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  • 1
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    Crew Launch Vehicle Mobile Launcher Solid Rocket Motor Plume Induced Environment (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The plume-induced environment created by the Ares 1 first stage, five-segment reusable solid rocket motor (RSRMV) will impose high heating rates and impact pressures on Launch Complex 39. The extremes of these environments pose a potential threat to weaken or even cause structural components to fail if insufficiently designed. Therefore the ability to accurately predict these environments is critical to assist in specifying structural design requirements to insure overall structural integrity and flight safety. This paper presents the predicted thermal and pressure environments induced by the launch of the Crew Launch Vehicle (CLV) from Launch Complex (LC) 39. Once the environments are predicted, a follow-on thermal analysis is required to determine the surface temperature response and the degradation rate of the materials. An example of structures responding to the plume-induced environment will be provided.
    Keywords: Space Transportation and Safety
    Type: KSC-2008-155 , 2008 Thermal Fluid Analysis Workshop (TFAWS 08); Aug 18, 2008 - Aug 22, 2008; Moffett Field, CA; United States
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  • 2
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    Multi-Element Unstructured Analyses of Complex Valve Systems (2004)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The safe and reliable operation of high pressure test stands for rocket engine and component testing places an increased emphasis on the performance of control valves and flow metering devices. In this paper, we will present a series of high fidelity computational analyses of systems ranging from cryogenic control valves and pressure regulator systems to cavitating venturis that are used to support rocket engine and component testing at NASA Stennis Space Center. A generalized multi-element framework with sub-models for grid adaption, grid movement and multi-phase flow dynamics has been used to carry out the simulations. Such a framework provides the flexibility of resolving the structural and functional complexities that are typically associated with valve-based high pressure feed systems and have been difficult to deal with traditional CFD methods. Our simulations revealed a rich variety of flow phenomena such as secondary flow patterns, hydrodynamic instabilities, fluctuating vapor pockets etc. In the paper, we will discuss performance losses related to cryogenic control valves, and provide insight into the physics of the dominant multi-phase fluid transport phenomena that are responsible for the choking like behavior in cryogenic control elements. Additionally, we will provide detailed analyses of the modal instability that is observed in the operation of the dome pressure regulator valve. Such instabilities are usually not localized and manifest themselves as a system wide phenomena leading to an undesirable chatter at high flow conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: SSTI-3000-0001-FLUIDS , 52 JANNAF Propulsion Meeting; May 10, 2004 - May 13, 2004; Las Vegas, NV; United States
    Format: application/pdf
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  • 3
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    Computational Analysis of Cryogenic Flow Through a Control Valve (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The initial efforts to develop the capability to model valves used in rocket engine component testing at Stennis Space Center are documented. An axisymmetric model of a control valve with LN2 as the working fluid was developed. The goal was to predict the effect of change in the plug/sear region of the valve prior to testing. The valve flow coefficient was predicted for a range of plug positions. Verification of the calculations was carried out to quantify the uncertainty in the numerical answer. The modeled results compared well qualitatively to experimental trends. Additionally, insights into the flow processes in the valve were obtained. Benefits from the verification process included the ability to use coarser grids and insight into ways to reduce computational time by using double precision accuracy and non-integer grid ratios. Future valve modeling activities will include shape optimization of the valve/seat region and dynamic grid modeling.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: SE-2003-06-00044-SSC , Proceedings of FEDSM''03 4th ASME-JSME Joint Fluids Engineering Conference; Jul 06, 2003 - Jul 11, 2003; Honolulu, HI; United States
    Format: text
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  • 4
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    Progress in Valve Modeling at Stennis Space Center (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Efforts to develop the capability to model values used in testing rocket engine components are documented. Cryogenic liquid and gas valves models are presented.
    Keywords: Spacecraft Propulsion and Power
    Type: SE-2002-12-00080-SSC , 14th Annual Symposium on Propulsion; Dec 10, 2002 - Dec 11, 2002; State College, PA; United States
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  • 5
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    Progress in Valve Modeling at Stennis Space Center (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Understanding valve behavior will aid testing of rocket components at Stennis Space Center. The authors of this viewgraph presentation have developed a computational model for a cryogenic liquid control valve, and a gas pressure regulator valve. The model is a compressible/incompressible pressure-based FDNS code from Marshall Space Flight Center (MSFC). It is a k-epsilon turbulence model with wall functions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: SE-2002-12-00081-SSC , 14th Annual Symposium on Propulsion; Dec 10, 2002 - Dec 11, 2002; State College, PA; United States
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  • 6
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    Computational Modeling of Liquid and Gaseous Control Valves (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In this paper computational modeling efforts undertaken at NASA Stennis Space Center in support of rocket engine component testing are discussed. Such analyses include structurally complex cryogenic liquid valves and gas valves operating at high pressures and flow rates. Basic modeling and initial successes are documented, and other issues that make valve modeling at SSC somewhat unique are also addressed. These include transient behavior, valve stall, and the determination of flow patterns in LOX valves. Hexahedral structured grids are used for valves that can be simplifies through the use of axisymmetric approximation. Hybrid unstructured methodology is used for structurally complex valves that have disparate length scales and complex flow paths that include strong swirl, local recirculation zones/secondary flow effects. Hexahedral (structured), unstructured, and hybrid meshes are compared for accuracy and computational efficiency. Accuracy is determined using verification and validation techniques.
    Keywords: Numerical Analysis
    Type: AIAA Paper 2005-4543 , NASA/NP-2005-07-00065-SSC , 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 10, 2005 - Jul 13, 2005; Tucson, AZ; United States
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  • 7
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    Construction and Utilization of a Beowulf Computing Cluster: A User's Perspective (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Lockheed Martin Space Operations - Stennis Programs (LMSO) at the John C Stennis Space Center (NASA/SSC) has designed and built a Beowulf computer cluster which is owned by NASA/SSC and operated by LMSO. The design and construction of the cluster are detailed in this paper. The cluster is currently used for Computational Fluid Dynamics (CFD) simulations. The CFD codes in use and their applications are discussed. Examples of some of the work are also presented. Performance benchmark studies have been conducted for the CFD codes being run on the cluster. The results of two of the studies are presented and discussed. The cluster is not currently being utilized to its full potential; therefore, plans are underway to add more capabilities. These include the addition of structural, thermal, fluid, and acoustic Finite Element Analysis codes as well as real-time data acquisition and processing during test operations at NASA/SSC. These plans are discussed as well.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TM-2000-210691 , NAS 1.15:210691 , SE-2000-10-00017-SSC
    Format: application/pdf
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