An aeromaritime satellite system payload definition

The application of a multibeam array system in a combined operational aeronautical and maritime mission for the years 1985 to 1992 is described. Topics include mission objective, frequency plan, coverage, transponder configuration, link budgets, and eclipse performance. The payload requirements were: mass 200 kg, payload power daylight maximum 2100 W, and eclipse typical 750 W. A three satellite aeronautical and maritime geostationary system was assumed. The most severe restrictions were: (1) lack of spectrum on return link to accommodate all required channels without resorting to use of extensive on board switching or frequency reuse; (2) undefined aircraft EIRP. Both of these problems were treated in a parametric way.