Last edited by Garn
Tuesday, July 14, 2020 | History

2 edition of Multi-kW solar arrays for earth orbit applications found in the catalog.

Multi-kW solar arrays for earth orbit applications

Multi-kW solar arrays for earth orbit applications

final report

  • 225 Want to read
  • 36 Currently reading

Published by Lockheed Missiles & Space Company, Inc. in Sunnyvale, Calif .
Written in English

    Subjects:
  • Cost effectiveness.,
  • Solar arrays.,
  • Spacecraft power supplies.,
  • Structural weight.,
  • Weight reduction.

  • Edition Notes

    Statementby Lockheed Missiles & Space Company, Inc.
    Series[NASA contractor report] -- NASA-CR-171538., NASA contractor report -- NASA CR-171538.
    ContributionsLockheed Missiles and Space Company., George C. Marshall Space Flight Center., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL16117569M

      Low Earth Orbit Cargo Operations Power Generation: 2 Fixed Wing Solar Arrays, Power Output: kW (sun-pointed) Foundation to Future Applications Cygnus is an Advanced Maneuvering Space Vehicle, Designed and Certified to Meet the Stringent Safety Requirements for Presentation for ISS.   WorldView-3 is the first multi-payload, super-spectral, high-resolution commercial satellite sensor operating at an altitude of km. WorldView-3 satellite provides 31 cm panchromatic resolution, m multispectral resolution, m short wave infrared resolution and 30 m CAVIS resolution. The satellite has an average revisit time of

      electric propulsion, the potential for plume impingement on solar arrays is a significant issue. As shown in Fig. , geosynchronous satellites are in a circular orbit coplanar with the Earth’s equator, with an orbital period of exactly one day. The satellite appears stationary to an observer on the Earth; however, the Earth’s equator is I looked into some numbers on this, comparing theoretical costs of nuclear power with a solar PV solution on Mars. Kilopower (NASA's research project for a Martian nuclear fission reactor, from the article): 7, kg for 40 kW. [1] ISS solar arrays: 14, kg for ~ kW in Earth orbit. [2]?id=

    An Update on EDDE, the ElectroDynamic Delivery Express earth orbit. EDDE consists mostly of a reinforced aluminum foil tape to collect and conduct electrons, plus solar arrays to drive   Validation of UltraFlex advanced solar array technology by ST 8 will radically reduce the mass, and thereby the cost, of future high-priority, medium-to-high power space and earth science missions, including those that use Solar Electric Propulsion (SEP) or space radars. The availability of very lightweight solar arrays having


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Multi-kW solar arrays for earth orbit applications Download PDF EPUB FB2

Planar and concentrator solar array concepts capable of providing kW to kW in low Earth orbit applications in the time period at an array recurring cost less than or equal to thirty dollars per watt are examined.

Silicon and gallium arsenide solar cell applicability are evaluated. On-orbit maintenance by space shuttle is also :// /abstract. Low cost low Earth orbit (LOW) and geosynchronous Earth orbit (GEO) Solar Array concepts in the to kW range which could be reduced to hardware in the mid 's, are identified.

Size scaling factors and longer life demands are recognized as the prime drivers for the designs if low life cycle costs for energy are to be :// /abstract. Get this from a library. Multi-kW solar arrays for Earth orbit applications: final report.

[George C. Marshall Space Flight Center,;] Study of multi-kW solar arrays for Earth orbit application. Abstract. Low cost low Earth orbit (LOW) and geosynchronous Earth orbit (GEO) Solar Array concepts in the to kW range which could be reduced to hardware in the mid 's, are identified.

Size scaling factors and longer life demands are recognized as the prime drivers Additional Physical Format: Online version: Multi-kW solar arrays for Earth orbit applications. Huntsville, Alabama: George C.

Marshall Space Flight Center, National Aeronautics & The present effort required the design of a modular solar array panel consisting of superstrate modules interconnected to provide the structural support for the solar cells.

The effort was divided into two tasks: (1) superstrate solar array panel design, and (2) superstrate solar array panel-to-panel ://   Study of~ Multi-Kilowatt lar Arrays for Earth Orbit Applications Spacecraft Engineering Division TRW Space & Technology Group One Space Park, Redondo Beach, CA Final Technical Report 15 October Contract NAS Document Number UE-OO Prepared by Robert E.

Patterson Work Performed for: Marshall Space Flight Center Solar arrays (see Figure ) for satellites come in flexible deployable arrays made up of hinged hinged panels are made of a sandwich of two face sheets bonded to an aluminum honeycomb core, after an insulating sheet is bonded to the panel surface on which the solar cells are to be placed to provide an electrical insulation between the cells and the ://   Need low-risk, light -weight solar arrays in the to kW range.

