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  • 1
    Electronic Resource
    Electronic Resource
    Springer
    Environmental biology of fishes 7 (1982), S. 277-284 
    ISSN: 1573-5133
    Keywords: Compound-dependent response ; Duration of exposure ; Embryonic age ; Embryotoxicity ; 96-h LC50 ; Survival potential
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology
    Notes: Synopsis Embryos in specific stage of the estuarine teleost, Fundulus heteroclitus, were exposed to mercuric chloride (MC) and methylmercuric chloride (MMC) under several distinct treatment conditions. Four-eight cell stage eggs (0-day old) were exposed for 4 days (continuous), 2 days and one day to each mercury compound. One-day old (mid-blastula), 2-day old (mid-neurula) and 5-day old (beating heart) embryos were exposed 4 days to MC and MMC. Mortality for the four days immediately following the initiation of exposure was the embryonic response measured. Under most exposure conditions to the 4–8 cell eggs, progressive and significant reductions in survival were observed at all concentrations above 40 and 30 μgHg++l−1 as MC and MMC, respectively. Reducing the duration of exposure to 1 day most significantly increased the survival potential of the 4–8 cell eggs. For all exposure treatments to the 4–8 cell eggs, significant differences in survival, between eggs exposed to MC and MMC, were determined at 40, 60 and 80 μgHg++l−1, indicating the presence of compound-dependent response differences. In all cases demonstrating response differences between MC and MMC exposed embryos, survival was significantly lower following exposure to MMC. Survival of embryos was progressively increased when the initiation of continuous exposure (4 days) was delayed 1, 2 and 5 days after fertilization. As a result, compound-dependent response differences were progressively shifted to higher He++ concentrations. For both MC and MMC, survival of 1-day old embryos exposed for 4 days was greater than that of 0-day old eggs exposed for 1 day. Of the embryonic stages examined, it appears that the earlier cleavage stages are the most sensitive to mercury intoxication.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 1980-07-01
    Print ISSN: 0141-1136
    Electronic ISSN: 1879-0291
    Topics: Biology , Energy, Environment Protection, Nuclear Power Engineering , Geosciences
    Published by Elsevier
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  • 3
    Publication Date: 1982-06-01
    Print ISSN: 0378-1909
    Electronic ISSN: 1573-5133
    Topics: Biology
    Published by Springer
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  • 4
    Publication Date: 2016-06-07
    Description: Contents include the following: (1) Introduction: Chandra X-ray observatory. Advanced CCD imaging spectrometer. (2) LEO and transfer orbit analyses: Geometric modeling in TSS w/specularity. Low earth orbital heating calculations. (3) Thermal testing and LMAC. (4) Problem solving. (5) VDA overcoat analyses. (6) VDA overcoat testing and MSFC. (7) Post-MSFC test evaluation.
    Keywords: Instrumentation and Photography
    Type: The Tenth Thermal and Fluids Analysis Workshop; NASA/CP-2001-211141
    Format: application/pdf
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  • 5
    Publication Date: 2019-07-18
    Description: The natural thermal environmental parameters used on the Space Station Program (SSP 30425) were generated by the Space Environmental Effects Branch at NASA's Marshall Space Flight Center (MSFC) utilizing extensive data from the Earth Radiation Budget Experiment (ERBE), a series of satellites which measured low earth orbit (LEO) albedo and outgoing long-wave radiation. Later, this temporal data was presented as a function of averaging times and orbital inclination for use by thermal engineers in NASA Technical Memorandum TM 4527. The data was not presented in a fashion readily usable by thermal engineering modeling tools and required knowledge of the thermal time constants and infrared versus solar spectrum sensitivity of the hardware being analyzed to be used properly. Another TM was recently issued as a guideline for utilizing these environments (NASA/TM-2001-211221) with more insight into the utilization by thermal analysts. This paper gives a top-level overview of the environmental parameters presented in the TM and a study of the effects of implementing these environments on an ongoing MSFC project, the Propulsive Small Expendable Deployer System (ProSEDS), compared to conventional orbital parameters that had been historically used.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Thermal and Fluids Analysis Workshop 2002; Aug 12, 2002 - Aug 16, 2002; Clear Lake, TX; United States
    Format: text
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  • 6
    Publication Date: 2019-07-13
    Description: As part of the aero-thermodynamics team supporting the Columbia Accident Investigation Board (CAB), the Marshall Space Flight Center was asked to perform engineering analyses of internal flows in the port wing. The aero-thermodynamics team was split into internal flow and external flow teams with the support being divided between shorter timeframe engineering methods and more complex computational fluid dynamics. In order to gain a rough order of magnitude type of knowledge of the internal flow in the port wing for various breach locations and sizes (as theorized by the CAB to have caused the Columbia re-entry failure), a bulk venting model was required to input boundary flow rates and pressures to the computational fluid dynamics (CFD) analyses. This paper summarizes the modeling that was done by MSFC in Thermal Desktop. A venting model of the entire Orbiter was constructed in FloCAD based on Rockwell International s flight substantiation analyses and the STS-107 reentry trajectory. Chemical equilibrium air thermodynamic properties were generated for SINDA/FLUINT s fluid property routines from a code provided by Langley Research Center. In parallel, a simplified thermal mathematical model of the port wing, including the Thermal Protection System (TPS), was based on more detailed Shuttle re-entry modeling previously done by the Dryden Flight Research Center. Once the venting model was coupled with the thermal model of the wing structure with chemical equilibrium air properties, various breach scenarios were assessed in support of the aero-thermodynamics team. The construction of the coupled model and results are presented herein.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Thermal and Fluids Analysis Workshop 2003; Aug 18, 2003 - Aug 22, 2003; Hampton, VA; United States
