Figure 10.4.13 Large Planar Array The concept is briefly presented to indicate both the direction of future technologies as ell as the potential for modular designs. This concept is a scaling of the concept 1 planar array by a factor of 4. As in concept 2, a suitable equatorial orbit would be desirable. It is assumed possible only by the projected drop in mass and cost of the of the antenna (factor of 10-100) as well as the solar array technology (factor of 10). For a more futuristic option, the planar array is regarded as attractive particularly for the integrated solar-array /transmitter technology (see section 7.2.1.5 of the report) which eliminates the large transmitter as a separate subsystem. There are also potential improvements in the efficiency by closely coupling the elements, as well as having a transmitting antenna of large dimension (that is, the area of the solar array would equal the area of the transmitting antenna). In addition, the concept works at 2.45 GHz and there is no dependence on the more difficult 35 GHz technology. This concept requires an open structure (since the solar array is on one side and the transmitting antenna on the other) and the size would be limited by the structural rigidity of the large array. In the above example, the central transmitting antennas would disappear. For such a platform, the power to the transmitting antenna would be of the order of 10 MW. With launch costs, the cost for such an integrated array platform may approach 1 billion US dollars for a 10 MW platform. As unit costs decrease, these integrated array platforms could assembled modularly or flown in constellations. Launch Cost Notes The STS launch was either a NASA sponsored project or a NASA Joint Venture Agreement which would not cost the project directly. One Energia launch was assumed to be 100 million US dollars. 10.4.4 Scheduling This section illustrates a feasible schedule in which the MW class demonstration is developed, constructed and made operational. The total time between conceptual studies and fully operational status is envisaged to be about 7 years. This includes approximately six months for the orbit raising and plane changing maneuver using the hybrid propulsion system discussed earlier.
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