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  • SPACECRAFT PROPULSION AND POWER  (79)
  • Spacecraft Propulsion and Power
  • 1990-1994  (82)
  • 1
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    Enhancement of the no-vent fill process (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents an analytical and experimental evaluation of an enhanced techniques for no-vent fill. The method entails injecting liquid through the top of the receiver vessel, thereby increasing surface area and agitation of the ullage/liquid interface. Both of these factors promote condensation induced ullage collapse, and reduce compressive impedance to the incoming liquid. The enhanced process was analyzed by modifying the surface area algorithm of an existing tank thermodynamic code to model a downward-pointing, conical jet impringing on a steadily rising liquid surface. Transient pressure and temperature measurements from several tests with Freon-114 were input into the revised model to calculate condensation rate as a function of fill level. By expressing these rates in dimensionless form (i.e., in terms of Stanton number and Prandtl number), an empirical correlation similar to the submerged jet model of Brown and Sonin (1989) was derived. This provided a basis for developing an expression which relates top fill to bottom fill performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-1842
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Cryogenic propellant thermal control system design considerations, analyses, and concepts applied to a Mars human exploration mission (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper analyzes, defines, and sizes cryogenic storage thermal control systems that meet the requirements of future NASA Mars human exploration missions. The design issues of this system include the projection of the existing Multilayer Insulation data base for cryogenic storage to much thicker (10 cm or more) insulation systems, the unknown heat leak from mechanical interfaces, and the thermal and structural performance effects of the large tank sizes required for a Mars mission. Acknowledging these unknown effects, heat loss projections are made based on extrapolation of the existing data base. The results indicate that hydrogen, methane, and oxygen are feasible propellants, and that the best suited thermal control sytems are 'thick' MLI, thermodynamic vent sytems, cryocoolers, and vacuum jackets.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-2353 , ; 17 p.|AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Analytical modeling of no-vent fill process (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 574-579
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    NASA TECHNICAL REPORTS
  • 4
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    Indium phosphide solar cells - Recent developments and estimated performance in space (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The current status of indium phosphide solar cell research is reviewed. In the NASA research program, efficiencies of 18.8 percent were achieved for standard n/p homojunction InP cells while 17 percent was achieved for ITO/InP cells processed by sputtering n-type indium tin oxide onto p-type indium phosphide. The latter represents a cheaper, simpler processing alternative. Computer modeling calculations indicate that efficiencies of over 21 percent are feasible. Relatively large area cells are produced in Japan with a maximum efficiency of 16.6 percent.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Power - Resources, Manufacturing and Development (ISSN 0883-6272); 9; 1, 19
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    NASA TECHNICAL REPORTS
  • 5
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    Effect of idealized asymmetric inhibitor stubs on circumferential flow in the Space Shuttle SRM (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 6; 5-10
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  • 6
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    Workshop on Solar Electric Propulsion (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A summary of the discussion at the workshop on solar electric propulsion (SEP) is presented. The purpose of ELITE SEP flight experiment is to demonstrate operation of solar array powered electric thrusters for raising spacecraft from parking orbit to higher altitudes, leading to definition of an operational SEP orbit transfer vehicles (OTV) for Air Force missions. Many of the problems or potential problems that may be associated with SEP are not well understood nor clearly identified, and system level phenomena such as interaction of thruster plume with the solar arrays cannot be simulated in a ground test. Therefore, an end-to-end system flight test is required to demonstrate solar electric propulsion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Proceedings of the 12th Space Photovoltaic Research and Technology Conference (SPRAT 12); p 331-333
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  • 7
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    Augmentation of the space station module power management and distribution breadboard (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The space station module power management and distribution (SSM/PMAD) breadboard models power distribution and management, including scheduling, load prioritization, and a fault detection, identification, and recovery (FDIR) system within a Space Station Freedom habitation or laboratory module. This 120 VDC system is capable of distributing up to 30 kW of power among more than 25 loads. In addition to the power distribution hardware, the system includes computer control through a hierarchy of processes. The lowest level consists of fast, simple (from a computing standpoint) switchgear that is capable of quickly safing the system. At the next level are local load center processors, (LLP's) which execute load scheduling, perform redundant switching, and shed loads which use more than scheduled power. Above the LLP's are three cooperating artificial intelligence (AI) systems which manage load prioritizations, load scheduling, load shedding, and fault recovery and management. Recent upgrades to hardware and modifications to software at both the LLP and AI system levels promise a drastic increase in speed, a significant increase in functionality and reliability, and potential for further examination of advanced automation techniques. The background, SSM/PMAD, interface to the Lewis Research Center test bed, the large autonomous spacecraft electrical power system, and future plans are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lyndon B. Johnson Space Center, Fourth Annual Workshop on Space Operations Applications and Research (SOAR 90); p 355-359
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  • 8
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    Rocket noise filtering system using digital filters (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A set of digital filters is designed to filter rocket noise to various bandwidths. The filters are designed to have constant group delay and are implemented in software on a general purpose computer. The Parks-McClellan algorithm is used. Preliminary tests are performed to verify the design and implementation. An analog filter which was previously employed is also simulated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, John F. Kennedy Space Center, Research Reports: 1990 NASA(ASEE Summer Faculty Fellowship Program; p 244-275
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  • 9
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    Integrated Power and Attitude Control System (IPACS) technology developments (1990)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: Integrated Power and Attitude Control System (IPACS) studies performed over a decade ago established the feasibility of storing electrical energy in flywheels and utilizing the resulting angular momentum for spacecraft attitude control. Such a system has been shown to have numerous attractive features relative to more contemporary technology, and is appropriate to many applications (including high-performance slewing actuators). Technology advances over the last two decades in composite rotors, motor/generator/electronics, and magnetic bearings are found to support the use of IPACS for increasingly sophisticated applications. It is concluded that the concept offers potential performance advantages as well as savings in mass and life-cycle cost. Viewgraphs and discussion on IPACS are included.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington, Technology for Space Station Evolution. Volume 4: Power Systems(Propulsion)Robotics; p 241-273
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  • 10
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    International Space Station Alpha's bearing, motor, and roll ring module developmental testing and results (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This paper presents the design and developmental testing associated with the bearing, motor, and roll ring module (BMRRM) used for the beta rotation axis on International Space Station Alpha (ISSA). The BMRRM with its controllers located in the electronic control unit (ECU), provides for the solar array pointing and tracking functions as well as power and signal transfer across a rotating interface.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, The 28th Aerospace Mechanisms Symposium; p 51-61; NASA-CP-3260
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