Aeroelastic Analysis of a High-Altitude Long-Endurance Joined-Wing Aircraft

Snyder, Richard; Hur, Jiyoung; Strong, Daniel; Beran, Philip S.

doi:10.2514/6.2005-1948

Cited by 13 publications

(4 citation statements)

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“…It is interesting to note that, according to the same reference [349], AFRL had a joined-wing baseline model consisting of two fuselages, see Figure 3. However, [328].…”

Section: Early Work and Collaboration Between Afrl Boeing Nasa And Us Navymentioning

confidence: 99%

See 1 more Smart Citation

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Cavallaro

Demasi

2016

Progress in Aerospace Sciences

122

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“…It is interesting to note that, according to the same reference [349], AFRL had a joined-wing baseline model consisting of two fuselages, see Figure 3. However, [328].…”

Section: Early Work and Collaboration Between Afrl Boeing Nasa And Us Navymentioning

confidence: 99%

“…In paper [328] a loosely coupled procedure for static aeroelastic analysis of HALE joined-wing aircraft was presented. A finite volume Navier-Stokes solvers was coupled with a linear mode-based structural solver.…”

Section: Aeroelastic Studies Of a Twin-fuselage Joined-wing Sensorcraftmentioning

confidence: 99%

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Cavallaro

Demasi

2016

Progress in Aerospace Sciences

122

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“…With the subsequent appearance of high-altitude long-endurance unmanned aerial vehicles, renewed interest in the nonlinear aeroelastic effects of large deformation led to additional research based on the coupling of nonlinear-beam models with essentially 2-D unsteady aerodynamics, suitable for the modeling of configurations of very high aspect ratios [4][5][6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

Demasi

Livne

2009

AIAA Journal

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Steady-state and time-domain methods are introduced for integrating commonly used frequency-domain unsteady aerodynamic modeling based on a modal approach with full-order finite element models for structures with geometric nonlinearities. The methods are aimed at airplane configurations in which geometric-stiffness effects are important but deformations are moderate, flow is attached, and linear unsteady aerodynamic modeling is adequate, such as joined-wing and strut-braced wings at small-to-moderate angles of attack or a low-aspect-ratio wing. The approach proposed in this paper is to use the full-order structural matrices to capture the nonlinear structural behavior and modally reduced aerodynamic matrices calculated by adopting a frequency-domain-based commercial code such as ZAERO or a doublet-lattice method or linearized modal-based generalized aerodynamic matrices generated by computational fluid dynamics codes.

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“…In Reference [14], an unstructured Navier-Stokes solver is used to converge on a static aeroelastic equilibrium condition of a joined-wing HALE configuration. Figure 2 comes from Reference [9] and is based on a built up membrane FEM model.…”

Section: Disciplinesmentioning

confidence: 99%

AVEC: A Computational Design Environment for Conceptual Innovations

Blair¹

2008

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RB-WP-TR-2008-3061 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited. SUPPLEMENTARY NOTESPAO Case Number: AFRL/WS 06-0535, 23 Feb 2006. Report contains color. ABSTRACTThis report summarizes programming techniques that aid multidisciplinary design programmers in developing computational designs that measure AFRL technology effectiveness. These techniques have been collected into an object-oriented design environment. The Air Vehicle Environment in C++ (AVEC) prototypes a practical approach toward computational design. Design innovators will benefit from AVEC at one of three levels. These three levels target (a) the end user through interactive operations and file I/O, (b) the object-oriented programmer through a compiled library of properly documented and inheritable objects, and (c) the AVEC developer who wishes to enhance AVEC capability with modifications to the source code. The pilot code presented here focuses on parent-child relationships, automated dependency management, geometry, meshing and analysis. All together, the overall capability leads to design variant management that will populate a response surface model and thereby address design optimization. The target SensorCraft design mission involves a suite of aeroelastic concepts with geometric non-linearity, in the form of non-linear coupling, large deformations and follower forces. Parallel programming environment developments are cited in this report. Specifically, this report highlights the in-house research that followed the cost-shared Dual-Use development effort, "Scenario-Based Affordability Assessment Tool" (SBAAT), contract F33615-00-2-3055. SUBJECT TERMSThe target application for the AVEC environment is any computational design model that requires both the computational efficiency of a compiled code and geometric design versatility associated with object-oriented programming. Extensions to the AVEC environment can be distributed in the form of shared libraries of class structures. Such extensions should address various geometric and meshing needs, analysis needs, graphical renderings, both static and dynamic. AVEC supports the integration of these class structures with automated dependency management to form an interactively managed design process.

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Aeroelastic Analysis of a High-Altitude Long-Endurance Joined-Wing Aircraft

Cited by 13 publications

References 0 publications

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

AVEC: A Computational Design Environment for Conceptual Innovations

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