A space power system based on laser beam power is sized to reduce mass, increase operational capabilities, and reduce complexity. The advantages of laser systems over solar-based systems are compared as a function of application. Power produced from the conversion of a laser beam that has been generated on the Earth's surface and beamed into cislunar space resulted in decreased round-trip time for Earth satellite electric propulsion tugs and a substantial landed mass savings for a lunar surface mission. The mass of a space-based laser system (generator in space and receiver near user) that beams down to an extraterrestrial airplane, orbiting spacecraft, surface outpost, or rover is calculated and compared to a solar system. In general, the advantage of low mass for these space-based laser systems is limited to high solar eclipse time missions at distances inside Jupiter. The power system mass is less in a continuously moving Mars rover or surface outpost using space-based laser technology than in a comparable solar-based power system, but only during dust storm conditions. Even at large distances for the Sun, the user-site portion of a space-based laser power system (e.g., the laser receiver component) is substantially less massive than a solar-based system with requisite on-board electrochemical energy storage.
Ground-Based and Space-Based Laser Beam Power Applications
1995
12 pages
Report
Keine Angabe
Englisch
Space Technology , Extraterrestrial Exploration , Electric & Ion Propulsion , Electric propulsion , Spacecraft power supplies , Laser applications , Laser beams , Laser outputs , Cislunar space , Electric energy storage , Electrochemical cells , Photovoltaic effect , Solar eclipses , Spaceborne lasers , Laser power beaming
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