Hardware Fault Insertion and Instrumentation System: Mechanization and Validation.

This effort was performed to provide automated test capability for extensive low-level hardware fault insertion testing. The capability developed was applied in a related task that is described in DOTFAACT-8634. The test capability was used to calibrate fault detection coverage and associated latency times as relevant to projecting overall system reliability. This report describes modifications made of the NASA Ames Reconfigurable Flight Control System RDFCS Facility to fully automate the total test loop involving the Draper Laboratories Fault Injector Unit. The automated capability provided included that application of sequences of simulated low-level hardware faults, the precise measurement of fault latency times, the identification of fault symptoms, and bulk storage and test case results. A PDP-1160 served as a test coordinator, and a PDP-1104 as an instrumentation device. The fault injector was controlled by applications test software in the PDP-1160, rather than by manual commands from a terminal keyboard. The time base was specially developed for this application to use a variety of even signal sources in the system simulator. Keywords Automated testing, Command files, Digital flight computers, Fault handling, Instrumentation, Time measurements.