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  • SPACE VEHICLES  (2,693)
  • Analytical Chemistry and Spectroscopy  (2,128)
  • Chemical Engineering  (1,794)
  • LUNAR AND PLANETARY EXPLORATION
  • 1970-1974  (7,082)
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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    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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  • 10
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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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  • 11
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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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  • 12
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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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  • 13
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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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  • 14
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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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  • 15
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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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  • 16
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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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  • 17
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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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  • 18
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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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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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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  • 24
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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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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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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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  • 30
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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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  • 31
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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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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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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  • 36
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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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  • 37
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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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  • 38
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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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  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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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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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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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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  • 54
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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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  • 55
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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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  • 56
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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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  • 57
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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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  • 58
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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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  • 59
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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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  • 60
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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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  • 61
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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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  • 62
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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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  • 63
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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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  • 64
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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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  • 65
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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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  • 66
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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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  • 67
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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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  • 68
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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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  • 69
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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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  • 70
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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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  • 71
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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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  • 72
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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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  • 73
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    Apollo 12 soil mechanics investigation (1971)
    In:  CASI
    Details
    Publication Date: 2006-08-20
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Calif. Univ. Res. in the Space Sci., v. 2; 24 p
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  • 74
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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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  • 75
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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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  • 76
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    Microbiological and experimental-histological investigations of lunar samples returned by the Lunar 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Lunar surface material was studied for its content of viable microorganisms (aerobic and anaerobic, fungi, and viruses); the effect of the lunar surface material on the growth of microorganisms and its interaction with somatic cells of mammals was also observed. No viable microorganisms were detected; the samples exhibited neither stimulant or inhibitory action on the growth of microorganisms, and also showed no cytopathogenic action on tissue cultures. A suspension of lunar surface material particles was not toxic when parenterally administered to certain laboratory animals. The particles were subjected to intense phagocytosis by connective tissue cells in vivo and in vitro.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 597-605
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  • 77
