Title page for ETD etd-08052004-220724

Type of Document Master's Thesis
Author Pilkington, Lawrence O.
Author's Email Address lpilking@vt.edu
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
  • textile composite
  • impact response
  • dynamic response
  • fuselage
Date of Defense 2004-07-30
Availability unrestricted
Impact 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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