Type of Document Master's Thesis Author Pilkington, Lawrence O. Author's Email Address firstname.lastname@example.org URN etd-08052004-220724 Title Impact Response and Failure of a Textile Composite Fuselage Frame Degree Master of Science Department Aerospace and Ocean Engineering Advisory Committee
Advisor Name Title Johnson, Eric R. Committee Chair Boitnott, Richard L. Committee Member Case, Scott W. Committee Member Keywords
- textile composite
- impact response
- dynamic response
Date of Defense 2004-07-30 Availability unrestricted AbstractImpact tests are performed on two circular circumferential frame segments using a
drop tower apparatus. These frames have a nominal radius of 120 inches, a forty-eight -
degree included angle, a thin-walled cross section in the shape of the letter J, and are
typical of the transverse fuselage frames found in a large transport aircraft. The material
is a 2D triaxial braided composite of carbon fiber yarns. Impact speeds of the 91.6 lb drop
mass are 23.7 ft/s or less. This speed range is the order of the vertical speed considered in
a survivable crash on a runway. Transient response characteristics and failure sequence
are compared to nominally identical frames tested quasi-statically in a previous study.
The peak load at the first major failure event and the corresponding displacement are
larger in impact tests than in the quasi-static tests. However, the fracture sequence in the
vicinity of the impact location is similar to what was observed in the static tests.
Preliminary transient simulations of the frame impact tests using the LSDyna software
were also performed. Using the available composite material failure criteria in the
software, reasonable correlation was achieved between the simulation and the tests on the
load-displacement plot. The computed strains distributions did not compare as well to the
measured strains at the first major failure event.
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