Energy and Mass Balance for a Cislunar Architecture Supporting SSP

Abstract

For large scale power generation in space, a key economic challenge is launch costs of fabricated components . An attractive alternative is to manufacture solar panels in space, specifically on the moon, where a factory can produce many times its mass in finished goods . This paper presents an architecture for a complete space solar power (SSP) system based on severa l recently developed technologies. Lunar manufactories produce oxygen, silicon, iron, and aluminum, plus a refractory slag. These elements can be formed into single crystal solar panels, thin dielectric films, conductors, and structural members for a lunar infrastructure capable of delivering solar panels to geostationary earth orbit (GEO). There, humans build the power management infrastructure while robots assemble solar panels into an array capable of 10 GW of electric power. An orbiting transmitting ant enna delivers the power to a terrestrial receiving antenna. Mass and energy for each stage of this architecture are presented, with the results that an installation of this size requires at least 2.8 years to build, and requires landing 753 MT delivered to the moon and 202 MT delivered to GEO. Lunar produced mass totals 629 MT, and terrestrial mass required is 2 million MT. Ignoring non recurring engineering costs and component costs, the launch costs of this system are competitive with terrestrial nuclear power on a cost per GW basis. This architecture and supporting technology describe an attractive approach to large -scale development of SSP for the benefit of all mankind.