Nonlinear Aeroelasticity

Dowell, Earl H.; Edwards, John W.; Strganac, Thomas W.

doi:10.2514/2.6876

Cited by 372 publications

(140 citation statements)

References 67 publications

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“…Compared to the design diving speed, reported in previous sections, it is possible to conclude that the airworthiness target is satisfied by the proposed configuration. Moreover, when the airplane shows a highly flexible wing, an advanced aeroelastic behaviour should be considered as stated in references [13], [23], and [24]. Moderate-to-large bending deflections, due to aerodynamic loads, cause non-linear coupling between edge-wise bending and torsion.…”

Section: Aeroelastic Considerationsmentioning

confidence: 99%

“…Another design indication that should be taken into account [13,23,25] is that the stiffness ratio between in-plane stiffness and out-of-plane stiffness could play an important role in increasing the flutter boundaries; the positive effect of increased flutter speed when a higher value of the stiffness ratio is introduced into the airplane structure design has been pointed out [23,25].…”

Section: Fig 15 Fe Model and Wing And Tails Deflectionmentioning

confidence: 99%

“…Moderate-to-large bending deflections, due to aerodynamic loads, cause non-linear coupling between edge-wise bending and torsion. Therefore, the trim condition and the natural frequencies of flight dynamics could be significantly affected by the inherent flexibility and non-linear deformations of the wing structure, leading to an overall change in the wing's aeroelastic characteristics [23,25].…”

Section: Aeroelastic Considerationsmentioning

confidence: 99%

See 2 more Smart Citations

Design of a High-Altitude Long-Endurance Solar-Powered Unmanned Air Vehicle for Multi-Payload and Operations

Romeo

Frulla

Cestino

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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Several researches are being carried out at the Politecnico di Torino with the aim of designing a high altitude very-long endurance/unmanned air vehicle (HAVE/UAV). Being able to fly in the stratosphere (15 -20 km) and with an endurance of about 4 months offers an advantage and possibility that is presently not available with conventional aircraft or satellites. A computer program has been developed to design the platform. The change in solar radiation over a period of a year, the altitude, masses, and efficiencies of the solar and fuel cells, as well as the aerodynamic, structural, flight mechanics, and aeroelastic performances have all been taken into account. Extensive use has been made of high modulus graphite/epoxy when designing the structure in order to minimize the airframe weight, but also to guarantee the required stiffness and aeroelastic performance.A blended wing body (BWB) configuration has been selected for solar HAVE aircraft multi payload and operation (SHAMPO) with eight brushless electric motors, as the result of a preliminary design. The BWB solution has been designed according to the conventional procedures and airworthiness regulations. It seems to be the best compromise between performance, available surfaces for solar cells and volume for multi-payload purposes, compared to conventional design.Several profiles and wing plans have been analysed and optimized to achieve the best efficiency using the Xfoil and Vsaero computational fluid dynamics (CFD) software. A finiteelement method and a classical theoretical analysis was carried out using the Msc/Patran/ Nastran code to predict the static and aeroelastic behaviour of the SHAMPO. Aeroelastic analysis has been performed starting with a classical linear flutter analysis and considering an undeformed equilibrium condition. Classical linear flutter speed show as the airworthiness requirements has been achieved in the case of SHAMPO configuration. A preliminary non-linear aeroelastic model is introduced in the design process in order to deal with specific phenomena correlated with high static structural deflections occurring during standard flight conditions. Important flutter speed reduction (i.e. up to 42 per cent in special cases) are possible including such kind of phenomena.

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Section: Aeroelastic Considerationsmentioning

confidence: 99%

Section: Fig 15 Fe Model and Wing And Tails Deflectionmentioning

confidence: 99%

Section: Aeroelastic Considerationsmentioning

confidence: 99%

See 1 more Smart Citation

Design of a High-Altitude Long-Endurance Solar-Powered Unmanned Air Vehicle for Multi-Payload and Operations

Romeo

Frulla

Cestino

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Detailed literature reviews of nonlinearity in aeroelasticity were carried out by Dowell et al [2] and Lee et al [3].…”

Section: Introductionmentioning

confidence: 99%

Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

Jiffri

Fichera

Mottershead

et al. 2017

Journal of Guidance, Control, and Dynamics

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“…In recent years, scholars domestic and foreign carried out much researches on nonlinear aeroelastic problems above mentioned [4][5][6][7], they deemed that we could approach the nonlinear flutter speed through calculating a series of flutter speeds at static aeroelastic equilibrium point of the wing by linearizing.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic tailoring of high-aspect-ratio composite joined-wing UAV

Chen¹,

Jing²

2017

Math. models, eng.

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Abstract. For the high-aspect-ratio composite joined-wing UAV, as the geometric nonlinear significant effect, nonlinear aeroelastic analysis method should be applied when study its aeroelastic tailoring method. In the paper, based on the secondary development of MSC/Nastran software with Direct matrix abstraction programme language, with the adopting the multidisciplinary design optimization platform Isight software integrating the MSC/Nastran software analysis, modules of the static aeroelastic analysis, nonlinear static analysis and flutter analysis, a nonlinear aeroelastic tailoring method for high -aspect-ratio composite joined-wing UAV has been presented. Example show that, the method proposed in this paper not only can solve nonlinear aeroelastic tailoring of high-aspect-ratio composite joined-wing UAV problem, but also can be applied to complex engineering structure.

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Nonlinear Aeroelasticity

Cited by 372 publications

References 67 publications

Design of a High-Altitude Long-Endurance Solar-Powered Unmanned Air Vehicle for Multi-Payload and Operations

Design of a High-Altitude Long-Endurance Solar-Powered Unmanned Air Vehicle for Multi-Payload and Operations

Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

Aeroelastic tailoring of high-aspect-ratio composite joined-wing UAV

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