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  • Other Sources  (4,070)
  • SPACE VEHICLES  (2,693)
  • COMMUNICATIONS  (1,377)
  • Chemistry
  • Humans
  • 1970-1974  (4,070)
Collection
Source
Keywords
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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    Antenna drive system for the Nimbus satellite (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A two-axis drive system is described for pointing a high gain antenna. Motion about each axis is provided by identical drive mechanisms. Only three gear passes are required to obtain the necessary 900:1 gear reduction. The drive system is a primary element of an experiment that will provide a real time data link between Nimbus and ground stations. Data are transmitted from Nimbus to the applications technology satellite, which relays the data to ground stations.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 117-120
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  • 7
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    The Intelsat 4 antenna positioner (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The Intelsat 4 communications satellite has two spot beam antennas which are pointed to selected land masses by gimbaled positioners. The positioners employ drive motors with electromagnetic brakes and jackscrews that are self-caging during the launch. The positioner uses dry lubricants for ball bearings, spur gears, screw and nut, and various journal bearings. A coefficient of friction of approximately 0.05 was demonstrated in vacuum operation. Success of the positioner was demonstrated on the first Intelsat 4 placed in orbit in January 1971. The developmental problems that were encountered and their solutions are discussed.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 109-116
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  • 8
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    Locations of solar radio bursts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Measurements of the positions of the sources of solar radio bursts at decameter wavelengths, 20- to 60-MHz range, provide information about physical conditions in a region of the corona extending from about one-half to several solar radii from the surface of the sun. Position measurements in the 20- to 60-MHz range were made with the Clark Lake sweep-frequency grating interferometer. Although the resolution of the instrument is sufficient to measure source position accurately, the highly variable effect of refraction in the earth's ionosphere severely limits the observations, distorting position determinations to such an extent as to make much of the position data useless unless ionospheric refraction can be taken into account. A method was developed for the removal of the refractive effect from the data to permit determination of true source position. With this technique it is considered possible to measure spatial extent of radio sources that will provide information about emission processes and physical parameters in the corona.
    Keywords: COMMUNICATIONS
    Type: Significant Accomplishments in Sci., 1970; p 149-153
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  • 9
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    Reduction of near-in sidelobes using phase reversal aperture rings (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A technique is described for reducing near-in sidelobes in spacecraft antennas by cancellation. This technique takes a small portion of the radiation from the antenna aperture and generates the near-in lobes, which are then fed out of phase relative to the main signal. Results of sample cases indicate that the first three lobes can be nearly eliminated at a 40% reduction in aperture efficiency.
    Keywords: COMMUNICATIONS
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 34-42
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  • 10
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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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  • 11
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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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  • 12
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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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  • 13
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    Electromagnetic compatibility fundamentals applied to spacecraft radio communication systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A design guide for minimizing electromagnetic interference in aerospace communication equipment for ground stations is presented. Specifically treated are the mechanisms of generating unwanted radio emissions that may affect station operations as well as other communications services, the mechanisms by which sensitive receivers become susceptible to interference, means for reducing interference, standard methods of measurement, and the problems of site selection. The sources of interference are viewed primarily as originating from communications transmitters aboard spacecraft and aircraft, ground transmitters within and outside the ground stations, and other electrical sources on the ground that are not intended to radiate.
    Keywords: COMMUNICATIONS
    Type: NASA. Goddard Space Flight Center Radio Freq. Interference Handbook; p 1-106
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  • 14
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    Experiment T001: Entry communication on the Gemini 3 mission (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Water addition to the Gemini 3 exhaust plasma was studied to determine its effectiveness in the establishment of communication links during the entry portion of the flight. Attenuation levels were measured with and without water injection at uhf frequencies of 230.4 and 296.8 megahertz and at the C-band frequency of 5690 megahertz. Ultrahigh frequency signals that had been blacked out were restored to significant levels, during early portions of the water-injection sequence, by the high flow rate injection. The C-band signal was enhanced by medium and high flow rate injections during the latter portion of the injection period. The uhf signal recovered during water injection resulted in an antenna pattern that was beamed in the radial direction of injection from the spacecraft. Postflight analysis showed that the uhf recovery data were consistent with injection-penetration theory.
