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  • 1
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    THE MERCURY CAPSULE ATTITUDE CONTROL SYSTEM (1962)
    In:  CASI
    Details
    Publication Date: 2009-12-22
    Description: Mercury capsule attitude control system
    Keywords: SPACE VEHICLES
    Type: Proceedings of the National Meeting on Manned Space Flight: Unclassified Portion
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    SPACE VEHICLE ATTITUDE STABILIZATION USING PULSE-MODULATED JET CONTROL (1961)
    In:  CASI
    Details
    Publication Date: 2008-08-25
    Description: Space vehicle attitude stabilization using pulse modulated jet control
    Keywords: SPACE VEHICLES
    Type: MTP-M-G&C-61-32
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Spacecraft (1964)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: Micrometeoroid satellite Explorer XIII - vehicle and launch
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Thermal control materials (1969)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Heat absorption and emission balance for thermal control system of spacecraft
    Keywords: SPACE VEHICLES
    Type: SPACE MATER. HANDBOOK 1969; P 77-172
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The ascent environment (1969)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Aerodynamic heating, vibration, shock, and random noise environments during spacecraft ascent
    Keywords: SPACE VEHICLES
    Type: SPACE MATER. HANDBOOK 1969; P 3-11
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Composite systems utilization for space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Research and development of composite material systems to show applicability of these materials to shuttle structures and to demonstrate availability through a hardware development program is reported. The various configurations studied and potential areas of composite structures use are described and an outline of ongoing composite programs, complementing the indicated feasible applications, including a typical cost study, is shown. The following composite systems are investigated: Boron filaments with epoxy, polyimide, or aluminum matrix, and graphite filaments with epoxy or polyimide matrix.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 605-644
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Flight loads and control (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of flight loads and their potential reduction, using various control logics for the space shuttle vehicles, is very complex. Some factors, not found on previous launch vehicles, that increase the complexity are large lifting surfaces, unsymmetrical structure, unsymmetrical aerodynamics, trajectory control system coupling, and large aeroelastic effects. Discussed are these load producing factors and load reducing techniques. Identification of potential technology areas is included.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 175-203
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    New considerations for pogo prevention on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Recommendations for improving the methodology of pogo suppression for the space shuttle include: Consideration of inter-pump location for accumulator or active device, inclusion of tank outflow effects in dynamic structural analysis, the use of simplified transfer functions in systems studies, three phase dynamic testing program for turbopump with development of dynamic flowmeters, and the use of a linearized mathematical model for engine physics studies.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington NASA Space Shuttle Technol. Conf.; p 97-116
    Format: text
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  • 9
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    Development of methods for fracture control of space shuttle structures (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The technology with respect to fracture control requirements of the shuttle is considered. The current state-of-the-art does permit an approach based on linear elastic fracture mechanics concepts. Development and implementation of a fracture control plan should recognize deficiencies and provide adequate resources for the extensive empirical test data which are required. With respect to the cost impact of such tests, recent experiences involving advanced aircraft systems have seen unit cost increases of from 200 to 500 percent.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 727-770
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Docking devices for Soyuz-type spacecraft (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two docking device designs for Soyuz-type spacecraft are compared. The first was flight tested successfully; the second achieves rigid and exact joining of two spacecraft, while incorporating changes to allow for the intravehicular transfer of crew members. The main functions of the docking device are considered, with the means by which they are accomplished, and measures for increasing its reliability and flexibility in service are noted.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 143-150
    Format: text
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    NASA TECHNICAL REPORTS
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