Capsule Abort Recontact Simulation

Pandya, Shishir A.; Onufer, Jeffrey; Chan, William; Klopfer, G. H.

doi:10.2514/6.2006-3324

Cited by 25 publications

(15 citation statements)

References 8 publications

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“…As for the numerical methods (e.g., inviscid and viscous fluxes, and time evolution), LS-FLOW has many options and only the used ones are summarized in Table 2 (for details, see the original literature [21][22][23][24][25][26][27][28][29][30] ). The second order of spatial accuracy, which is usually adopted in aerodynamic simulations for modern rockets 3,9,[11][12][13][14][15] , is achieved. Cell geometrical properties such as volumes and centroids are calculated according to Wang 21 and Shima et al 22 Validation study on "LS-FLOW" was conducted for several benchmark tests in Ref.…”

Section: B Numerical Methodsmentioning

confidence: 99%

“…Similar studies for other rocket configurations were conducted in Refs. [8][9][10][11][12][13][14][15][16], but our work differs from them in the following aspects. Firstly, those studies [8][9][10][11][12][13][14][15][16] presented either of aerodynamic characteristics, flow simulations, or wind-tunnel experiments independently; however, our study shows all those results and relates them together to thoroughly understand detailed flow structure and aerodynamics of the rocket.…”

Section: Introductionmentioning

confidence: 96%

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Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

Kitamura

Nonaka

Kuzuu

et al. 2013

Journal of Spacecraft and Rockets

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The Epsilon Launch Vehicle, successor of M-V rocket which conveyed "MUSES-C (Hayabusa)," is currently under the development in Japan. The Epsilon is also designed for sending scientific satellites to outer space and its first flight is scheduled to be in 2013. In this study, by conducting both numerical simulations and wind tunnel tests, the aerodynamic characteristics and associated flow features of the Epsilon Launch Vehicle are extensively investigated at Mach 1.5. The results provided are axial/normal/side forces, pitching/yawing/ rolling moments, detailed three-dimensional flow structure, along with effects of Reynolds number (between wind-tunnel and flight conditions), Skin Stringers (small devices on the main body), and difference from another configuration called "NextGenEpsilon." This set of data includes unavailable ones at either the experiment standalone or the actual flight. Magnitudes of computed aerodynamic coefficients are in good agreement with the experiment and within the design criteria. According to the results, axial force is not affected by those above-mentioned factors, but local normal force is influenced around Skin Stringers by Reynolds number, and rolling moment can change even its sign. Detailed M x = rolling moment, (y-y cg )f z -(z-z cg )f y ] [N·m] M y = pitching moment, (z-z cg )f x -(x-x cg )f z ] [N·m] M z = yawing moment, (x-x cg )f y -(y-y cg )f x ] [N·m] p = static pressure [Pa] Pr = Prandtl number, 0.72 [-] q = dynamic pressure [Pa] Re = Reynolds number [-] S = reference area, πD 2 /4 [m 2 ] T = temperature [K] u, v, w = velocity components in Cartesian coordinates [m/s] x, y, z = Cartesian coordinates [m] x cg , y cg , z cg = center of gravity coordinates, (0.6363L, 0, 0) [m] x n , y n , z n = normal vector components in Cartesian coordinates [-]  = angle of attack [deg.]  = slip angle [deg.]  = roll angle [deg.]  = specific heat ratio, 1.4 [-]  = thermal conductivity [W/(m·K)]  = (molecular) viscosity [Pa·s]  = density [kg/m 3 ] Subscripts FL = flight condition F = forebody t = turbulent WT = wind-tunnel test condition ∞ = freestream value 0 = initial or stagnation value American Institute of Aeronautics and Astronautics 4

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Section: B Numerical Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 96%

Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

Kitamura

Nonaka

Kuzuu

et al. 2013

Journal of Spacecraft and Rockets

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“…[1][2][3][4][5][6] Over the years, various methods have been developed for domain connectivity or overset grid assembly. [7][8][9][10][11][12][13][14][15] Since both the surface and volume grids are allowed to overlap arbitrarily, grid points that fall inside solid bodies or outside the computational domain need to be identified and excluded from the process of solving the governing field equations.…”

Section: Introductionmentioning

confidence: 99%

Advances in Distance-Based Hole Cuts on Overset Grids

Chan

Pandya

2015

22nd AIAA Computational Fluid Dynamics Conference

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An automatic and efficient method to determine appropriate hole cuts based on distances to the wall and donor stencil maps for overset grids is presented. A new robust procedure is developed to create a closed surface triangulation representation of each geometric component for accurate determination of the minimum hole. Hole boundaries are then displaced away from the tight grid-spacing regions near solid walls to allow grid overlap to occur away from the walls where cell sizes from neighboring grids are more comparable. The placement of hole boundaries is efficiently determined using a mid-distance rule and Cartesian maps of potential valid donor stencils with minimal user input. Application of this procedure typically results in a spatially-variable offset of the hole boundaries from the minimum hole with only a small number of orphan points remaining. Test cases on complex configurations are presented to demonstrate the new scheme.

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“…In this year, the shuttle was phased out and replaced by a new human-rated rocket and crewed capsule, i.e., a new space transportation system (STS) using capsule/rocket configurations such as Apollo and Soyuz. 2,3) There, an advanced abort system such as the Launch Abort System (LAS) is required. In the launch escape system of the Apollo program, the capsule was connected to a rocket.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Supersonic Oscillatory Flow with Strong Interference over a Capsule-shaped Abort System

Wang¹,

Ozawa²,

Nakamura³

2012

Trans. Japan Soc. Aero. S Sci.

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The flow past a capsule-shaped space transportation system (STS) is numerically analyzed using computational fluid dynamics (CFD) for different free stream Mach numbers ranging from 1.2 to 5.0, where a capsule is modeled by a cone, and a rocket by a circular cylinder. The objective of this research is to study Mach number effects on phenomena of the supersonic aerodynamic interference with periodic flow oscillations at supersonic regime. So far we have considered two models: model A (without disk) and model B (with disk). It was found from experimental and computational results that the flow around model A becomes steady, where aerodynamic interaction is not observed, while in model B, flow becomes unsteady with periodic oscillations. This flow oscillation is considered to be a potentially high risk in separation of the capsule and rocket. Therefore, the present study focuses on the unsteady case of model B. Numerical results at M ¼ 3:0 compared well with experimental ones, which validates the present CFD. Time-averaged results are employed to see the whole trajectories of shock waves and the variation in amplitude of flow oscillation during one cycle. Moreover, a fence is proposed as a device to suppress the flow oscillation.

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Capsule Abort Recontact Simulation

Cited by 25 publications

References 8 publications

Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5

Advances in Distance-Based Hole Cuts on Overset Grids

Numerical Investigation of Supersonic Oscillatory Flow with Strong Interference over a Capsule-shaped Abort System

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