Automated tow placement (ATP) and stitching of dry textile composite preforms followed by resin transfer molding (RTM) are being studied as cost effective manufacturing processes for obtaining damage tolerant fuselage and wing structures for transport aircraft. Data are presented to assess the damage tolerance of ATP and RTM fuselage elements with stitched-on stiffeners from compression tests of impacted three J-stiffened panels and from stiffener pull-off tests. Data are also presented to assess the damage tolerance of RTM wing elements which had stitched skin and stiffeners from impacted single stiffener and three blade stiffened compression tests and stiffener pull-off tests.
Test and Analysis Results for Composite Transport Fuselage and Wing Structures
1992
25 pages
Report
No indication
English
Aircraft , Composite Materials , Manufacturing, Planning, Processing & Control , Manufacturing Processes & Materials Handling , Aircraft construction materials , Composite structures , Compression tests , Fuselages , Impact tests , Resin transfer molding , Wings , Reinforcement (Structures) , Sewing , Stiffening , Cost effectiveness , Durability , Manufacturing , Preforms , Structural analysis , Tolerances (Mechanics) , Transport aircraft
Test results from large wing and fuselage panels
NTRS | 1993
|Test Results from Large Wing and Fuselage Panels
NTIS | 1993
|