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    Study of friction properties of lunar surface material and its analogs (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A description is given of instruments for determining the friction properties of the surficial layer of lunar surface material returned by the Luna 16 automatic lunar station, as well as the friction properties of its analogs: andesite-basaltic sand and basalts. The experimental method and results are presented.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 590-596
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  • 78
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    Results of investigating the physicomechanical properties of a sample of lunar surface material in a research chamber in nitrogen (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Results are reported on an investigation of the mechanical properties of the lunar surface material sample returned by the Luna 16 automatic station. The study included determination of the specific weight of the surface material, the nature of its disintegration, and the determination of its compressibility characteristics, shear resistance, and bearing capacity. Quantitative data are presented on mechanical properties for the lunar surface material, many of which are determined for the first time. The instruments and experimental techniques are described.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 556-569
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  • 79
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    Results of investigating thermal and electrical properties of lunar surface material and its analogs (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Thermal and electrical properties are reported of lunar surface material returned to Earth by the Luna 16 automatic station and its terrestrial analogs studied in a vacuum and in a helium atmosphere. Study of the lunar surface material and its analogs showed that their specific heat capacity and electrical properties are similar in value but the coefficients of thermal conductivity differ. The results are compared with data on thermal and electrical properties of the surficial layer of the Moon obtained by indirect radiometric methods, and with results obtained for samples of lunar surface material returned to Earth by the crew of the Apollo 11 spacecraft.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 549-555
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  • 80
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    Heat-physical properties of lunar surface material returned to earth by the Luna 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Density, specific heat capacity, and coefficient of thermal conductivity were studied on a sample of lunar surface material returned by the Luna 16 automatic station. The study was carried out in a helium-filled chamber. The density of the surface material when freely heaped was 1.2 g/cu cm, and when shaken down -- 1.7 g/cu cm. The specific heat capacity was 0.177 + or - 0.010 cal x g/1 x deg/1. The coefficient of thermal conductivity in the material was 4.8 x 10/6 + or - 1.2 x 10/6 cal x cm/1 x sec/1 x deg/1.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F15881); p 538-548
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  • 81
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    Temperature emission spectrum of exoelectrons of lunar regolith (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Thermostimulated exoelectronic emission of eight fragments of regolith returned by the Soviet Luna 16 automatic station was studied. The nature of the exoemission glove-curves was determined by particle type. Fragments of breccia, sinter, slag, anorthosite, glass plate, and leucocratic gabbro after the first heating disclosed a single exoemission maximum, whose temperature position is in the range 115 to 200 C. The data obtained indicate the complex and inhomogeneous energy structure of some regolith fragments. The presence of surface states capable of forming sorptive bonds can be assumed for most particles. The exoemission of anorthosite, olivine, and the glass spherule is due to the presence of formation defects at their surfaces.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 528-537
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  • 82
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    Exoelectronic emission of particles of lunar surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A secondary electron multiplier was used to study the thermostimulated exoelectronic emission of particles of lunar surface material returned by the Soviet Luna 16 automatic station. The natural exoemission from fragments of slag, glass, anorthosite, and a metallic particle was recorded in the isochronic and isothermal thermostimulation regimes. The temperature of emission onset depended on the type of regolith fragment. For the first three particles the isothermal drop in emission is described by first-order kinetic equations. For the anorthosite fragment, exoemission at constant temperature is characterized by a symmetric curve with a maximum. These data indicate the presence of active surface defects, whose nature can be due to the prehistory of the particles.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 521-527
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  • 83
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    Magnetic properties of lunar samples returned by Luna 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Results of measuring the specific magnetic susceptibility of regolith are presented. The data indicate that regolith samples from the Sea of Tranquillity and the Sea of Fertility are similar in order of magnitude of the specific magnetic susceptibility. Several stony meteorites of subgroup L have a similar value of this quantity. After comparison with artificial analogs, it can be concluded that the bulk content of ferromagnetic minerals in regolith samples is 3 to 4 percent.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 502-511
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  • 84
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    Metallographic study of metallic fragment of lunar surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A high precision investigation of a metallic fragment from the lunar material returned by the Soviet Luna 16 automatic station revealed three characteristic temperature intervals with different kinetics of solid solution decomposition. The following were found in the structure of the iron-nickel-cobalt alloy: (1) delta-phase and alpha-ferrite of diffusional, displacement origin in the grain boundary and acicular forms; and (2) martensite of isothermal and athermal nature, acicular, lamellar, massive, and dendritic. The diversity of the shapes of structural constituents is associated with the effect on their formation of elastic distortions and various mechanisms of deformation relaxation processes.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 512-520
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  • 85
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    Cathodoluminescence of regolith returned by Luna 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Observations of local variations in the intensity and spectral composition of the cathodoluminescence of lunar regolith are described. These variations are caused by structural features, by the kind and quantity of the material, and by the admixtures. In addition, cathodoluminescent emission is also associated with a change in the temperature of the lunar surface. Periodic diurnal illumination and darkening of the moon is responsible for a temperature gradient normal to the lines of longitude. These observations made of regolith, using a scanning electron microscope with an attachment for temperature variation, simulate the indicated thermal changes of the cathodoluminescent properties of lunar material.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 496-501
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  • 86
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    Infrared transmission spectra of Sea of Fertility regolith (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Transmission spectra in the 2-25 micrometer region were obtained for samples of lunar regolith returned by the Luna 16 automatic station. A comparison of the Luna 16, Apollo 11, and Apollo 12 samples showed that the infrared transmission spectra of regolith samples from the mare regions are similar and characteristic of basic basaltic rocks. The absorption bands show up in the vibration region of the SiO4 groups. No water and OH groups were found in the samples based on the spectrum. Spectra of regolith samples calcined at 1000C showed changes that can be interpreted as changes in the spectra of irradiated crystals (especially distinctly for the Luna 16 samples).
