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  • 1
    Publication Date: 2019-07-13
    Description: The DECLIC (Device for the Study of Critical Liquids and Crystalization) Facility was launched to the International Space Station (ISS) on Shuttle flight 17-A (August 2009) and has been in service for a little over three years. Activity from the three originally planned investigations, the HTI (High Temperature Insert) investigation, the ALI (Alice Like Insert) investigation and the DSI (Directional Solidication Insert) investigation has led to fruitful collaborations among a team of scientists, sponsored by NASA and CNES, to extend the utility of the inserts and the breadth of science beyond its initial scope. These follow-on investigations plan to use inserts that have been returned to earth for refurbishment, two of which (i.e., HTI-R and DSI-R) simply entail changing the test sample and the third (i.e., ALI-R) entails a slight hardware modication to allow for precise changes in sample volume. The first investigation, the Supercritical Water Mixture (SCWM) experiment, uses the refurbished HTI-R, which will accommodate a dilute aqueous mixture of Na2SO4 -0.5% w. This investigation will extend earlier observations of pure water at near-critical conditions. The second experiment uses a modified insert, the DSI-R, with a different concentration of succinonitrile-camphor than the original flight sample. This will allow, among other objectives, a detailed study of dendritic sidebranch formation in extended three-dimensional arrays, with the goal of elucidating whether noise amplication and/or a deterministic limit cycle is the main cause of sidebranch formation. The final experiment, the ALI-R, uses a sample cell with variable density to allow for additional observations of thermo-physical properties on SF6 at near critical conditions. The presentation will provide a discussion of the DECLIC facility's hardware, its modied inserts, and an overview of the extended science that will be achieved through these collaborative activities.
    Keywords: Inorganic, Organic and Physical Chemistry
    Type: GRC-E-DAA-TN7149 , E-18609 , 28th Annual Meeting of the American Society for Space and Gravitational Research; Nov 28, 2012 - Dec 02, 2012; New Orleans, LA; United States
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  • 2
    Publication Date: 2019-07-13
    Description: This paper presents development efforts to establish modeling capabilities for launch vehicle liftoff acoustics and ignition transient environment predictions. Peak acoustic loads experienced by the launch vehicle occur during liftoff with strong interaction between the vehicle and the launch facility. Acoustic prediction engineering tools based on empirical models are of limited value in efforts to proactively design and optimize launch vehicles and launch facility configurations for liftoff acoustics. Modeling approaches are needed that capture the important details of the plume flow environment including the ignition transient, identify the noise generation sources, and allow assessment of the effects of launch pad geometric details and acoustic mitigation measures such as water injection. This paper presents a status of the CFD tools developed by the MSFC Fluid Dynamics Branch featuring advanced multi-physics modeling capabilities developed towards this goal. Validation and application examples are presented along with an overview of application in the prediction of liftoff environments and the design of targeted mitigation measures such as launch pad configuration and sound suppression water placement.
    Keywords: Acoustics
    Type: M11-1288 , M12-1816 , M12-1860 , 18th AIAA/CEAS Aeroacoustics Conference; Jun 04, 2012 - Jun 06, 2012; Colorado Springs, CO; United States|33rd AIAA Aeroacoustics Conference; Jun 04, 2012 - Jun 06, 2012; Colorado Springs, CO; United States
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  • 3
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: M11-1228 , 162 ASA Meeting and Noise-Con 2011; Oct 31, 2011 - Nov 04, 2011; San Diego, CA; United States
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  • 4
    Publication Date: 2019-07-19
    Description: The Ares I Scale Model Acoustics Test (ASMAT) is a series of live-fire tests of scaled rocket motors meant to simulate the conditions of the Ares I launch configuration. These tests have provided a well documented set of high fidelity acoustic measurements useful for validation including data taken over a range of test conditions and containing phenomena like Ignition Over-Pressure and water suppression of acoustics. To take advantage of this data, a digital representation of the ASMAT test setup has been constructed and test firings of the motor have been simulated using the Loci/CHEM computational fluid dynamics software. Results from ASMAT simulations with the rocket in both held down and elevated configurations, as well as with and without water suppression have been compared to acoustic data collected from similar live-fire tests. Results of acoustic comparisons have shown good correlation with the amplitude and temporal shape of pressure features and reasonable spectral accuracy up to approximately 1000 Hz. Major plume and acoustic features have been well captured including the plume shock structure, the igniter pulse transient, and the ignition overpressure.
    Keywords: Acoustics
    Type: M11-0744 , 162nd ASA Meeting and Noise-Con 2011; Oct 31, 2011 - Nov 04, 2011; San Diego, CA; United States
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  • 5
    Publication Date: 2019-07-19
    Description: This paper presents development efforts at the NASA Marshall Space flight Center to establish a hybrid Computational Fluid Dynamics and Computational Aero-Acoustics (CFD/CAA) simulation system for launch vehicle liftoff acoustics environment analysis. Acoustic prediction engineering tools based on empirical jet acoustic strength and directivity models or scaled historical measurements are of limited value in efforts to proactively design and optimize launch vehicles and launch facility configurations for liftoff acoustics. CFD based modeling approaches are now able to capture the important details of vehicle specific plume flow environment, identifY the noise generation sources, and allow assessment of the influence of launch pad geometric details and sound mitigation measures such as water injection. However, CFD methodologies are numerically too dissipative to accurately capture the propagation of the acoustic waves in the large CFD models. The hybrid CFD/CAA approach combines the high-fidelity CFD analysis capable of identifYing the acoustic sources with a fast and efficient Boundary Element Method (BEM) that accurately propagates the acoustic field from the source locations. The BEM approach was chosen for its ability to properly account for reflections and scattering of acoustic waves from launch pad structures. The paper will present an overview of the technology components of the CFD/CAA framework and discuss plans for demonstration and validation against test data.
