Continuous Dynamic Simulation for Morphing Wing Aeroelasticity

Liu, D. D.; Chen, P. C.; Zhang, Z.; Wang, Z.; Yang, Sun; Lee, D. H.; Mignolet, Marc P.; Kim, K.; Liu, F.; Lindsley, Ned; Beran, Philip S.

doi:10.2514/6.2009-2572

Cited by 22 publications

(17 citation statements)

References 11 publications

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“…Other techniques could be used to reach the goal of having an efficient and general reduced order aeroelastic capability. For example, the procedures developed in References [39], [40], and [41] could be adopted. However, these methods require (for a basis of just a few modes) several hundreds of fully nonlinear computationally expensive off-line analyses to evaluate some modal stiffness coefficients adopted to reconstruct the structural behavior.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Analysis of PrandtlPlane Joined Wings. Part II: Effects of Anisotropy

Cavallaro¹,

Demasi²,

Passariello³

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

13
3
41
1

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Structural geometrical nonlinearities strongly affect the response of PrandtlPlane Joined Wings: it has been shown that linear buckling evaluations are unreliable and only a fully nonlinear stability analysis can safely identify the unstable state. This work focuses on the understanding of the main physical mechanisms driving the wing system's response and the snap-buckling instability. Several counterintuitive effects typical of unconventional non-planar wing systems are discussed and explained. In particular, an appropriate design of the joint-to-wing connection may reduce the amount of bending moment transferred, and this is shown to dramatically improve the stability properties. It is also demonstrated that the lower-to-upper-wing stiffness ratio and the torsional-bending coupling, due to both the geometrical layout and anisotropy of the composite laminates, present a major impact on the nonlinear response. How the material anisotropy modifies the Snap Buckling Region and the response is also discussed. The findings of this work could provide useful indications to develop effective aeroelastic reduced order models tailored for airplanes experiencing important geometric nonlinearities such as PrandtlPlane aircraft, Truss-braced and Strut-Braced wings and sensorcrafts.

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Section: Introductionmentioning
confidence: 99%

Nonlinear Analysis of PrandtlPlane Joined Wings. Part II: Effects of Anisotropy
Cavallaro¹,
Demasi²,
Passariello³
2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
13
3
41
1
View full text Add to dashboard Cite

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“…One such procedure that models both structural and aerodynamic nonlinearities in called ELSTEP/FAT. 34 It is a structural reduced order model procedure that operates on MSC.Nastran nonlinear static structural analysis module (Solution 106) to extract the coefficients of the nonlinear structural ROM from a given finite element model. This nonlinear structural ROM is then coupled with a nonlinear aerodynamic solver to perform a nonlinear aerodynamic and nonlinear structural interaction simulation.…”

Section: Present Day Workmentioning
confidence: 99%

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration
Bhasin¹,
Chen²,
Wang³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite
3
0
8
0
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The unsteady vortex lattice method (UVLM) is coupled via OpenFSI with MD Nastran's dynamic nonlinear structural solver to study the aeroelastic response of the joined wing configuration in a subsonic regime. Initially, a number of static nonlinear structural analyses are performed on the nonlinear beam model to investigate the nonlinearities associated with the structure. The primary reason for the investigation of the structural nonlinearities is to make intelligible the aeroelastic response of the structure. After a successful validation of UVLM.OpenFSI, a panel based aerodynamic model is splined with the structural model for accurate transfer of forces and displacements at every time step via OpenFSI. A new boundary value problem is solved for the modified aerodynamic model at every time step. Evolution of the wake and its aerodynamic effects are well accounted for. Time domain responses of the lift generated by the joined wing configuration under various loading conditions is obtained. The flutter boundary of the joined wing configuration is calculated by interpolating between the dampings values evaluated for stable and unstable time domain responses. Also presented is the time domain response of the joined wing configuration when subjected to external excitations, predicting the onset of flutter and the post flutter behavior.

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“…Unfortunately, in the case of Joined Wings the strong structural nonlinearities makes an efficient reduced order model very difficult to achieve. 39 The procedures developed in References [40], [41], and [42] could be adopted. However, these methods require (for a basis of just a few modes) several hundreds of fully nonlinear computationally expensive off-line analyses to evaluate some modal stiffness coefficients adopted to reconstruct the structural behavior.…”

Section: Introductionmentioning
confidence: 99%

A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives
Teunisse
¹
,
Demasi
²
,
Tiso
³

et al. 2014
55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
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Past studies showed that the overconstrained nature of Joined Wings and the strong structural geometric nonlinearities make difficult the use of standard packages of aeroelastic solvers (usually modally reduced and frequency domain based) which have been effectively adopted by the industry for decades. We present here a study on the reduction of the computational cost in presence structural nonlinear effects that cannot be neglected in Joined Wings, even at small angles of attack and attached flow. In particular, a reduced order model is achieved with a basis constituted by vibration modes augmented with the corresponding modal derivatives. The results can be considered excellent when compared to the full order reference solution. However, a convergence test showed that the required number of vectors is relatively high and the basis needs to be often updated to achieve the best performance. More investigations will be necessary for an effective use in the industry and complicate dynamic problems involving the unsteadiness of the aerodynamics.

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Continuous Dynamic Simulation for Morphing Wing Aeroelasticity

Cited by 22 publications

References 11 publications

Nonlinear Analysis of PrandtlPlane Joined Wings. Part II: Effects of Anisotropy

Nonlinear Analysis of PrandtlPlane Joined Wings. Part II: Effects of Anisotropy

Dynamic Nonlinear Aeroelastic Analysis of the Joined Wing Configuration

A Computational Method for Structurally Nonlinear Joined Wings Based on Modal Derivatives

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