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 486-495
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  • 87
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    Photo-polarization study of lunar samples: Negative branch (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Polarization measurements with a telescope for the degree of polarization of light reflected by planetary surfaces, and comparative measurement of terrestrial minerals, meteorites, and returned lunar samples are reported. The polarization curve plots of the dependence of the degree of polarization on the phase angle V are plotted and compared with each other to determine the optical characteristics of the planetary surfaces.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 477-485
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  • 88
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    Photometric and polarimetric analysis of samples of lunar surface material returned by the Luna 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Polarimetric properties were determined for the L-16-19-1-116 samples, weighing 0.087 g. The measurements were made for five wavelengths between 3540 and 5850 AU. In addition, the normal albedo was determined for each of these wavelengths. The albedo for the measured sample was slightly lower than for the typical material of the dark lunar maria and in addition, there was a well developed branch of negative polarization, which resembles the branch obtained for carbonaceous chondrites crushed into powder, and the branch obtained for the powders of several terrestrial basaltic and ultrabasic rocks.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 468-476
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  • 89
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    Light scattering indicatrices of lunar surface material returned by Luna 16 automatic station (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Measurements are made of the indicatrix of scattering of lunar surface material with an indicatometer that has a spread of the illuminating beam of less than 0.5 deg and of the detected beam of about 1.5 deg. The results are compared with the indicatrices for the lunar mean obtained by terrestrial telescopic measurements. It is concluded that the main features of the reflection of light by the moon) (rapid rise in brightness with approach to the full moon) are accounted for by the microrelief caused principally by grains smaller than a millimeter.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 449-452
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  • 90
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    Infrared spectroscopy of lunar mare regolith (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Spectra of reflection, emission, and transmission of regolith returned by the Luna 16 automatic station were investigated in the 1.8-13 micrometers region. A reflection maximum was shown to be present in the region 3 to 5 micrometer, along with a corresponding minimum in the emission coefficient. The spectra were interpreted based on a comparison of the optical properties with the chemical and structural properties of the regolith. The regolith in the entire array of properties in the infrared region differs appreciably from terrestrial objects. Spectra of diffuse reflection and the spectra at angles of incidence 0 deg and angles of reflection 15 and 30 deg with samples of the regolith returned by the Apollo 11 and Apollo 12 missions revealed a similarity of the infrared reflection characteristics of the regolith from different lunar mare regions.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 453-467
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  • 91
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    Optical characteristics of regolith from the Sea of Fertility, Sea of Tranquillity, and Ocean of Storms (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: A diffuse reflection spectra analysis is reported for regolith returned by the Luna 16 automatic station and by the Apollo 11 and Apollo 12 expeditions. The spectra of the specular reflection of Sea of Fertility regolith, as well as the spectra of diffuse reflection from polished sections of lunar rocks from the Sea of Tranquillity and the Ocean of Storms have no well-defined structures and are close to each other. The lowest reflectivity is exhibited by the Sea of Tranquillity regolith, and the highest -- by the Ocean of Storms regolith. A weak absorption band with a maximum near 1 nm is noted in the spectra, corresponding to the Fe-2(+) ion in the octahedral position in the lattice of regolith mineral constituents. When the indicatrix of scattering of the regolith was recorded, a specular component was detected.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 441-448
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  • 92
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    Rb-Sr age and content of potassium, rubidium strontium, barium, and rare earths in surface material from the Sea of Fertility (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The Luna 16 automatic station returned from the Sea of Fertility a 35 cm long column of lunar surface material. 1 g of the Luna 16 lunar surface material, taken at a depth of 22 cm, consists of fine material: surface material and fine fragments of rocks from 1 to 4 mm in diameter. Analyses made on 17 mg of the fine lunar surface material are presented. The results obtained for the Luna 16 surface material are plotted on the diagram of the isotopic evolution of strontium and show that this surface material is most depleted of radiogenic Sr-87 of all the known lunar surface materials and that the point characterizing Lunar 16 lies somewhat to the right of the line corresponding to an age of 4.6 billion years.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 436-440
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  • 93
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    Absolute age of lunar regolith material from the Sea of Fertility (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: By averaging the absolute age of lunar regolith materials from the Sea of Fertility for the fine regolith fraction from the core zone V, an age of 4.65 10 to the 9th power + 0.4 10 to the 9th power years was obtained, employing as the primordial Sr-87/Sr-86 ratio 0.69884 (ADOR). Also close to this age value is the age estimate based on the Pb-207/Pb-206 ratio. Using the value 0.69898 (BABI) as a primordial Sr-87/Sr-86 ratio reduces the calculated age of the fine regolith fraction to 4.25 X 10 to the 9th power years. The fine fraction of lunar regolith from the Sea of Fertility is also characterized by a minimum addition of radiogenic Sr-87, a minimum Rb/Sr ratio, and a maximum K/Rb ratio compared with analogous lunar material from other points.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 410-435
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  • 94
