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  • Chemistry  (27,165)
  • SPACE VEHICLES  (2,693)
  • PROPULSION SYSTEMS  (1,456)
  • Humans
  • 1970-1974  (31,314)
Collection
Keywords
Publisher
Years
Year
  • 1
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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
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  • 2
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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
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  • 3
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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
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  • 4
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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
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  • 5
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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
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  • 6
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    Aerospace transporter and lifting body activities in Europe and potential participation in the development of the space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The course of European aerospace research regarding reentry problems is briefly reviewed for the period from 1966 up to the present. The considerable experience gained by Europe, and particularly Germany, is shown to have led to their involvement and participation in the U.S. space shuttle program. The areas of investigation and expected contributions by European cooperation in the shuttle program are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 969-995
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  • 7
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    Development of payload subsystem-primate mission-Biosatellite program (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Design and operation of the primate life support subsystem for the Biosatellite Program as used during the flight of Biosatellite 3 are discussed. Included are preflight changes necessitated by the primate's (a Macaca nemistrina monkey) influence on the initial equipment design.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 177-183
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  • 8
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    Docking-mechanism attenuator with electromechanical damper (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Theoretical and practical problems involved in the application of electromechanical damping for spacecraft docking-mechanism attenuation are discussed. Some drawbacks of hydraulic dampers used for the purpose are pointed out. The basic scheme of the attenuator with the electromechanical damper is given.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 43-57
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  • 9
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    Supersonic cruise inlets (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design and characteristics of supersonic cruise inlets
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 283-312
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  • 10
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    The importance of nondestructive testing for the coated metallic thermal protection system (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Nondestructive testing techniques for coated metallic thermal protection system for space shuttles
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 261-272
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  • 11
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    Materials reuse, evaluation, inspection and repair (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Properties, evaluation, inspection, and repair of alloys and silicide coatings for space shuttles
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 247-260
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  • 12
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    Temperature control for the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Temperature control system for space shuttles
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 201-207
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  • 13
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    Space shuttle structural fatigue considerations (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle structural fatigue analysis
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 33-47
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  • 14
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    Structural design technology - Introduction and overview (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: NASA plan for development of space shuttle structural design technology
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 9-16
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  • 15
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    Problems of atmospheric entry (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Aerodynamic and heating problems of spacecraft entry into Mars and Venus atmospheres
    Keywords: SPACE VEHICLES
    Type: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 175-288
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  • 16
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    Space shuttle acoustics (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Farfield and nearfield acoustic environments of space shuttle
    Keywords: SPACE VEHICLES
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 401-422
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  • 17
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    Shuttle pogo review (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Results of pogo stability analyses
    Keywords: SPACE VEHICLES
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 359-399
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  • 18
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    Effects of space shuttle configuration on wing buffet and flutter. Part 1 - Launch vehicle with tip fin (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Influence of space shuttle configurations on wing aeroelastic behavior
    Keywords: SPACE VEHICLES
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 181-199
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  • 19
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    Recent studies of effects of ground winds on space shuttle vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Studying ground-wind loads with models of space shuttle configurations to assess aerodynamic instabilities on erected space shuttle vehicles
    Keywords: SPACE VEHICLES
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 155-179
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  • 20
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    Some landing gear considerations for space shuttle vehicles (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Criteria for designing space shuttle landing systems
    Keywords: SPACE VEHICLES
