Equivalent plate analysis of aircraft wing box structures with general planform geometry

Giles, G. L.

doi:10.2514/6.1986-940

Cited by 18 publications

(14 citation statements)

References 3 publications

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“…Aerodynamic computations are performed using an in-house developed code which is based on the Vortex Lattice Method (VLM). Structural analysis is carried out using either the Equivalent Plate Method (EPM) 13 or the Finite Element Method (FEM). These medium/high fidelity methods are integrated with WingOpt.…”

Section: B Aerodynamic and Structural Analysismentioning

confidence: 99%

MDO Architectures for Coupled Aerodynamic and Structural Optimization of a Flexible Wing

Ajmera¹,

Mujumdar²,

Sudhakar³

2004

45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics &Amp;amp; Materials Conference

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This paper deals with the formulation and testing of different variants of some existing single level generic architectures, specifically for coupled aerodynamic and structural optimization of wing, focused on static aeroelasticity. The design problem involves simultaneous optimization of the wing aerodynamic plan-form and section variables along with its structural sizing variables for minimum load carrying structural weight subjected to structural, aerodynamic, performance and geometric constraints. The associated Multi-Disciplinary Analysis (MDA) problem essentially involves coupled solution of the state equations of the aerodynamic and the structural disciplines by nested iterations. The Multidisciplinary Design Optimization (MDO) problem is posed as a three discipline coupled problem, with the trim (maneuver) process required to define structural design loads considered as a separate discipline. This leads to a number of interesting reformulations of the MDO problem based on (i) the reordering of the nested iterations and (ii) decoupling the nested iterations at different levels through the introduction of pseudo design variables and pseudo constraints. Formulation of six variants of the MDO problem and their implementation is presented along with computational issues related to convergence of the iterative processes. A special constraint based on a divergence control parameter has been formulated to handle instability. Optimization results from the different formulations are compared to study their computational performance and bring out the impact of aeroelasticity on the design of the flexible wing.

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Section: B Aerodynamic and Structural Analysismentioning

confidence: 99%

MDO Architectures for Coupled Aerodynamic and Structural Optimization of a Flexible Wing

Ajmera¹,

Mujumdar²,

Sudhakar³

2004

45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics &Amp;amp; Materials Conference

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“…The strain and kinetic energies contained in a finite-element of equivalent continuum beam-rod can be expressed by< 29 .. (12) where EI is the bending rigidity, GA the transverse shear rigidity, and GJ the torsional rigidity of the continuum element. By substituting Equations (6) and (11) into Equations (12), the energy expressions can be rewritten in the form x'…”

Section: Energy Expressions For a Finite-element Of Continuum Beam-romentioning

confidence: 99%

Equivalent dynamic beam–rod models of aircraft wing structures

Lee¹

1995

Aeronaut. j.

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The equivalent continuum beam-rod model of an aircraft wing structure with composite laminated skins has been developed based on the concept of energy equivalence. The equivalent structural properties of the continuum beam-rod model are obtained by directly comparing the reduced stiffness and mass matrices for a typical segment of aircraft wing with those for a finite element of continuum beam-rod model. The finite element stiffness and mass matrices are condensed through the well known finite element formulation procedure to be used in calculating the reduced stiffness and mass matrices for the aircraft wing segment in terms of the continuum degrees of freedom introduced in this paper. The present method of continuum modelling may yield every equivalent structural property including all possible couplings between bending, torsional and transverse shear deformations. To evaluate the equivalent continuum beam-rod model developed herein, the free vibration and aeroelastic analyses for a box-beam type aircraft wing structure have been conducted by using the continuum beam-rod model, and the numerical results are compared with the results by using other different models of the aircraft wing structure.

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“…Wing Modeling, ELAPS In contrast to other approaches to aeroelastic modeling, a finite-element code was not considered to be appropriate for this research, due to the large amounts of computer time required, and size of the programs. Instead, an equivalent plate model of the wing was chosen, since it represents a reasonable compromise of accuracy and computational effort 12 . The associated program ELAPS 13 , which has proven its applicability to tailoring of composite wings, performs a modal analysis of the wing's dynamics.…”

Section: Aircraft Plant Modelmentioning

confidence: 99%

An approach to tiltrotor wing aeroservoelastic optimization through increased productivity

Stettner

Schrage

1992

4th Symposium on Multidisciplinary Analysis and Optimization

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The paper describes one way to approach the multidisciplinary task of optimizing a tiltrotor wing structure which is equipped with an active flutter suppression system. Objective function is a productivity index, as a measure for aircraft cost-effectiveness. Short digress is held on the characteristics of the tiltrotor's dynamic system and its aeroelastic behavior. Contributing analyses (CA's) for calculating aircraft performance, modeling the dynamic system, and designing an active flutter suppression control system are selected. Multilevel and non-hierarchic decomposition techniques are discussed. A file structure for handling data transfer between the CA's and the optimizer is presented. Preliminary results are shown which highlight some peculiarities of this optimization problem. Nomenclature

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Equivalent plate analysis of aircraft wing box structures with general planform geometry

Cited by 18 publications

References 3 publications

MDO Architectures for Coupled Aerodynamic and Structural Optimization of a Flexible Wing

MDO Architectures for Coupled Aerodynamic and Structural Optimization of a Flexible Wing

Equivalent dynamic beam–rod models of aircraft wing structures

An approach to tiltrotor wing aeroservoelastic optimization through increased productivity

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