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  • Other Sources  (918)
  • NASA Technical Reports  (918)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (918)
  • Analytical Chemistry and Spectroscopy
  • Deutschland
  • 1975-1979  (918)
  • 1
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    Space shuttle (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: The transportation cost associated with space materials processing were studied to determine the feasibility of space manufacturing. The assumptions use to determining the cost estimates for a 12 year planning period are listed, and the orbitor is described in terms of payloads. Shuttle operational costs, ground operational costs, and nonrecurring investment and development costs were analyzed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Econ. Analysis of Materials Processing in Space; p 8-39
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Design development of the Apollo command and service module thrust vector attitude control systems (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Development of the Apollo thrust vector control digital autopilot (TVC DAP) was summarized. This is the control system that provided pitch and yaw attitude control during velocity change maneuvers using the main rocket engine on the Apollo service module. A list of ten primary functional requirements for this control system are presented, each being subordinate to a more general requirement appearing earlier on the list. Development process functions were then identified and the essential information flow paths were explored. This provided some visibility into the particular NASA/contractor interface, as well as relationships between the many individual activities.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 63-82
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    NASA TECHNICAL REPORTS
  • 3
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    Cryogenic helium 2 systems for space applications (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Two cryogenic systems are described which will provide cooling for experiments to be flown on Spacelab 2 in the early 1980's. The first system cools a scanning infrared telescope by the transfer of cold helium gas from a separate superfluid helium storage dewar. The flexible design permits the helium storage dewar and transfer assembly to be designed independent of the infrared experiment. Where possible, modified commerical apparatus is used. The second cryogenic system utilizes a specially designed superfluid dewar in which a superfluid helium experiment chamber is immersed. Each dewar system employs a porous plug as a phase separator to hold the liquid helium within the dewar and provide cold gas to a vent line. To maintain the low vapor pressure of the superfluid, each system requires nearly continuous prelaunch vacuum pump service, and each will vent to space during the Spacelab 2 flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 507-515
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental control requirements for life sciences (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The Life Sciences dedicated Spacelab will enable scientists to test hypotheses in various disciplines. Building upon experience gained in mission simulations, orbital flight test experiments, and the first three Spacelab missions, NASA will be able to progressively develop the engineering and management capabilities necessary for the first Life Sciences Spacelab. Development of experiments for these missions will require implementation of life-support systems not previously flown in space. Plant growth chambers, animal holding facilities, aquatic specimen life-support systems, and centrifuge-mounted specimen holding units are examples of systems currently being designed and fabricated for flight.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 467-472
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  • 5
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    Thermal integration of Spacelab experiments (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The method of thermally integrating the experiments for Spacelab is discussed. The scientific payload consists of a combination of European and United States sponsored experiments located in the module as well as on a single Spacelab pallet. The thermal integration must result in accomodating the individual experiment requirements as well as ensuring that the total payload is within the Spacelab Environmental Control System (ECS) resource capability. An integrated thermal/ECS analysis of the module and pallet is performed in concert with the mission timeline to ensure that the agreed upon experiment requirements are accommodated and to ensure the total payload is within the Spacelab ECS resources.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 545-559
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  • 6
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    An assessment of thermal design procedures for Shuttle payloads (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: A review of the thermal design options for unmanned Shuttle payloads is presented. Because many future Shuttle payloads will have budgets and less time available for the definition of their thermal subsystems, simplified design procedures will be the most cost-effective. The thermal interface between an individual payload and the Orbiter is discussed. A simplified, modular thermal control system that will reduce the cost of providing thermal protection by minimizing both the initial procurement cost of any specialized hardware and the need for a detailed thermal interface analysis is described.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA Spacecraft Thermal and Environ. Control Systems; p 481-486
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  • 7
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    Further development of the multipactor discharge electron source (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: A modification to the multipactor electron source used in the study of the behavior of spacecraft insulating materials is described. The electron accelerating system was included within the source, freeing the region between the source and the target of fields produced by the source electrodes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 881-886
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    NASA TECHNICAL REPORTS
  • 8
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    The Qualification of a large electron irradiation facility for telecommunication satellite differential charging simulation (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The definition and procurement program is presented for the set up of a test simulating an electron environment on a model of a communication satellite to study the degradation of the thermal insulation materials during electron bombardment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 819-833
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  • 9
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    Secondary electron effects on spacecraft charging (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Calculations were conducted to determine the effects of electron-produced secondary electrons on the net charging current and the equilibrium voltage of spacecraft surfaces immersed in hot (keV) plasmas. The effects of secondary electrons produced by the primary plasma electrons were examined for aluminum, Teflon, Mylar, and Kapton. The results indicate that it is the primary electron energy region over which the secondary electrons are emitted (rather than the ratio of secondary to primary electrons) which determines the effectiveness of the secondary electrons in limiting the net charging current. While the electron-produced secondary electrons decreased the charging current, they had little effect upon the equilibrium voltages attained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Spacecraft Charging Technol., 1978; p 756-768
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  • 10
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    Parameter dependence of equilibrium charging potentials (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Equilibrium surface potentials for slab configurations (representative e.g. of a large solar power satellite) are determined under extensive parametric variations of materials, solar exposure and substorm characteristics. The dependence of the charging process for dielectric surfaces on the various material response characteristics is described. The results are used as a guide to the material selection and design of large space systems to minimize dielectric breakdowns and reduce parasitic leakage currents on SPS.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA Lewis Res. Center Spacecraft Charging Technol., 1978; p 711-733
    Format: text
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