    Keywords: COMMUNICATIONS
    Type: The Gemini Porgram: Phys. Sci. Expt. Sum.; p 471-485
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  • 15
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    Investigations on a cylindrical antenna as a diagnostic probe for isotropic and magnetized plasmas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Impedance behavior of short cylindrical antenna used as diagnostic probe in isotropic and magnetized plasmas
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 47-56
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  • 16
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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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  • 17
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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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  • 18
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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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  • 19
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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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  • 20
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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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  • 21
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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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  • 22
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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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  • 23
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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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  • 24
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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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  • 25
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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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  • 26
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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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  • 27
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    Communications control group assembly - Teletype line switching equipment (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Communications control group teletype line switching equipment for space stations
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 113-116
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  • 28
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    Antenna rigging angle optimization within structural member size design optimization (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Antenna rigging angle optimization within structural member design for improved antenna performance
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 81-87
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  • 29
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    Antenna structures - Evaluation of reflector surface distortions (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Reflector surface distortions of 210 ft antenna and their effects on radio frequency performance
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 76-80
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  • 30
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    Tracking and data acquisition elements research - Polarization diverse S band feed cone (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Polarization diverse S band feed cone for DSIF reflector antennas
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 66-72
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  • 31
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    A second/third order hybrid phase locked receiver for tracking Doppler rates (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Second/third order hybrid phase locked receiver for tracking frequency ramp signals
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 42-45
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  • 32
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    Refractivity influence on DSS Doppler data (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Examination of deep space Doppler data for terrestrial media contamination
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 31-41
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  • 33
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    The effects of spatial nonuniformities on high temperature microwave breakdown (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Effects on high temperature microwave antenna breakdown of ionization frequency, collision frequency, diffusion coefficient, and breakdown parameters
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 489-508
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  • 34
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    An automatic antenna impedance matcher for reentry vehicle applications (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Impedance matcher for automatically maximizing power radiated from X band antenna on reentry vehicle by eliminating power dissipated as heat
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 449-463
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  • 35
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    Electromagnetic wave propagation in a lossy plasma slab with a gradient transverse to the incident wave (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Computer solution of plane electromagnetic wave interaction with bounded inhomogeneous plasma slab with electron density gradient transverse to wave
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 427-448
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  • 36
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    Radiation from circumferential slots on plasma-clad cones (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Slot antenna radiation pattern distortion produced by boundary layer plasma sheath around conical reentry vehicles
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 411-425
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  • 37
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    Antenna performance in the presence of a turbulent plasma (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Antenna radiation patterns and electron density profiles in turbulent plasma flow
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 379-410
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  • 38
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    Effects of reentry plasma on RAM C-1 VHF telemetry antennas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Reentry plasma effects on RAM C-1 VHF telemetry antenna radiation patterns
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 183-201
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  • 39
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    Shock tube measurement of admittance of RAM C and RAM C-C diagnostic antennas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Shock tube measurements of admittance of RAM C-2 and RAM C-3 diagnostic antenna admittance to analyze accuracy of calculated electron density
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 157-182
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  • 40
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    RAM C-3 S-band diagnostic experiment (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: RAM C-3 S band diagnostic antenna systems and calculations of electron density profiles
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 137-155
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  • 41
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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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  • 42
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    Communications system research (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Coding, synchronization, combinatorial, multiple access, propagation, and permutation studies for telecommunications systems
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 25-89
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  • 43
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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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    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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  • 45
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    Television experiment (1973)
    In:  CASI
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    Publication Date: 2005-11-30
    Description: The fixed and variable Martian features investigated by the TV experiment on Mariner 9 are described. Articles are presented concerning the dust storm of October to November over the Southern Hemisphere; global surface geodesy and cartography; geology; and the satellite astronomy.
    Keywords: COMMUNICATIONS
    Type: Mariner Mars 1971 Proj., Vol. 5; p 63-70
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    Status of reusable surface insulation thermal protection system technology programs (1972)
    In:  CASI
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    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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  • 47
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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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    Assessment of potential buffet problems on the space shuttle vehicle (1972)
    In:  CASI
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    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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  • 49
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    Dynamic analysis for shuttle design verification (1972)
    In:  CASI
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    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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    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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  • 51
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    The Goddard helical tape recorder (1972)
    In:  CASI
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    Publication Date: 2005-11-30
    Description: A spacecraft recorder was developed with the objective of functioning continuously for 5 years. The resulting design employed a metallic tape wound in a 200-turn helix. A direct drive, brushless dc torquer and servo speed control drove the recorder at 3 rpm for recording and 54 rpm for playback.
