US 6,206,327 B1 · Modular spacecraft bus

Abstract

A mission configurable modular satellite bus structure composed of several scalable modules, including a propulsion module and one or more stackable space modules, each using standard subsystems or components with common structures and/or interfaces, that can be processed in parallel to minimize nonrecurring and recurring costs. Each stackable space module includes a generally cylindrical central hub having a plurality of radial rib panels extending outwardly therefrom to form a plurality of bays for containing subsystem equipment. The hub includes a hollow center sized to receive the propulsion module as a fully assembled unit. The radial rib panels carry the primary structural load of the spacecraft. Also provided are removable side access panels that form enclosures for the bays. The side access panels include equipment mounts along an inside surface for mounting the subsystem components and radiators along an outside surface to provide thermal cooling for the mounted subsystem equipment. The modular bus structure of the present invention is lightweight, stiff, strong, dimensionally stable and is therefore most suitable for highly agile, remote sensing commercial, civil space and government missions. The high degree of access to the spacecraft interior afforded by the present invention allows the various subsystems to be installed as separate, line tested assemblies.

Claims15

Dependent claims

A space module for a mission configurable and scalable spacecraft bus said space module having a stackable configuration which adapts both to a payload at one end of the space module and to a mounting ring of a propulsion module at the other end of the space module, said space module comprising:

a) a central hub portion of generally cylindrical shape having an outer periphery and having a hollow interior portion sized to receive a propulsion tank of a propulsion module centrally and longitudinally within the hollow interior portion;
b) a plurality of spaced apart radial rib panels extending from said outer periphery of said central hub portion and defining a plurality of bays between the rib panels and the central hub portion and sized for containing subsystem components, said radial ribs panels being constructed to provide a primary structural load pathway through the space module from the mounting ring of a propulsion module to a payload;
c) a base panel enclosing a lower portion of each of said bays and constructed to provide a bulkhead for connection to the mounting ring of a propulsion module,
d) a top panel enclosing an upper portion of each of said bays and constructed to provide an interface with a payload;
and
e) a plurality of removable exposed side panels for enclosing said bays, and wherein each side panel includes an interior wall portion adapted to mount subsystem components thereon and an exposed exterior wall portion defining a radiator to remote heat generated by said subsystem components.

3 more elements

A mission configurable and scalable modular spacecraft bus, comprising:

a) a propulsion module including a mounting ring, a propulsion tank supported on the mounting ring and extending upwardly and centrally from the mounting ring, said propulsion tank having a longitudinal length which can be configured to provide the propellant volume required for a specific mission requirement, a launch vehicle interface supported on the mounting ring and having booster adapter interface structure for connecting the mounting ring to a launch vehicle a plurality of thrusters connected to and extending from the mounting ring, all fully assembled and pressure tested prior to installation within the spacecraft;
b) a first space module having a stackable configuration and which adapts to both a payload at one end of the first space module and to said mounting ring of said propulsion module at the other end of the first space module, said first space module comprising:
i) a central hub portion of generally cylindrical shape having an outer periphery and having a hollow interior portion sized to receive said propulsion tank of said propulsion module within the hollow interior portion;
ii) a plurality of spaced apart radial rib panels extending from said outer periphery of said central hub portion and defining a plurality of bays between the rib panels and the central hub portion and sized for containing subsystem components, said radial ribs panels being constructed to provide a primary structural load pathway through the first space module from said mounting ring to a payload;
iii) a base panel enclosing a lower portion of each of said bays and constructed to provide a bulkhead for connection to said mounting ring;
iv) a top panel enclosing an upper portion of each of said bays and constructed to provide an interface with a payload;
and
v) a plurality of removable exposed side panels for enclosing said bays, and wherein each side panel includes an interior wall portion adapted to mount subsystem components thereon and an exposed exterior wall portion defining a radiator to remote heat generated by said subsystem components.

5 more elements

Dependencies are inferred from the claim text.

Modular spacecraft bus

Life of this patent

Modular spacecraft bus

Life of this patent

Abstract

Claims15