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  • 1
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    Inconsistent Definitions of the Pressure-Coupled Response and the Admittance of Solid Propellants (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: When an acoustic wave is present in a solid propellant combustion environment, the mass flux from the combustion zone oscillates at the same frequency as the acoustics. The acoustic wave is either amplified or attenuated by the response of the combustion to the acoustic disturbance. When the acoustic wave is amplified, this process is called combustion instability. The amplification is quantitatively measured by a response function. The ability to predict combustion stability for a solid propellant formulation is essential to the formulator to prevent or minimize the effects of instabilities, such as an oscillatory thrust. Unfortunately, the prediction of response values for a particular propellant remains a technical challenge. Most predictions of the response of propellants are based on test data, but there are a number of questions about the reliability of the standard test method, the T-burner. Alternate methods have been developed to measure the response of a propellant, including the ultrasound burner, the magnetic flowmeter and the rotating valve burner, but there are still inconsistencies between the results obtained by these different methods. Aside from the experimental differences, the values of the pressure-coupled responses obtained by different researchers are often compared erroneously, for the simple reason that inconsistencies in the definitions of the responses and admittances are not considered. The use of different definitions has led to substantial confusion since the first theoretical treatments of the problem by Hart and McClure in 1959. The definitions and relations derived here seek to alleviate this problem.
    Keywords: Propellants and Fuels
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The NASA GSFC MEMS Colloidal Thruster (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A number of upcoming missions require different thrust levels on the same spacecraft. A highly scaleable and efficient propulsion system would allow substantial mass savings. One type of thruster that can throttle from high to low thrust while maintaining a high specific impulse is a Micro-Electro-Mechanical System (MEMS) colloidal thruster. The NASA GSFC MEMS colloidal thruster has solved the problem of electrical breakdown to permit the integration of the electrode on top of the emitter by a novel MEMS fabrication technique. Devices have been successfully fabricated and the insulation properties have been tested to show they can support the required electric field. A computational finite element model was created and used to verify the voltage required to successfully operate the thruster. An experimental setup has been prepared to test the devices with both optical and Time-Of-Flight diagnostics.
    Keywords: Spacecraft Propulsion and Power
    Type: 40th AIAA/ASME/ASEE/SAE Joint Propulsion Conference; Jul 11, 2004 - Jul 14, 2004; Fort Lauderdale, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Propulsion Options for the Global Precipitation Measurement Core Satellite (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This study was conducted to evaluate several propulsion system options for the Global Precipitation Measurement (GPM) core satellite. Orbital simulations showed clear benefits for the scientific data to be obtained at a constant orbital altitude rather than with a decay/reboost approach. An orbital analysis estimated the drag force on the satellite will be 1 to 12 mN during the five-year mission. Four electric propulsion systems were identified that are able to compensate for these drag forces and maintain a circular orbit. The four systems were the UK-10/TS and the NASA 8 cm ion engines, and the ESA RMT and RITl0 EVO radio-frequency ion engines. The mass, cost, and power requirements were examined for these four systems. The systems were also evaluated for the transfer time from the initial orbit of 400 x 650 km altitude orbit to a circular 400 km orbit. The transfer times were excessive, and as a consequence a dual system concept (with a hydrazine monopropellant system for the orbit transfer and electric propulsion for drag compensation) was examined. Clear mass benefits were obtained with the dual system, but cost remains an issue because of the larger power system required for the electric propulsion system. An electrodynamic tether was also evaluated in this trade study.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Joint Propulsion Conference; Jul 20, 2003 - Jul 23, 2003; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Green Propellant Infusion Mission Program Development and Technology Maturation (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Space Technology Mission Directorate's (STMD) Green Propellant Infusion Mission (GPIM) Technology Demonstration Mission (TDM) is comprised of a cross-cutting team of domestic spacecraft propulsion and storable green propellant technology experts. This TDM is led by Ball Aerospace & Technologies Corp. (BATC), who will use their BCP- 100 spacecraft to carry a propulsion system payload consisting of one 22 N thruster for primary divert (DeltaV) maneuvers and four 1 N thrusters for attitude control, in a flight demonstration of the AF-M315E technology. The GPIM project has technology infusion team members from all three major market sectors: Industry, NASA, and the Department of Defense (DoD). The GPIM project team includes BATC, includes Aerojet Rocketdyne (AR), Air Force Research Laboratory, Aerospace Systems Directorate, Edwards AFB (AFRL), NASA Glenn Research Center (GRC), NASA Kennedy Space Center (KSC), and NASA Goddard Space Flight Center (GSFC). STMD programmatic and technology oversight is provided by NASA Marshall Space Flight Center. The GPIM project shall fly an operational AF-M315E green propulsion subsystem on a Ball-built BCP-100 spacecraft.
