Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations

Ricciardi, Anthony; Patil, Mayuresh; Caneld, Robert A.; Lindsley, Ned

doi:10.2514/6.2011-2043

Cited by 11 publications

(7 citation statements)

References 26 publications

(37 reference statements)

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“…7,8 The model is representative of the detailed AFRL/Boeing SensorCraft design. The beam model serves as a convenient target model for scaling methodology development.…”

Section: Discussionmentioning

confidence: 99%

Nonlinear Aeroelastic Scaling of a Joined Wing Aircraft

Ricciardi¹,

Canfield²,

Patil³

et al. 2012

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

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This paper develops and demonstrates a nonlinear aeroelastic scaling procedure. Previous work showed that matching scaled structural frequencies and mode shapes as well as a buckling eigenvalue produced a scaled model that did not have adequately consistent nonlinear behavior. A new scaling methodology is developed that uses direct matching of the nonlinear static response to account for geometric nonlinearities. The optimization is facilitated by an Equivalent Static Loads (ESL) approach. Natural frequencies and mode shapes are matched by optimizing nonstructural mass. A joined-wing beam model is used as a target for scaling a joined wingbox model. The models are representative of a full scale SensorCraft concept developed by AFRL and Boeing. The aeroelastic frequency and damping response and the nonlinear static response are matched successfully. IntroductionA multi-national team of researchers are working to aeroelastically scale, manufacture, and flight test a 1/9 th scale joined-wing remotely piloted aircraft. Scaling of nonlinear aeroelastic effects are crucial to the program goals. Previous attempts to develop a methodology for nonlinear scaling produced inadequate matching of the nonlinear response. This paper develops a methodology that successfully scales both the linear aeroelastic response and nonlinear stiffness of a joined wingbox model. The developed methodology is useful for any flight test or wind tunnel model needing to scale geometrically nonlinear behavior. Motivation

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“…7,8 The model is representative of the detailed AFRL/Boeing SensorCraft design. The beam model serves as a convenient target model for scaling methodology development.…”

Section: Discussionmentioning
confidence: 99%

Nonlinear Aeroelastic Scaling of a Joined Wing Aircraft
Ricciardi¹,
Canfield²,
Patil³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite
13
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15
0
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“…al. 12 extended the transient capabilities of NATASHA to allow large deviation of the response from the steady state trim conditions. Results from the improved transient capabilities were used to evaluate quasi-static gust analysis methods.…”

Section: Literature Reviewmentioning
confidence: 98%

A Hybrid Quasi-steady CFD-Inflow Approach for Gust Response Analysis of Highly Flexible Aircraft
Sotoudeh¹,
Canfield²,
Patil³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite
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This paper uses geometrically exact, fully intrinsic equations to study the gust response of highly flexible aircraft, including the joined-wing concept. It also introduces a hybrid quasi-steady CFD-inflow model to capture unsteady effects in a computationally efficient method. This is the first step in an attempt to develop a multifidelity program for aeroelastic analysis of such aircraft. Such a program can be used in optimization and sensitivity analysis.

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“…In addition, there is growing interest in multi-disciplinary design optimization (MDO) in order to explore the vast and complicated design spaces in which these novel configurations exist. 1,2 Gradient-based optimization algorithms are often used in MDO frameworks. Therefore, design sensitivities associated with the various analyses are required.…”

Section: Introductionmentioning
confidence: 99%

Continuum Shape Sensitivity with Spatial Gradient Reconstruction of Nonlinear Aeroelastic Gust Response
Cross
¹
,
Canfield
²

2012
12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis And
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Accurate modeling of the aeroelastic response due to gust loads is becoming a design necessity for many novel concepts. Both the high aspect ratio wings of high altitude long endurance (HALE) aircraft and flexible membrane wings of micro aerial vehicles (MAVs) are susceptible to large deformations, geometric nonlinearities, and rigid body motion when gust loads are encountered. Using gradient based optimization for aeroelastic shape design of such configurations can be computationally expensive. Furthermore, multidisciplinary design optimization frameworks that use gradient-based algorithms are becoming increasingly popular. A major challenge in developing such frameworks is implementing accurate and efficient sensitivity analyses for the various disciplines. This becomes especially challenging when a "black box" analysis tool is used and access to the source code is not possible. Presented in this paper is a continuum shape sensitivity method which does not require access to or knowledge of source code formulation. A static nonlinear beam bending problem and a static linear plate bending problem are presented as benchmarks. In addition, continuum shape sensitivities are computed for an aeroelastic gust response of both a one-and two-dimensional structure. In all cases, the analysis tool is treated as a "black box". Nomenclature ߙ= Incident angle of attack ߙ = Gust angle ߙ = Effective angle of attack ‫ܣ‬ = General time-space differential operator ‫ܣ‬ ̅ = General time-space differential operator of local sensitivity system ‫ܣ‬ ̅ ்௧ = General time-space differential operator of total sensitivity system ܾ = Design variable (shape parameter) ‫ܤ‬ = General boundary operator ‫ܤ‬ ത = General boundary operator of local sensitivity system ‫ܥ‬ ഀ = Lift curve slope ߜ = Perturbation ∇ = Gradient operator ∆ = Essential boundary displacement ݂ = Generalized loads ‫ܨ‬ = Applied load ‫ܨ‬ = Quasi-steady lift force ߁ = Spatial boundary *The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the Air Force Research Laboratory or the U.S. Government. 2 ݃ = Loads applied at the boundary ℎ = Plunge degree of freedom ‫ܯ‬ = Internal bending moment ܰ = Internal axial force Ω = Spatial domain ߮ = Rotation ‫ݍ‬ ஶ = Dynamic pressure ܳ = Generalized element force ߩ ஶ = Air density ‫ݏ‬ = Effective lifting area ‫ݐ‬ = Time variable ߠ = Rotation degree of freedom ‫ݑ‬ = General response variable and horizontal displacement ܷ = Gust velocity ܷ ஶ = Free stream velocity Ѵ = Design velocity ܸ = Internal shear force ‫ݓ‬ = Transverse displacement ‫ݔ‬ = Point in spatial domain

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Utility of Quasi-Static Gust Loads Certification Methods for Novel Configurations

Cited by 11 publications

References 26 publications

Nonlinear Aeroelastic Scaling of a Joined Wing Aircraft

Nonlinear Aeroelastic Scaling of a Joined Wing Aircraft

A Hybrid Quasi-steady CFD-Inflow Approach for Gust Response Analysis of Highly Flexible Aircraft

Continuum Shape Sensitivity with Spatial Gradient Reconstruction of Nonlinear Aeroelastic Gust Response

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