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  • Spacecraft Propulsion and Power  (208)
  • 2000-2004  (208)
  • 1990-1994
  • 1940-1944
  • 2002  (208)
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  • 2000-2004  (208)
  • 1990-1994
  • 1940-1944
Year
  • 1
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    Stirling Technology Development at NASA GRC (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The Department of Energy, Stirling Technology Company (STC), and NASA Glenn Research Center (NASA Glenn) are developing a free-piston Stirling convertor for a high-efficiency Stirling Radioisotope Generator (SRG) for NASA Space Science missions. The SRG is being developed for multimission use, including providing electric power for unmanned Mars rovers and deep space missions. NASA Glenn is conducting an in-house technology project to assist in developing the convertor for space qualification and mission implementation. Recent testing, of 55-We Technology Demonstration Convertors (TDC's) built by STC includes mapping, of a second pair of TDC's, single TDC testing, and TDC electromagnetic interference and electromagnetic compatibility characterization on a nonmagnetic test stand. Launch environment tests of a single TDC without its pressure vessel to better understand the convertor internal structural dynamics and of dual-opposed TDC's with several engineering mounting structures with different natural frequencies have recently been completed. A preliminary life assessment has been completed for the TDC heater head, and creep testing of the IN718 material to be used for the flight convertors is underway. Long-term magnet aging tests are continuing to characterize any potential aging in the strength or demagnetization resistance of the magnets used in the linear alternator (LA). Evaluations are now beginning on key organic materials used in the LA and piston/rod surface coatings. NASA Glenn is also conducting finite element analyses for the LA, in part to look at the demagnetization margin on the permanent magnets. The world's first known integrated test of a dynamic power system with electric propulsion was achieved at NASA Glenn when a Hall-effect thruster was successfully operated with a free-piston Stirling power source. Cleveland State University is developing a multidimensional Stirling computational fluid dynamics code to significantly improve Stirling loss predictions and assist in identifying convertor areas for further improvements. This paper will update the status and results for these efforts.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2001-211315/REV1 , E-13119/REV1 , NAS 1.15:211315/REV1 , Space Technology and Applications International Forum; Feb 03, 2002 - Feb 07, 2002; Albuquerque, NM; United States
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    NASA TECHNICAL REPORTS
  • 2
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    Ram Burn Observations (RAMBO) (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-08-15
    Description: Ram Burn Observations (RAMBO) is a Department of Defense experiment that observes shuttle Orbital Maneuvering System engine burns for the purpose of improving plume models. On STS-107 the appropriate sensors will observe selected rendezvous and orbit adjust burns.
    Keywords: Spacecraft Propulsion and Power
    Type: STS 107 Shuttle Press Kit: Providing 24/7 Space Science Research; 96
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    NASA TECHNICAL REPORTS
  • 3
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    Gyro-based Maximum-Likelihood Thruster Fault Detection and Identification (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: When building smaller, less expensive spacecraft, there is a need for intelligent fault tolerance vs. increased hardware redundancy. If fault tolerance can be achieved using existing navigation sensors, cost and vehicle complexity can be reduced. A maximum likelihood-based approach to thruster fault detection and identification (FDI) for spacecraft is developed here and applied in simulation to the X-38 space vehicle. The system uses only gyro signals to detect and identify hard, abrupt, single and multiple jet on- and off-failures. Faults are detected within one second and identified within one to five accords,
    Keywords: Spacecraft Propulsion and Power
    Type: 2002 American Control Conference; May 08, 2002 - May 10, 2002; Anchorage, AL; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Space Solar Power Demonstrations: Challenges and Progress (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-08-14
    Description: The prospects of using electrical power beamed from space are coming closer to reality with the continued pursuit and improvements in the supporting space solar research and technology. Space Solar Power (SSP) has been explored off and on for approximately three decades as a viable alternative and clean energy source. Results produced through the more recent Space Solar Power Exploratory Research and Technology (SERT) program involving extensive participation by industry, universities, and government has provided a sound technical basis for believing that technology can be improved to the extent that SSP systems can be built, economically feasible, and successfully deployed in space. Considerable advancements have been made in conceptual designs and supporting technologies including solar power generation, wireless power transmission, power management distribution, thermal management and materials, and the integrated systems engineering assessments. Basic technologies have progressed to the point were the next logical step is to formulate and conduct sophisticated demonstrations involving prototype hardware as final proof of concepts and identify high end technology readiness levels in preparation for full scale SSP systems designs. In addition to continued technical development issues, environmental and safety issues must be addressed and appropriate actions taken to reassure the public and prepare them for the future use of this alternative renewable energy resource. Accomplishing these objectives will allow informed future decisions regarding further SSP and related R&D investments by both NASA management and prospective external partners. In particular, accomplishing these objectives will also guide further definition of SSP and related technology roadmaps including performance objectives, resources and schedules; including 'multi-purpose' applications (terrestrial markets, science, commercial development of space, and other government missions).
    Keywords: Spacecraft Propulsion and Power
    Type: 53rd International Astro. Congress; Oct 10, 2002 - Oct 19, 2002; Houston, TX; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Space Solar Power Technology Demonstration for Lunar Polar Applications: Laser-Photovoltaic Wireless Power Transmission (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Space Solar Power technology offers unique benefits for near-term NASA space science missions, which can mature this technology for other future applications. "Laser-Photo-Voltaic Wireless Power Transmission" (Laser-PV WPT) is a technology that uses a laser to beam power to a photovoltaic receiver, which converts the laser's light into electricity. Future Laser-PV WPT systems may beam power from Earth to satellites or large Space Solar Power satellites may beam power to Earth, perhaps supplementing terrestrial solar photo-voltaic receivers. In a near-term scientific mission to the moon, Laser-PV WPT can enable robotic operations in permanently shadowed lunar polar craters, which may contain ice. Ground-based technology demonstrations are proceeding, to mature the technology for this initial application, in the moon's polar regions.