At 30 kW, a W/kg array saves > kg relative to an 80 W/kg array. • ISS arrays are about 27 W/kg and   Solar Energy • The solar constant, G s = W/m2, is the total solar energy incident on a unit area perpendicular to the sun’s rays at the mean Earth-Sun distance outside the Earth’s atmosphere • It varies between about and on an annual cycle, with max at perihelion and min at ~cdhall/courses/aoe/   Orbit: Altitude: km Type: Sun synchronous, am descending node Period: min.

Mission Life: years, including all consumables and degradables (e.g. propellant) Spacecraft Size, Mass and Power: m ( ft) tall x m (8 ft) across m (23 ft) across the deployed solar arrays kg ( lbs) kW solar array, Ahr   The Study of Multi-kW Solar Arrays for Earth Orbit Applications was performed by Rick Mills.

The panel hinge deployment stress analysis was performed by j Eric Abrahamson from the Structures and Structural Dynamics Department. Cost i analysis was provided by Mike Hitesman. The project organization is shown In Figure (f f t1 9 ' • ' I i1   • Solar Arrays – Body mounted, rigid panel and flexible deployable arrays are currently being used in many spacecraft.

– These arrays are mostly suitable for low–medium power ( kW) applications Cell Type Efficiency High Efficiency Si Cells 16 % Multi Junction Solar Cells % Array Type Specific Power (W/kg) Rigid Panel Array 30   materials degradation in space, the low‑Earth orbit (LEO) environment, defined as ‑1, km above Earth’s surface, is a particularly harsh environment for most non‑metallic materials, because single‑oxygen atoms (atomic oxygen [AO]) are present along with all other environmental components (Yang and de Groh, ).

/NPJSC_Space_Environment-ISS-Mini-Bookpdf. @article{osti_, title = {Solar array electrical performance assessment for Space Station Freedom}, author = {Smith, B.K. and Brisco, H.}, abstractNote = {Electrical power for Space Station Freedom will be generated by large Photovoltaic arrays with a beginning of life power requirement of kW per array.

The solar arrays will operate in a Low Earth Orbit (LEO) over a design life of These results show that the solar array and the battery capacity are appropriate for the consumption considered.

Aquarius/SAC-D mission. SAC-D mission has a similar profile to that of the SAOCOM mission: the orbit is Sun-synchronous, frozen at approximately km height, with an inclination of 98° and an orbital hour of 6 PM for the ascending :// PV arrays and transmitter to minimize PMAD/mass Arrays of multi bandgap PV Figure 4 Integrated Symmetrical Concentrator 81 Technologies used in the ISC include arrays inflatable toroids and thin film mirrors concentrating sunlight onto multi-band gap photovoltaic (PV) arrays.

The solar collectors always face the Sun with very little, if any The power for Hubble's scientific discoveries comes from solar cells. Designing and constructing Hubble's first two sets of solar cell arrays constituted a huge technological achievement for the European Space Agency and European industry.

After an in-orbit life of more than 8 years, this example of pioneering space technology was this morning (European time) replaced by new, more powerful ://   Keywords—Low earth orbit satellites, Passive Radar, Synthetic Aperture Radar, DVB-T I.

INTRODUCTION Over the last decades space-borne Synthetic Aperture Radar (SAR) has proved its capability as a remote sensing technique of great power and value over a plethora of applications[1]–[3].

However, these very capable orbital systems come with a highhttps://radarorg/abstracts/pdf/abstract_pdf. Outer Solar System and Deep Space Exploration Satellites in Earth orbit can generate kW of electrical power from photovoltaic arrays of reasonable size (a few square metres).

However, the inverse-square relationship between solar radiation flux and distance means that the situation is very different for the outer planets (Jupiter and beyond). NASA has taken an interest in solar for a long time. While the very first satellites were battery powered, solar arrays became common in orbit by the ’60s.

Regular silicon cells were used first, until gallium arsenide made it out of R&D in the ’90s. Now, almost everything DE-STAR or Directed Energy System for Targeting of Asteroids and exploRation is a proposed system to deflect asteroids, comets, and other near-Earth objects (NEO) that pose a credible risk of objects that cross Earth’s orbit, even relatively small ones, can still have a devastating effect.

We propose an orbital planetary defense system capable of heating the surface of potentially    meters (14 feet) tall x meters (8 feet) across, meters (23 feet) across the deployed solar arrays; kilograms ( pounds); kW solar array, Ahr battery Sensor Bands Panchromatic 8 Multispectral (4 standard colors: red, blue, green, near-IR), 4 new colors: red edge, coastal, yellow, near-IR2