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  • 1
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    Development of structural composite mirror technology for submillimeter space telescopes (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: ASTRONOMY
    Type: Acta Astronautica (ISSN 0094-5765); 29; 7; p. 537-545.
    Format: text
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  • 2
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    Survey of deployable antenna concepts (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Deployable space antenna concepts are surveyed. Precision reflector antennas, stiffened membrane antennas, truss antennas, infrared antennas, and electrostatically figured membrane reflectors are described.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Antenna Systems Technol., Pt. 1; p 381-422
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    NASA TECHNICAL REPORTS
  • 3
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    JPL antenna technology development (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Plans for evaluating, designing, fabricating, transporting and deploying cost effective and STS compatible offset wrap rib antennas up to 300 meters in diameter for mobile communications, Earth resources observation, and for the orbiting VLBI are reviewed. The JPL surface measurement system, intended for large mesh deployable antenna applications will be demonstrated and validated as part of the antenna ground based demonstration program. Results of the offset wrap rib deployable antenna technology development will include: (1) high confidence structural designs for antennas up to 100 meters in diameter; (2) high confidence estimates of functional performance and fabrication cost for a wide range of antenna sizes (up to 300 meters in diameter); (3) risk assessment for fabricating the large size antennas; and (4) 55 meter diameter flight quality hardware that can be cost effectively completed toto accommodate a flight experiment and/or application.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Systems Technol., 1980, Vol. 1; p 287-294
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    NASA TECHNICAL REPORTS
  • 4
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    Development of structural-composite reflector panels for a submillimeter space telescope (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Reflector panels for the Large Deployable Reflector (LDR) for a 20m, Earth-orbiting, submillimeter and infrared telescope were designed. The panels must be 1 to 2 m in diameter with surface precision and thermal stability of a few microns, and an areal density of or = 10 kg/sqm. Using a combination of design, analytical modeling, panel fabrication, and testing, two sizes of graphite/epoxy panels were produced. One is 15 sqcm the other 60 sqcm, both weighing 5 to 7 kg/sqm with manufactured surface accuracies of a few tenths of a micron and thermal stability at LDR orbital temperatures of a few microns.
    Keywords: COMPOSITE MATERIALS
    Type: ESA Proceedings of 3rd European Symposium on Spacecraft Materials in Space Environment; p 167-172
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  • 5
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    System concept for a moderate cost Large Deployable Reflector (LDR) (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A study was carried out at JPL during the first quarter of 1985 to develop a system concept for NASA's LDR. Major features of the concept are a four-mirror, two-stage optical system; a lightweight structural composite segmented primary reflector; and a deployable truss backup structure with integral thermal shield. The two-stage optics uses active figure control at the quaternary reflector located at the primary reflector exit pupil, allowing the large primary to be passive. The lightweight composite reflector panels limit the short-wavelength operation to approximately 30 microns but reduce the total primary reflector weight by a factor of 3 to 4 over competing technologies. On-orbit thermal analysis indicates a primary reflector equilibrium temperature of less than 200 K with a maximum gradient of about 5 C across the 20-m aperture. Weight and volume estimates are consistent with a single Shuttle launch, and are based on Space Station assembly and checkout.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Optical Engineering (ISSN 0091-3286); 25; 1045-105
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  • 6
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    Survey of deployable antenna concepts (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Deployable space antenna concepts are surveyed. Precision reflector antennas, stiffened membrane antennas, truss antennas, infrared antennas, and electrostatically figured membrane reflectors are described.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
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  • 7
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    JPL antenna technology development (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Systems-level technology for evolving cost-effective, STS compatible antennas that will be automatically deployed in orbit to perform a variety of missions in the 1985 to 2000 time period is discussed. For large space-based antenna systems, the LSST program has selected deployable antennas for development. The maturity of this class of antenna, demonstrated by the success of smaller size apertures, provides a potential capability for satisfying a significant number of near-term, space-based applications. The offset wrap-rib concept development is the basis of the JPL LSST antenna technology development program. Supporting technology to the antenna concept development include analytical performance prediction, the capability for measuring and evaluating mechanical antenna performance in the intended service environment, and the development of candidate system-level configurations for potential applications utilizing the offset wrap-rib antenna concept.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA. Langley Research Center Large Space Systems Technol., Pt. 2, 1981; p 429-438
    Format: text
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  • 8
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    In-step Inflatable Antenna Experiment (1992)
    In:  CASI
    Details
    Publication Date: 2014-09-03
    Description: The topics are presented in viewgraph form and include the following: potential space antenna applications; experiment objectives; experiment technical approach; experiment scenario; spartan services; experiment orbital configuration; experiment canister structure; surface measurement system configuration; and orbital functional sequences.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington, NASA(DOD Flight Experiments Technical Interchange Meeting Proceedings; 12 p
    Format: application/pdf
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  • 9
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    Lightweight composite reflector panels (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Hexel Corp. has produced additional composite panels, based on JPL designs, that: (1) have increased the panel size from 0.15 to 0.40 meters, (2) have improved the as-manufactured surface precision 3.0 to approx. 1.0 micron RMS, (3) have utilized different numbers of face sheet plys, (4) have improved face sheet fiber orientation, (5) have variations of aluminum honeycomb core cell size, (6) have combined graphite/epoxy (Gr/Ep) face sheets with E-glass honeycomb cores, and (7) have used standard aluminum core with face sheets composed of combinations of glass, Kevlar, and carbon fibers. Additionally, JPL has identified candidate alternate materials for the facesheets and core, modified the baseline polymer panel matrix material, and developed new concepts for panel composite cores. Dornier designed and fabricated three 0.6 meter Gr/Ep panels, that were evaluated by JPL. Results of both the Hexel and Dornier panel work were used to characterize the state-of-the-art for Gr/Ep mirrors.
    Keywords: COMPOSITE MATERIALS
    Type: Report of the Asilomar 3 LDR Workshop; p 74-75
    Format: application/pdf
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  • 10
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    Antenna Technology Shuttle Experiment (ATSE) (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Numerous space applications of the future will require mesh deployable antennas of 15 m in diameter or greater for frequencies up to 20 GHz. These applications include mobile communications satellites, orbiting very long baseline interferometry (VLBI) astrophysics missions, and Earth remote sensing missions. A Lockheed wrap rip antennas was used as the test article. The experiments covered a broad range of structural, control, and RF discipline objectives, which is fulfilled in total, would greatly reduce the risk of employing these antenna systems in future space applications. It was concluded that a flight experiment of a relatively large mesh deployable reflector is achievable with no major technological or cost drivers. The test articles and the instrumentation are all within the state of the art and in most cases rely on proven flight hardware. Every effort was made to design the experiments for low cost.
    Keywords: COMMUNICATIONS AND RADAR
    Type: NASA-Langley Research Center NASA(DOD Control)Structures Interaction Technology, 1986; p 779-807
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