Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology

Paper #:
  • 1999-01-5640

Published:
  • 1999-10-19
Citation:
Zink, P., Mavris, D., Flick, P., and Love, M., "Development of Wing Structural Weight Equation for Active Aeroelastic Wing Technology," SAE Technical Paper 1999-01-5640, 1999, https://doi.org/10.4271/1999-01-5640.
Pages:
13
Abstract:
A multidisciplinary design study considering the impact of Active Aeroelastic Wing (AAW) technology on the structural wing weight of a lightweight fighter concept is presented. The study incorporates multidisciplinary design optimization (MDO) and response surface methods to characterize wing weight as a function of wing geometry. The study involves the sizing of the wing box skins of several fighter configurations to minimum weight subject to static aeroelastic requirements. In addition, the MDO problem makes use of a new capability, trim optimization for redundant control surfaces, to accurately model AAW technology. The response surface methodology incorporates design of experiments, least squares regression, and makes use of the parametric definition of a structural finite element model and aerodynamic model to build response surface equations of wing weight as a function of wing geometric parameters for both AAW technology and conventional control technology. The goal for this design study is to demonstrate a process by which some of the benefits associated with AAW technology can be quantified over the wing geometry design space, so that future conceptual designers may make the best use of the technology.
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