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 121-154
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  • 21
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    Acoustic environment characteristics of the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle acoustic environment characteristics and plume induced flow separation phenomenon
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 285-300
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  • 22
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    Trajectory and performance (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Trajectory and performance of Agena-Nimbus 3 satellite
    Keywords: SPACE VEHICLES
    Type: THORAD-AGENA PERFORMANCE FOR THE ~NIMBUS 3 MISSION JUN. 1970; P 13-19
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  • 23
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    Development of the ideas of K. E. Tsiolkovskiy concerning 'rocket trains' in the transactions of Soviet and foreign scientists (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Mass ratio allowances for mathematical modeling of optimal multistage rocket vehicles
    Keywords: SPACE VEHICLES
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 27-41
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  • 24
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    Pulse performance analysis for small hypergolic propellant rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Small rocket engine tests were conducted for the purpose of obtaining pulse performance data to aid in preliminary design and evaluation of attitude control systems. Both monopropellant and hypergolic bipropellant engines of thrust levels from 5 to 445 N (1 to 100 lb) were tested. The performance data for the hypergolic propellant rockets are compared with theoretical performance calculated from idealized chamber filling and evacuation characteristics. Electromechanical delays in valve response and heat transfer characteristics were found to cause substantial deviation between theoretical performance and test performance. The theoretical analysis is modified to obtain a semiempirical model for hypergolic propellant rockets.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 61-74
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  • 25
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    Extendible rocket nozzle development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An evaluation is presented of J-2 engine modifications that will simplify operation and improve reliability of the advanced Saturn 1C launch vehicle. Methods of increasing thrust without extensively modifying the S-2 or S-4B stages are also evaluated. A thrust increase was achieved by raising engine combustion through a redesign of the engine thrust chamber and propellant feed system.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 105-115
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  • 26
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of three low-density rigidized insulation materials for the shuttle TPS application is reported. These materials consist of one high purity silica system and two systems based on mullite, an aluminum silicate. Both systems consist of fibers joined together with appropriate binders to obtain a rigidized insulation composite. Both material systems require the application of a glassy coating to provide a wear resistant, high emittance surface and to prevent the absorption of water by the fiber matrix. The technology program has addressed the development of water impervious coatings, methods of assembling the materials in design concepts while minimizing the thermal stress in the insulation, achieving compatibility between the RSI material and the structural system, and test evaluations to demonstrate the feasibility of the surface insulation concept.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 435-474
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  • 27
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    Overview of technology relative to the pogo instability on space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The prediction of pogo contains a major source of uncertainty in the difficulty of defining the dynamic characteristics of certain components. An overview of the space shuttle technology with respect to each the following pogo problem areas is presented: structure, tank-liquid interaction, feedline, engine (pump), pogo-loop/control-loop interaction, and stability analysis.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 117-138
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  • 28
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    Assessment of potential buffet problems on the space shuttle vehicle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Buffet of the space shuttle launch and reentry configuration is an area requiring continued evaluation to produce a safe reliable vehicle of minimum weight. Buffet forces result from flow separation and therefore can not be predicted accurately. Buffet loads are highly sensitive to configuration, angle of attack, and Mach number and can be reliably determined only by wind tunnel tests of elastically scaled models.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 25-43
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  • 29
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    Dynamic analysis for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Two approaches that are used for determining the modes and frequencies of space shuttle structures are discussed. The first method, direct numerical analysis, involves finite element mathematical modeling of the space shuttle structure in order to use computer programs for dynamic structural analysis. The second method utilizes modal-coupling techniques of experimental verification made by vibrating only spacecraft components and by deducing modes and frequencies of the complete vehicle from results obtained in the component tests.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 205-230
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  • 30
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    Surface studies on Surveyor 3 tubing sections (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Sections C and E of the unpainted, polished aluminum tubing from the strut of the radar altimeter and Doppler velocity sensor were examined in a transmission electron microscope for micrometeorite damage and ion bombardment. Both sections were contaminated and eroded on one side; it is suggested that these conditions were caused by sandblasting by lunar dust and retrorocket plume contamination during Surveyor 3 landing. Microcraters of different configurations were found on the bright sides of the tubes. Several degrees of violence were involved in the formation of the craters, and the particle size could be responsible for some differences. All micropits found were on the bright areas and data indicate 0.2 hypervelocity impact/sq cm and 2/sq cm for other types of craters. The greatest degree of damage resulted from particle impact and was limited to a maximum depth of 2 microns.
