On the static aeroelastic tailoring of composite aircraft swept wings modelled as thin-walled beam structures

Librescu, Liviu; Song, Ohseop

doi:10.1016/0961-9526(92)90039-9

Cited by 96 publications

(47 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Even though not described in Ref. 7, the results suggest that the authors used the first method of disregarding transverse shear effects. As one can see from Fig.…”

Section: Static Aeroelastic Tailoringmentioning

confidence: 77%

“…7 continues the work of the first author where the effects of restrained warping, transverse shear effects, and sweep angle are studied in the presence of a more sophisticated structural model. This work uses a thin-walled beam model based on the following premises: i) cross sections do not deform in their own planes; ii) transverse shear measures are included; iii) the warping restraint effect is taken into account through the non-uniform torsion (constrained torsion); iv) the primary warping is associated with uniformtorsion only; and v) the secondary warping is based on the work of Ref.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aeroelastic analysis of composite wings

Cesnik

Hodges

Patil

1996

37th Structure, Structural Dynamics and Materials Conference

View full text Add to dashboard Cite

An aeroelastic stability analysis is presented for high-aspect ratio composite wings. The structural model is based on an asymptotically correct crosssectional formulation and a nonlinear geometric exact beam analysis, both derivable from 3-D elasticity. A new 2-D unsteady inflow finite-state theory is considered for the aerodynamic part of the solution. Theodorsen theory is also implemented and used for most of the preliminary tests. The paper discusses, among other things, the importance of using the right stiffness formulation in order to model material couplings, the variations of divergence and flutter speeds with the changes in the lamination angle of a box-beam model of a wing cross section, and some of the effects of a nonlinear structural model on the aeroelastic stability of a slender wing.

show abstract

“…Even though not described in Ref. 7, the results suggest that the authors used the first method of disregarding transverse shear effects. As one can see from Fig.…”

Section: Static Aeroelastic Tailoringmentioning

confidence: 77%

Section: Introductionmentioning

confidence: 99%

Aeroelastic analysis of composite wings

Cesnik

Hodges

Patil

1996

37th Structure, Structural Dynamics and Materials Conference

View full text Add to dashboard Cite

show abstract

“…The model does not take into account the effects of restrained warping and transverse shear. [30] found this leads to either a conservative estimate of the resulting divergence speed, or the difference was less than 2% for slender structures such as the wingbox considered here.…”

Section: Structural Modelmentioning

confidence: 99%

“…This is of particular interest if aerodynamic considerations beyond that required for the aeroelastic analysis are to be taken into account. However, strip theory allows computationally cheap optimization to be undertaken, especially where the focus of the work is on composite tailoring for the aeroelastic response and preliminary design [15,5,29,30]. The lift is then given by:…”

mentioning

confidence: 99%

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Bach

Jebari

Viti

et al. 2016

Struct Multidisc Optim

View full text Add to dashboard Cite

A method for stacking sequence optimization and aeroelastic tailoring of forward-swept composite wings is presented. It exploits bend-twist coupling to mitigate aeroelastic divergence. The method proposed here is intended for estimating potential weight savings during the preliminary aircraft design stages. A structural beam model of the composite wingbox is derived from anisotropic shell theory and the governing aeroelastic equations are presented for a spanwise discretized forward swept wing. Optimization of the system to reduce wing mass is undertaken for sweep angles of -35 • to 0 • and Mach numbers from 0.7 to 0.9. A subset of lamination parameters (LPs) and the number of laminate plies in each pre-defined direction (restricted to {0 • ,±45 • , 90 • }) serve as design variables. A bi-level hybrid optimization approach is employed, making use of a genetic algorithm (GA) and a subsequent gradientbased optimizer. Constraints are implemented to match lift requirements and prevent aeroelastic divergence, excessive deformations, airfoil stalling and structural failure. A permutation GA is then used to match specific composite ply stacking sequences to the optimum design variables with a limited number of manufacturing constraints considered for demonstration purposes. The optimization results in positive bend-twist coupling and

show abstract

“…Other refined beam models can be found in the excellent reviews by Kapania and Raciti [32][33], which focused on: bending, vibration, wave propagations, buckling and post-buckling. Excellent papers on structural dynamic and aeroelastic problems of thin-walled structures by means of higher-order beams are those by Librescu [34][35][36].…”

Section: Introductionmentioning

confidence: 99%

Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Petrolo¹

2012

International Journal of Aeronautical and Space Sciences

View full text Add to dashboard Cite

An advanced aeroelastic formulation for flutter analyses is presented in this paper. Refined 1D structural models were coupled with the doublet lattice method, and the g-method was used for flutter analyses. Structural models were developed in the framework of the Carrera Unified Formulation (CUF). Higher-order 1D structural models were obtained by using Taylor-like expansions of the cross-section displacement field of the structure. The order (N) of the expansion was considered as a free parameter since it can be arbitrarily chosen as an input of the analysis. Convergence studies on the order of the structural model can be straightforwardly conducted in order to establish the proper 1D structural model for a given problem. Flutter analyses were conducted on several wing configurations and the results were compared to those from literature. Results show the enhanced capabilities of CUF 1D in dealing with the flutter analysis of typical wing structures with high accuracy and low computational costs.

show abstract

On the static aeroelastic tailoring of composite aircraft swept wings modelled as thin-walled beam structures

Cited by 96 publications

References 10 publications

Aeroelastic analysis of composite wings

Aeroelastic analysis of composite wings

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Contact Info

Product

Resources

About