ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
  • 1
    facet.materialart.
    Unknown
    Box truss development and applications (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The development and applications of a box truss design for large space antennas are discussed. A kinematic model with a mesh reflector was constructed. A prototype cube is described. Details of fabrication are given.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 527-544
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    A 15-meter deployable aperture microwave radiometer (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Large Antenna Multifrequency Microwave Radiometer (LAMMR) was a 4-meter-diameter mechanically scanned (at 1 rps) antenna operating at frequencies from 4.3 to 36 GHz. This LAMMR system was scheduled to fly on the National Oceanic Satellite System (NOSS) in 1986 to measure sea surface temperature and wind speed along with several other atmospheric and sea ice parameters. The LAMMR was limited to a 4-meter solid reflector to stay within the Shuttle/NOSS launch volume and to operate with radiometric precision up to 36.5 GHz. Under the 4-meter aperture constraint, LAMMR could not meet the user resolution requirement for sea surface temperature (25 km minimum, 50 km goal) in an RFI free band, i.e., 4.3 GHz. This study explores the feasibility of meeting this requirement goal with a 15-meter mechanically scanned deployable reflector. Two other research objectives can also be studied by adding one active (approximately 5 GHz) and two additional passive (1.4 and 6.4 GHz) channels to investigate soil moisture and precipitation profiles over land. These two objectives are closely related because the precipitation is the source of the soil moisture in unirrigated regions, and the soil moisture changes between samples (2/day) could indicate that precipitation may have occurred while the sensor was not in view.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 131-156
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    Space deployable truss structure design (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The development status of the deployable box truss structure is summarized. Potential applications for this structural system are described. Structural and component design requirements derived from these applications are discussed. Components of prototype 4.6 m cubes which incorporate graphite/epoxy structural members, fittings, and mechanisms are described. The benefits of the component designs and their respective manufacturing processes are presented.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 137-146
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    Hybrid deployable/erectable solar dynamic box truss system (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The design of a hybrid deployable/erectable solar dynamic box truss power generation system for the initial operation capability (IOC) of the Space Shuttle is examined. An organic Rankine cycle heat engine for IOC solar power generation is studied. The design configuration is a simple parabolic concentration where the receiver is located in the focal plane with its aperture at the focal point. The relationship between concentrator size and collection efficiency is analyzed. The geometry of the deployable graphite/epoxy box truss ring and the reflective panels of the system are described. Mass properties and dynamic analyses are performed to evaluate the center of gravity location and moments of inertia characteristics of the energy conversion subsystem (ECS). The deployable/erectable truss is applicable for large IR space telescopes and center and offset fed ECSs.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-0955
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Extendable mast (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Extendable mast is constructed from mutually supporting members that unfold as mast is deployed from compact package. Extendable mast is sturdy and can be compared to conventional rigid structures.
    Keywords: MACHINERY
    Type: LAR-12078 , NASA Tech Briefs (ISSN 0145-319X); 4; 2; P. 280
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    Radial rib antenna surface deviation analysis program (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital computer program was developed which analyzes any radial rib antenna with ribs radiating from a central hub. The program has the capability for calculating the antenna surface contour (reversed pillowing effect), the optimum rib shape for minimizing the rms surface error, and the actual rms surface error. Rib deflection due to mesh tension and catenary cable tension can also be compensated for, and the pattern from which the mesh gores are cut can be determined.
    Keywords: COMMUNICATIONS
    Type: NASA-CR-124570 , JPL-TM-33-518
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Analysis of performance characteristics and weight variations of large-area roll-up solar arrays (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Performance characteristics analysis of large area roll-up solar arrays based on support structure size and weight
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 69-WA/ENER-11 , AMERICAN SOCIETY OF MECHANICAL ENGINEERS, WINTER ANNUAL MEETING; Nov 16, 1969 - Nov 20, 1969; LOS ANGELES, CA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    Parametric study of the performance characteristics and weight variations of large-area roll-up solar arrays (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance characteristics and weight variations of large area, roll-up, solar arrays
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-115821 , JPL-TR-32-1502
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    RUSAP: A computer program for the calculation of Roll-Up Solar Array Performance characteristics (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: RUSAP is a FORTRAN 4 computer program designed to determine the performance characteristics (power-to-weight ratio, blanket tension, structural member section dimensions, and resonant frequencies) of large-area, roll-up solar arrays of the single-boom, tensioned-substrate design. The program includes the determination of the size and weight of the base structure supporting the boom and blanket and the determination of the blanket tension and deployable boom stiffness needed to achieve the minimum-weight design for a specified frequency for the first mode of vibration. A complete listing of the program, a description of the theoretical background, and all information necessary to use the program are provided.
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-CR-135898 , JPL-TM-33-634
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...