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  • Other Sources  (237)
  • Spacecraft Propulsion and Power  (156)
  • Aircraft Design, Testing and Performance
  • Female
  • 2010-2014  (111)
  • 1995-1999  (118)
  • 1950-1954  (5)
  • 1940-1944  (3)
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  • 1
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    Solar Thermal Upper Stage Liquid Hydrogen Pressure Control Testing and Analytical Modeling (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The demonstration of a unique liquid hydrogen (LH2) storage and feed system concept for solar thermal upper stage was cooperatively accomplished by a Boeing/NASA Marshall Space Flight Center team. The strategy was to balance thermodynamic venting with the engine thrusting timeline during a representative 30-day mission, thereby, assuring no vent losses. Using a 2 cubic m (71 cubic ft) LH2 tank, proof-of-concept testing consisted of an engineering checkout followed by a 30-day mission simulation. The data were used to anchor a combination of standard analyses and computational fluid dynamics (CFD) modeling. Dependence on orbital testing has been incrementally reduced as CFD codes, combined with standard modeling, continue to be challenged with test data such as this.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-2012-217469 , M-1345
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Helicon Plasma Source Optimization Studies for VASIMR (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: A helicon plasma source at Oak Ridge National Laboratory is being used to investigate operating scenarios relevant to the VASIMR (VAriable Specific Impulse Magnetoplasma Rocket). These include operation at high magnetic field (〉 = 0.4 T), high frequency (〈= 30 MHz), high power (〈 = 3 kW), and with light ions (He+, H+). To date, He plasmas have been produced with n(sub e0) = 1.7 x 10(exp 19)/cu m (measured with an axially movable 4mm microwave interferometer), with Pin = I kW at f = 13.56 MHz and absolute value of B(sub 0) = 0.16 T. In the near future, diagnostics including a mass flow meter and a gridded energy analyzer array will be added to investigate fueling efficiency and the source power balance. The latest results, together with modeling results using the EMIR rf code, will be presented.
    Keywords: Spacecraft Propulsion and Power
    Type: Plasma Propulsion Physics Mini Conference; Nov 15, 1999 - Nov 19, 1999; Seattle, WA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Development of Modeling Approaches for Nuclear Thermal Propulsion Test Facilities (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: SSTI-8080-0069 , Nuclear and Emerging Technologies for Space (NETS) Conference; Feb 24, 2014 - Feb 26, 2014; Bay Saint Louis, MS; United States
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    NASA TECHNICAL REPORTS
  • 4
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    Solar Sail Propulsion: Enabling New Capabilities for Heliophysics (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Solar sails can play a critical role in enabling solar and heliophysics missions. Solar sail technology within NASA is currently at 80% of TRL-6, suitable for an in-flight technology demonstration. It is conceivable that an initial demonstration could carry scientific payloads that, depending on the type of mission, are commensurate with the goals of the three study panels of the 2010 Heliophysics Survey. Follow-on solar sail missions, leveraging advances in solar sail technology to support Heliophysics Survey goals, would then be feasible. This white paper reports on a sampling of missions enabled by solar sails, the current state of the technology, and what funding is required to advance the current state of technology such that solar sails can enable these missions
    Keywords: Spacecraft Propulsion and Power
    Type: M11-0117
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Analytical Fuselage and Wing Weight Estimation of Transport Aircraft (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method of estimating the load-bearing fuselage weight and wing weight of transport aircraft based on fundamental structural principles has been developed. This method of weight estimation represents a compromise between the rapid assessment of component weight using empirical methods based on actual weights of existing aircraft, and detailed, but time-consuming, analysis using the finite element method. The method was applied to eight existing subsonic transports for validation and correlation. Integration of the resulting computer program, PDCYL, has been made into the weights-calculating module of the AirCraft SYNThesis (ACSYNT) computer program. ACSYNT has traditionally used only empirical weight estimation methods; PDCYL adds to ACSYNT a rapid, accurate means of assessing the fuselage and wing weights of unconventional aircraft. PDCYL also allows flexibility in the choice of structural concept, as well as a direct means of determining the impact of advanced materials on structural weight. Using statistical analysis techniques, relations between the load-bearing fuselage and wing weights calculated by PDCYL and corresponding actual weights were determined.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-110392 , A-961451 , NAS 1.15:110392
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Propulsion System Airframe Integration Issues and Aerodynamic Database Development for the Hyper-X Flight Research Vehicle (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA's Hyper-X Research Vehicle will provide a unique opportunity to obtain data on an operational airframe integrated scramjet propulsion system at true flight conditions. The airframe integrated nature of the scramjet engine with the Hyper-X vehicle results in a strong coupling effect between the propulsion system operation and the airframe s basic aerodynamic characteristics. Comments on general airframe integrated scramjet propulsion system effects on vehicle aerodynamic performance, stability, and control are provided, followed by examples specific to the Hyper-X research vehicle. An overview is provided of the current activities associated with the development of the Hyper-X aerodynamic database, including wind tunnel test activities and parallel CFD analysis efforts. A brief summary of the Hyper-X aerodynamic characteristics is provided, including the direct and indirect effects of the airframe integrated scramjet propulsion system operation on the basic airframe stability and control characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: ISOABE-99-7215 , XIV ISOABE; Sep 05, 1999 - Sep 10, 1999; Florence; Italy