    Keywords: COMMUNICATIONS
    Type: 6th Aerospace Mech. Symp.; p 89-93
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  • 52
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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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    Bias and spread in extreme value theory measurements of probability of error (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Extreme value theory is examined to explain the cause of the bias and spread in performance of communications systems characterized by low bit rates and high data reliability requirements, for cases in which underlying noise is Gaussian or perturbed Gaussian. Experimental verification is presented and procedures that minimize these effects are suggested. Even under these conditions, however, extreme value theory test results are not particularly more significant than bit error rate tests.
    Keywords: COMMUNICATIONS
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 58-68
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  • 54
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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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    On the possibility of Earth reentry simulation of shallow angle Jupiter entry (1972)
    In:  CASI
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    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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    The use of the Earth-Moon system as a radio tracking facility (1971)
    In:  CASI
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    Publication Date: 2005-11-30
    Description: The use of the earth-moon system for radio tracking has several potentially useful aspects, from a scientific standpoint: extension of the baseline by two orders of magnitude, absence of lunar atmosphere, higher-velocity parallax with a longer period, and the moon's more modellable rotation. The facility would be a convenient base station for other research, not directly involving the tracking capability, but utilizing its orbiting data link features.
    Keywords: COMMUNICATIONS
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 249-251
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  • 57
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    Radio tracking with the Deep Space Network (1971)
    In:  CASI
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    Publication Date: 2005-11-30
    Description: Range and Doppler measurements for the Mariner 6 and 7 spacecraft are described. The Doppler tracking system and the two systems of spacecraft ranging apparatus being used in the Deep Space Network are illustrated. Charged particle calibration is considered. Equipment characteristics are presented for the ranging apparatus.
    Keywords: COMMUNICATIONS
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 158-165
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    Experiment Do14: Ultrahigh and very high frequency polarization (1971)
    In:  CASI
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    Publication Date: 2005-11-30
    Description: The measurement of inhomogeneities in the electron content along the orbital paths of Gemini 8 and Gemini 9 missions was not accomplished because the tracking information was not available. The use of ultrahigh frequency radio transmission was the primary factor in the successful removal of a very high frequency Faraday rotation ambiguity; but, as was expected, this was not very useful for fine-scale polarization studies. Ionosonde data were useful in the computation of the slab thickness at the closest point of approach of the spacecraft.
    Keywords: COMMUNICATIONS
    Type: NASA. Manned Spacecraft Center The Gemini Program: Phys. Sci. Expt. Sum.; p 487-507
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  • 59
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    Materials properties and allowables for the space shuttle (1970)
    In:  CASI
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    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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  • 60
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    Thermal protection systems - Introduction and overview (1970)
    In:  CASI
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    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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  • 61
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    The development of effective fracture control procedures for space shuttle (1970)
    In:  CASI
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    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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  • 62
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    Orbiting astronomical observatory mission operations (1970)
    In:  CASI
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    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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    Spacecraft telecommunications systems - A digital command system development (1970)
    In:  CASI
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    Description: All digital, single channel command subsystem for spacecraft communication
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 126-129
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    Applied mechanics (1970)
    In:  CASI
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    Publication Date: 2005-11-27
    Description: Spacecraft antenna optimization, receptance coupling program, deformation modes and dynamic response of structures, and holographic measurements
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 171-190
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  • 65
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    Calibration of radar data from Apollo 16 results, part X (1972)
    In:  CASI
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    Description: Predictions of surface and near surface blockiness using earth based radar measurements were made. Two polarizations of the radar echoes were measured - polarized and depolarized. Particular attention was given to the depolarized echoes. North Ray and South Ray Craters and a 512-m diameter lunar crater in the Flamsteed Ring were used for the study.
