least one integration rule, the damage information indicating whether or not a given voxel has sustained damage. Damage information for areas of the finite element mesh that do not include damage information is interpolated by applying at least one interpolation rule. A finite element model including a finite element mesh having damage information associated therewith is output.

Abstract: Methods, systems, and computer readable media for generating a non-destructive inspection model for a composite part from a design model of the composite part are provided where such methods, systems and computer readable media are particularly suitable for use, for example and without limitation, with aerospace parts or components. The subject matter described herein can in one aspect include a method including steps occurring at a computing platform with a memory and a processor. The steps can include analyzing, by the processor, a design model file stored in the memory to determine one or more properties of a composite part, the design model file describing one or more physical characteristics of the composite part. The steps also can include generating, by the processor, a non-destructive inspection model for the composite part based on the one or more properties of the composite part determined by analyzing the design model file.

Abstract: A method to develop a plan to dismantle an airframe including: enhancing a digital mock-up model (DMU) of the airframe with data identifying hazardous materials in parts of the airframe; positioning at least one cut through the DMU of the airframe; based on the position of the cut, identifying intersections between the cut and fluid conduits identified in the DMU of the airframe; analyzing the identified intersections of the fluid conduits and data regarding hazardous waste fluids in the conduits of the airframe to identify the conduits having the hazardous waste which would be ruptured by the positioned cut, and generating a report of the identified conduits that would be ruptured and have the hazardous waste.

Abstract: In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Abstract: The invention relates to a process for making a reinforced curved metallic structure, made from a heavy-gauge or plate-gauge sheet of an aluminium alloy containing scandium. The process consists in combining forming (200) and machining (300) steps, the forming step (200) giving the structure curvature(s) and the machining step (300) producing a network of ribs for reinforcing the structure. A finishing step (400) can complete the preceding steps. Such a process makes it possible to obtain a monobloc metallic structure with good mechanical properties simply and quickly. Application to the manufacture of a reinforced curved metallic structure of an aircraft subassembly.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenization, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: The present invention relates to a method for producing Al—Zn—Cu—Mg type alloy plates comprising between 4 and 12% zinc, less than 4% magnesium and less than 4% copper, other elements?0.5% each, and the remainder aluminum. The method comprising hot rolling, solution heat-treatment, quenching, controlled stretching with permanent elongation greater than 0.5% and aging, wherein the elapsed time D between the end of quenching and the start of controlled stretching is less than 2 hours. The invention further relates to plates and products produced or capable of being produced using such methods.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.