    Keywords: SPACE VEHICLES
    Type: NASA, Washington Analysis of Surveyor 3 Mater. and Phot. Returned by Apollo 12; p 154-158
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  • 31
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    Velocity diagrams (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The selection and design of velocity diagrams for axial flow turbines are considered. Application is treated in two parts which includes: (1) mean-section diagrams, and (2) radial variation of diagrams. In the first part, the velocity diagrams occurring at the mean section are assumed to represent the average conditions encountered by the turbine. The different types of diagrams, their relation to stage efficiency, and their selection when staging is required are discussed. In the second part, it is shown that in certain cases the mean-section diagrams may or may not represent the average flow conditions for the entire blade span. In the case of relatively low hub- to tip-radius ratios, substantial variations in the velocity diagrams are encountered. The radial variations in flow conditions and their effect on the velocity diagrams are considered.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 69-99
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  • 32
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 2: Hypersonics (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An early version of an external hydrogen-oxygen tank orbiter was used as a baseline vehicle to experimentally evaluate: (1) nose shape and canopy effects on longitudinal, lateral, and directional stability and trim, and (2) yaw due to aerodynamic roll control at hypersonic speeds. Nose alterations were examined since that part of the vehicle may be subject to modifications because of internal packaging requirements, alleviation of potential high heating areas, and/or possible improvements in aerodynamic stability and control. There was also some concern about the effect of the rather high profile canopy on the aerodynamics; therefore its removal was examined. In addition, roll-yaw coupling was investigated because of its impact on the RCS fuel requirements for entry maneuvers.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 803-830
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  • 33
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    Impact of subsonic aerodynamic considerations on a space shuttle booster configuration (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Considerations of cruise-back efficiency and subsonic flying qualities are shown to have resulted in a configuration with an aft high wing of moderate aspect ratio and with vertical tails located at the wing tips. The need to protect the air breathing engines during ascent and reentry and the desire for a low trim penalty longitudinal control surface led to consideration of a jet-flap canard. The advantages of this application of STOL technology to a space system are examined and the results of both wind tunnel tests and flight simulations are discussed. Since the use of the jet-flap canard concept offers the potential for a minimum weight vehicle, a proposed technology development program is outlined in order that the full benefit of this concept may be realized.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol.3; p 737-784
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  • 34
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    On the possibility of Earth reentry simulation of shallow angle Jupiter entry (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Possible Earth reentry simulation of shallow-angle (3 to 30 deg) Jupiter entry was investigated in terms of four parameters of the bow shock layer ahead of a blunt vehicle: peak (equilibrium) temperature, peak pressure, peak inward radiative flux, and time-integrated radiative flux. It is shown that simulation ranging from fair to good can be achieved. Reentry is easiest (lowest Earth reentry speed) at steep Earth reentry, in the Earth entry speed range of 15 to 22 km/sec, for both the Jupiter nominal and cool atmospheres. Increased Earth speed is required, generally, for increasing Jupiter entry angle, and for increasing temperature, radiative flux, time-integrated flux and pressure, in that order.
    Keywords: SPACE VEHICLES
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 19-29
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  • 35
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    Materials properties and allowables for the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle materials properties and allowables
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 273-287
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  • 36
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    Thermal protection systems - Introduction and overview (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle thermal protection systems technology program summary
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 139-144
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  • 37
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    The development of effective fracture control procedures for space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Structural fracture causes and control procedures for space shuttles
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 49-60
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  • 38
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    Orbiting astronomical observatory mission operations (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Stabilization and control system and mission operations for OAO
    Keywords: SPACE VEHICLES
    Type: OPT. TELESCOPE TECHNOL. 1970; P 635-643
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  • 39
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    Application of composite materials to space shuttle tanks (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tanks are broken down into two categories: pressure vessels that carry primarily pressure loads, and structural tanks that carry structural loads such as thrust or bending in addition to pressure. A significant portion of the shuttle orbiter structure are tanks and in order to minimize both weight and cost growth on these shuttle tank structures, composite material tanks of both types are considered.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 573-603
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  • 40
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    Advanced design concepts for shuttle airframe structure (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of weight-saving advanced design concepts for shuttle airframe structure is presented. Design concepts under investigation employ selective composite reinforcement and/or efficient geometric arrangements. An effort to develop metallic panel designs which exploit the relaxation of smooth external-surface requirements for skin structure is reviewed. Available highlights from research and development studies which investigate the application of composite reinforcement to the design of two types of fuselage panels, a shear web, a large fuselage frame, and a landing-gear-door assembly are presented. Preliminary results from these studies suggest weight savings of 25 percent can be obtained.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 537-572
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    Flutter technology for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The development of analytical and experimental techniques needed to predict space shuttle flutter boundaries and insure adequate flutter margins and anticipated problems associated with aeroelastic-model and full-scale testing to validate flutter clearance are considered. Results illustrating the best available tools for subsonic and supersonic flutter prediction are presented. Programs currently underway which will help overcome the difficult problems envisioned for the transonic wind-tunnel and flight flutter test program are also discussed.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 1-24
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  • 42
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    Gas-powered reentry body erection mechanism (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design, analysis, testing, and flight of the supersonic planetary entry decelerator 2 spacecraft are described. The vehicle was launched in a folded condition and deployed to its required configuration following exit from the atmosphere. This concept was selected primarily because it allows utilization of existing launch vehicle systems in the most economical manner possible.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 101-107
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  • 43
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    Satellite temperature correlation of predicted, test, and flight data (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: This study compares satellite temperature predictions with thermal vacuum test results and shows the improvement from testing. Orbital data were compared with prediction/test results to determine quantitatively an expected error criteria.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 425-443
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  • 44
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    Experiments on the dynamic stability of the space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some dynamic stability experiments on the space shuttle using a half-model oscillatory technique are discussed. Resulting information from the experiments is presented and includes: (1) dynamic pitching characteristics of both the orbiter and the booster alone as well as of the two models mated into a single launch configuration; (2) the static and dynamic interference effects during an abort separation maneuver; and (3) the dynamic plume interference effect.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 933-968
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  • 45
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    Manned spacecraft electrical fire safety (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The fire hazards created in spacecraft compartments by malfunction of electrical wiring are described. The tests for electrical wire/cable current overload flammability are presented. The application of electrical and material technologies to the reduction of fire hazards in spacecraft are examined.
