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  • Spacecraft Propulsion and Power  (13)
  • Space Transportation and Safety  (5)
  • 1240,  (3)
  • 2005-2009  (21)
  • 1
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    Radioisotope Electric Propulsion Centaur Orbiter Spacecraft Design Overview (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Radioisotope electric propulsion (REP) has been shown in past studies to enable missions to outerplanetary bodies including the orbiting of Centaur asteroids. Key to the feasibility for REP missions are long life, low power electric propulsion (EP) devices, low mass radioisotope power systems (RPS) and light spacecraft (S/C) components. In order to determine what are the key parameters for EP devices to perform these REP missions a design study was completed to design an REP S/C to orbit a Centaur in a New Frontiers cost cap. The design shows that an orbiter using several long lived (approximately 200 kg Xenon throughput), low power (approximately 700 W) Hall thrusters teamed with six (150 W each) Advanced Stirling Radioisotope Generators (ASRG) can deliver 60 kg of science instruments to a Centaur in 10 yr within the New Frontiers cost cap. Optimal specific impulses for the Hall thrusters were found to be around 2000 sec with thruster efficiencies over 40%. Not only can the REP S/C enable orbiting a Centaur (when compared to an all chemical mission only capable of flybys) but the additional power from the REP system can be reused to enhance science and simplify communications.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2009-215488 , AIAA Paper 2008-5179 , E-16578-1 , 44th Joint Propulsion Conference and Exhibit; Jul 21, 2008 - Jul 23, 2008; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Static stress change from the 8 October, 2005 M = 7.6 Kashmir earthquake (2006)
    In:  Geophys. Res. Lett., Philadelphia, 4, vol. 33, no. 6, pp. 1063-1066, pp. L06304, (ISSN: 1340-4202)
    Details
    Publication Date: 2006
    Keywords: Stress ; Coulomb ; Earthquake ; Pakistan ; India ; GRL ; 7215 ; Seismology: ; Earthquake ; source ; observations ; (1240) ; 7223 ; Earthquake ; interaction, ; forecasting, ; and ; prediction ; (1217, ; 1242) ; 7230 ; Seismicity ; and ; tectonics ; (1207, ; 1217, ; 1240, ; 1242) ; 8164 ; Tectonophysics: ; Stresses: ; crust ; and ; lithosphere ; FROTH ; CMILKEREIT
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    A hypothesis for delayed dynamic earthquake triggering (2005)
    In:  Geophys. Res. Lett., Philadelphia, 4, vol. 32, no. 4, pp. 1063-1066, pp. L04302, (ISSN: 1340-4202)
    Details
    Publication Date: 2005
    Keywords: Stress ; Seismicity ; Dynamic ; Waves ; Aftershocks ; Friction ; Fault zone ; Physical properties of rocks ; Omori ; GRL ; 7209 ; Seismology: ; Earthquake ; dynamics ; (1242) ; 7223 ; Earthquake ; interaction, ; forecasting, ; and ; prediction ; (1217, ; 1242) ; 7230 ; Seismicity ; and ; tectonics ; (1207, ; 1217, ; 1240, ; 1242) ; 7260 ; Theory
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Tectonic stressing in California modeled from Global Positioning System observations (2006)
    In:  J. Geophys. Res., Philadelphia, 4, vol. 111, no. B3, pp. 1063-1066, pp. B03407, (ISSN: 1340-4202)
    Details
    Publication Date: 2006
    Keywords: Stress ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Finite Element Method ; Modelling ; Coulomb ; Fort ; Tejon ; JGR ; stressing ; rate ; finite ; element ; model ; Global Positioning System ; 1209 ; Geodesy ; and ; Gravity: ; Tectonic ; deformation ; (6924) ; 7230 ; Seismology: ; Seismicity ; and ; tectonics ; (1207, ; 1217, ; 1240, ; 1242) ; 8106 ; Tectonophysics: ; Continental ; margins: ; transform ; 8164 ; Stresses: ; crust ; and ; lithosphere
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    The development of a bismuth feed system for the very high Isp thruster with anode layer VHITAL program (2005)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: A bismuth feed system was developed for the VHITAL Program to deliver 8-12 mg/s of bismuth vapor at a few Torr to the VHITAL-160. A carbon vaporizer developed to control vapor flow rates to the thruster.
