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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

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.

대표청구항 ▼

[ What is claimed is:] [1.] A satellite assembly with modular bus components for delivery to and placement in an orbit, said satellite assembly comprising:a plurality of bus modules, each bus module comprised of a structural frame having substantially identical shape and defining interior spaces hav

[ What is claimed is:] [1.] A satellite assembly with modular bus components for delivery to and placement in an orbit, said satellite assembly comprising:a plurality of bus modules, each bus module comprised of a structural frame having substantially identical shape and defining interior spaces having approximately equal volumes, each bus module having substantially identical bus subsystems, said substantially identical bus subsystems comprising a thermal subsystem, a telemetry, tracking and control subsystem, a power subsystem, an attitude, orientation and control subsystem, and a propulsion subsystem;a single apogee booster coupled to said plurality of bus modules for taking the satellite assembly to a final orbit, said apogee booster configured to detach from said plurality of bus modules after ascent of said satellite assembly to said final orbit;a separation system for separating the plurality of bus modules into individual satellite subassemblies after detachment of the apogee booster from said plurality of bus modules, each individual satellite subassembly being a separate satellite and comprised of one or more of said bus modules, andwherein at least one individual satellite assembly is comprised of at least two of said bus modules.