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  • 1
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    Effect of model selection on combustor performance and stability using ROCCID (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The ROCket Combustor Interactive Design (ROCCID) methodology is an interactive computer program that combines previously developed combustion analysis models to calculate the combustion performance and stability of liquid rocket engines. Test data from a 213 kN (48,000 lbf) Liquid Oxygen (LOX)/RP-1 combustor with a O-F-O (oxidizer-fuel-oxidizer) triplet injector were used to characterize the predictive capabilities of the ROCCID analysis models for this injector/propellant configuration. Thirteen combustion performance and stability models have been incorporated into ROCCID, and ten of them, which have options for triplet injectors, were examined in this study. Calculations using different combinations of analysis models, with little or no anchoring, were carried out on a test matrix of operating conditions matching those of the test program. Results of the computer analyses were compared to test data, and the ability of the model combinations to correctly predict combustion stability or instability was determined. For the best model combination(s), sensitivity of the calculations to fuel drop size and mixing efficiency was examined. Error in the stability calculations due to uncertainty in the pressure interaction index (N) was examined. The recommended model combinations for this O-F-O triplet LOX/RP-1 configuration are proposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3226
    Format: text
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  • 2
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    A comparison of analytical results for 20 K LOX/hydrogen instabilities (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Test data from NASA Lewis' Effect of Thrust Per Element on Combustion Stability Characteristics of Hydrogen-Oxygen Rocket Engines test program are used to validate two recently released stability analysis tools. The first tool is a design methodology called ROCCID (ROCket Combustor Interactive Design). ROCCID is an interactive design and analysis methodology that uses existing performance and combustion stability analysis codes. The second tool is HICCIP (High frequency Injection Coupled Combustion Instability Program). HICCIP is a recently developed combustion stability analysis model. Using a matrix of models, results from analytic comparisons with 20 K LOX/H2 experimental data are presented.
    Keywords: PROPELLANTS AND FUELS
    Type: AIAA PAPER 90-2241
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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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    Combustor design and analysis using the ROCket Combustor Interactive Design (ROCCID) Methodology (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The ROCket Combustor Interactive Design (ROCCID) Methodology is a newly developed, interactive computer code for the design and analysis of a liquid propellant rocket combustion chamber. The application of ROCCID to design a liquid rocket combustion chamber is illustrated. Designs for a 50,000 lbf thrust and 1250 psi chamber pressure combustor using liquid oxygen (LOX)RP-1 propellants are developed and evaluated. Tradeoffs between key design parameters affecting combustor performance and stability are examined. Predicted performance and combustion stability margin for these designs are provided as a function of the combustor operating mixture ratio and chamber pressure.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-2240
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  • 5
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    Program For Analyzing Designs Of Liquid-Propellant Rockets (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Rocket Combustor Interactive Design Computer Methodology (ROCCID) computer program provides standardized methodology, using state-of-art codes and procedures, for analysis of combustion performance and stability of liquid-propellant rocket engine. Provides combustion analyst with software tool to analyze existing combustor design (point-analysis option), or design high-performance, stable combustor, given set of input design requirements (point-design option). Written in ANSI FORTRAN 77 and VAX FORTRAN.
    Keywords: MECHANICS
    Type: LEW-15114 , NASA Tech Briefs (ISSN 0145-319X); 19; 1; P. 76
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  • 6
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    International Space Exploration Coordination Group Assessment of Technology Gaps for LOx/Methane Propulsion Systems for the Global Exploration Roadmap (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As part of the Global Exploration Roadmap (GER), the International Space Exploration Coordination Group (ISECG) formed two technology gap assessment teams to evaluate topic discipline areas that had not been worked at an international level to date. The participating agencies were ASI, CNES, DLR, ESA, JAXA, and NASA. Accordingly, the ISECG Technology Working Group (TWG) recommended two discipline areas based on Critical Technology Needs reflected within the GER Technology Development Map (GTDM): Dust Mitigation and LOX/Methane Propulsion. LOx/Methane propulsion systems are enabling for future human missions Mars by significantly reducing the landed mass of the Mars ascent stage through the use of in-situ propellant production, for improving common fluids for life support, power and propulion thus allowing for diverse redundancy, for eliminating the corrosive and toxic propellants thereby improving surface operations and resusabilty, and for inceasing the performance of propulsion systems. The goals and objectives of the international team are to determine the gaps in technology that must be closed for LOx/Methane to be used in human exploration missions in cis-lunar, lunar, and Mars mission applications. An emphasis is placed on near term lunar lander applications with extensibility to Mars. Each agency provided a status of the substantial amount of Lox/Methane propulsion system development to date and their inputs on the gaps in the technology that are remaining. The gaps, which are now opportunities for collaboration, are then discussed.