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Reusable Rocket Engine Advanced Health Management System. Architecture and Technology Evaluation: Summary (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In this study, we proposed an Advanced Health Management System (AHMS) functional architecture and conducted a technology assessment for liquid propellant rocket engine lifecycle health management. The purpose of the AHMS is to improve reusable rocket engine safety and to reduce between-flight maintenance. During the study, past and current reusable rocket engine health management-related projects were reviewed, data structures and health management processes of current rocket engine programs were assessed, and in-depth interviews with rocket engine lifecycle and system experts were conducted. A generic AHMS functional architecture, with primary focus on real-time health monitoring, was developed. Fourteen categories of technology tasks and development needs for implementation of the AHMS were identified, based on the functional architecture and our assessment of current rocket engine programs. Five key technology areas were recommended for immediate development, which (1) would provide immediate benefits to current engine programs, and (2) could be implemented with minimal impact on the current Space Shuttle Main Engine (SSME) and Reusable Launch Vehicle (RLV) engine controllers.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 99-2527 , Joint Propulsion; Jun 20, 1999 - Jun 24, 1999; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Hybrid-PIC Modeling of a High-Voltage, High-Specific-Impulse Hall Thruster (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The primary life-limiting mechanism of Hall thrusters is the sputter erosion of the discharge channel walls by high-energy propellant ions. Because of the difficulty involved in characterizing this erosion experimentally, many past efforts have focused on numerical modeling to predict erosion rates and thruster lifespan, but those analyses were limited to Hall thrusters operating in the 200-400V discharge voltage range. Thrusters operating at higher discharge voltages (V(sub d) 〉= 500 V) present an erosion environment that may differ greatly from that of the lower-voltage thrusters modeled in the past. In this work, HPHall, a well-established hybrid-PIC code, is used to simulate NASA's High-Voltage Hall Accelerator (HiVHAc) at discharge voltages of 300, 400, and 500V as a first step towards modeling the discharge channel erosion. It is found that the model accurately predicts the thruster performance at all operating conditions to within 6%. The model predicts a normalized plasma potential profile that is consistent between all three operating points, with the acceleration zone appearing in the same approximate location. The expected trend of increasing electron temperature with increasing discharge voltage is observed. An analysis of the discharge current oscillations shows that the model predicts oscillations that are much greater in amplitude than those measured experimentally at all operating points, suggesting that the differences in oscillation amplitude are not strongly associated with discharge voltage.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2013-3887 , GRC-E-DAA-TN10205 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit; Jul 14, 2013 - Jul 17, 2013; San Jose CA; United States|International Energy Conversion Engineering Conference (IECEC); Jul 15, 2013 - Jul 17, 2013; San Jose CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Cryogenic Propulsion Stage (CPS) Configuration in Support of NASA's Multiple Design Reference Missions (DRMs) (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In support of the National Aeronautics and Space Administration's (NASA) Human Exploration and Operations Mission Directorate (HEOMD), the Space Launch System (SLS) is being designed for safe, affordable, and sustainable human and scientific exploration missions beyond Earth's or-bit (BEO). The SLS Team is tasked with developing a system capable of safely and repeatedly lofting a new fleet of spaceflight vehicles beyond Earth orbit. The Cryogenic Propulsion Stage (CPS) is a key enabler for evolving the SLS capability for BEO missions. This paper reports on the methodology and initial recommendations relative to the CPS, giving a brief retrospective of early studies on this promising propulsion hardware. This paper provides an overview of the requirements development and CPS configuration in support of NASA's multiple Design Reference Missions (DRMs).
    Keywords: Spacecraft Propulsion and Power
    Type: M12-1738 , Space Propulsion 2012; May 07, 2012 - May 10, 2012; Bourdeax; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Lessons Learned from the Design, Certification, and Operation of the Space Shuttle Integrated Main Propulsion System (IMPS) (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Space Shuttle Integrated Main Propulsion System (IMPS) consists of the External Tank (ET), Orbiter Main Propulsion System (MPS), and Space Shuttle Main Engines (SSMEs). The IMPS is tasked with the storage, conditioning, distribution, and combustion of cryogenic liquid hydrogen (LH2) and liquid oxygen (LO2) propellants to provide first and second stage thrust for achieving orbital velocity. The design, certification, and operation of the associated IMPS hardware have produced many lessons learned over the course of the Space Shuttle Program (SSP). A subset of these items will be discussed in this paper for consideration when designing, building, and operating future spacecraft propulsion systems. This paper will focus on lessons learned related to Orbiter MPS and is the first of a planned series to address the subject matter.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-CN-24087 , 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 31, 2011 - Aug 03, 2011; San Diego, CA; United States|9th Annual International Energy Conversion Engineering Conference; Jul 31, 2011 - Aug 03, 2011; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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