Method and system for assembly of a plurality of panels
OwnerFranck Darras, Yannick Wattierinventors
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Abstract
The invention relates to a system for assembling a plurality of panels of an aircraft fuselage, said system comprising at least one anvil body, at least one first panel and one second panel, and movement means mounted on the said anvil body, the said movement means being arranged to move the first panel in relation to the second panel between a first machining position in which one edge of the first panel and one edge of the second panel are spaced a machining distance apart so as to allow a machining tool to pass between the said edges in order to machine them simultaneously and a second welding position in which the said edge of the first panel and the said edge of the second panel are adjacent and resting on the said anvil body.
Claims21
-15. (canceled)
A system for assembling a plurality of panels of an aircraft fuselage, the plurality of panels comprising at least one first panel and at least one seond panel, the system comprising:
- at least one anvil body comprising a support surface supporting the plurality of panels;
- at least one anvil rail movably mounted in a cavity of the at least one anvil body and configured to move between a top position in which an upper surface of the at least one anvil rail extends into an extension of the support surface and a bottom position in which a workspace is created between the upper surface of the at least one anvil rail and the support surface so as to enable the passage of a tool;
- the at least one anvil rail comprising a structural beam extending along the at least one anvil body and a guide bar for the tool;
- and
- movement means mounted on the at least one anvil body, the movement means being arranged to move the at least one first panel in relation to the at least one second panel between a first machining position in which an edge of the at least one first panel and an edge of the at least one second panel are spaced a machining distance apart so as to allow the tool to pass between the edges of the at least one first panel and the at least one second panel in order to machine them simultaneously, and a second welding position in which the edge of the at least one first panel and the edge of the at least one second panel are adjacent and resting on the at least one anvil body.
A method for assembling a plurality of panels of an aircraft fuselage, said method comprising:
- positioning a joining edge of a first panel and a joining edge of a second panel opposite to each other and separated by a machining distance;
- machining the joining edge of the first panel and the joining edge of the second panel simultaneously by means of a machining tool passing beneath the first panel and the second panel between the joining edge of the first panel and the joining edge of the second panel;
- positioning the joining edge of first panel and the joining edge of the second panel edge together in a welding position;
- and
- welding the joining edge of the first panel to the joining edge of the second panel.
Dependencies are inferred from the claim text.