Validation of Fluid-Structure Interaction Capabilities in US3D.

Gidzak, Vladimyr M.; Candler, Graham V.

doi:10.2514/6.2011-2543

Cited by 5 publications

(4 citation statements)

References 5 publications

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“…A good example of this is the work done by Stein et al [7]. References [8][9][10][11][12][13][14] present similar CFD analyses. The CFD approaches all require extensive computation time and are configuration specific, with the accompanying need for complex grid generation and many empirical inputs to the theory.…”

Section: Review Of Theories and Experimentsmentioning

confidence: 88%

Modification of Parachute Canopy Stiffness Scaling Laws for Opening Time Prediction

Niemi

Bevillard

2015

Journal of Aircraft

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Nomenclature a = acoustic speed C eff = effective porosity of fabric D, D o = parachute constructed diameter or characteristic dimension D max = maximum open mouth diameter in hang test D z = suspension line damping factor; dD o ∕m l V s d = diameter of fabric yarns, or suspension line damping coefficient E = elastic modulus of fabric EI = flexural rigidity of canopy e c = nondimensional canopy rigidity; EI∕ρV 2 D 4 e s = nondimensional suspension line elasticity; k∕ρV 2 D F p = peak force on payload F r = Froude number; V 2 s ∕gD F z = suspension line elastic factor; kD 2 o ∕m l V 2 s g = acceleration due to gravity K p = parachute spring constant k = suspension line spring constant M = Mach number; V∕a M r;l = mass ratio based on payload mass; m l ∕ρD 3 M r;p = mass ratio based on parachute mass (canopy and lines); m p ∕ρD 3 M r;T = mass ratio based on total system mass; m T ∕ρD 3 m l = payload mass m p = parachute mass (canopy and lines) m T = total system mass q s = dynamic pressure at parachute snatch; 1∕2ρV 2 s R = canopy Reynolds number; ρVD∕μ R f = fabric Reynolds number based on yarn diameter; ρVd∕μ S = canopy projected area t = thickness of fabric, or canopy opening time t f = filling time of canopy V = velocity V s = snatch velocity W c = weight of canopy w cl = weight per unit area of fabric X p = nondimensional opening shock; F p ∕m l g β o = semiaperture angle between suspension lines γ o = initial trajectory angle ζ = effective stiffness index of parachute η = canopy stiffness index μ = dynamic viscosity of air ν = Poisson's ratio of fabric ρ = air density σ = modified stiffness index τ = nondimensional opening time; V s t∕D τ f = nondimensional filling time; V s t f ∕D

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Section: Review Of Theories and Experimentsmentioning

confidence: 88%

Modification of Parachute Canopy Stiffness Scaling Laws for Opening Time Prediction

Niemi

Bevillard

2015

Journal of Aircraft

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“…13 It uses an orthotropic stress-strain relation to compute traction forces within the material. These tractions, along with the aerodynamic loads are then used to integrate forward the velocity and displacement of the parachute using an explicit RK3 scheme.…”

Section: Preliminary Structural Responsementioning

confidence: 99%

Simulation of Drogue Parachute for the Multi-Purpose Crew Vehicle using Computational Fluid Dynamics

Dinzl

Gidzak

Candler³

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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Simulations of a 10% scale Multi-Purpose Crew Vehicle and its drogue parachute were carried out using US3D, a finite-volume computational fluid dynamics code, with capsule angles of attack at 0, 30 and 50 degrees. A model for the geometric porosity of the parachute is incorporated which locally varies the mass flux through the surface based on the instantaneous flowfield. These simulations were then compared to wind tunnel tests, including mean drag measurements and particle image velocimetry data. It was found that the simulations matched the wind tunnel drag within 4% for α = 0 and 30 • with the maximum drag deficit due to the capsule being 13.4% at α = 0 • . Pressure data from the simulations was used to deform a structural model of the parachute to the correct inflated shape, as a precursor to future fluid structural interaction work.

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“…In non-near-wall regions, the grid deforms through a combination of rigid-body translation, rigid-body rotation, and compression. 44 The grid deformation is enforced at grid nodes, not at element centroids, which is crucial for maintaining grid quality and preventing high-frequency instabilities in the grid.…”

Section: Iiig Unsteady Grid Motionmentioning

confidence: 99%

Development of the US3D Code for Advanced Compressible and Reacting Flow Simulations

Candler

Johnson²,

Nompelis³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

147

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Aerothermodynamics and hypersonic flows involve complex multi-disciplinary physics, including finite-rate gas-phase kinetics, finite-rate internal energy relaxation, gas-surface interactions with finite-rate oxidation and sublimation, transition to turbulence, large-scale unsteadiness, shock-boundary layer interactions, fluid-structure interactions, and thermal protection system ablation and thermal response. Many of the flows have a large range of length and time scales, requiring large computational grids, implicit time integration, and large solution run times. The University of Minnesota / NASA US3D code was designed for the simulation of these complex, highly-coupled flows. It has many of the features of NASA's well-established DPLR code, but uses unstructured grids and has many advanced numerical capabilities and physical models for multi-physics problems. The main capabilities of the code are described, the physical modeling approaches are discussed, the different types of numerical flux functions and time integration approaches are outlined, and the parallelization strategy is overviewed. Comparisons between US3D and the NASA DPLR code are presented, along with several advanced simulations to illustrate some novel features of the code.

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Validation of Fluid-Structure Interaction Capabilities in US3D.

Cited by 5 publications

References 5 publications

Modification of Parachute Canopy Stiffness Scaling Laws for Opening Time Prediction

Modification of Parachute Canopy Stiffness Scaling Laws for Opening Time Prediction

Simulation of Drogue Parachute for the Multi-Purpose Crew Vehicle using Computational Fluid Dynamics

Development of the US3D Code for Advanced Compressible and Reacting Flow Simulations

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