    Keywords: Propellants and Fuels
    Type: GRC-E-DAA-TN16257 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Dust Mitigation Vehicle (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A document describes the development and demonstration of an apparatus, called a dust mitigation vehicle, for reducing the amount of free dust on the surface of the Moon. The dust mitigation vehicle would be used to pave surfaces on the Moon to prevent the dust from levitating or adhering to surfaces. The basic principle of operation of these apparatuses is to use a lens or a dish mirror to concentrate solar thermal radiation onto a small spot to heat lunar regolith. In the case of the prototype dust mitigation vehicle, a Fresnel lens was used to heat a surface layer of regolith sufficiently to sinter or melt dust grains into a solid mass. The prototype vehicle has demonstrated paving rates up to 1.8 square meters per day. The proposed flight design of the dust mitigation vehicle is also described.
    Keywords: Man/System Technology and Life Support
    Type: GSC-15488-1 , NASA Tech Briefs, July 2011; 31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Vacuum Pyrolysis and Related ISRU Techniques (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A number of ISRU-related techniques have been developed at NASA Goddard Space Flight Center. The focus of the team has been on development of the vacuum pyrolysis technique for the production of oxygen from the lunar regolith. However, a number of related techniques have also been developed, including solar concentration, solar heating of regolith, resistive heating of regolith, sintering, regolith boiling, process modeling, parts manufacturing, and instrumentation development. An initial prototype system was developed to vaporize regolith simulants using a approx. l square meter Fresnel lens. This system was successfully used to vaporize quantities of approx. lg, and both mass spectroscopy of the gasses produced and Scanning Electron Microscopy (SEM) of the slag were done to show that oxygen was produced. Subsequent tests have demonstrated the use of a larger system With a 3.8m diameter reflective mirror to vaporize the regolith. These results and modeling of the vacuum pyrolysis reaction have indicated that the vaporization of the oxides in the regolith will occur at lower temperature for stronger vacuums. The chemical modeling was validated by testing of a resistive heating system that vaporized quantities of approx. 10g of MLS-1A. This system was also used to demonstrate the sintering of regolith simulants at reduced temperatures in high vacuum. This reduction in the required temperature prompted the development of a small-scale resistive heating system for application as a scientific instrument as well as a proof-of principle experiment for oxygen production.
    Keywords: Inorganic, Organic and Physical Chemistry
    Type: Space Technology and Applications International Forum; Feb 15, 2007 - Feb 17, 2007; Albuquerque, NM; United States
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    NASA TECHNICAL REPORTS
  • 7
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    An Analysis of Green Propulsion Applied to NASA Missions (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The advantages of green propulsion for five mission classes are examined, including a Low Earth Orbit (LEO) mission (GPM), a Geosynchronous Earth Orbit (GEO) mission (SDO), a High Earth Orbit (HEO) mission (MMS), a lunar mission (LRO), and a planetary mission (MAVEN). The propellant mass benefits are considered for all five missions, as well as the effects on the tanks, propellant loading, thruster throughput, thermal considerations, and range requirements for both the AF-M315E and LMP-103S propellants.
    Keywords: Spacecraft Propulsion and Power
    Type: GSFC-E-DAA-TN14280 , Space Propulsion 2014; May 19, 2014 - May 22, 2014; Cologne; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Implementation of an Online Database for Chemical Propulsion Systems (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Johns Hopkins University, Chemical Propulsion Information Analysis Center (CPIAC) has been working closely with NASA Goddard Space Flight Center (GSFC); NASA Marshall Space Flight Center (MSFC); the University of Alabama at Huntsville (UAH); The Johns Hopkins University, Applied Physics Laboratory (APL); and NASA Jet Propulsion Laboratory (JPL) to capture satellite and spacecraft propulsion system information for an online database tool. The Spacecraft Chemical Propulsion Database (SCPD) is a new online central repository containing general and detailed system and component information on a variety of spacecraft propulsion systems. This paper only uses data that have been approved for public release with unlimited distribution. The data, supporting documentation, and ability to produce reports on demand, enable a researcher using SCPD to compare spacecraft easily, generate information for trade studies and mass estimates, and learn from the experiences of others through what has already been done. This paper outlines the layout and advantages of SCPD, including a simple example application with a few chemical propulsion systems from various NASA spacecraft.
    Keywords: Spacecraft Propulsion and Power
    Type: M09-0575 , 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Aug 02, 2009 - Aug 05, 2009; Denver, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Propulsion Options for the LISA Mission (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The LISA mission is a constellation of three spacecraft operating at 1 AU from the Sun in a position trailing the Earth. After launch, a propulsion module provides the AV necessary to reach this operational orbit, and separates from the spacecraft. A second propulsion system integrated with the spacecraft maintains the operational orbit and reduces nongravitational disturbances on the instruments. Both chemical and electrical propulsion systems were considered for the propulsion module, and this trade is presented to show the possible benefits of an EP system. Several options for the orbit maintenance and disturbance reduction system are also briefly discussed, along with several important requirements that suggest the use of a FEEP thruster system.
    Keywords: Spacecraft Propulsion and Power
    Type: 40th AIAA/ASME/ASEE/SAE Joint Propulsion Conference; Jul 12, 2004 - Jul 14, 2004; Fort Lauderdale, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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