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  • Propellants and Fuels  (13)
  • Spacecraft Propulsion and Power  (12)
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  • 1
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    IHPRPT Steering Committee Meeting - NASA Spacecraft Propulsion Update (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: The activities and status of NASA Spacecraft Propulsion is presented including recent accomplishments.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN11245 , IHPRPT Steering Committee Meeting; 18 Sept. 2013; Edwards Air Force Base, California; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Forced Convection Boiling and Critical Heat Flux of Ethanol in Electrically Heated Tube Tests (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Electrically heated tube tests were conducted to characterize the critical heat flux (transition from nucleate to film boiling) of subcritical ethanol flowing at conditions relevant to the design of a regeneratively cooled rocket engine thrust chamber. The coolant was SDA-3C alcohol (95% ethyl alcohol, 5% isopropyl alcohol by weight), and tests were conducted over the following ranges of conditions: pressure from 144 to 703 psia, flow velocities from 9.7 to 77 ft/s, coolant subcooling from 33 to 362 F, and critical heat fluxes up to 8.7 BTU/in(exp 2)/sec. For the data taken near 200 psia, critical heat flux was correlated as a function of the product of velocity and fluid subcooling to within +/- 20%. For data taken at higher pressures, an additional pressure term is needed to correlate the critical heat flux. It was also shown that at the higher test pressures and/or flow rates, exceeding the critical heat flux did not result in wall burnout. This result may significantly increase the engine heat flux design envelope for higher pressure conditions.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1998-206612 , E-11032 , NAS 1.15:206612 , AIAA Paper 98-1055 , Aerospace Sciences Meeting and Exhibit; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Mastering Cryogenic Propellants (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Propellants and Fuels
    Type: GRC-E-DAA-TN16903 , 2014 Proplusion & Energy Forum; Jul 28, 2014 - Jul 30, 2014; Cleveland, Ohio; United States
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    NASA TECHNICAL REPORTS
  • 4
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    The Cryogenic Propellant Storage and Transfer Technology Demonstration Mission: (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This presentation provides an overview of the Cryogenic Propellant Storage and Transfer (CPST) Mission from formulation through Systems Requirements Review and into preparation for Preliminary Design Review. Accomplishments of the technology maturation phase of the project are included. The presentation then summarizes the transition, due to Agency budget constraints, of CPST from a flight project into a ground project titled evolvable Cryogenics (eCryo).
    Keywords: Propellants and Fuels
    Type: GRC-E-DAA-TN16864 , Propulsion and Energy Forum 2014; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Technology Area Roadmap for In-Space Propulsion Technologies (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The exponential increase of launch system size.and cost.with delta-V makes missions that require large total impulse cost prohibitive. Led by NASA fs Marshall Space Flight Center, a team from government, industry, and academia has developed a flight demonstration mission concept of an integrated electrodynamic (ED) tethered satellite system called PROPEL: \Propulsion using Electrodynamics.. The PROPEL Mission is focused on demonstrating a versatile configuration of an ED tether to overcome the limitations of the rocket equation, enable new classes of missions currently unaffordable or infeasible, and significantly advance the Technology Readiness Level (TRL) to an operational level. We are also focused on establishing a far deeper understanding of critical processes and technologies to be able to scale and improve tether systems in the future. Here, we provide an overview of the proposed PROPEL mission. One of the critical processes for efficient ED tether operation is the ability to inject current to and collect current from the ionosphere. Because the PROPEL mission is planned to have both boost and deboost capability using a single tether, the tether current must be capable of flowing in both directions and at levels well over 1 A. Given the greater mobility of electrons over that of ions, this generally requires that both ends of the ED tether system can both collect and emit electrons. For example, hollow cathode plasma contactors (HCPCs) generally are viewed as state-of-the-art and high TRL devices; however, for ED tether applications important questions remain of how efficiently they can operate as both electron collectors and emitters. Other technologies will be highlighted that are being investigated as possible alternatives to the HCPC such as Solex that generates a plasma cloud from a solid material (Teflon) and electron emission (only) technologies such as cold-cathode electron field emission or photo-electron beam generation (PEBG) techniques
    Keywords: Spacecraft Propulsion and Power
    Type: M12-1836 , M12-1798 , Global Space Exploration Conference; May 22, 2012 - May 24, 2012; Washinton, DC; United States
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    NASA TECHNICAL REPORTS
  • 6
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    Testing of a Liquid Oxygen/Liquid Methane Reaction Control Thruster in a New Altitude Rocket Engine Test Facility (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A relocated rocket engine test facility, the Altitude Combustion Stand (ACS), was activated in 2009 at the NASA Glenn Research Center. This facility has the capability to test with a variety of propellants and up to a thrust level of 2000 lbf (8.9 kN) with precise measurement of propellant conditions, propellant flow rates, thrust and altitude conditions. These measurements enable accurate determination of a thruster and/or nozzle s altitude performance for both technology development and flight qualification purposes. In addition the facility was designed to enable efficient test operations to control costs for technology and advanced development projects. A liquid oxygen-liquid methane technology development test program was conducted in the ACS from the fall of 2009 to the fall of 2010. Three test phases were conducted investigating different operational modes and in addition, the project required the complexity of controlling propellant inlet temperatures over an extremely wide range. Despite the challenges of a unique propellant (liquid methane) and wide operating conditions, the facility performed well and delivered up to 24 hot fire tests in a single test day. The resulting data validated the feasibility of utilizing this propellant combination for future deep space applications.
