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  • Other Sources  (8)
  • 2015-2019  (5)
  • 2005-2009  (3)
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  • 2015-2019  (5)
  • 2005-2009  (3)
  • 2000-2004
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  • 1
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    Joint Eglin Acoustics Week 2013 Data Report (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Far-field acoustic measurements were obtained for the AH-64D, HH-60M and CV-22B at the Eglin AFB, Test Area C-72, in July/August 2013. The primary purpose for this flight test was to obtain a benchmark database of detailed acoustic source noise characteristics for the aircraft operating at typical mission gross weights over a range of typical mission operating conditions. Data were acquired for a range of steady-state level and descending flight conditions, hover, and a variety of unsteady maneuver conditions. Between 30 and 37 microphones were deployed during these tests. Vehicle position and state data, as well as weather data were acquired simultaneously with the acoustic data. This paper describes the test aircraft, onboard instrumentation, ground instrumentation, and the data acquired. Data from this test are available upon request and review.
    Keywords: Aeronautics (General); Acoustics
    Type: NASA/TM-2017-219681 , AMRDEC-SR-RDMR-AD-17-02 , L-20832 , NF1676L-27413
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  • 2
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    Ribozyme Evolution in an RNA-Mineral World (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Space Sciences (General)
    Type: ARC-E-DAA-TN42113 , Astrobiology Science Conference (AbSciCon 2017); Apr 24, 2017 - Apr 28, 2017; Mesa, AZ; United States
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  • 3
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    Volatile Analysis by Pyrolysis of Regolith (Vapor) on the Moon using Mass Spectrometry (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The identification of lunar resources such as water is a fundamental component of the the NASA Vision for Space Exploration. The Lunar Prospector mission detected high concentrations of hydrogen at the lunar poles that may indicate the presence of water or other volatiles in the lunar regolith [1]. One explanation for the presence of enhanced hydrogen in permanently shadowed crater regions is long term trapping of water-ice delivered by comets, asteroids, and other meteoritic material that have bombarded the Moon over the last 4 billion years [2]. It is also possible that the hydrogen signal at the lunar poles is due to hydrogen implanted by the solar wind which is delayed from diffusing out of the regolith by the cold temperatures [3]. Previous measurements of the lunar atmosphere by the LACE experiment on Apollo 17, suggested the presence of cold trapped vola'tiles that were expelled by solar heating [4]. In situ composition and isotopic analyses of the lunar regolith will be required to establish the abundance, origin, and distribution of water-ice and other volatiles at the lunar poles. Volatile Analysis by Pyrolysis of Regolith (VAPoR) on the Moon using mass spectrometry is one technique that should be considered. The VAPoR pyrolysis-mass spectrometer (pyr-MS) instrument concept study was selected for funding in 2007 by the NASA Lunar Sortie Science Opportunities (LSSO) Program. VAPoR is a miniature version of the Sample Analysis at Mars (SAM) instrument suite currently being developed at NASA Goddard for the 2009 Mars Science Laboratory mission (Fig. 1).
    Keywords: Lunar and Planetary Science and Exploration
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  • 4
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    High Temperature Life Testing of 80Ni-20Cr Wire in a Simulated Mars Atmosphere for the Sample Analysis at Mars (SAM) Instrument Suite Gas Processing System (GPS) Carbon Dioxide Scrubber (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In support of the GPS for the SAM instrument suite built by NASA/GSFC, a life test facility was developed to test the suitability of 80Ni-20Cr alloy wire, 0.0142 cm diameter, for use as a heater element for the carbon dioxide scrubber. The element would be required to operate at 1000 C in order to attain the 800 C required for regeneration of the getter. The element also would need to operate in the Mars atmosphere, which consists mostly of CO2 at pressures between 4 and 12 torr. Data on the high temperature degradation mechanism of 80Ni- 20Cr in low pressure CO2, coupled with the effects of thermal cycling, were unknown. In addition, the influence of work hardening of the wire during assembly and the potential for catastrophic grain growth also were unknown. Verification of the element reliability as defined by the mission goals required the construction of a test facility that would accurately simulate the duty cycles in a simulated Mars atmosphere. The experimental set-up, along with the test protocol and results will be described.