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    Study of radiation damage and structure of Luna 16 sample particles using high-resolution electron microscopes (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Using an electron scanning microscope and a high voltage microscope, a study was made of the radiation damage and structure of micron sized grains and grains separated from the 200-mesh fraction of the L-16-19 surface material sample. Then the structural features were compared with those found by studying with the same techniques grains separated from 20 different samples of lunar dust taken from the Apollo 11, Apollo 12, Apollo 14, and Apollo 15 collections. The L-16-19 sample is similar to the most intensely irradiated samples returned to earth by Apollo craft.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 404-409
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  • 95
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    Study of sample of Sea of Fertility lunar surface material by the track method (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Tracks in crystals of feldspars, olivines, pyroxenes, and in several fragments of basalts from a sample of Luna 16 lunar surface material were studied. A high track density, exceeding 10 to the 8th power cm/2 was found. The tracks were produced mainly by iron group nuclei of cosmic galactic and solar rays.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 400-403
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  • 96
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    Radiation damage and structure recorded at high resolution in grains from fine fractions of Luna 16 surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Samples returned to earth by Luna 16, were studied with a high voltage electron microscope for ultramicroscopic features. The following amazing features were noted in particles of surface material returned in all the lunar trips: A very high density of tracks of nuclear particles, ultrathin amorphous shells, highly rounded forms, and amazingly good ordering of crystal lattice. These features were used along with calibration experiments in solving the following problems: (1) determining the energy spectrum and chemical abundances of the very heavy nuclei in the solar wind and in the solar cosmic rays; (2) studying the past activity of the sun; (3) obtaining data on lunar dynamic processes affecting dust particles; (4) analyzing composite effects caused by penetration of solar wind into the lunar surface material; and (5) establishing the existence of the ancient lunar atmosphere and magnetic field.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 388-399
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  • 97
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    Some results of track method of investigating Luna 16 lunar material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Preliminary data from an investigation of tracks in olivine crystals, separated from the five zones of a lunar surface material core, are reported. The gradients of track densities, their lengths, and their angular distribution were measured with an optical microscope. Throughout the core depth (35 cm) crystals bearing traces of exposure to low energy solar cosmic rays were found, indicating the occurrence of mixing processes in the surficial layer of lunar surface material. The age of the occurrence of the samples investigated on the lunar surface, calculated from the track density, is in the interval 0.7 to 16 million years.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 379-387
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  • 98
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    Gamma-spectrometric analysis of Luna 16 sample of lunar surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Using a scintillation gamma spectrometer with shielding against anticoincidences, the content of the natural radioelements (K, U, and Th) and long-lived cosmogenic radioisotopes (Al-26, Na-22, and Mn-54) in a sample of Sea of Fertility regolith was determined. Based on the content data of natural radioelements, an attempt was made to classify this sample in the scale of petrochemical types of terrestrial rocks arranged in accordance with their silicic content and alkalinity. Within the frame of reference of calcium-uranium systematics of lunar samples, a comparison was made of the K/U ratio obtained for the Sea of Fertility sample with analogous data for other regions of the moon. Also discussed are problems on the depthwise distribution of cosmogenic radioisotopes along the regolith profile.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 311-319
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  • 99
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    Cosmogenic Al-26 and Na-22 in Luna-16 lunar regolith (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The activities of cosmogenic isotopes Al-26 and Na-22 in two samples taken from different depths of the lunar regolith core returned by the Luna 16 automatic station were measured by scintillation gamma spectrometer. The measured activities, when recalculated to the time of sampling of the lunar surface material, are: Al-26 - 62 + or - 8 and 54 + or - 9; Na-22 - 42 + or - 8 and 48 + or - 9. Depthwise distributions of the activities of these isotopes in lunar rocks of different types indicate the presence of a considerable depth gradient of activity near the surface caused by the fall off in the fluxes of primary and secondary cosmic radiation. The absence of this gradient in the measured samples, along with data on the tracks and content of inert gases, as well as the granulometric characteristics of the regolith indicate that the surficial layer of the regolith at the sampling site underwent mixing.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar Soil from the Sea of Fertility (NASA-TT-F-15881); p 358-369
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  • 100
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    Problem of nature of inert gases in lunar surface material (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The origin of isotopes of inert gases in lunar surface material was investigated from the standpoint of the isotopic two-component status of inert gases in the solar system. Helium and neon represent the solar wind component, while krypton and xenon are planetary gases. Type A gases are trapped by the material of the regolith in the early stages of the existence of the solar system and were brought to the lunar surface together with dust. The material of the regolith therefore cannot be considered as the product of the erosion of the crystalline rocks of the moon and in this sense are extralunar. The regolith material containing type A gases must be identified with the high temperature minerals of the carbonaceous chondrites.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar soil from the Sea of Fertility (NASA-TT-F-15881); p 348-357
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