    Keywords: SPACE VEHICLES
    Type: Conf. on Mater. for Improved Fire Safety; p 173-178
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  • 46
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    Aerospace vehicle separation mechanisms selection, design, and use considerations (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The principal types of separation systems and mechanisms used in spacecraft are described and compared. Important parameters to be considered in tradeoff studies are discussed. Several examples of successful applications and failures and the lessons learned from them are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 17-23
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  • 47
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    Secondary structures and mechanisms - Design trouble area for the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Secondary structure and mechanism design problems for space shuttles
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 93-99
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  • 48
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    Structural design and analysis of the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle structural design and finite element analysis
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 61-71
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  • 49
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    Apollo telescope mount operations and data-handling (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Observation mission and data handling operations for Apollo Telescope Mount
    Keywords: SPACE VEHICLES
    Type: OPT. TELESCOPE TECHNOL. 1970; P 645-656
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  • 50
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    Thorad vehicle system performance (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Thorad launch vehicle system performance
    Keywords: SPACE VEHICLES
    Type: THORAD-AGENA PERFORMANCE FOR THE NIMBUS 3 MISSION JUN. 1970; P 21-40
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  • 51
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    Agena vehicle system performance (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Agena rocket vehicle system description and performance
    Keywords: SPACE VEHICLES
    Type: THORAD-AGENA PERFORMANCE FOR THE NIMBUS 3 MISSION JUN. 1970; P 41-62
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  • 52
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    Realization of the ideas of K. E. Tsiolkovskiy in the reports of the GSRM (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design and development of rocket engines
    Keywords: PROPULSION SYSTEMS
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 1-10
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  • 53
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    Basic turbine concepts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Turbine geometric, flow, energy transfer, efficiency, and performance characteristics are considered by the use of definitions, diagrams, and dimensionless parameters. Emphasis is placed on the determination of the fluid velocity as it passes from one blade row to the next. The general methods for constructing velocity diagrams and relating them to the work and flow capacity of the turbine are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 21-67
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  • 54
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    Dynamic testing for shuttle design verification (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Space shuttle design verification requires dynamic data from full scale structural component and assembly tests. Wind tunnel and other scaled model tests are also required early in the development program to support the analytical models used in design verification. Presented is a design philosophy based on mathematical modeling of the structural system strongly supported by a comprehensive test program; some of the types of required tests are outlined.
    Keywords: SPACE VEHICLES
    Type: NASA Space Shuttle Technol. Conf.; p 231-265
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  • 55
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    Neuter docking mechanism study (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Neuter (or androgynous) docking systems that allow space vehicles with similar or identical docking hardware to dock are discussed. Basic requirements applicable to docking mechanism design, four neuter concepts that were studied, and the concept selected by the NASA Manned Spacecraft Center for detailed investigation are presented.
