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Aeroelastic response and blade loads of a composite rotor in forward flightThe aeroelastic response, blade and hub loads, and shaft-fixed aeroelastic stability is investigated for a helicopter with elastically tailored composite rotor blades. A new finite element based structural analysis including nonclassical effects such as transverse shear, torsion related warping and inplane elasticity is integrated with the University of Maryland Advanced Rotorcraft Code. The structural dynamics analysis is correlated against both experimental data and detailed finite element results. Correlation of rotating natural frequencies of coupled composite box-beams is generally within 5-10 percent. The analysis is applied to a soft-inplane hingeless rotor helicopter in free flight propulsive trim. For example, lag mode damping can be increased 300 percent over a range of thrust conditions and forward speeds. The influence of unsteady aerodynamics on the blade response and vibratory hub loads is also investigated. The magnitude and phase of the flap response is substantially altered by the unsteady aerodynamic effects. Vibratory hub loads increase up to 30 percent due to unsteady aerodynamic effects.
Document ID
19920051856
Document Type
Conference Paper
Authors
Smith, Edward C. (NASA Langley Research Center Hampton, VA, United States)
Chopra, Inderjit (Maryland, University College Park, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
AIAA PAPER 92-2566
Meeting Information
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference(Dallas, TX)
Funding Number(s)
CONTRACT_GRANT: DAAL03-88-C-0002
CONTRACT_GRANT: NAG1-1253
Distribution Limits
Public
Copyright
Other