Abstract: A satellite assembly (60, 68, 70) is formed from any number of bus modules (22) which have a substantially common shape and interior space volume. Each bus module (22) includes a structural frame (20) which is part of a structural subsystem and at least one and possibly all of a propulsion subsystem (28), a power subsystem (30), a thermal subsystem (32), an attitude, orientation and control subsystem (34), a telemetry, tracking and control subsystem (42) and a payload subsystem (44). Within each bus module (22), the subsystems are substantially non-redundant. Bus modules (22) attach together permanently or temporarily through attachment mechanisms (36). Permanent attachment is used to form large and/or redundancy within the satellites. Temporary attachment is used to increase the structural rigidity of individual bus modules (22) for launch purposes, then the assembly (60) is decomposed into individual satellites.

Abstract: A self-contained fueling module (10) provides the exact amount of hydrazine necessary to fuel a satellite (50) prior to launch. The fueling module (10) includes a propellant tank (14), a vacuum tank (12) and a pressurant tank (16). The propellant tank, filled with hydrazine, is shipped to the launch site where it is installed in the fueling module. Prior to launch, the fueling module is connected to the satellite and the hydrazine is driven with Helium pressurant into the satellite fuel tank. The Helium also pressurizes the satellite fuel tank to flight pressure. Any remaining fuel is evacuated from the connections (45) and fuel transfer lines (42) with the vacuum tank. Personnel do not have to wear self-contained atmospheric pressurized environment (SCAPE) suits because there is no risk of hydrazine exposure.