    Keywords: Physics (General)
    Type: M11-0749 , 162nd Acoustical Society of America (ASA) Meeting; Oct 31, 2011 - Nov 04, 2011; San Diego, CA; United States
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  • 6
    Publication Date: 2019-08-13
    Description: The Ares I Scale Model Acoustics Test (ASMAT) is a series of live-fire tests of scaled rocket motors meant to simulate the conditions of the Ares I launch configuration. These tests have provided a well documented set of high fidelity measurements useful for validation including data taken over a range of test conditions and containing phenomena like Ignition Over-Pressure and water suppression of acoustics. Building on dry simulations of the ASMAT tests with the vehicle at 5 ft. elevation (100 ft. real vehicle elevation), wet simulations of the ASMAT test setup have been performed using the Loci/CHEM computational fluid dynamics software to explore the effect of rainbird water suppression inclusion on the launch platform deck. Two-phase water simulation has been performed using an energy and mass coupled lagrangian particle system module where liquid phase emissions are segregated into clouds of virtual particles and gas phase mass transfer is accomplished through simple Weber number controlled breakup and boiling models. Comparisons have been performed to the dry 5 ft. elevation cases, using configurations with and without launch mounts. These cases have been used to explore the interaction between rainbird spray patterns and launch mount geometry and evaluate the acoustic sound pressure level knockdown achieved through above-deck rainbird deluge inclusion. This comparison has been anchored with validation from live-fire test data which showed a reduction in rainbird effectiveness with the presence of a launch mount.
    Keywords: Acoustics
    Type: M11-0657 , JANNAF 5th Spacecraft Propulsion Subcommittee Meeting; Dec 05, 2012 - Dec 09, 2012; Huntsville, AL; United States|JANNAF 6th Liquid Propulsion Subcommittee Meeting; Dec 05, 2012 - Dec 09, 2012; Huntsville, AL; United States|JANNAF 8th Modeling and Simulation Subcommittee Meeting; Dec 05, 2012 - Dec 09, 2012; Huntsville, AL; United States
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  • 7
    Publication Date: 2019-08-13
    Description: Since the Columbia accident, the threat to the Shuttle launch vehicle from debris during the liftoff timeframe has been assessed by the Liftoff Debris Team at NASA/MSFC. In addition to engineering methods of analysis, CFD-generated flow fields during the liftoff timeframe have been used in conjunction with 3-DOF debris transport methods to predict the motion of liftoff debris. Early models made use of a quasi-steady flow field approximation with the vehicle positioned at a fixed location relative to the ground; however, a moving overset mesh capability has recently been developed for the Loci/CHEM CFD software which enables higher-fidelity simulation of the Shuttle transient plume startup and liftoff environment. The present work details the simulation of the launch pad and mobile launch platform (MLP) with truncated solid rocket boosters (SRBs) moving in a prescribed liftoff trajectory derived from Shuttle flight measurements. Using Loci/CHEM, time-accurate RANS and hybrid RANS/LES simulations were performed for the timeframe T0+0 to T0+3.5 seconds, which consists of SRB startup to a vehicle altitude of approximately 90 feet above the MLP. Analysis of the transient flowfield focuses on the evolution of the SRB plumes in the MLP plume holes and the flame trench, impingement on the flame deflector, and especially impingment on the MLP deck resulting in upward flow which is a transport mechanism for debris. The results show excellent qualitative agreement with the visual record from past Shuttle flights, and comparisons to pressure measurements in the flame trench and on the MLP provide confidence in these simulation capabilities.
    Keywords: Space Transportation and Safety
    Type: M11-0654
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  • 8
    Publication Date: 2019-08-13
    Description: The Ares I Scale Model Acoustics Test (ASMAT) is a series of live-fire tests of scaled rocket motors meant to simulate the conditions of the Ares I launch configuration. These tests have provided a well documented set of high fidelity measurements useful for validation including data taken over a range of test conditions and containing phenomena like Ignition Over-Pressure and water suppression of acoustics. Expanding from initial simulations of the ASMAT setup in a held down configuration, simulations have been performed using the Loci/CHEM computational fluid dynamics software for ASMAT tests of the vehicle at 5 ft. elevation (100 ft. real vehicle elevation) with worst case drift in the direction of the launch tower. These tests have been performed without water suppression and have compared the acoustic emissions for launch structures with and without launch mounts. In addition, simulation results have also been compared to acoustic and imagery data collected from similar live-fire tests to assess the accuracy of the simulations. Simulations have shown a marked change in the pattern of emissions after removal of the launch mount with a reduction in the overall acoustic environment experienced by the vehicle and the formation of highly directed acoustic waves moving across the platform deck. Comparisons of simulation results to live-fire test data showed good amplitude and temporal correlation and imagery comparisons over the visible and infrared wavelengths showed qualitative capture of all plume and pressure wave evolution features.
    Keywords: Acoustics
    Type: M11-0653 , JANNAF 5th Spacecraft Propulsion Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States|JANNAF 6th Liquid Propulsion Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States|JANNAF 8th Modeling and Simulation Subcommittee Meeting; Dec 05, 2011 - Dec 09, 2011; Huntsville, AL; United States
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  • 9
    Publication Date: 2020-01-04
    Description: No abstract available
    Keywords: Life Sciences (General)
    Type: M19-7792 , Annual Meeting of the American Society for Gravitational and Space Research (ASGSR); Nov 20, 2019 - Nov 23, 2019; Washington, DC; United States
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  • 10
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: M11-1234 , 2nd Workshop on Lunar and Martian Plume Effects and Mitigation; Jan 20, 2012 - Jan 21, 2012; NASA Kennedy Space Center, FL; United States
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