    Keywords: Quality Assurance and Reliability
    Type: 25th Space Simulation Conference/Inst. of Environmental Sciences and Technology; Oct 20, 2008 - Oct 23, 2008; Annapolis, MD; United States
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  • 5
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    Establishing the Response of Low Frequency Auditory Filters (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: The response of auditory filters is central to frequency selectivity of sound by the human auditory system. This is true especially for realistic complex sounds that are often encountered in many applications such as modeling the audibility of sound, voice recognition, noise cancelation, and the development of advanced hearing aid devices. The purpose of this study was to establish the response of low frequency (below 100Hz) auditory filters. Two experiments were designed and executed; the first was to measure subject's hearing threshold for pure tones (at 25, 31.5, 40, 50, 63 and 80 Hz), and the second was to measure the Psychophysical Tuning Curves (PTCs) at two signal frequencies (Fs= 40 and 63Hz). Experiment 1 involved 36 subjects while experiment 2 used 20 subjects selected from experiment 1. Both experiments were based on a 3-down 1-up 3AFC adaptive staircase test procedure using either a variable level narrow-band noise masker or a tone. A summary of the results includes masked threshold data in form of PTCs, the response of auditory filters, their distribution, and comparison with similar recently published data.
    Keywords: Acoustics
    Type: NF1676L-27590 , Meeting of the Acoustical Society of America; Dec 04, 2017 - Dec 08, 2017; New Orleans, LA; United States
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  • 6
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    Sound Diffraction Modeling of Rotorcraft Noise Around Terrain (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A new computational technique, Wave Confinement (WC), is extended here to account for sound diffraction around arbitrary terrain. While diffraction around elementary scattering objects, such as a knife edge, single slit, disc, sphere, etc. has been studied for several decades, realistic environments still pose significant problems. This new technique is first validated against Sommerfeld's classical problem of diffraction due to a knife edge. This is followed by comparisons with diffraction over three-dimensional smooth obstacles, such as a disc and Gaussian hill. Finally, comparisons with flight test acoustics data measured behind a hill are also shown. Comparison between experiment and Wave Confinement prediction demonstrates that a Poisson spot occurred behind the isolated hill, resulting in significantly increased sound intensity near the center of the shadowed region.
    Keywords: Acoustics
    Type: NF1676L-25339 , AHS International Annual Forum and Technology Display; May 09, 2017 - May 11, 2017; Fort Worth, TX; United States
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  • 7
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    Global Exploration Roadmap Derived Concept for Human Exploration of the Moon (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Taking advantage of the development of Mars-forward assets in cislunar space, a human lunar surface concept is proposed to maximize value for both lunar exploration and future deep space missions. The human lunar surface missions will be designed to build upon the cislunar activities that precede them, providing experience in planetary surface operations that cannot be obtained in cislunar space. To enable a five-mission limited campaign to the surface of the Moon, two new elements are required: a human lunar lander and a mobile surface habitat. The human lunar lander will have been developed throughout the cislunar phase from a subscale demonstrator and will consist of a descent module alongside a reusable ascent module. The reusable ascent module will be used for all five human lunar surface missions. Surface habitation, in the form of two small pressurized rovers, will enable 4 crew to spend up to 42 days on the lunar surface.
    Keywords: Spacecraft Design, Testing and Performance; Lunar and Planetary Science and Exploration
    Type: JSC-CN-39682 , Global Space Exploration Conference (GLEX) 2017; Jun 06, 2017 - Jun 08, 2017; Beijing; China
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  • 8
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    Liquid Oxygen/Liquid Methane Ascent Main Engine Technology Development (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LO2)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon the Exploration Systems Architecture Study (ESAS). The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. The current application considering this technology is the lunar ascent main engine (AME). AME is anticipated to be an expendable, pressure-fed engine to provide ascent from the moon at the completion of a 210 day lunar stay. The engine is expected to produce 5,500 lbf (24,465 N) thrust with variable inlet temperatures due to the cryogenic nature of the fuel and oxidizer. The primary technology risks include establishing reliable and robust ignition in vacuum conditions, maximizing specific impulse, developing rapid start capability for the descent abort, providing the capability for two starts and producing a total engine bum time over 500 seconds. This paper will highlight the efforts of the Marshall Space Flight Center (MSFC) in addressing risk reduction activities for this technology.
    Keywords: Spacecraft Propulsion and Power
    Type: IAC-08-C4.1.02 , MSFC-2022 , MSFC-2140 , 59th International Astronautical Conference; Sep 29, 2008 - Oct 03, 2008; Scotland; United Kingdom
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