    Keywords: Propellants and Fuels
    Type: NASA/TM-2012-217643 , E-18201 , E-18201-1 , Space Propulsion 2012; May 07, 2012 - May 10, 2012; Bordeaux; France
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    NASA TECHNICAL REPORTS
  • 7
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    Cryogenic Propellant Storage and Transfer Technology Demonstration For Long Duration In-Space Missions (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The high specific impulse of cryogenic propellants can provide a significant performance advantage for in-space transfer vehicles. The upper stages of the Saturn V and various commercial expendable launch vehicles have used liquid oxygen and liquid hydrogen propellants; however, the application of cryogenic propellants has been limited to relatively short duration missions due to the propensity of cryogens to absorb environmental heat resulting in fluid losses. Utilizing advanced cryogenic propellant technologies can enable the efficient use of high performance propellants for long duration missions. Crewed mission architectures for beyond low Earth orbit exploration can significantly benefit from this capability by developing realistic launch spacing for multiple launch missions, by prepositioning stages and by staging propellants at an in-space depot. The National Aeronautics and Space Administration through the Office of the Chief Technologist is formulating a Cryogenic Propellant Storage and Transfer Technology Demonstration Mission to mitigate the technical and programmatic risks of infusing these advanced technologies into the development of future cryogenic propellant stages or in-space propellant depots. NASA is seeking an innovative path for human space exploration, which strengthens the capability to extend human and robotic presence throughout the solar system. This mission will test and validate key cryogenic technological capabilities and has the objectives of demonstrating advanced thermal control technologies to minimize propellant loss during loiter, demonstrating robust operation in a microgravity environment, and demonstrating efficient propellant transfer on orbit. The status of the demonstration mission concept development, technology demonstration planning and technology maturation activities in preparation for flight system development are described.
    Keywords: Propellants and Fuels
    Type: NASA/TM-2012-217642 , E-18200 , E-18200 , Space Propulsion 2012; May 07, 2012 - May 10, 2012; Bordeaux; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Roadmap for In-Space Propulsion Technology (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA has created a roadmap for the development of advanced in-space propulsion technologies for the NASA Office of the Chief Technologist (OCT). This roadmap was drafted by a team of subject matter experts from within the Agency and then independently evaluated, integrated and prioritized by a National Research Council (NRC) panel. The roadmap describes a portfolio of in-space propulsion technologies that could meet future space science and exploration needs, and shows their traceability to potential future missions. Mission applications range from small satellites and robotic deep space exploration to space stations and human missions to Mars. Development of technologies within the area of in-space propulsion will result in technical solutions with improvements in thrust, specific impulse (Isp), power, specific mass (or specific power), volume, system mass, system complexity, operational complexity, commonality with other spacecraft systems, manufacturability, durability, and of course, cost. These types of improvements will yield decreased transit times, increased payload mass, safer spacecraft, and decreased costs. In some instances, development of technologies within this area will result in mission-enabling breakthroughs that will revolutionize space exploration. There is no single propulsion technology that will benefit all missions or mission types. The requirements for in-space propulsion vary widely according to their intended application. This paper provides an updated summary of the In-Space Propulsion Systems technology area roadmap incorporating the recommendations of the NRC.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2012-217641 , E-18195 , E-18195-1 , Space Propulsion 2012; May 07, 2012 - May 10, 2012; Bordeaux; France
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  • 9
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    Liquid Oxygen/Liquid Methane Propulsion and Cryogenic Advanced Development (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Exploration Systems Architecture Study conducted by NASA in 2005 identified the liquid oxygen (LOx)/liquid methane (LCH4) propellant combination as a prime candidate for the Crew Exploration Vehicle Service Module propulsion and for later use for ascent stage propulsion of the lunar lander. Both the Crew Exploration Vehicle and Lunar Lander were part the Constellation architecture, which had the objective to provide global sustained lunar human exploration capability. From late 2005 through the end of 2010, NASA and industry matured advanced development designs for many components that could be employed in relatively high thrust, high delta velocity, pressure fed propulsion systems for these two applications. The major investments were in main engines, reaction control engines, and the devices needed for cryogenic fluid management such as screens, propellant management devices, thermodynamic vents, and mass gauges. Engine and thruster developments also included advanced high reliability low mass igniters. Extensive tests were successfully conducted for all of these elements. For the thrusters and engines, testing included sea level and altitude conditions. This advanced development provides a mature technology base for future liquid oxygen/liquid methane pressure fed space propulsion systems. This paper documents the design and test efforts along with resulting hardware and test results.
    Keywords: Propellants and Fuels
    Type: IAC-11-C4.1.5 , E-17931 , E-17931-1 , 62nd International Aeronautical Congress; Oct 03, 2011 - Oct 07, 2011; Cape Town; South Africa
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    NASA TECHNICAL REPORTS
  • 10
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    Concept Design of Cryogenic Propellant Storage and Transfer for Space Exploration (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Propellants and Fuels
    Type: E-18444-1 , 63rd International Astronautical Congress; Oct 02, 2012 - Oct 05, 2012; Naples; Italy
    Format: application/pdf
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