    Keywords: Propellants and Fuels
    Type: JSC-CN-35694 , AIAA Space 2016; Sep 13, 2016 - Sep 16, 2016; Long Beach, CA; United States
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  • 7
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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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  • 8
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    Feasibility of Large High-Powered Solar Electric Propulsion Vehicles: Issues and Solutions (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Human exploration beyond low Earth orbit will require the use of enabling technologies that are efficient, affordable, and reliable. Solar electric propulsion (SEP) has been proposed by NASA s Human Exploration Framework Team as an option to achieve human exploration missions to near Earth objects (NEOs) because of its favorable mass efficiency as compared to traditional chemical systems. This paper describes the unique challenges and technology hurdles associated with developing a large high-power SEP vehicle. A subsystem level breakdown of factors contributing to the feasibility of SEP as a platform for future exploration missions to NEOs is presented including overall mission feasibility, trip time variables, propellant management issues, solar array power generation, array structure issues, and other areas that warrant investment in additional technology or engineering development.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2012-217275 , AIAA Paper-2011-7251 , E-18030 , Space 2011 Conference and Exposition; Sep 27, 2011 - Sep 29, 2011; Long Beach, CA; United States
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  • 9
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    JANNAF liquid rocket combustion instability panel research recommendations (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Joint Army, Navy, NASA, Air Force (JANNAF) Liquid Rocket Combustion Instability Panel was formed in 1988, drawing its members from industry, academia, and government experts. The panel was charted to address the needs of near-term engine development programs and to make recommendations whose implementation would provide not only sufficient data but also the analysis capabilities to design stable and efficient engines. The panel was also chartered to make long-term recommendations toward developing mechanistic analysis models that would not be limited by design geometry or operating regime. These models would accurately predict stability and thereby minimize the amount of subscale testing for anchoring. The panel has held workshops on acoustic absorbing devices, combustion instability mechanisms, instability test hardware, and combustion instability computational methods. At these workshops, research projects that would meet the panel's charter were suggested. The JANNAF Liquid Rocket Combustion Instability Panel's conclusions about the work that needs to be done and recommendations on how to approach it, based on evaluation of the suggested research projects, are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-103653 , E-5826 , NAS 1.15:103653 , JANNAF Combustion Meeting; Nov 05, 1990 - Nov 09, 1990; Cheyenne, WY; United States
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  • 10
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    JANNAF Liquid Rocket Combustion Instability Panel Research Recommendations (1990)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The Joint Army, Navy, NASA, Air Force (JANNAF) Liquid Rocket Combustion Instability Panel was formed in 1988, drawing its members from industry, academia, and government experts. The panel was chartered to address the needs of near-term engine development programs and to make recommendations whose implementation would provide not only sufficient data but also the analysis capabilities to design stable and efficient engines. The panel was also chartered to make long-term recommendations toward developing mechanistic analysis models that would not be limited by design geometry or operating regime. These models would accurately predict stability and thereby minimize the amount of subscale testing for anchoring. The panel has held workshops on acoustic absorbing devices and combustion instability computational methods. At these workshops, research projects that would meet the panel's charter were suggested. The panel's conclusions about the work that needs to be done and recommendations on how to approach it, based on evaluation of the suggested research projects, are presented.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: 27th JANNAF Combustion Subcommittee Meeting; 3; 345-351
    Format: application/pdf
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