    Keywords: SPACE VEHICLES
    Type: 6th Aerospace Mech. Symp.; p 43-49
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  • 56
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    Aerodynamic studies of delta-wing shuttle orbiters. Part 1: Low speed (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Numerous wind tunnel tests conducted on the evolving delta-wing orbiters have generated a fairly large aerodynamic data base over the entire entry operation range of these vehicles. A limited assessment is made of some of the aerodynamics of the current HO type orbiters, and several specific problem areas selected from the broad data base are discussed. These include, from a subsonic viewpoint, discussions of trim drag effect; effects of the installation of main rocket engine nozzles, OMS and RCS packages, Reynolds number effects, lateral-directional stability characteristics, and landing characteristics.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 785-802
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  • 57
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    Wing optimization for space shuttle orbiter vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The results were presented of a parametric study performed to determine the optimum wing geometry for a proposed space shuttle orbiter. The results of the study establish the minimum weight wing for a series of wing-fuselage combinations subject to constraints on aerodynamic heating, wing trailing edge sweep, and wing over-hang. The study consists of a generalized design evaluation which has the flexibility of arbitrarily varying those wing parameters which influence the vehicle system design and its performance. The study is structured to allow inputs of aerodynamic, weight, aerothermal, structural and material data in a general form so that the influence of these parameters on the design optimization process can be isolated and identified. This procedure displays the sensitivity of the system design of variations in wing geometry. The parameters of interest are varied in a prescribed fashion on a selected fuselage and the effect on the total vehicle weight is determined. The primary variables investigated are: wing loading, aspect ratio, leading edge sweep, thickness ratio, and taper ratio.
    Keywords: SPACE VEHICLES
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 831-860
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  • 58
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    Status of Langley studies of aerodynamics and interference effects of tandem launch vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Some of the aerodynamic and interference effects measured from wind-tunnel tests of three fully reusable space shuttle configurations at transonic and low-supersonic speeds are presented, and the status is given of an assessment of the analytical approach to date. The three configurations tested were a low-fineness-ratio booster combined in tandem with a delta-wing orbiter, designated the "low-fineness-ratio configuration,' and a phase B shuttle configuration consisting of the delta-wing orbiter and high-fineness-ratio booster, designated the "stage-arrangement configuration,' arranged in tandem and in parallel. The force measurements obtained at a Mach number of 1.5 for the low-fineness-ratio configuration were representative of the transonic and low-supersonic speed ranges where the interference effects are predominant and were used for comparison with values calculated at the same Mach number. This comparison is the basis for a preliminary assessment of the initial application of the analytical approach.
    Keywords: SPACE VEHICLES
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 3; p 707-736
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  • 59
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    Flammability control in the oxygen environment of the Apollo guidance and navigation equipment (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The Apollo guidance and navigation (G&N) equipment test program, the redesign philosophy, and the actual equipment modifications that were used to limit burn rates in an environment of 100 percent oxygen at pressures of 6.2 and 16 psia are described. The major approach was a serious basic review of the real function of the nonmetallic materials of concern. The result of this review was that the materials could be replaced, eliminated, or covered by nonflammable metallic materials. Although several low-flammability nonmetallic materials were investigated, the direct approach of cover, eliminate, or replace generally proved to be quicker and more effective.
    Keywords: SPACE VEHICLES
    Type: Conf. on Mater. for Improved Fire Safety; p 211-217
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  • 60
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    Low-cost ablative heat shields (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Low cost ablative heat shield program
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 195-200
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  • 61
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    Superalloy heat shield technology for the space shuttle (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Heat resistant alloy technology for space shuttle reentry shields
    Keywords: SPACE VEHICLES
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 145-158
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  • 62
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    Space shuttle structural prototype design, fabrication, and test (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Space shuttle structural prototype design, fabrication and test program
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 123-138
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  • 63
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    Applications of advanced composite materials to space shuttle structures (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: NASA programs for composite space shuttle structures
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 73-92
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  • 64
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    Space shuttle structural design criteria development (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: NASA structural design criteria development and specific problem areas requiring more study
    Keywords: SPACE VEHICLES
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 3 JUL. 1970; P 17-32
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  • 65
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    Development of Tsiolkovskiy's ideas on the use of air in the engines of space vehicles (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Atmospheric air storage for use in space vehicle engines during planetary flight
    Keywords: PROPULSION SYSTEMS
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 69-76
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  • 66
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    A nutation damper for a spinning satellite (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design, testing, and fabrication of nutation damper for small spinning satellites
    Keywords: SPACE VEHICLES
    Type: JPL PROC. OF THE 4TH AEROSPACE MECH. SYMP. 15 JAN. 1970; P 135-142
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  • 67
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    A despin assembly for the TACOMSAT communications satellite (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design and testing of torque motor driven bearing assembly with integral slip ring unit for experimental tactical communications satellite
    Keywords: SPACE VEHICLES
