The objective of this program was to study and evaluate the concept of using a damage accumulation monitoring system based on microprocessor technology for individual aircraft tracking (IAT) needed to satisfy the Force Management requirements of MIL-STD-1503A. The two major components of this study were: (1) the evaluation of selected output and input IAT parameters required to monitor the potential crack growth of each of two major classes of aircraft (Bomber/Transport and Fighter/Attack/Trainer aircraft), and (2) the definition of the microprocessor-based IAT system in terms of capabilities and requirements. A number of existing and planned IAT programs which were considered as typical for the two major classes of aircraft were studied to determine problem areas, to evolve advanced concepts, and to evaluate the output/input parametric requirements and the functional characteristics needed to satisfy IAT system goals. Several conceptual microprocessor based IAT systems and one existing microprocessor based IAT system capable of satisfying the requisite functional requirements were developed, studied, and described. In addition, the study was extended to examine the capability of microprocessor based IAT systems to satisfy in part or wholly, the load and environment spectra survey (L/ESS) functions. Several system concepts were developed and described.

An analytical and experimental program was conducted to evaluate the crack growth gage concept for application as an individual aircraft tracking device. Three gage designs were evaluated. Volume I discusses the evaluation of two versions of a stepped thickness gage and a stepped width gage. Volume II discusses the evaluation of a side-grooved constant thickness gage. An analytical evaluation of the change in transfer function corresponding to gage design parameter changes was performed to determine the configuration of the gages to be tested. Initial spectrum tests were conducted on the first stepped gage design to determine the ranking ability of the gage. Then constant amplitude tests were conducted on the second stepped gage design. A modification of the gage was made to improve spectrum test response. The modified gage was subjected to both constant amplitude testing and spectrum testing. The analytically derived crack growth rates were compared to the test data. In general, the analysis predicted slightly higher growth rates than observed.

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)