The first ten megawatts of III&amp;#x2013;V multi-junction concentrator solar cell production

Aiken, D.; Clevenger, B.; Newman, F.H.; Smith, Bruce; Tourino, Cory; Wilson, Jerry W; Wood, Jody

doi:10.1109/pvsc.2008.4922471

Cited by 5 publications

(5 citation statements)

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“…The photovoltaic cells selected for this application are commercially-available concentrator solar cells 21,22 . Although these cell designs are designed for terrestrial concentrator application, not for space applications, the cell technology is identical to the space cell technology 17,18 , with the exception that the metallization used for ohmic The performance specifications for these cells can be obtained from the vendors as a function of both the concentration and the temperature.…”

Section: Photovoltaic Cellsmentioning

confidence: 99%

Solar Power System Design for the Solar Probe+ Mission

Landis

Schmitz²,

Kinnison

et al. 2008

6th International Energy Conversion Engineering Conference (IECEC)

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Solar Probe+ is an ambitious mission proposed to the solar corona, designed to make a perihelion approach of 9 solar radii from the surface of the sun. The high temperature, high solar flux environment makes this mission a significant challenge for power system design. This paper summarizes the power system conceptual design for the solar probe mission. Power supplies considered included nuclear, solar thermoelectric generation, solar dynamic generation using Stirling engines, and solar photovoltaic generation. The solar probe mission ranges from a starting distance from the sun of 1 AU, to a minimum distance of about 9.5 solar radii, or 0.044 AU, from the center of the sun. During the mission, the solar intensity ranges from one to about 510 times AM0. This requires power systems that can operate over nearly three orders of magnitude of incident intensity. NomenclatureA r = Radiator area (m 2 ) I = incident intensity (W/m 2 ) P electric = power generated (W) R s = solar radius (696 000 km) T = temperature (K) Th = hot-end temperature of thermal conversion system (K) Tc = cold-end temperature of thermal conversion system (K) α = solar absorptivity (equal to 1 minus the reflectivity) ε f ,ε r = thermal (IR) emissivity of the front and rear surfaces η = conversion efficiency σ = Stefan-Boltzmann constant, 5.67×10

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Section: Photovoltaic Cellsmentioning

confidence: 99%

Solar Power System Design for the Solar Probe+ Mission

Landis

Schmitz²,

Kinnison

et al. 2008

6th International Energy Conversion Engineering Conference (IECEC)

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“…One of the actively developing directions in this field is the design and creation of photovoltaic modules with lens concentrators, in which a high sunlight concentration ratio (up to 500X and higher) is ensured [1][2][3][4]. However, in spite of the use of highly-effective multijunction SCs (the efficiency of which exceeds 35-37%, AM1.5 LAOD, 1000 W/m 2 ), the total efficiency of the concentrator modules does not reach even 30% [5,6].…”

Section: Introductionmentioning

confidence: 99%

Development and testing of high concentration flat-plate Fresnel lenses

Shvarts

Soluyanov²

2009

SPIE Proceedings

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In the work, stages of designing, optimizing, manufacturing and testing the circular flat-plate Fresnel lenses (FLs) for photovoltaic modules with multi-junction solar cells (SCs) are presented. A mathematical model based on ray tracing has been developed for optimizing lenses design parameters and calculating their optical-power characteristics (OPCs). In searching the optimum combination of the lens aperture, its focal distance and refracting profile parameters, the optimization criterion was the maximum of the average sunlight concentration at high optical efficiency in the focal spot of minimum size. Analysis of OPCs of circular Fresnel lenses with conical (the generatrix of surface is a straight line) and curvilinear (the generatrix of surface is a curved line) refracting surfaces has been carried out. Fresnel lens specimens were fabricated and a control of their profile parameters has been done. Experimental lens OPCs have been obtained with use of newly developed optical test bench. A degree of the effect of the light flux and Fresnel lens geometrical imperfections on validity of the experimental data interpretation has been determined. To establish the lens optical efficiency values at standard irradiance conditions, the correction of the calculation model was done. Also, the effect of temperature on the lens optical efficiency is studied.

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“…The result is a mission called Solar Probe Plus, where the "Plus" represents the improvement in science objectives met by the current concept over previous concepts. The plan for the mission is to penetrate to a distance of 9.5 solar radii, 6.6 x 10 6 km. (i.e., 8.5 solar radii away from the surface of the sun).…”

mentioning

confidence: 99%

“…The array is actively cooled using a pumped water cooling loop. As Solar Probe Plus approaches the Sun, the primary array is progressively tilted up off the direct sun-pointing orientation, to limit the incident solar flux and maintain the array's cells within thermal limits of under 180° C. This secondary array section operates in a solar irradiance regime that is similar to the regime in which terrestrial concentrator cells operate, and hence it was believed that cell technology would be similar to terrestrial concentrator cell technology [6,7]. The secondary array is at an angle to the sun, and receives a net flux that is reduced by the TPS penumbra and by a factor of the cosine of the array angle.…”

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confidence: 99%

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Testing of solar cells for the Solar Probe Plus mission

Scheiman

Piszczor

Snyder

et al. 2011

2011 37th IEEE Photovoltaic Specialists Conference

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The Solar Probe Plus (SPP) is an upcoming mission in NASA's "Living with a Star Program" to be built by the Johns Hopkins University Applied Physics Laboratory. The spacecraft will orbit the sun for a primary mission duration of seven years, making a closest approach to the sun at a distance of 0.0442 AU. Instrumentation on SPP will focus on two primary science investigations: the sun's coronal heating and solar wind acceleration, and the production, evolution, and transport of solar energetic particles. The mission is scheduled for a launch no later than 2018. The spacecraft will have a thermal shield to protect the main portions of the spacecraft from the solar irradiance, and is powered by a pair of solar array wings. Each wing is actively cooled, and sectioned into a primary array for normal orbital operations, with a secondary for operation at high solar intensity during closest approach to the sun. Near the sun, the arrays are tilted at a high angle, withdrawing the primary array section behind the thermal shield and exposing only the secondary section, which is in the penumbra of the thermal shield to minimize the operating temperature. This secondary section will experience environmental conditions that include high solar flux, radiation, high temperature, and off-normal light incidence. It will use solar cells based on the state-of-theart triple junction solar cells (InGaP/GaAs/Ge) for space with modifications to handle the higher irradiance and temperature. NASA Glenn Research Center tested prephase A solar cells for the secondary (high irradiance) section under a variety of conditions which include temperatures up to 150°C at 1 sun and 40X concentration. These measurements were made before and after irradiations that include 1 and 3.3 MeV electrons, 1, 4, and 10 MeV protons at two different fluencies. Additional testing included off-angle performance, extended temperature exposure, and UV exposure. BACKGROUND

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The first ten megawatts of III–V multi-junction concentrator solar cell production

Cited by 5 publications

References 0 publications

Solar Power System Design for the Solar Probe+ Mission

Solar Power System Design for the Solar Probe+ Mission

Development and testing of high concentration flat-plate Fresnel lenses

Testing of solar cells for the Solar Probe Plus mission

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