    Keywords: COMMUNICATIONS
    Type: NASA. Lyndon B. Johnson Space Center Apollo 16 Prelim. Sci. Rept.; 3 p
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    Bistatic-radar investigation (1972)
    In:  CASI
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    Description: The purpose of the reported experiment was to determine the principal electromagnetic and structural properties of the lunar surface from the observation of command and service module (CSM) radio transmissions that were reflected from the lunar surface and received on earth. These transmissions emanate from the CSM communication systems at wavelengths of 13 cm (S-band) and 116 cm (very high frequency (VHF)). Lunar crustal properties such as dielectric constant, average slope and slope probability, density, small-scale surface roughness, and embedded rocks to a depth of 20 m may be determined. The results are proving to be most useful in understanding the processes that have produced and modified the crust and in distingushing between adjacent and subjacent geological units. The experimental observations are also of intrinsic interest in the study of electromagnetic scattering.
    Keywords: COMMUNICATIONS
    Type: NASA. Lyndon B. Johnson Space Center Apollo 16 Prelim. Sci. Rept.; 13 p
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    Application of composite materials to space shuttle tanks (1972)
    In:  CASI
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    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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    Advanced design concepts for shuttle airframe structure (1972)
    In:  CASI
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    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
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    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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  • 70
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    Gas-powered reentry body erection mechanism (1972)
    In:  CASI
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    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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    Satellite temperature correlation of predicted, test, and flight data (1972)
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    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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    Experiments on the dynamic stability of the space shuttle (1972)
    In:  CASI
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    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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  • 73
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    Manned spacecraft electrical fire safety (1971)
    In:  CASI
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    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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    Aerospace vehicle separation mechanisms selection, design, and use considerations (1971)
    In:  CASI
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    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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    Electromagnetic compatibility design guideline for STADAN (1971)
    In:  CASI
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    Description: Procedures for achieving electromagnetic compatibility in electronic and electrical equipment for aerospace ground stations are investigated. The application of shielding theory to good design is treated and standards of good practice are outlined for bonding, grounding, wiring, and cabling. Some aspects of filter design are explained, and suggestions are given for the application of filters to electronic and electrical equipment.
    Keywords: COMMUNICATIONS
    Type: NASA Goddard Space Flight Center Radio Freq. Interference Handbook; p 107-198
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  • 76
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    Overview of the AF Avionics Laboratory reentry electromagnetics program (1970)
    In:  CASI
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    Description: Radio wave propagation through plasmas studied for communication with hypersonic vehicles during reentry
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 3-17
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    Secondary structures and mechanisms - Design trouble area for the space shuttle (1970)
    In:  CASI
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    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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  • 78
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    Structural design and analysis of the space shuttle (1970)
    In:  CASI
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    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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    Apollo telescope mount operations and data-handling (1970)
    In:  CASI
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    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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    Communications elements research (1970)
    In:  CASI
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    Description: Components and techniques for radio and optical space communication
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 90-120
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  • 81
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    Thorad vehicle system performance (1970)
    In:  CASI
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    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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    Agena vehicle system performance (1970)
    In:  CASI
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    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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    Spacecraft radio - TOPS radio frequency subsystem (1970)
    In:  CASI
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    Publication Date: 2005-11-27
    Description: Radio frequency subsystem requirements and estimated reliability data for Thermoelectric Outer Planet Spacecraft
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 121-125
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  • 84
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    Evolution of a spacecraft antenna system (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Mechanically despun antenna system design for spin stabilized spacecraft used in ATS and Intelsat systems
    Keywords: COMMUNICATIONS
    Type: JPL PROC. OF THE 4TH AEROSPACE MECH. SYMP. 15 JAN. 1970; P 13-18
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  • 85
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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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  • 86
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    Radar augmentation device (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The radar augmentation device (RAD) serves to increase the radar response of a target body and thus expedite radar acquisition. The design and development of the RAD are discussed with particular emphasis on technical problems that were encountered and solved. Discussions of the mode of operation of the RAD and the ground test history are also included.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 65-72
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  • 87
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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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  • 88
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    Magnetospheric radio noise (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Observations, made by the RAE satellite, of earth magnetospheric noise are reported. The observations show radio noise exists at 700 kHz and below. The results are included in graphs.
    Keywords: COMMUNICATIONS
    Type: Significant Accomplishments in Sci., 1970; p 75-80
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  • 89
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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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  • 90
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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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  • 91
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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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  • 92
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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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  • 93
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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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  • 94
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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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  • 95
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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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  • 96
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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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  • 97
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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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  • 98
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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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  • 99
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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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  • 100
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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
    Format: text
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