Accession Number:
ADA254285
Title:
Nonlinear Aeroelasticity of Composite Structures
Descriptive Note:
Final rept. 1 Jul 1986-31 Jan 1991
Corporate Author:
MASSACHUSETTS INST OF TECH CAMBRIDGE TECHNOLOGY LAB FOR ADVANCED COMPOSITES
Personal Author(s):
Report Date:
1991-10-01
Pagination or Media Count:
24.0
Abstract:
The nonlinear, stalled, aeroelastic behavior of rectangular, graphiteepoxy, cantilevered plates with varying amounts of bending-torsion stiffness coupling and with NACA 0012 Styrofoam airfoil shapes is investigated for low Reynolds number flow 200,000. A general Rayleigh-Ritz formulation is used to calculate point load static deflections, and nonlinear static vibration frequencies and mode shapes for varying tip deflections. Nonlinear lift and moment aerodynamics are used in the context of the Rayleigh-Ritz formulation to calculate static airload deflections. The nonlinear, stalled ONERA model using non-constant coefficients - initially developed by Tran and Petot - is reformulated into a harmonic balance form and compared against a time-marching Runge-Kutta scheme. Low angle-of-attack, linear flutter calculations are done by applying Fourier analysis to extract the harmonic balance method and a Newton- Raphson solver to the resulting nonlinear. Rayleigh-Ritz aeroelastic formulation.
Descriptors:
- *STALLING
- *FLUTTER
- *GRAPHITE EPOXY COMPOSITES
- *COMPOSITE WINGS
- FREQUENCY
- ANGLES
- VIBRATION
- MODELS
- LAMINATES
- STIFFNESS
- FORMULATIONS
- ATTACK
- SHAPE
- HARMONICS
- DEFLECTION
- COMPOSITE STRUCTURES
- MOMENTS
- GRAPHITE
- ANGLE OF ATTACK
- BENDING
- AIRFOILS
- LOW ANGLES
- COUPLINGS
- AERODYNAMICS
- TORSION
- FOURIER ANALYSIS
- REYNOLDS NUMBER
- STATICS
- LIFT
- NUMBERS
- NONLINEAR ANALYSIS
- FLOW
- BEHAVIOR
- BALANCE
- CONSTANTS
- COEFFICIENTS
- PLATES
- TIME
- AEROELASTICITY
- THREE DIMENSIONAL
Subject Categories:
- Aerodynamics
- Aircraft
- Laminates and Composite Materials