NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Rotorcraft Damage Tolerance Evaluated by Computational SimulationAn integrally stiffened graphite/epoxy composite rotorcraft structure is evaluated via computational simulation. A computer code that scales up constituent micromechanics level material properties to the structure level and accounts for all possible failure modes is used for the simulation of composite degradation under loading. Damage initiation, growth, accumulation, and propagation to fracture are included in the simulation. Design implications with regard to defect and damage tolerance of integrally stiffened composite structures are examined. A procedure is outlined regarding the use of this type of information for setting quality acceptance criteria, design allowables, damage tolerance, and retirement-for-cause criteria.
Document ID
20000032868
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chamis, Christos C.
(NASA Lewis Research Center Cleveland, OH United States)
Minnetyan, Levon
(Clarkson Univ. Potsdam, NY United States)
Abdi, Frank
(Alpha Star Corp. Long Beach, CA United States)
Date Acquired
August 19, 2013
Publication Date
February 1, 2000
Publication Information
Publication: Application of Damage Tolerance Principles for Improved Airworthiness of Rotorcraft
Subject Category
Computer Programming And Software
Distribution Limits
Public
Copyright
Other
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available