Aeroelastic Scaling and Optimization of a Joined-Wing Aircraft Concept

Pereira, Pedro; Almeida, Luís Pedro; Suleman, Afzal; Bond, Vanessa L.; Canfield, Robert A.; Blair, Maxwell

doi:10.2514/6.2007-1889

Cited by 24 publications

(21 citation statements)

References 1 publication

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“…Results from transient response analysis of the actively controlled wind tunnel model were also shown. Pereira et al 22 developed a scaling methodology for a joinedwing wind tunnel model. The scaled structure was designed by optimizing the scaled natural frequencies of the model to match the full scale design.…”

Section: Related Scaling Workmentioning

confidence: 99%

Nonlinear Aeroelastic Scaled Model Optimization Using Equivalent Static Loads

Ricciardi

Canfield

Patil

et al. 2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A new nonlinear aeroelastic scaling methodology is developed that uses direct matching of linear and nonlinear static responses while simultaneously satisfying modal frequency constraints. To demonstrate this technique, a 1/9 th scaled vehicle is designed to match the nonlinear aeroelastic response of a joined-wing concept. This is the first demonstration of an optimization that simultaneously combines equivalent static loads for nonlinear statics with structural dynamics. Recently developed nonlinear aeroelastic analysis was upgraded to facilitate scaled model verification. This is the first || scaling demonstration to include nonlinear aeroelastic verification. Results show marked improvement over results from a vehicle designed using traditional linear methods.

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Section: Related Scaling Workmentioning

confidence: 99%

Nonlinear Aeroelastic Scaled Model Optimization Using Equivalent Static Loads

Ricciardi

Canfield

Patil

et al. 2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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show abstract

“…Model similitude to a full-scale vehicle requires that wind-tunnel flow conditions and model structural characteristics satisfy various relationships. 1,5,[17][18][19][20] Some facilities study the aeroelastic and buffet phenomena of a wind tunnel model and tunnel support system without relation to a flight vehicle. 21 An important distinction for TDT is that the aeroelastic and buffet phenomena discussed in this document refer to events experienced by a flight vehicle and the corresponding ability of a wind tunnel model to simulate those events.…”

Section: A Typical Aeroelastic Scaling Parametersmentioning

confidence: 99%

“…(6) for conditions where gas thermodynamic scaling can be neglected (Refs. 1,5,[17][18][19][20]. The application and importance of these parameters will be discussed in the following sections.…”

Section: A Typical Aeroelastic Scaling Parametersmentioning

confidence: 99%

Unique Testing Capabilities of the NASA Langley Transonic Dynamics Tunnel, an Exercise in Aeroelastic Scaling

Ivanco

2013

AIAA Ground Testing Conference

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The NASA Langley Research Center Transonic Dynamics Tunnel (TDT) is well known for its aeroelastic testing capabilities. Its large size, transonic speed range, variable pressure capability, and use of either air or R-134a heavy gas as a test medium enable unparalleled manipulation of flow-and-structure-dependent scaling quantities. This paper will present select scaling quantities that are important for the proper characterization of any dynamic phenomenon and many static aeroelastic phenomena. An analytical demonstration is presented comparing the unique ability of TDT to match these scaling quantities by comparison to other leading facilities with other test mediums. Complementary to aeroelastic testing, the TDT is well-suited for high risk testing and for those tests that require unusual model mount or support systems. Examples are presented. In addition to its unique aeroelastic testing capabilities, flow quality and Reynolds number capability are briefly discussed. Finally, the ability of the TDT to support future NASA research thrusts and likely vehicle designs is presented.* Research Aerospace Engineer, Aeroelasticity Branch, Mail Stop 340, AIAA Senior Member. https://ntrs.nasa.gov/search.jsp?R=20140000340 2020-07-16T13:47:06+00:00Z HE NASA Langley Research Center (LaRC) Transonic Dynamics Tunnel (TDT) has been operational since 1960 investigating a wide range of aeroelastic and non-aeroelastic phenomena. 1-4 A dedicated aeroelastic test facility, the TDT is a large, variable pressure, transonic wind tunnel that can use either air or heavy gas (R-134a) as a test medium. Unlike typical wind tunnel testing which focuses upon modeling the aerodynamics experienced by a flight vehicle, the study of aeroelasticity requires modeling of the structural response of the flight vehicle when exposed to representative aerodynamics. The coupling between fluid and structural interaction can be described by a series of non-dimensional scaling parameters. Fluid and structural-response coupling tends to increase in sensitivity as the sonic condition is approached since the lift-curve-slope steepens as a function of Mach number and slight structural perturbations have an increasing aerodynamic effect. 5 As a result, many vehicles experience a "transonicdip" in the stability boundary with the lowest stability margins existing at high subsonic Mach numbers. 5,6 High subsonic Mach numbers are where most transport aircraft cruise, where high performance aircraft pass through, where launch vehicles experience the highest unsteady buffet loads during ascent, 7 and are also where computational fluid dynamics (CFD) codes have the greatest difficulty in modeling flow physics; especially unsteady flow physics. 8 Therefore, experimental data in the transonic speed range is of particular importance. Typically regarded as the world's premier aeroelastic test facility, [9][10][11][12][13] TDT fulfills a unique niche in the wind tunnel infrastructure as a result of its unparalleled ability to manipulate fluid-structure scaling parameters. T...

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“…To overcome these two problems, it is necessary to research the similarity of the impact response for the deep space exploration inflatable landing attenuation system. Although considerable research has been devoted to dynamic similarity of structural aeroelastic characteristics [13][14][15], considerably less attention has been paid to similarity of the impact response of inflatable landing attenuation.…”

Section: Introductionmentioning

confidence: 99%

Similarity Design Method of the Inflatable Buffer Landing System

Wang

2019

International Journal of Aerospace Engineering

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The inflatable buffer landing system, such as the airbag, has been widely used for deep space exploration as a low-cost entry. The impact performance of an airbag landing attenuation system on Mars had to be proven through cushion testing on Earth. In this paper, a design method for the airbag landing attenuation system on Earth is proposed based on similarity relation. With this method, the impact response of the spherical airbag landing attenuation system is derived based on assumptions, and the principal factors have great influence on the impact response of the landing system have been proved. Then, the similarity relation between the full-scale airbag landing attenuation system in the Martian atmosphere and its Earth prototype is obtained through theoretical derivation. Finally, the proposed similarity relationship has been tested on several ground prototypes by FEA. The results of the study show that the Earth prototype by the developed design method is capable of predicting the impact response with good accuracy.

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Aeroelastic Scaling and Optimization of a Joined-Wing Aircraft Concept

Cited by 24 publications

References 1 publication

Nonlinear Aeroelastic Scaled Model Optimization Using Equivalent Static Loads

Nonlinear Aeroelastic Scaled Model Optimization Using Equivalent Static Loads

Unique Testing Capabilities of the NASA Langley Transonic Dynamics Tunnel, an Exercise in Aeroelastic Scaling

Similarity Design Method of the Inflatable Buffer Landing System

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