Satellite configurations based on the Satellite Power System baseline requirements were analyzed and a preferred concept selected. A satellite construction base was defined, precursor operations incident to establishment of orbital support facilities identified, and the satellite construction sequence and procedures developed. Rectenna construction requirement were also addressed. Mass flow to orbit requirements were revised and traffic models established based on consutrcution of 60 instead of 120 satellites. Analyses were conducted to determine satellite control, resources, manufacturing, and propellant requirements. The impact of the laser beam used for space-to-Earth power transmission upon the intervening atmosphere was examined as well as the inverse effect. The significant space environments and their effects on spacecraft components were investigated to define the design and operational limits imposed by the environments on an orbit transfer vehicle. The results show that LEO altitude 300 nmi and transfer orbit duration 6 months are preferrable.
Satellite Power Systems (SPS) Concept Definition Study. Volume 5: Special Emphasis Studies
1980
265 pages
Report
Keine Angabe
Englisch
Solar Energy , Electric Power Production , Unmanned Spacecraft , Antenna design , Orbital assembly , Rectennas , Satellite design , Satellite ground support , Satellite power transmission (To earth) , Solar power satellites , Environment effects , Lasers , Orbit transfer vehicles , Space maintenance , Space plasmas , Spacecraft charging , Spacecraft power supplies , Support systems