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  • 1
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    Antimatter Requirements and Energy Costs for Near-Term Propulsion Applications (1999)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The superior energy density of antimatter annihilation has often been pointed to as the ultimate source of energy for propulsion. However, the limited capacity and very low efficiency of present-day antiproton production methods suggest that antimatter may be too costly to consider for near-term propulsion applications. We address this issue by assessing the antimatter requirements for six different types of propulsion concepts, including two in which antiprotons are used to drive energy release from combined fission/fusion. These requirements are compared against the capacity of both the current antimatter production infrastructure and the improved capabilities that could exist within the early part of next century. Results show that although it may be impractical to consider systems that rely on antimatter as the sole source of propulsive energy, the requirements for propulsion based on antimatter-assisted fission/fusion do fall within projected near-term production capabilities. In fact, a new facility designed solely for antiproton production but based on existing technology could feasibly support interstellar precursor missions and omniplanetary spaceflight with antimatter costs ranging up to $6.4 million per mission.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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  • 2
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    Aerospike Engine Post-Test Diagnostic System Delivered to Rocketdyne (2000)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: The NASA Glenn Research Center at Lewis Field, in cooperation with Rocketdyne, has designed, developed, and implemented an automated Post-Test Diagnostic System (PTDS) for the X-33 linear aerospike engine. The PTDS was developed to reduce analysis time and to increase the accuracy and repeatability of rocket engine ground test fire and flight data analysis. This diagnostic system provides a fast, consistent, first-pass data analysis, thereby aiding engineers who are responsible for detecting and diagnosing engine anomalies from sensor data. It uses analytical methods modeled after the analysis strategies used by engineers. Glenn delivered the first version of PTDS in September of 1998 to support testing of the engine s power pack assembly. The system was used to analyze all 17 power pack tests and assisted Rocketdyne engineers in troubleshooting both data acquisition and test article anomalies. The engine version of PTDS, which was delivered in June of 1999, will support all single-engine, dual-engine, and flight firings of the aerospike engine.
    Keywords: Spacecraft Propulsion and Power
    Type: Research and Technology 1999; NASA/TM-2000-209639
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  • 3
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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
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  • 4
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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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  • 5
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    Effect of Injector Geometry on Atomization of a Liquid-Liquid Double Swirl Coaxial Injector Using Non-invasive Laser, Optical and X-ray Techniques (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The spray characteristics of a liquid-liquid double swirl coaxial injector were studied using non-invasive optical, laser, and X-ray diagnostics. A parametric study of injector exit geometry demonstrated that spray breakup time, breakup type and sheet stability could be controlled with exit geometry. Phase Doppler interferometry was used to characterize droplet statistics and non-dimensional droplet parameters over a range of inlet conditions and for various fluids allowing for a study on the role of specific fluid properties in atomization. Further, X-ray radiography allowed for investigation of sheet thickness and breakup length to be quantified for different recess exit diameters and inlet pressures. Finally, computed tomography scans revealed that the spray cone was distinctively non-uniform and comprised of several pockets of increased mass flux.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-CN-31422 , Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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  • 6
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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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  • 7
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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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  • 8
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    Cryogenic Propellant Storage and Transfer (CPST) Tour Stop (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: E-664451
    Format: application/pdf
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  • 9
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    Technology Area Roadmap for In Space Propulsion Technologies (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This roadmap describes a portfolio of in-space propulsion technologies that can meet future space science and exploration needs.
    Keywords: Spacecraft Propulsion and Power
    Type: M11-0738 , 7th Symposium on Realistic Near-Term Advanced Scientific Space Missions; Jul 11, 2011 - Jul 14, 2011; Aosta; Italy
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  • 10
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    In-Vacuum Photogrammetry of a 10-Meter Solar Sail (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In July 2004, a 10-meter solar sail structure developed by L Garde, Inc. was tested in vacuum at the NASA Glenn 30-meter Plum Brook Space Power Facility in Sandusky, Ohio. The three main objections of the test were to demonstrate unattended deployment from a stowed configuration, to measure the deployed shape of the sail at both ambient and cryogenic room temperatures, and to measure the deployed structural dynamic characteristics (vibration modes). This paper summarizes the work conducted to fulfill the second test objective. The deployed shape was measured photogrammetrically in vacuum conditions with four 2-megapixel digital video cameras contained in custom made pressurized canisters. The canisters included high-intensity LED ring lights to illuminate a grid of retroreflective targets distributed on the solar sail. The test results closely matched pre-test photogrammetry numerical simulations and compare well with ABAQUS finite-element model predictions.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2005-1889 , 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference; Apr 18, 2005 - Apr 21, 2005; Austin, TX; United States
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