    Keywords: Spacecraft Propulsion and Power
    Type: International Electric Propulsion Conference 2005
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Advanced Development Program for a 625 lbf thrust engine for Ares First Stage Roll Control System (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-19
    Description: NASA's new Ares Launch Vehicle will require twelve thrusters to provide roll control of the vehicle during the first stage firing. All twelve roll control thrusters will be located at the inter-stage segment that separates the solid rocket booster first stage from the second stage. NASA selected a mono propellant hydrazine solution and as a result awarded Aerojet-General a contract in 2007 for an advanced development program for an MR-80- series 625 Ibf vacuum thrust monopropellant hydrazine thruster. This thruster has heritage dating back to the 1976 Viking Landers and most recently for the 2011 Mars Science Laboratory. Prior to the Ares application, the MR-80-series thrusters had been equipped with throttle valves and not typically operated in pulse mode. The primary objective of the advanced development program was to increase the technology readiness level and retire major technical risks for the future flight qualification test program. Aerojet built on their heritage MR-80 rocket engine designs to achieve the design and performance requirements. Significant improvements to cost and lead-time were achieved by applying Design for Manufacturing and Assembly (DFMA) principles. AerojetGeneral has completed Preliminary and Critical Design Reviews, followed by two successful rocket engine development test programs. The test programs included qualification random vibration and firing lite that significantly exceed the flight qualification requirements. This paper discusses the advanced development program and the demonstrated capability of the MR-80C engine. Y;
    Keywords: Spacecraft Propulsion and Power
    Type: M10-0087 , 46th AIAA Joint Propulsion Conference; Jul 25, 2010 - Jul 28, 2010; Nashville, TN; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    NASA Expendable Launch Vehicle (ELV) Payload Safety Review Process (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Issues addressed by this program: (1) Complicated roles and responsibilities associated with multi-partner projects (2) Working relationships and communications between all organizations involved in the payload safety process (3) Consistent interpretation and implementation of safety requirements from one project to the rest (4) Consistent implementation of the Tailoring Process (5) Clearly defined NASA decision-making-authority (6) Bring Agency-wide perspective to each ElV payload project. Current process requires a Payload Safety Working Group (PSWG) for eac payload with representatives from all involved organizations.
    Keywords: Space Transportation and Safety
    Type: KSC-2008-055
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    NASA ELV Payload Safety Program Information Exchange (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This presentation details the Expendable Launch Vehicle (ELV) Payload Safety Program in its development and plan for implementation. It is an overview of the program's policies, process and requirements.
    Keywords: Space Transportation and Safety
    Type: KSC-2007-028
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Composite Tank Technologies Development (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The need for cryogenic fuel tanks continues to expand, and research at NASA Marshall Space Flight Center (MSFC) is addressing these needs. This viewgraph presentation provides an overview of composite tank development, including tank testing, cryogenic materials research, tank liners, and dual-walled tanks, at MSFC.
    Keywords: Spacecraft Propulsion and Power
    Type: SAMPE Conference; May 02, 2005 - May 06, 2005; Long Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Landing and Population Hazard Analysis for Stardust Entry in Operations and Entry Planning (2006)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Stardust is a comet sample return mission that successfully returned to Earth on January 15, 2006. Stardust's targeted landing area was the Utah Test and Training Range in the Northwest corner of Utah. Requirements for the risks associated with landing were levied on Stardust by the Utah Test and Training Range and NASA. This paper describes the analysis to verify that these requirements were met and and includes calculation of debris survivability, generation of landing site selection plots, and identification of keep-out zones, as well as appropriate selection of the landing site. Operationally the risk requirements were all met for both of the GOMO-GO polls, so entry was authorized.
    Keywords: Space Transportation and Safety
    Type: AIAA/AAS Astrodynamics Specialist Conference; Aug 20, 2006 - Aug 25, 2006; Keystone, Co; United States
    Format: text
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    NASA TECHNICAL REPORTS
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