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• W2315463156 abstract "Space quality multi-junction (MJ), gallium arsenide (GaAs), and silicon (Si) solar cells have respective test efficiencies of approximately 24%, 18.5% and 14.8%. Multi-junction and gallium arsenide solar cells weigh more than silicon solar cells and cost approximately five times as much per unit power at the cell level. Trade results are reported that determined which of these cell types offer a performance and price advantage to small to medium size low earth orbiting spacecraft with rigid solar arrays of typical and state of the art weights. A trade is carried out hi some detail in this paper for the TRACE spacecraft This spacecraft is small, will operate mostly in full sunlight and has a typical solar array weight The results of other trades, obtained using the same methodology detailed for the TRACE spacecraft, are summarized. The trades find that the high efficiency solar cells buy additional science at a cost per weight from $57,000 to $141,000 per kilogram, with the higher cost occurring when the cells are used with lightweight substrates and deployment systems. These costs buy the same thing as the science launch and support cost per unit weight for the spacecraft These costs run from $552,000 to $680,000. Tradeoff Between Multi-Junction and Gallium Arsenide Solar Cells for TRACE The Transition Regional and Coronal Explorer (TRACE) spacecraft has already chosen gallium arsenide cells for its solar array. These cells were selected in 1994 before multi-junction cells were available. Thus the trade that follows is only of hypothetical interest to TRACE, but should be useful in determining the relative value of the multi-junction, gallium arsenide, and silicon cells to small spacecraft that, like TRACE, have rigid deployable arrays. The trade presented below closely follows the methodology and format used for an earlier trade completed for the Tropical Rainfall Measuring Mission (TRMM) spacecraft TRACE is planned to be earth pointing and to fly for two years starting at an altitude of 700 km and an inclination of 98°. The spacecraft has two solar array wings. The spacecraft will be oriented such that the plane of the array is sun pointing. In addition, the spacecraft will operate mostly in full sunlight orbits. The wings for the more efficient more costly, multijunction3 cells are of course smaller than the wings for the gallium arsenide solar cells. The weight of these two arrays and the weight of a silicon cell design is summarized in Table I. The cost of these three arrays, including test costs is summarized in Table n. With respect to the multijunction solar cells some caution is in order. The price estimates used assume that the multi-junction solar cells are mature. The price is derived by using a ratio of .86 between gallium arsenide and multi-junction cell arrays. This will not be the case for the first few multi-junction solar cell array produced. As a result the price for the multi-junction cell array in Table n is much too low for the first few multi-junction arrays. This underestimate is taken into account hi a later section of this paper. Table n does not show the price advantage of the multijunction and gallium arsenide solar arrays to the 5pacecraftJIhisisJ*eause these arrays offer weight reductions, and some of this reduction can increase the amount of science that the spacecraft can carry hence increasing the cost effectiveness of the spacecraft * Head, Energy Conversion and Analysis Section Senior Member AIAA f Member, Power Systems Section Copyright © 1996 by the American Institute of Aeronautics and Astronautics, Inc. No copyright is asserted in the United States under Title 17, U. S. Code. The U. S. Government has a royalty free license to exercise all rights under the copyright claimed herein for government purposes. AH other rights are reserved by the copyright owner. Below, this advantage is estimated first for the gallium arsenide and then the multi-junction cells. Value of GaAs Array Weight Reduction on Spacecraft Science From Table I, the silicon array is 6.2 kilograms heavier than the gallium arsenide array. This means that if the silicon array is used some weight must be taken out of the science on the spacecraft, but not necessarily the entire 6.2 kilograms as some of the weight can come out of the various spacecraft systems that support the science. Such systems are assumed to decrease hi weight in rough proportion to the percentage weight decrease hi science. The amount of decrease is computed by the following equations (1) through (5). Some of TRACE'S systems, those whose size is primarily determined by the spacecraft weight, remain unaffected by the decrease hi science. These are attitude control, rocket interface, structure, global positioning system interface, and thermal. The equations (1) through (5) and their solutions quantify the decrease hi weight of the spacecraft systems that are assumed proportional to the weight of science. The five equations imply that the capability of the spacecraft systems is proportional to weight. Although this is a reasonable approximation, it is not necessarily the case. For the greatest accuracy, each spacecraft subsystem would have to be redesigned for decreased capability and then its weight reestimated. In the context of this paper, the resources to do this are not available and the approximation used is satisfactory. The five equations predict a decrease hi the power output and weight of the silicon solar array from that given in Table I. The silicon solar array weight decreases, as do the other subsystem weights, because of the decrease in the science capability. This means that the silicon array can be less powerful than the gallium arsenide array. The data hi Tables I and II do not reflect this. To finally obtain costs for the spacecraft array this change hi array and other subsystem costs is accounted for later in Table HI. In equations (1) through (5), the variables INSTR, DATA, COMM, FJLEC, PWR, and SA are respectively the weights of the scientific instruments; command and data handling, communications, electrical, power exclusive of the solar array, and solar array systems on the spacecraft with the gallium arsenide array. The variables ADATA, ACOMM, AELEC, APWR and ASA are the decreases in the weights of the respective systems as a result of the relaxed capability they have in serving the science when the gallium arsenide array is replaced by a silicon array. The variable CF is the fraction of the command and data handling system that is used to support science. This fraction is assumed to be approximately 0.9. This same fraction is used for the communications and high gam antenna. The variable PF is the fraction of power that is used by the instrument hi nominal operation, in this case 72 watts, out of the total spacecraft wattage of 246 watts. SF is the fraction of weight by which the solar array increases when there is an increase in the array's power producing capability. In this case it means that the solar array increases .863% for every 1.0% increase in the array's power producing capability. (1) CF*DATA(-6.2-ADATA-ACOMM-AELECAPWR-ASA}/INSTR = ADATA (2) CF*COMM{-6.2-ADATA-ACOMM-AELECAPWR-ASA)/INSTR = ACOMM (3) PF*ELEC(-6.2-ADATA-ACOMM-AELECAPWR-ASA)/INSTR = AELEC (4) PF* PWR(-6.2-ADATA-ACOMM-AELECAPWR-ASA)/INSTR = APWR (5) SF*PF*SA(-6.2-ADATA-ACOMM-AELECAPWR-ASA)/INSTR = ASA" @default.
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• W2315463156 date "1996-01-15" @default.
• W2315463156 modified "2023-10-14" @default.
• W2315463156 title "Relative cost effectiveness of multi-junction, gallium arsenide, and silicon solar cells" @default.
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• W2315463156 doi "https://doi.org/10.2514/6.1996-123" @default.
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