The Design, Simulation and Development Testing of the Space and Shuttle Data Bus System,
SINGER CO WAYNE N J KEARFOTT DIV
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The result of current LSI and future VHSIC component technology is to develop avionics of greater information throughput capability operating at higher frequencies yet achieving tenfold packaging densities. The aircraft or spacecraft designer faced with demands to add more mission andor functional capability capitalizes on the above mentioned trend by adding more avionics to the vehicle thereby increasing the demand on the DBS to provide a high integrity interconnect with no degradation to the intrinsic avionic capability. The Space Shuttle Orbiter having 5 to I0 Processors computers and over 400 elements of avionics dedicated to interfacing via 24 interconnecting data buses is an example of this trend. This paper describes a suggested sequence to be followed in the design, development, analysis and simulation of a digital DBS. It discusses the computer modelingsimulations performed and the hardware verification test results obtained on elements of the Space Shuttle Orbiter data bus.