Stiffness, thermal expansion, and thermal bending formulation of stiffened, fiber-reinforced composite panels
A method is presented for formulating stiffness terms and thermal coefficients of stiffened, fiber-reinforced composite panels. The method is robust enough to handle panels with general cross sectional shapes, including those which are unsymmetric and/or unbalanced. Nonlinear, temperature and load dependent constitutive material data of each laminate are used to 'build-up' the stiffened panel membrane, bending, and membrane-bending coupling stiffness terms and thermal coefficients. New thermal coefficients are introduced to quantify panel response from through-the-thickness temperature gradients. A technique of implementing this capability with a single plane of shell finite elements using the MSC/NASTRAN analysis program (FEA) is revealed that provides accurate solutions of entire airframes or engines with coarsely meshed models. An example of a composite, hat-stiffened panel is included to demonstrate errors that occur when an unsymmetric panel is symmetrically formulated as traditionally done. The erroneous results and the correct ones produced from this method are compared to analysis from discretely meshed three-dimensional FEA. 14 refs.
- OSTI ID:
- 6300249
- Report Number(s):
- AIAA-Paper-93-1569; CONF-9304186-; CNN: NAS1-19000
- Resource Relation:
- Conference: 34. American Institute of Aeronautics and Astronautics/American Society of Mechanical Engineers (AIAA/ASME) adaptive structures conference, La Jolla, CA (United States), 19-22 Apr 1993; Other Information: 2279-2290
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
COMPOSITE MATERIALS
THERMAL STRESSES
FINITE ELEMENT METHOD
MESH GENERATION
AERODYNAMIC HEATING
BENDING
N CODES
REINFORCED MATERIALS
THERMAL EXPANSION
CALCULATION METHODS
COMPUTER CODES
DEFORMATION
EXPANSION
HEATING
MATERIALS
NUMERICAL SOLUTION
STRESSES
360603* - Materials- Properties