Optimum Aeroelastic Characteristics for Composite Supermaneuverable Aircraft.
Abstract
In this preliminary investigation of an aeroelastically-induced constrained warping phenomenon for a composite (supermaneuverable type) aircraft wing, the wing is analytically modelled as a straight flat laminated plate using various forms of highly simplified aerodynamic loads. The free vibrations and (stability importance aspects are examined to obtain physical insights and determine their importance and/or design implications. An affine transformation concept and a non-dimensionalization scheme were used and an evolution of effective warping parameters with which to study this phenomenon was performed. The virtual work theorem and variational principles were used to derive the equations of motion based on the assumed wing displacements. Closed form solutions to the uncoupled versions of these equations were examined with the following results: 1) incorrect modelling of the warping phenomenon can leads to errors in excess of 80% for the analytically predicted aeroelastic characteristics of composite aircraft wings; 2) accurate modelling of the warping phenomenon is particularly important for wings with mass coupling or elastic coupling (e.g., wings aeroelastically tailored using elastic coupling) and for higher vibration modes; 3) neglect of the warping constraint can result in either under- or overpredicted analytical results and lead to incorrect identification of aeroelastic divergence modes. The existence of closed-form free vibrations solutions for composite wings with elastic coupling and constraint of warping was established.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 31, 1986
- Accession Number
- ADA174785
Entities
People
- Gabriel A. Oyibo
- Terrence A. Weisshaar