Multiphysics Simulation Capability using the SIMULIA Co-Simulation Engine

Blades, Eric; Miskovish, R. Scott; Luke, Edward A.; Collins, Eric; Kurkchubashe, Albert G.

doi:10.2514/6.2011-3397

Cited by 53 publications

(12 citation statements)

References 17 publications

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“…In previous work, the computational framework discussed in the next section was applied to the validation problems of static and dynamic aeroelasticity in high subsonic and mildly supersonic flows [6]. Additionally, the techniques have been extended to supersonic nozzle flows [7].…”

Section: Objectivesmentioning

confidence: 99%

Demonstration of Multiphysics Analysis Tools on Representative Hypersonic Vehicle Structures

Blades

Shah

Nucci

et al. 2013

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

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This paper extends a previously developed computational framework for coupled aerothermoelastic simulations for hypersonic vehicle structures in extreme environments. An aeroheating verification and validation case is first conducted on a Mach 6.5+ spherical dome protuberance that was tested in a NASA wind tunnel by Glass and Hunt [1986] and was also computationally simulated by Ostoich et al. [2011, 2012]. ATA's simulation includes aerothermoelasticity in the physics and captures the heating of the compliant dome structure during the first five seconds of exposure to hypersonic flow. This case is followed by a coupled quasi-static aerothermoelastic analysis of an acreage panel-level structural component for a sustained, reusable, air-breathing Mach 5-7 cruise horizontal-takeoff platform. A notional hypersonic vehicle (NHV) has been defined, and analyses are underway for two panels based on recent industry detailed designs. The panels were consistent with the NHV outer mold line (OML), allowing the fully coupled simulation of two realistic structures in a realistic hypersonic environment. The paper presents results from a first quasi-static simulation of an orthogrid stiffened, curved panel that bows into the flow due to thermal stress and an assumed internal pressure. The effect of the stiffeners on the panel's response is profound and includes global and localized bowing relative to the undeformed panel and vehicle OML, resulting in the generation of multiple shock structures. The longterm vision of the analysis framework is to enable accurate, quantitative assessment of panels in regions where improper accounting of nonlinear coupling makes structural response and life prediction problematic and may lead to excessive structural risk and/or weight as a result of excessive conservatism.

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Section: Objectivesmentioning

confidence: 99%

Demonstration of Multiphysics Analysis Tools on Representative Hypersonic Vehicle Structures

Blades

Shah

Nucci

et al. 2013

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

Self Cite

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“…18 Loci/CHEM numerical models have been demonstrated to be at least 2 nd -order accurate in space and time through rigorous verification using the method of manufactured solutions (MMS). 19 Loci/ CHEM supports adaptive mesh refinement, 20 complex equations-of-state including cryogenic fluids, 21 conjugate heat transfer through solids, 22 fluid-structure interaction modeling, [23][24][25] and overset moving boundary simulations with contact detection and collision modeling to support multiple-body proximate flight in highspeed air-delivered systems. 26,27 III.…”

Section: Overview Of Loci Framework and Loci/chem Flow Solvermentioning

confidence: 99%

Validation of Overset Discontinuous Galerkin and Hybrid RANS/LES Method for Jet Noise Prediction

Harris

Arslanbekov

Collins

et al. 2016

46th AIAA Fluid Dynamics Conference

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Launch vehicles experience extreme acoustic loads during lift-off which are capable of damaging sensitive mechanical components of the vehicle and payload, and may lead to significant injury in passengers. The noise is driven by the exhaust plumes and their interaction with ground structures, and accurate prediction of this environment poses several unique challenges when compared to traditional jet noise modeling techniques. In particular, acoustic and Mach waves propagating from the exhaust plume are in the vicinity of obstructions and are generally in the nonlinear regime, which renders the classical acoustic analogy and linearized approaches invalid. This work continues the development of a recently introduced novel approach for the accurate prediction of lift-off acoustic environments. The method makes use of unstructured hybrid RANS/LES to predict the complex exhaust plume physics, and an overset high-order accurate discontinuous Galerkin solver to accurately propagate acoustic waves across large distances throughout the environment. The framework upon which the solvers are developed is described along with details outlining the overset grid assembly and interpolation methods. Detailed validation studies are presented to demonstrate the accuracy of the method for prediction of noise due to the impingement of a supersonic jet on a 45 degree inclined flat plate, and comparisons with experimental data show the method to be effective and accurate in terms of predicted overall sound pressure level spectra.

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“…10 Loci/CHEM numerical models have been demonstrated to be at least second order accurate in space and time through rigorous verification using the Method of Manufactured Solutions (MMS). 11 Loci/CHEM supports adaptive mesh refinement, 12 simulations of complex equations-of-state including cryogenic fluids, 13 multiphase simulations of dispersed liquid and solid particulates using both Lagrangian and Eulerian approaches, 14 conjugate heat transfer through solids, 15 fluid structure interaction modeling, 16 and non-gray radiative heat transfer associated with both, gas and particulate phases. 17 The Loci/CHEM solver infrastructure supports overset meshes for efficient simulation of flows over complex geometry and moving boundary problems.…”

Section: Overview Of Loci Framework and Loci/chem Flow Solvermentioning

confidence: 99%

Towards a Predictive Capability for Multiple-Body Proximate-Flight in High-Speed Air-Delivered Systems

Harris

Liever

Luke

et al. 2012

42nd AIAA Fluid Dynamics Conference and Exhibit

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Multiple-body high-speed air-delivered systems are subjected to a complex flow environment characterized by inter-body collisions, large interference pressures, and strong moving shock systems. These unique physics are prevalent in the strong interaction phase early in the projectile deployment, and have a first-order effect on the resulting projectile dispersion pattern. Since classical engineering-level simulation methods cannot predict these patterns with adequate confidence, highfidelity methods that include all relevant physics are necessary to accurately predict the projectile trajectories at the conclusion of the interference-dominated flight phase. Newly developed capabilities in the Loci/CHEM framework have enabled multiple-body proximate flight simulations including high-fidelity aerodynamics with six degrees of freedom modeling and collision response that are well-suited for simulation of large numbers of projectiles. Unlike many approaches for moving body simulation, the approach presented here utilizes unstructured overset grids with fully automatic grid assembly and no ancillary preprocessing requirements beyond those necessary for static body simulation. The solution methodology and collision modeling capabilities are described in detail. Results are presented for supersonic air-delivered systems with dozens of projectiles in close-proximity released from a carrier vehicle under several different deployment configurations. The results demonstrate the effectiveness of the developed capabilities for simulation of high-speed proximate-flight among many projectiles including strong aerodynamic interference effects and frequent inter-body collisions.

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Multiphysics Simulation Capability using the SIMULIA Co-Simulation Engine

Cited by 53 publications

References 17 publications

Demonstration of Multiphysics Analysis Tools on Representative Hypersonic Vehicle Structures

Demonstration of Multiphysics Analysis Tools on Representative Hypersonic Vehicle Structures

Validation of Overset Discontinuous Galerkin and Hybrid RANS/LES Method for Jet Noise Prediction

Towards a Predictive Capability for Multiple-Body Proximate-Flight in High-Speed Air-Delivered Systems

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