    Format: application/pdf
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  • 7
    Publication Date: 2019-07-17
    Description: Thermal analyses of the Shuttle and Transfer Orbit of the Advanced X-Ray Astrophysics Facility Charge-Coupled Device (CCD) Imaging Spectrometer (ACIS), one of two science instruments on the Chandra X-Ray Observatory, revealed a low-earth orbit (LEO) overheating problem on the goldized Kapton faces of two radiator shades. The shades were coated with the goldized Kapton to provide a low hemispherical emittance to minimize direct and backloaded heating from the sun and the observatory and high specularity to optimize the coupling to space on two passive radiators which cool the focal plane to -120 C +/- 1 C during on-orbit operations. Since the observatory has a highly elliptical final orbit of 10,000 kilometers by 140,000 kilometers and the ACIS radiators and shades are oriented anti-sun, the high solar absorptance to emittance ratio of the goldized Kapton was not an issue. However, during Shuttle bay-to-earth operations, the short duration solar heating occurring near the eclipse entry and exit resulted in shade temperatures in excess of the cure temperature of the adhesive used to bond the goldized Kapton and honeycomb face-sheets. The detailed thermal analysis demonstrating the LEO overheating as well as the redesign options and thermal testing of a redesigned development unit shade are presented.
    Keywords: Instrumentation and Photography
    Type: Thermal and Fluids Analysis; Sep 13, 1999 - Sep 17, 1999; Huntsville, AL; United States
    Format: text
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  • 8
    Publication Date: 2019-07-13
    Description: Most spacecraft thermal analysis tools assume that the spacecraft is in orbit around a planet and are designed to calculate solar and planetary fluxes, as well as radiation to space. On NASA Constellation projects, thermal analysts are also building models of vehicles in their pre-launch condition on the surface of a planet. This process entails making some modifications in the building and execution of a thermal model such that the radiation from the planet, both reflected albedo and infrared, is calculated correctly. Also important in the calculation of pre-launch vehicle temperatures are the natural environments at the vehicle site, including air and ground temperatures, sky radiative background temperature, solar flux, and optical properties of the ground around the vehicle. A group of Constellation projects have collaborated on developing a cohesive, integrated set of natural environments that accurately capture worst-case thermal scenarios for the pre-launch and launch phases of these vehicles. The paper will discuss the standardization of methods for local planet modeling across Constellation projects, as well as the collection and consolidation of natural environments for launch sites. Methods for Earth as well as lunar sites will be discussed.
    Keywords: Lunar and Planetary Science and Exploration
    Type: 2008 Thermal Fluids and Analysis Workshop; Aug 18, 2008 - Aug 22, 2008; San Jose, CA; United States
    Format: application/pdf
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  • 9
    Publication Date: 2019-07-13
    Description: The thermal protection system (TPS) for the Ares-I Upper Stage will be based on Space Transportation System External Tank (ET) and Solid Rocket Booster (SRB) heritage materials. These TPS materials were qualified via hot gas testing that simulated ascent and re-entry aerothermodynamic convective heating environments. From this data, the recession rates due to ablation were characterized and used in thermal modeling for sizing the thickness required to maintain structural substrate temperatures. At Marshall Space Flight Center (MSFC), the in-house code ABL is currently used to predict TPS ablation and substrate temperatures as a FORTRAN application integrated within SINDA/G. This paper describes a comparison of the new ablation utility in Thermal Desktop and SINDA/FLUINT with the heritage ABL code and empirical test data which serves as the validation of the Thermal Desktop software for use on the design of the Ares-I Upper Stage project.
    Keywords: Space Transportation and Safety
    Type: Thermal/Fluids Analysis Workshop (TFAWS); Sep 10, 2007 - Sep 14, 2007; Cleveland, OH; United States
    Format: application/pdf
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  • 10
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    In:  CASI
    Publication Date: 2019-07-13
    Description: As part of a Constellation session at the 2007 Thermal & Fluids Analysis Workshop (TFAWS), an overview of the Crew Launch Vehicle (CLV), Crew Exploration Vehicle (CEV) and Lunar Lander systems will be given. This presentation provides a general description of the CLV (also known as Ares-I)and Ares-V vehicles portion of the session. The presentation will provide an overview of the thermal requirements, design environments, challenges and thermal modeling examples.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Thermal/Fluids Analysis Workshop (TFAWS); Sep 10, 2007 - Sep 14, 2007; Cleveland, OH; United States
    Format: application/pdf
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