Numerical simulation of the integrated space shuttle vehicle in ascent

Buning, Pieter G.; Chiu, Ing-Tsau; Obayashi, Shigeru; Rizk, Yehia M.; Steger, J. L.

doi:10.2514/6.1988-4359

Cited by 154 publications

(53 citation statements)

References 2 publications

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“…Other pioneering work includes that of Starius [6][7][8], Kreiss [9], and Steger et al [10] who referred to the approach as Chimera grids. Since this early work, the overlapping grid technique has been used successfully to solve a wide variety of problems in high-speed reactive flow [2,3,11], reactive and non-reactive multi-material flow [12,13], combustion [14], aerodynamics [15][16][17][18][19][20][21], blood flow [22], flows around ships [23], visco-elastic flows [24], and flows with deforming boundaries [25][26][27], among others. The use of AMR in combination with overlapping grids was considered by Brislawn et al [28], Boden and Toro [29], Meakin [21], Henshaw and Schwendeman [2,3], and Banks et al [12,13].…”

Section: Introductionmentioning

confidence: 99%

Parallel computation of three-dimensional flows using overlapping grids with adaptive mesh refinement

Henshaw¹,

Schwendeman²

2008

Journal of Computational Physics

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This paper describes an approach for the numerical solution of time-dependent partial differential equations in complex three-dimensional domains. The domains are represented by overlapping structured grids, and block-structured adaptive mesh refinement (AMR) is employed to locally increase the grid resolution. In addition, the numerical method is implemented on parallel distributed-memory computers using a domain-decomposition approach. The implementation is flexible so that each base grid within the overlapping grid structure and its associated refinement grids can be independently partitioned over a chosen set of processors. A modified bin-packing algorithm is used to specify the partition for each grid so that the computational work is evenly distributed amongst the processors. All components of the AMR algorithm such as error estimation, regridding, and interpolation are performed in parallel.The parallel time-stepping algorithm is illustrated for initial-boundary-value problems involving a linear advectiondiffusion equation and the (nonlinear) reactive Euler equations. Numerical results are presented for both equations to demonstrate the accuracy and correctness of the parallel approach. Exact solutions of the advection-diffusion equation are constructed, and these are used to check the corresponding numerical solutions for a variety of tests involving different overlapping grids, different numbers of refinement levels and refinement ratios, and different numbers of processors. The problem of planar shock diffraction by a sphere is considered as an illustration of the numerical approach for the Euler equations, and a problem involving the initiation of a detonation from a hot spot in a T-shaped pipe is considered to demonstrate the numerical approach for the reactive case. For both problems, the solutions are shown to be well resolved on the finest grid. The parallel performance of the approach is examined in detail for the shock diffraction problem.

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Section: Introductionmentioning

confidence: 99%

Parallel computation of three-dimensional flows using overlapping grids with adaptive mesh refinement

Henshaw¹,

Schwendeman²

2008

Journal of Computational Physics

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“…27,28 The Chimera overlapping grid approach, combined with the development of the OVERFLOW CFD code, developed by Dr. Pieter Buning, was the first method that could accurately predict the ascent flow field at flight Reynolds Number with all five plumes. 29,30,31,32,33,34 The resulting flow field is shown in Figure 14. The insight obtained into the very complex launch vehicle aerodynamic loads was an essential part of the Performance Enhancement Certification that made the launching of the ISS components possible.…”

Section: B Space Shuttle Launch Vehicle Aerodynamic Issuesmentioning

confidence: 99%

Legacy of the Space Shuttle From an Aerodynamic and Aerothermodynamic Perspective

Martin

2011

AIAA SPACE 2011 Conference &Amp; Exposition

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The development of the Space Shuttle Orbiter thermal protection system heating environment is described from a design stand point that began in the early 1970s. The desire for a light weight, reusable "heat shield" required the development of new technology, relative to previous manned spacecraft, and a systems approach to the design of the vehicle, entry guidance, and thermal protection system. Several unanticipated issues had to be resolved in both the entry and ascent phases of flight, which are discussed at a high level. During the life of the Program, significant improvements in computing power and numerical methods have been applied to Space Shuttle aerodynamic and aerothermodynamic issues, with the Shuttle Program often being the motivation, and or sponsor of the analysis development.

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“…[1][2][3][4][5][6] However, the computational methodology is not as mature for the solution of unsteady flows, which is one of the next big challenges for the CFD community. The unsteadiness could be self-induced, such as for large separated flows, be created by flow control devices, or generated by many other mechanisms.…”

Section: Introductionmentioning

confidence: 99%

Re-evaluation of an Optimized Second Order Backward Difference (BDF2OPT) Scheme for Unsteady Flow Applications

Vatsa

Carpenter

Lockard

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Recent experience in the application of an optimized, second-order, backward-difference (BDF2OPT) temporal scheme is reported. The primary focus of the work is on obtaining accurate solutions of the unsteady Reynolds-averaged Navier-Stokes equations over long periods of time for aerodynamic problems of interest. The baseline flow solver under consideration uses a particular BDF2OPT temporal scheme with a dual-timestepping algorithm for advancing the flow solutions in time. Numerical difficulties are encountered with this scheme when the flow code is run for a large number of time steps, a behavior not seen with the standard secondorder, backward-difference, temporal scheme. Based on a stability analysis, slight modifications to the BDF2OPT scheme are suggested. The performance and accuracy of this modified scheme is assessed by comparing the computational results with other numerical schemes and experimental data.

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Numerical simulation of the integrated space shuttle vehicle in ascent

Cited by 154 publications

References 2 publications

Parallel computation of three-dimensional flows using overlapping grids with adaptive mesh refinement

Parallel computation of three-dimensional flows using overlapping grids with adaptive mesh refinement

Legacy of the Space Shuttle From an Aerodynamic and Aerothermodynamic Perspective

Re-evaluation of an Optimized Second Order Backward Difference (BDF2OPT) Scheme for Unsteady Flow Applications

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