transmission of electricity by a complex network of grids, using coal locations as booster stations for ultra high voltage DC transmission lines, with reconversion to AC in consumer areas. In the Soviet Union, therefore, not only the concern over the general level of energy resources remaining and the optimum use to which these resources can be put, but also the unique problems posed by its geography point towards the need to develop an alternative method of power supply which is both independent of the primary fuel sources and of their geographical location. As the use of hydro-electric power, even if it could provide a larger percentage of the total required, still has a geographical problem, this means an increasing use of nuclear power, or the exploitation of some other new source, in the future. The scheme for the introduction of space energy production via the interim step of power retransmission from ground generators, as outlined by Sarkisjan et al, gains considerable currency when viewed in the light of the above. The means The literature available from Soviet authors has contained references to a change from ‘the main direction' [6,7], This change seems to have taken place about 10 years ago, following the abandonment of the old TT-5 based moon programme. The main direction was regarded as the gradual progression of man's activity from LEO, through cislunar space, interplanetary space and beyond, as a purely scientific exercise. However, it seems that about 1976 a decision was taken to make use of space in a much more economic fashion, with industrial returns being exploited as the major objective. The ‘main line' would still be there but now as an activity funded on the back of a more profitable activity. References began to be made to the characteristics of the transportation system and to the topic of space industrialization. In particular, Grishin and Chekalin [6] and Feoktiskov [8] have discussed payload size, propellant types (solids vs. liquids), fleet size, launch rates, recoverability and launch costs. Sarkisjan et al have indicated more specific data, including the LEO orbit altitude. From these discussions, Grishin and Chekalin put the upper payload limit at 500 tonnes for acoustic reasons. They settle in the same section for a ‘nominal value' of 250 tonnes when discussing space solar power satellites. Also referred to are: “complex future transportation systems based on the liquid propellant rocket engine, but with lower specific costs than those at present.” One must be cautious, however, because the section leans heavily on US studies of reusable systems. Feoktiskov discusses payload masses between 200-400 tonnes and a fleet of 50-100 ships. He considers 20 launches per year of each ship at some date early in the next century. This would create a cargo flow to LEO of 200-800 thousand tonnes per year, the flow envisaged for active space industrialization. The objective, he states, is to achieve a specific launch cost below 50 roubles/kg or 5-10% of those of the USA's
RkJQdWJsaXNoZXIy MTU5NjU0Mg==