A fault-tolerant avionics suite for an entry research vehicleA highly-reliable avionics suite has been designed for an Entry Research Vehicle. The autonomous spacecraft would be deployed from the Space Shuttle Orbiter and perform a variety of aerodynamic and propulsive maneuvers which may be required for future space transportation system vehicles. The flight electronics consist of a central fault-tolerant processor, which is resilient to all first failures, reliably cross-strapped to redundant and distributed sets of sensors and effectors. This paper describes the preliminary design and analysis of the architecture which resulted from a fifteen month study by the Charles Stark Draper Laboratory for the NASA Langley Research Center. After a brief introduction to the design task, the architecture of the central flight computer and its interface to the vehicle are discussed. Following this, the method and results of the baseline reliability study for the avionic suite are presented.
Document ID
19890030767
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dzwonczyk, Mark (Charles Stark Draper Laboratory, Inc. Cambridge, MA, United States)
Stone, Howard (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1988
Subject Category
Spacecraft Instrumentation
Report/Patent Number
AIAA PAPER 88-3975
Meeting Information
Meeting: AIAA/IEEE Digital Avionics Systems Conference