    Type: JPL PROC. OF THE 4TH AEROSPACE MECH. SYMP. 15 JAN. 1970; P 95-102
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  • 68
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    Performance characteristics of the lifting body vehicle (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Prediction of performance characteristics for lifting body vehicle
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 43-58
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  • 69
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    Correlation of flight-test loads with wind- tunnel predicted loads on three lifting body vehicles (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Correlation of flight test loads with wind tunnel predicted loads on three lifting body vehicles
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 59-72
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  • 70
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    Assessment of lifting body vehicle handling qualities (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Assessment of lifting body vehicle handling qualities
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 29-41
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  • 71
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    Stability and control derivatives of the lifting body vehicles (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Wind tunnel and flight tests for stability and control derivatives of lifting body vehicles
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 11-27
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  • 72
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    Background and current status of the lifting body program (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Lifting body application to design of space shuttle system
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 1-10
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  • 73
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    Flight test results pertaining to the Space Shuttlecraft - Final remarks and future plans (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Analysis of research on space shuttle systems
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 147-151
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  • 74
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    Rationale for proposed flying-qualities specifications (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Proposed flying qualities specifications for space shuttle
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 127-145
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  • 75
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    Summary of primary results of the lifting body program (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Summary of primary results of lifting body program for space shuttle system
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 89-97
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  • 76
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    Approach and landing studies (1970)
    In:  CASI
    Details
    Publication Date: 2005-08-18
    Description: Application of approach and landing data to design of space shuttle
    Keywords: SPACE VEHICLES
    Type: FLIGHT TEST RESULTS PERTAINING TO THE SPACE SHUTTLECRAFT OCT. 1970; P 99-108
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  • 77
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    Some contamination problems in the European TD satellite (1972)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Materials were selected for the European TD satellite with a view to avoiding contamination of its stellar ultraviolet telescopes. Materiels were selected using the micro-VCM technique, and some typical cases of materials evaluation are described. The cleanliness of the satellite was monitored during integration and test phases, and in particular during long duration thermal vacuum tests.
    Keywords: SPACE VEHICLES
    Type: NASA. Goddard Space Flight Center Space Simulation; p 613-627
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  • 78
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    Surveyor spacecraft real-time payload operations (1970)
    In:  CASI
    Details
    Publication Date: 2009-11-16
    Description: Command and control system for real-time operation of Surveyor spacecraft
    Keywords: SPACE VEHICLES
    Type: NASA, WASHINGTON OPT. TELESCOPE TECHNOL. 1970; P 615-633
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  • 79
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    K. E. Tsiolkovskiy and the first practical steps in Soviet rocketry (1970)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Formula for determining optimal rocket motion from mass ratio and exhaust stream velocity
    Keywords: SPACE VEHICLES
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SEI. HERITAGE OF E. K. TSIOLKOVSKIY APR. 1970; P 62-68
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  • 80
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    Investigation of the possibility of use of vibroacoustical signals for purposes of diagnostics in aeronautical engineering (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The application of vibroacoustic techniques for diagnosing aircraft engine malfunctions is discussed. An experiment was conducted to determine the defects introduced by the nature of change in the amplitude-frequency characteristics of the noises and vibrations of an aircraft jet engine. The manner in which the defects were simulated is explained. The test equipment used during the experiment is identified. The results of the amplitude-frequency characteristics investigation are summarized to show optimum location of the microphone pick-up to record the acoustic data.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 317-319
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  • 81
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    The problem of carrying out a diagnosis of an internal combustion engine by vibroacoustical parameters (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The physics of noise formation in an internal combustion engine is discussed. A dependence of the acoustical radiation on the engine operating process, its construction, and operational parameters, as well as on the degree of wear on its parts, has been established. An example of tests conducted on an internal combustion engine is provided. A system for cybernetic diagnostics for internal combustion engines by vibroacoustical parameters is diagrammed.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 247-249
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  • 82
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    Minimum impulse tests of 0.45-N liquid hydrazine catalytic thrusters (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An exploratory test series was conducted on three types of 0.45-N (0.1 lbf) liquid hydrazine thrusters to ascertain the minimum impulse bit capability for this class of engine. The test series is described and the results are presented. The testing was performed at 21 and 145 C (70 and 300 F) while maintaining nominal 0.45 N (0.1 lbf) upstream conditions. Valve on-times as low as 0.008 sec were applied. Impulse bits were observed for thruster temperatures of 21 and 145 C (70 and 300 F), respectively.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 107-112
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  • 83
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    Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 113-122
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  • 84
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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
