FIELD: aircraft engineering.
SUBSTANCE: invention relates to the field of aircraft construction and concerns the technology of assembling an aircraft wing, the parts of which are made of carbon fiber composite material and metals. In the process of modular assembly of the box of the wing console of the aircraft, the individual components (IC) of the box are assembled in parallel independently of each other in separate assembly modules, reference beams and reference frames at various places of the assembly shop. After the assembly is completed, the ICs of the box are placed in space relative to each other and the box is assembled of them. At the same time, the box ICs that are not connected to each other in a single structure and do not have sufficient rigidity to preserve the guaranteed spatial arrangement of interface elements are not unfixed and are not removed from the corresponding assembly modules of reference beams and reference frames.
EFFECT: ensuring the reliability and geometric accuracy of the design of the wing console box, excluding the appearance of deformations of the components of the design of the wing console box during assembly, to ensuring minimum labor intensity and a given assembly cycle of the wing console caisson.
18 cl, 16 dwg
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Authors
Dates
2022-06-23—Published
2021-09-17—Filed