Development of a Aerothermoelastic-Acoustics Simulation Capability of Flight Vehicles

Gupta, K. K.; Choi, Sang Bum

doi:10.2514/6.2010-50

Cited by 14 publications

(5 citation statements)

References 7 publications

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“…It was demonstrated earlier [17] that, if the material is changed to titanium (Ti)-Al, the wing becomes stable and aerothermoelasticacoustics simulation results become convergent.…”

Section: Numerical Examplesmentioning

confidence: 97%

Aerothermoelastic-Acoustics Simulation of Flight Vehicles

2017

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This paper describes a novel computational-fluid-dynamics-based numerical solution procedure for effective simulation of aerothermoacoustics problems with application to aerospace vehicles. A finite element idealization is employed for both fluid and structure domains, which fully accounts for thermal effects. The accuracies of both the fluid and structure capabilities are verified with flight-and ground-test data. A time integration of the structural equations of motion , with the governing flow equations, is conducted for the computation of the unsteady aerodynamic forces, which uses a transpiration boundary condition at the surface nodal points in lieu of the updating of the fluid mesh. Two example problems are presented herein to that effect. The first one relates to a cantilever wing with a NACA 0012 airfoil. The solution results demonstrate the effect of temperature loading that causes a significant increase in acoustic response. A second example, the hypersonic X-43 vehicle, is also analyzed; and relevant results are presented. The common finite element-based aerothermoelastic-acoustics simulation process, its applicability to the efficient and routine solution of complex practical problems, the employment of the effective transpiration boundary condition in the computational fluid dynamics solution, and the development and public domain distribution of an associated code are unique features of this paper.

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“…It was demonstrated earlier [17] that, if the material is changed to titanium (Ti)-Al, the wing becomes stable and aerothermoelasticacoustics simulation results become convergent.…”

Section: Numerical Examplesmentioning

confidence: 97%

Aerothermoelastic-Acoustics Simulation of Flight Vehicles

2017

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“…In a similar approach to [70], Gupta et al [190] extended the FEMbased aeroelastic analysis framework in [22] to include thermal effects by carrying out a heat conduction analysis [190] subsequent to a steady-state flow analysis. The resulting temperature distributions were used to compute the heated modes and frequencies of the structure for use in an aeroelastic analysis of the system.…”

Section: B Aerothermoelastic Studiesmentioning

confidence: 99%

“…Figure 49 provides an [4] PT, VD FEM --NASP [25,170,173,174] PT, blended VD/NI FEM APAS X-33 [178] PT Equiv. plate --X-33 [180] PT, Euler FEM --X-34 [177] PT FEM --X-43 [22] PT, ARMA Euler FEM --X-43 [190] NS FEM NS Lifting/control surfaces NASP [171] VD FEM X-15 data Generic [70,71] PT, Euler, NS FEM --Generic [70] PT, Euler FEM NS Generic [191] PT, ROM ROM NS-based ROM excellent summary and perspective of the important flow physics and modeling requirements for such a problem. An overview on the methods used in the analysis and preflight database development for the X-43 test flights was also provided [222].…”

Section: Airframe-propulsion Integration and Multidisciplinary Analysmentioning

confidence: 99%

Aeroelastic and Aerothermoelastic Analysis in Hypersonic Flow: Past, Present, and Future

2011

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is actively engaged in research on hypersonic aeroelasticity and aerothermoelasticity, multidisciplinary analysis and control of hypersonic vehicles, wind turbine aerodynamics and aeroelasticity, and turbomachinery aeromechanics. His research in hypersonic aeroelasticity and aerothermoelasticity was recognized with the 2004 ASME/Boeing Structures and Materials Award. He is currently a Senior Member of the AIAA.

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“…It is a fully functioning aircraft simulation including realistic engine and actuator behavior, sensor models and a flight control system. Although a significant number of failure scenarios were considered, computed and tested in CFD and wind tunnels [19], only a few of them were implemented in the distributed Simulink simulation model. Moreover, the problem of comparability between various new developments is also present within the field of aircraft system identification.…”

Section: Introductionmentioning

confidence: 99%

VIRTTAC - A Family of Virtual Test Aircraft for Use in Flight Mechanics and GNC Benchmarks

Deiler

Fezans

2019

AIAA Scitech 2019 Forum

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A new generic aircraft model called VIRTTAC-Castor is introduced. This model was developed by DLR and will be made available for the research community. VIRTTAC-Castor is the first member of a complete model family available in the future. The "VIRtual TesT AirCraft" models will consist of several aircraft designs of different sizes and configurations to be used for manifold applications. Each model of the VIRTTAC family can be utilized for virtual flight test just as engineers would perform with a real aircraft. The VIRTTAC family is designed to provide high-quality validation benchmark models for e.g. system identification, controller design and demonstration of fault-tolerant controllers as well as reduced envelope protection functions.

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Development of a Aerothermoelastic-Acoustics Simulation Capability of Flight Vehicles

Cited by 14 publications

References 7 publications

Aerothermoelastic-Acoustics Simulation of Flight Vehicles

Aerothermoelastic-Acoustics Simulation of Flight Vehicles

Aeroelastic and Aerothermoelastic Analysis in Hypersonic Flow: Past, Present, and Future

VIRTTAC - A Family of Virtual Test Aircraft for Use in Flight Mechanics and GNC Benchmarks

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