Propeller Effects on the Dynamic Response of HALE Aircraft

Teixeira, Patrícia Santos; Cesnik, Carlos E. S.

doi:10.2514/6.2018-1202

Cited by 6 publications

(7 citation statements)

References 14 publications

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“…UM/NAST originally also incorporated just thrust to model the propeller effects. However, developments made by previous works of the authors (31,32,33) made possible the complete inclusion of the propeller effects in a nonlinear aeroelastic framework (composed of all the resultant aerodynamic loads on the hub, the aerodynamic effects of propeller slipstream, and its inertial effects). The unsteady aerodynamics is based on Lifting Line plus Viscous Vortex Particle method for the propellers combined with an Unsteady Vortex Lattice for the lifting surfaces, allowing it to capture propwash effects as well as the interaction of the flow among multiple lifting surfaces.…”

Section: Propeller Modeling On Nonlinear Aeroelastic Frameworkmentioning

confidence: 99%

“…To accomplish these objectives, an enhanced aeroelastic framework developed in previous works by the authors (31,32,33) , and capable of incorporating the different propeller effects, is employed to generate snapshots data for a HALE aircraft model with propellers. Also, a method to extract frequencies, damping, and modes from time-series data, based on a combination of Proper Orthogonal Decomposition (POD) and system identification (sys ID), is proposed and verified for a purely structural case, for which reference data is available.…”

Section: Paper Objectives and Organizationmentioning

confidence: 99%

“…The remaining of this paper is organised as follows: Section 2 describes key aspects of the enhanced aeroelastic framework with propellers previously developed by the authors (31,32,33) . Section 3 describes the motivation and strategy of an alternative approach to extract dynamic information from simulations of VFA with propellers.…”

Section: Paper Objectives and Organizationmentioning

confidence: 99%

“…In order to take into account the different propeller effects, the original UM/NAST framework was enhanced, as described in previous works by the authors (31,32,33) , with an Unsteady Vortex Lattice for the lifting surfaces and a Lifting Line and Viscous Vortex Particle (LL/VVP) methods to model the propeller aerodynamics. Furthermore, inertia effects associated with the rigid rotating blades were also incorporated.…”

Section: Aeroelastic Framework With Propellermentioning

confidence: 99%

See 3 more Smart Citations

Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

Teixeira

Cesnik

2020

Aeronaut. j.

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This work investigates the propeller’s influence on the stability of High Altitude Long Endurance aircraft, incorporating all resultant loads at the propeller hub, propeller slipstream, and gyroscopic loads. Such effects are usually neglected in the aeroelastic simulation of HALE aircraft. For that goal, a previously developed framework, which couples a geometrically nonlinear structural solver with an Unsteady Vortex Lattice method (uVLM) for lifting surfaces and a Viscous Vortex Particle (VVP) method for propeller slipstream, was employed to generate time-data series. Also, a method, based on a combination of Proper Orthogonal Decomposition and system identification, to extract dynamic information (frequencies, damping, and modes) of the aircraft from a time-series signal is proposed and successfully tested for a purely structural case, for which reference data is available. The method is then applied to investigate the stability of aeroelastic cases. The results demonstrate that the presence of propellers can influence the aeroelastic stability of a Very Flexible Aircraft.

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Section: Propeller Modeling On Nonlinear Aeroelastic Frameworkmentioning

confidence: 99%

Section: Paper Objectives and Organizationmentioning

confidence: 99%

Section: Paper Objectives and Organizationmentioning

confidence: 99%

Section: Aeroelastic Framework With Propellermentioning

confidence: 99%

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Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

Teixeira

Cesnik

2020

Aeronaut. j.

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“…The VPM is a direct numerical simulation of vorticity-governed flows that accurately preserves vortical structures and is absent of the numerical dissipation associated to conventional mesh-based approaches like RANS and large-eddy simulation (LES). This method has been shown to achieve a continuum of fidelity levels, from low fidelity apt for conceptualdesign [24][25][26][27][28][29][30][31] to high fidelity apt for research-quality computational fluid dynamics, [32][33][34][35] while offering a considerable speed up over a RANS or LES approach. Fig.…”

Section: Introductionmentioning

confidence: 99%

Modeling Multirotor Aerodynamic Interactions Through the Vortex Particle Method

Alvarez

Ning

2019

AIAA Aviation 2019 Forum

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Distributed electric propulsion and vertical takeoff and landing has recently opened a new design space for urban air mobility. However, the use of multiple rotors operating in close proximity introduces complicated aerodynamic interactions that are not well understood, are not captured through conventional design tools, and need to be addressed in the conceptual design stage. This study investigates the accuracy of the viscous vortex particle method (VPM) in modeling rotor-on-rotor aerodynamic interactions in a sideby-side configuration as encountered in tilt-rotor, quadrotor, and distributed propulsion aircraft. The VPM approach has the potential to enable the use of mid/high fidelity models capturing multirotor interactions during conceptual design. Validation of the individual rotor is presented in both hovering and forward-flight configurations at both low and high Reynolds numbers. Validation of the hovering multirotor is then presented, followed by a detailed parametric study of rotor-to-rotor interactions during hover and forward flight, constructing the response surface of thrust, torque, and propulsive efficiency as a function of operational parameters.

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Rapid dynamic aeroelastic response analysis of the highly flexible wing with distributed propellers influence

Wu,

Zhou,

Wang

2024

Aeronaut. j.

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A rapid nonlinear aeroelastic framework for the analysis of the highly flexible wing with distributed propellers is presented, validated and applied to investigate the propeller effects on the wing dynamic response and aeroelastic stability. In the framework, nonlinear beam elements based on the co-rotational method are applied for the large-deformation wing structure, and an efficient cylinder coordinate generation method is proposed for attached propellers at different position. By taking advantage of the relatively slow dynamics of the high-aspect-ratio wing, propeller wake is modeled as a quasi-steady skewed vortex cylinder with no updating process to reduce the high computational cost. Axial and tangential induced velocities are derived and included in the unsteady vortex lattice method. For the numerical cases explored, results indicate that large deformation causes thrust to produce wing negative torsion which limits the displacement oscillation, and slipstream mainly increases the response values. In addition, an improvement of flutter boundary is found with the increase of propeller thrust while slipstream brings a destabilising effect as a result of the increment of dynamic pressure and local lift. The great potential of distributed propellers in gust alleviation and flutter suppression of such aircraft is pointed out and the method as well as conclusions in this paper can provide further guidance.

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Propeller Effects on the Dynamic Response of HALE Aircraft

Cited by 6 publications

References 14 publications

Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

Propeller influence on the aeroelastic stability of High Altitude Long Endurance aircraft

Modeling Multirotor Aerodynamic Interactions Through the Vortex Particle Method

Rapid dynamic aeroelastic response analysis of the highly flexible wing with distributed propellers influence

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