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  • 85
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    Fan and compressor technology (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Characteristics of fans and compressors for aircraft turbine engines
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 1-36
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  • 86
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    Dynamics and control (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Dynamics and control of supersonic propulsion systems
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 351-395
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  • 87
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    Effects of engine inlet disturbances on engine stall performance (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Effects of engine inlet disturbances on engine stall performance
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 313-341
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  • 88
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    Supersonic exhaust nozzles (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Design and characteristics of exhaust system for supersonic aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 233-282
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  • 89
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    V/STOL propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Propulsion technology for STOL and V/STOL commercial aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 135-168
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  • 90
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    Turbine cooling research (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Development of improved turbine cooling processes and facilities for conducting turbine cooling research
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 57-96
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  • 91
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    A technique for the determination of the dipole moment of a spacecraft from a limited amount of near field data (1970)
    In:  CASI
    Details
    Publication Date: 2006-04-25
    Description: Field measurements by rotating spacecraft for dipole moment determination
    Keywords: SPACE VEHICLES
    Type: NIFICANT ACCOMPLISHMENTS IN SCI. AND TECHNOL. AT GODDARD SPACE FLIGHT CENTER 1970; P 324-326
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  • 92
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    An analysis of thermally induced oscillations of stem type booms (1970)
    In:  CASI
    Details
    Publication Date: 2006-04-25
    Description: Dynamic thermal oscillation analysis on satellite boom rod
    Keywords: SPACE VEHICLES
    Type: NIFICANT ACCOMPLISHMENTS IN SCI. AND TECHNOL. AT GODDARD SPACE FLIGHT CENTER 1970; P 216-220
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  • 93
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    Low cost engines for aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Development and characteristics of low cost engines for general aviation aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 211-231
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  • 94
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    Combustion (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Effects of engine design and propulsion system configurations on combustion efficiency
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 97-134
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  • 95
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    Solar-electric propulsion breadboard thrust subsystem (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A solar-electric propulsion breadboard thrust subsystem has been designed, built, and tested. A 1500-h test was performed to demonstrate the functional capabilities of the subsystem. Described are the subsystem functions and testing process. The results show that the ground work has been established for development of an engineering model of the thrust subsystem.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 100-112
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  • 96
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    Miscellaneous losses (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The boundary-layer losses associated with the flow process in the blade channel are discussed. To determine the overall design point efficiency of a turbine, other losses must also be considered; these include tip clearance loss and disk friction loss. The sum of these losses normally comprises all the losses that are considered in the design of a full admission axial flow turbine. If, however, a partial admission turbine is being considered, there are additional losses that must be included. The partial admission losses usually considered are the pumping loss in the inactive blade channels and the filling-and-emptying loss in the blade passages as they pass through the admission arc. Finally, a loss that occurs at off-design operation of any turbine is the incidence loss.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 2; p 125-148
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  • 97
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    Channel flow analysis (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The design of a proper blade profile requires calculation of the blade row flow field in order to determine the velocities on the blade surfaces. An analysis theory is presented for several methods used for this calculation and associated computer programs that were developed are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 2; p 27-56
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  • 98
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    Blade design (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The design of turbine blading is considered that will produce the flow angles and velocities required by velocity diagrams consistent with the desired efficiency and/or number of stages. The determination of the size, shape, and spacing of the blades is fundamental.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl. Vol. 2; p 1-25
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  • 99
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    Architecture in outer space (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Mulilayer thin film structures consisting of systems of shells filled with gas at some pressure are recommended for outer space structures: Large mirrors to collect light and radio waves, protection against meteoric impact and damage, and for connectors between state space stations in the form of orbital rings. It is projected that individual orbital rings will multiply and completely seal a star trapping its high temperature radiation and transforming it into low temperature infrared and short wave radio emission; this radiation energy could be utilized for technological and biological processes.
    Keywords: SPACE VEHICLES
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 161-169
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  • 100
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    Spacecraft of the future (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Manned interstellar expeditions require future ion propulsion rocket engines able to achieve a flight velocity of 0.3 times the speed of light, and a closed ecological system onboard the interstellar spacecraft that incorporates biological links and complicated technical facilities to insure long term life support for its crew.
    Keywords: SPACE VEHICLES
    Type: Inhabited Space, Pt. 2 (NASA-TT-F-820); p 135-153
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