Aircraft Electrical Malfunction
The electrical
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The electrical systems of modern airplanes are very complex. Most contain numerous electrical installations. Moreover, the use of electric power in aviation will only become more widespread. Engineers are currently looking for ways to use electricity to drive aviation subsystems previously powered by other means (e.g., mechanical or hydraulic power). Obviously, airplane electrical systems must be highly reliable and fault tolerant. Most aircraft electrical failures result from interconnection breakdowns. Such malfunctions can affect numerous aircraft subsystems. For example, a connector problem could result in the complete failure of an airplane's avionics system. As part of a contract awarded by the Air Force in 1989, Failure Analysis Associates conducted a survey of data on failures of aircraft electronic and electrical components. The purpose of the survey was to identify problematic components. It concluded that "problems with interconnections are major contributors to aircraft electrical equipment failures (Galler & Slenski 3-7)." In addition, environmental factors, such as corrosion, may significantly contribute to wiring and connector failure. Fortunately, recent technological progress has made modern aircraft much less vulnerable. Modern aircraft employ a variety of electronic innovations. For example, components employed on the Boeing 777 include integrated computing architecture and the advanced ARINC 629 communication bus. Such systems grea
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m several functions (Morgan, 1991, pp. 9-12)." These include the following: (1) flight management; (2) display; (3) central maintenance; (4) airplane condition monitoring; (5) communication management; (6) data conversion gateway; and (7) engine data interface. The ARINC 629--as well as the ARINC 429 and discrete I/O channels--connect the cabinets to the airplane's interfaces.
One important aspect of aircraft electrical systems is failure detection. Computer monitoring systems have been developed for the evaluation of electrical equipment (Jianming et al. 887-890). In order to perform failure detection, such systems must constantly measure the electrical system's different output variables. At nominal conditions, these variables generally follow some known pattern (i.e., within a certain degree of uncertainty; deviations may result from system disturbances). When failures occur, the observable output variables typically deviate from their nominal, predictable trajectories. It is these unusual deviations which must be recognized by failure detection devices (Napolitano et al. 999-1003).
Jainmig and associates (1991) has described one computer monitoring and testing system that might be used to evaluate aircraft electric
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Approximate Word count = 1765
Approximate Pages = 7 (250 words per page)
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