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  • 1
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    Enhanced Feasibility Assessment of Payload Adapters for NASAs Space Launch System (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: No abstract available
    Keywords: Launch Vehicles and Launch Operations
    Type: M18-7043-2 , IEEE Aerospace Conference; Mar 02, 2019 - Mar 09, 2019; Big Sky, MT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Enhanced Feasibility Assessment of Payload Adapters for NASAs Space Launch System (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The first flight of NASAs new exploration-classlaunch vehicle, the Space Launch System (SLS), will test amyriad of systems designed to enable the next generation of deepspace human spaceflight, and launch from Kennedy SpaceCenter no earlier than December 2019. The initial Block 1configuration for EM-1 will be capable of lofting at least 70metric tons (t) of payload and send the Orion crew vehicle intoa distant retrograde lunar orbit, paving the way for future crewmissions to cislunar space and eventually Mars. A Block 1Bversion of SLS will lift at least 34 t to trans-lunar injection (TLI)in its crew configuration and at least 37 t to TLI in its cargoconfiguration no earlier than 2024. For Mars-class payloads,larger fairings and payload adapters for the Block 2 cargovehicle are under consideration. For missions beyond the Earth-Moon system, SLS offers greater characteristic energy (C3)than any other launch vehicle, enabling shorter transit times orheavier payloads with more robust science packages formissions to the outer solar system. Indeed, the unmatchedcombination of thrust, payload volume and departure energythat SLS provides opens new opportunities for human androbotic exploration of deep space.
    Keywords: Launch Vehicles and Launch Operations
    Type: M18-7043-1 , IEEE Aerospace Conference; Mar 02, 2019 - Mar 09, 2019; Big Sky, MT; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Enhanced Feasibility Assessment of Payload Adapters for NASAs Space Launch System (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: No abstract available
    Keywords: Launch Vehicles and Launch Operations
    Type: M19-7209 , IEEE Aerospace Conference; Mar 02, 2019 - Mar 09, 2019; Big Sky, MT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Space Launch System Mission Flexibility Assessment (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Space Launch System (SLS) is envisioned as a heavy lift vehicle that will provide the foundation for future beyond low Earth orbit (LEO) missions. While multiple assessments have been performed to determine the optimal configuration for the SLS, this effort was undertaken to evaluate the flexibility of various concepts for the range of missions that may be required of this system. These mission scenarios include single launch crew and/or cargo delivery to LEO, single launch cargo delivery missions to LEO in support of multi-launch mission campaigns, and single launch beyond LEO missions. Specifically, we assessed options for the single launch beyond LEO mission scenario using a variety of in-space stages and vehicle staging criteria. This was performed to determine the most flexible (and perhaps optimal) method of designing this particular type of mission. A specific mission opportunity to the Jovian system was further assessed to determine potential solutions that may meet currently envisioned mission objectives. This application sought to significantly reduce mission cost by allowing for a direct, faster transfer from Earth to Jupiter and to determine the order-of-magnitude mass margin that would be made available from utilization of the SLS. In general, smaller, existing stages provided comparable performance to larger, new stage developments when the mission scenario allowed for optimal LEO dropoff orbits (e.g. highly elliptical staging orbits). Initial results using this method with early SLS configurations and existing Upper Stages showed the potential of capturing Lunar flyby missions as well as providing significant mass delivery to a Jupiter transfer orbit.
    Keywords: Launch Vehicles and Launch Operations
    Type: GLEX-2012.05.1.1x12345 , M12-1752 , M12-1787 , 2012 Global Space Exploration Conference; May 22, 2012 - May 24, 2012; Washington, DC; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Performance Evaluation of Particle Sampling Probes for Emission Measurements of Aircraft Jet Engines (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Considerable attention has been recently received on the impact of aircraft-produced aerosols upon the global climate. Sampling particles directly from jet engines has been performed by different research groups in the U.S. and Europe. However, a large variation has been observed among published data on the conversion efficiency and emission indexes of jet engines. The variation results surely from the differences in test engine types, engine operation conditions, and environmental conditions. The other factor that could result in the observed variation is the performance of sampling probes used. Unfortunately, it is often neglected in the jet engine community. Particle losses during the sampling, transport, and dilution processes are often not discussed/considered in literatures. To address this issue, we evaluated the performance of one sampling probe by challenging it with monodisperse particles. A significant performance difference was observed on the sampling probe evaluated under different temperature conditions. Thermophoretic effect, nonisokinetic sampling and turbulence loss contribute to the loss of particles in sampling probes. The results of this study show that particle loss can be dramatic if the sampling probe is not well designed. Further, the result allows ones to recover the actual size distributions emitted from jet engines.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-2001-211201 , E-13047 , NAS 1.26:211201
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    NASA TECHNICAL REPORTS
  • 6
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    Particle Size Distributions Measured in B757 Engine Plume During EXCAVATE (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A ground-based test, the Experiment to Characterize Aircraft Volatile Aerosols and Trace Species Emissions (EXCAVATE), was conducted at NASA Langley Research Center, January 26 - 27, 2002, with a Boeing 757 aircraft. The aircraft was anchored on a tarmac and two probes were positioned downstream of the right-side engine, a Rolls Royce RB211-585. One probe was designed and fabricated by Arnold Engineering Development Center (AEDC) and had a 45.6 mm (1.794 in.) ID. A second probe, constructed of 6.4 mm (0.25 in.) stainless-steel tubing at NASA Langley Research Center, had a 6 mm (0.22 in.) ID. The engine was run on JP-5 with three different sulfur concentrations, 810 ppm, 1050 ppm, 1820 ppm; and was operated over a range of power settings from idle to near-full power. Particulate size-distributions and concentrations were measured at four downstream axial locations: 1 m and 10 m with the AEDC particulate probe, and 25 m and 35 m with the Langley probe. Fuel with various sulfur contents was tested to address the long-standing question of the role of sulfur in the formation of volatile species. Several experimental and modeling studies have shown a correlation between fuel sulfur-content and particulate-emissions. The object of EXCAVATE was to further study the effect of sulfur content on particulate number concentration and size-distribution as a function of location in the engine plume and engine operating conditions.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Particle Size Distributions Measured in the B757 Engine Plume During EXCAVATE (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The Experiment to Characterize Aircraft Volatile Aerosols and Trace Species Emissions (EXCAVATE) took place at NASA Langley Research Center during January 2002. This ground based study was conducted to examine the role of fuel sulfur content on particulate emissions. Size distributions as a function of engine operating conditions were measured in the exhaust plume of a B-757 at four downstream axial locations (1 m, 10 m, 25 m and 35 m). The engine was run on JP-5 with three different sulfur concentrations, 810 ppm, 1050 ppm, 1820 ppm; and was operated over a range of power settings from idle to near-full power. Zalabsky differential-mobility analyzers DMAS), Met One condensation-nuclei counters (CNCs), and a TSI 3022 condensation-particle counter (CPC) were used to measure the size distributions. The total number-count (particle concentration), number-based Emissions Index (EInumber) and mass-based Emissions Index (E1-J increased with fuel sulfur-content and engine pressure ratio (EPR). Count Mean Diameter (Ch4D) also increased with EPR yet remained fairly constant with fuel sulfur-content for a fixed location in the exhaust plume. Also the mode and CMD both increased with distance in the plume.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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