Optical: systems and elements – Deflection using a moving element – Using a periodically moving element
Reexamination Certificate
1998-10-21
2001-12-11
Pascal, Leslie (Department: 2633)
Optical: systems and elements
Deflection using a moving element
Using a periodically moving element
C359S199200, C359S199200
Reexamination Certificate
active
06330093
ABSTRACT:
BACKGROUND OF THE INVENTION
This invention relates generally to modular spacecraft engineering and design and, more particularly, to techniques for interconnecting spacecraft electronic equipment modules that are externally mounted on a core spacecraft structure. Conventional spacecraft designs have placed electronic equipment on panels located inside box-like modules, with the panels typically forming the walls of the modules. The modules are mounted onto a spacecraft and interconnected with extremely complex wiring harnesses. This approach makes spacecraft design, integration and testing a costly and time-consuming effort, and renders even small design changes difficult or practically impossible. Clearly, a more modular approach is called for, but efforts to provide a “standard” spacecraft bus, on which equipment and avionics modules are mounted, have not resulted in elimination of the wiring harness as the preferred interconnection medium. The present invention addresses these difficulties and provides an elegant solution to the problem.
SUMMARY OF THE INVENTION
The present invention resides in a backbone interface for use in a modular spacecraft having a core structure and a plurality of largely independent spacecraft modules. The backbone interface comprises a power bus extending along a spacecraft core structure, for coupling to connectors on modules plugged into the backbone interface and for supplying electrical power to the modules; an optical data bus also extending along the spacecraft core structure, for carrying data signals in optical form from one module to another; and an optical interface associated with each module, for converting optical signals from the optical data bus to electrical signals, directing the converted electrical signals to appropriate destinations on the module, and adding data signals derived from sources located on the module back onto the optical data bus.
The backbone interface of the invention may also comprise either or both of a conventional electrical data bus also extending along the spacecraft core structure, for coupling to data connectors on the modules plugged into the backbone interface, and a radio-frequency (RF) bus also extending along the spacecraft core structure, having a plurality of waveguide channels for selective coupling to connectors on the modules plugged into the backbone interface.
More specifically, the optical interface includes an optical demultiplexer to separate multiple optical channels carried on the optical data bus; a detector array for generating electrical signals from signals on the multiple optical channels; switching logic to determine module destinations for the electrical signals and for routing electrical signals generated on the module; a plurality of light sources coupled to the switching logic, to generate optical signals for coupling onto the optical data bus; and an optical multiplexer, for combining a plurality of optical signals from the light sources, for launching onto the optical data bus. In the presently preferred embodiment of the invention, the optical signals are wavelength division multiplexed onto the optical data bus. The optical demultiplexer generates multiple optical signals at different wavelengths, and the plurality of light sources include lasers operating at the same respective wavelengths as the multiple optical signals.
It will be appreciated from the foregoing that the present invention represents a significant advance in the field of spacecraft design and construction. In particular, the invention is a key to facilitating design, construction and modification of spacecraft, since it provides a standardized interface between a spacecraft core structure and a plurality of similar modules. Using the interface, each module is easily plugged into a backbone bus on the core structure, to provide a path for distribution of electrical power, command and control signals, and mission-specific data. An optical path provides for the transmission of large volumes of data from one spacecraft module to another, through an optical data bus incorporated into the backbone structure. A significant advantage of the standardized interface is that modules can be more easily designed, upgraded and replaced without disruptive redesign of mechanical, thermal and electrical interconnections between modules. Other aspects and advantages of the invention will become apparent from the following more detailed description, taken in conjunction with the accompanying drawings.
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Coronel Ramon
Eller Howard S.
Harkness Gary T.
Heal Noel F.
Pascal Leslie
Phan Hanh
TRW Inc.
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