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  • 11
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    PILOT SAFETY AND MERCURY ATLAS (1963)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Beschreibung: Safety devices for mercury project - manned space flight
    Schlagwort(e): SPACE SCIENCES
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 12
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    Design evolution of the orbiter reaction control subsystem (1985)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The challenges of space shuttle orbiter reaction control subsystem development began with selection of the propellant for the subsystem. Various concepts were evaluated before the current Earth storable, bipropellant combination was selected. Once that task was accomplished, additional challenges of designing the system to satisfy the wide range of requirements dictated by operating environments, reusability, and long life were met. Verification of system adequacy was achieved by means of a combination of analysis and test. The studies, the design efforts, and the test and analysis techniques employed in meeting the challenges are described.
    Schlagwort(e): SPACE TRANSPORTATION
    Materialart: Space Shuttle Tech. Conf., Pt. 2; p 656-672
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 13
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    Automatic startup for nuclear reactors (1964)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-21
    Beschreibung: Automatic startup technique for nuclear reactors
    Schlagwort(e): PHYSICS, GENERAL
    Materialart: LAMS-3111
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 14
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    Conceptual design of a lunar colony (1972)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-27
    Beschreibung: A systems engineering study is presented for a proposed lunar colony. The lunar colony was to grow from an existent, 12-man, earth-dependent lunar surface base and was to utilize lunar resources, becoming as earth-independent as possible. An in-depth treatment of some of the aspects of the lunar colony was given. We have found that the use of lunar resources is feasible for oxygen production (both for breathing and for space tug fuel), food production, and building materials. A program is outlined for recycling waste materials developed at the colony as well as a full program for growth and research activity of the colony to a level of 180 colonists. Recommendations for the lunar colony are given.
    Schlagwort(e): FACILITIES, RESEARCH, AND SUPPORT
    Materialart: NASA-CR-129164 , Sept. 1972; Houston, TX; United States
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 15
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    Swell Sleeves for Testing Explosive Devices (2003)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A method of testing explosive and pyrotechnic devices involves exploding the devices inside swell sleeves. Swell sleeves have been used previously for measuring forces. In the present method, they are used to obtain quantitative indications of the energy released in explosions of the devices under test. A swell sleeve is basically a thick-walled, hollow metal cylinder threaded at one end to accept a threaded surface on a device to be tested (see Figure 1). Once the device has been tightly threaded in place in the swell sleeve, the device-and-swell-sleeve assembly is placed in a test fixture, then the device is detonated. After the explosion, the assembly is removed from the test fixture and placed in a coordinate-measuring machine for measurement of the diameter of the swell sleeve as a function of axial position. For each axial position, the original diameter of the sleeve is subtracted from the diameter of the sleeve as swollen by the explosion to obtain the diametral swelling as a function of axial position (see Figure 2). The amount of swelling is taken as a measure of the energy released in the explosion. The amount of swelling can be compared to a standard amount of swelling to determine whether the pyrotechnic device functioned as specified.
    Schlagwort(e): Man/System Technology and Life Support
    Materialart: MSC-23306 , NASA Tech Briefs, February 2003; 34
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 16
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    Description of the Space Shuttle Reaction Control System (1975)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-27
    Beschreibung: The Space Shuttle RCS (reaction control system) is required to provide propulsion thrust for precise attitude control and three-axis translation. This capability must be provided for external tank separation, on-orbit operation, deorbit, and reentry. In order to meet these requirements a bipropellant, pressure-fed system utilizing monomethylhydrazine as fuel, and nitrogen tetroxide as oxidizer has been selected. The RCS engines include 38 primary thrusters rated at 870 lbf thrust and 6 vernier thrusters rated at 25 lbf thrust. The system is divided into three removable modules (one forward and two aft) to achieve maintenance and turnaround requirements. In order to provide additional mission flexibility, the aft modules can be connected together or interconnected with the OMS (orbital maneuvering system).
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 75-1299
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 17
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    Automated Propellant Blending (2000)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: An automated propellant blending apparatus and method that uses closely metered addition of countersolvent to a binder solution with propellant particles dispersed therein to precisely control binder precipitation and particle aggregation is discussed. A profile of binder precipitation versus countersolvent-solvent ratio is established empirically and used in a computer algorithm to establish countersolvent addition parameters near the cloud point for controlling the transition of properties of the binder during agglomeration and finishing of the propellant composition particles. The system is remotely operated by computer for safety, reliability and improved product properties, and also increases product output.
    Schlagwort(e): Propellants and Fuels
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 18
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    Propellant for the NASA Standard Initiator (2000)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: This paper discusses processes employed in manufacturing zirconium-potassium perchlorate propellant for the NASA standard initiator. It provides both a historical background on the NSI device-detailing problem areas and their resolution--and on propellant blending techniques. Emphasis is placed on the precipitation blending method. The findings on mixing equipment, processing, and raw materials are described. Also detailed are findings on the bridgewire slurry operation, one of the critical steps in the production of the NASA standard initiator.
    Schlagwort(e): Propellants and Fuels
    Materialart: NASA/TP-2000-210186 , S-861 , NAS 160:210186
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 19
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    Viton's Impact on NASA Standard Initiator Propellant Properties (2000)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: This paper discusses some of the properties of Viton that are relevant to its use as a pyrotechnic binder in a NASA standard initiator (NSI) propellant. Nearly every aspect of NSI propellant manufacture and use is impacted by the binder system. The effect of Viton's molecular weight on solubility, solution viscosity, glass transition temperature, and strength characteristics as applied to NSI production and performance are reviewed. Emphasis is placed on the Viton fractionation that occurs during the precipitation cycle and its impact on bridgewire functions. Special consideration is given to the production of bridgewire slurry mixtures.
    Schlagwort(e): Propellants and Fuels
    Materialart: NASA/TP-2000-210187 , S-867 , NAS 160:210187
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 20
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    Automated Propellant Blending (1999)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: An automated propellant blending apparatus and method uses closely metered addition of countersolvent to a binder solution with propellant particles dispersed therein to precisely control binder precipitation and particle aggregation. A profile of binder precipitation versus countersolvent-solvent ratio is established empirically and used in a computer algorithm to establish countersolvent addition parameters near the cloud point for controlling the transition of properties of the binder during agglomeration and finishing of the propellant composition particles. The system is remotely operated by computer for safety, reliability and improved product properties, and also increases product output.
    Schlagwort(e): Propellants and Fuels
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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