CFRTP fuselage skin panel
KHI has developed a methos called " local co-consolidation" for fabricating complex skin panels using thermoplastic composites.
This method combines temperature distribution in molds and progressive feeding of movable lower mold against a fixed upper mold, along with simultaneous welding/integration of stringers during skin consolidation.
This method combines temperature distribution in molds and progressive feeding of movable lower mold against a fixed upper mold, along with simultaneous welding/integration of stringers during skin consolidation.
Why and Whom
Current composite skin/stringer panels in commercial aircraft fuselage structure is made from thermoset composite cured in autoclaves.
KHI developed an OoA (Out-of-Autoclave) method - " local co-consolidation" suitable for thermoplastic composite (CFRTP).
KHI developed an OoA (Out-of-Autoclave) method - " local co-consolidation" suitable for thermoplastic composite (CFRTP).
Partners
JAMCO Corporation | Toray Industries, Inc. | SURUGA ENGINEERING ,INC. | Kawasaki Hydromechanics Corp. | SUNWA TRADING CORPORATION
Key Benefits
Realize fabrication of ling CFTTP stiffened panel in shorter flow time than autoclave process.
Realize a process that does not require a large press to apply pressure to the entire part shape simultaneously.
Realize one-process joining of multiple stringers to skin with stable quality.
Realize a process that does not require a large press to apply pressure to the entire part shape simultaneously.
Realize one-process joining of multiple stringers to skin with stable quality.
Awards
Award Finalist Aerospace Process