    Keywords: Spacecraft Propulsion and Power
    Type: International Astronautical Congress; Oct 17, 2002; Houston, TX; United States
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    NASA TECHNICAL REPORTS
  • 6
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    In-Space Propulsion Program Overview and Status (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-08-14
    Description: NASA's In-Space Propulsion (ISP) Program is designed to develop advanced propulsion technologies that can enable or greatly enhance near and mid-term NASA science missions by significantly reducing cost, mass, and/or travel times. These technologies include: Electric Propulsion (Solar and Nuclear Electric) [note: The Nuclear Electric Propulsion work will be transferred to the NSI program in FY03]; Propellantless Propulsion (aerocapture, solar sails, plasma sails, and momentum exchange tethers); Advanced Chemical Propulsion. The ISP approach to identifying and prioritizing these most promising technologies is to use mission analysis and subsequent peer review. These technologies under consideration are mid-Technology Readiness Level (TRL) up to TRL-6 for incorporation into mission planning within three - five years of initiation. In addition, maximum use of open competition is encouraged to seek optimum solutions under ISP. Several NASA Research Announcements (NRAs) have been released asking industry, academia and other organizations to propose propulsion technologies designed to improve our ability to conduct scientific study of the outer planets and beyond. The ISP Program is managed by NASA HQ (Headquarters) and implemented by the Marshall Space Flight Center in Huntsville, Alabama.
    Keywords: Spacecraft Propulsion and Power
    Type: 28th International Electric Propulsion Conference (IEPC); Mar 17, 2003 - Mar 21, 2003; Toulouse; France
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    NASA TECHNICAL REPORTS
  • 7
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    Power Control and Monitoring Requirements for Thermal Vacuum/Thermal Balance Testing of the MAP Observatory (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The specific heater control requirements for the thermal vacuum and thermal balance testing of the Microwave Anisotropy Probe (MAP) Observatory at the Goddard Space Flight Center (GSFC) in Greenbelt, Maryland are described. The testing was conducted in the 10m wide x 18.3m high Space Environment Simulator (SES) Thermal Vacuum Facility. The MAP thermal testing required accurate quantification of spacecraft and fixture power levels while minimizing heater electrical emissions. The special requirements of the MAP test necessitated construction of five (5) new heater racks.
    Keywords: Spacecraft Propulsion and Power
    Type: 22nd IEST-NASA/ASTM/AIAA/CSA Space Simulation Conference; Oct 21, 2002 - Oct 24, 2002
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    NASA TECHNICAL REPORTS
  • 8
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    Turbulent Mixing of Primary and Secondary Flow Streams in a Rocket-Based Combined Cycle Engine (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This viewgraph presentation gives an overview of the turbulent mixing of primary and secondary flow streams in a rocket-based combined cycle (RBCC) engine. A significant RBCC ejector mode database has been generated, detailing single and twin thruster configurations and global and local measurements. On-going analysis and correlation efforts include Marshall Space Flight Center computational fluid dynamics modeling and turbulent shear layer analysis. Potential follow-on activities include detailed measurements of air flow static pressure and velocity profiles, investigations into other thruster spacing configurations, performing a fundamental shear layer mixing study, and demonstrating single-shot Raman measurements.
    Keywords: Spacecraft Propulsion and Power
    Type: JANNAF 38th Combustion Subcommittee Meeting; Apr 08, 2002 - Apr 12, 2002; Destin, FL; United States
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    NASA TECHNICAL REPORTS
  • 9
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    Design and Study of a LOX/GH2 Throttleable Swirl Injector for Rocket Applications (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A LOX/GH2 swirl injector was designed for a 10:1 propellant throttling range. To accomplish this, a dual LOX (liquid oxygen) manifold was used feeding a single common vortex chamber of the swirl element. Hot-fire experiments were conducting for rocket chamber pressures from 80 to 800 psia at a mixture ratio of nominally 6.0 using steady flow, single-point-per-firing cases as well as dynamic throttling conditions. Low frequency (mean) and high frequency (fluctuating) pressure transducer data, flow meter measurements, and Raman spectroscopy images for mixing information were obtained. The injector design, experimental setup, low frequency pressure data, and injector performance analysis will be presented. C efficiency was very high (approximately 100%) at the middle of the throttle-able range with somewhat lower performance at the high and low ends. From the analysis of discreet steady state operating conditions, injector pressure drop was slightly higher than predicted with an inviscid analysis, but otherwise agreed well across the design throttling range. Analysis of the dynamic throttling data indicates that the injector may experience transient conditions that effect pressure drop and performance when compared to steady state results.
    Keywords: Spacecraft Propulsion and Power
    Type: 2002 JANNAF 38th Combustion Subcommittee Meeting; Apr 08, 2002 - Apr 12, 2002; Destin, FL; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Measurement of Doubly Charged Ions in Ion Thruster Plumes (2002)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The ratio of doubly to singly charged ions was measured in the plumes of a 30 cm and of a 40 cm ion thruster. The measured ratio was correlated with observed erosion rates and thruster operating conditions. The measured and calculated erosion rates paralleled variation in the j(sup ++)/j(sup +) ratio and indicated that the erosion was dominated by Xe III. Simple models of cathode potential surfaces which were developed in support of this work were in agreement with this conclusion and provided a predictive capability of the erosion given the ratio of doubly to singly charged ion currents.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2002-211295 , E-13098 , NAS 1.15:211295 , IEPC-01-310 , 27th International Electric Propulsion Conference; Oct 14, 2001 - Oct 19, 2001; Pasadena, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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