Today, the troubleshooting process for gas turbine engines, coupled electrical systems and sub-systems installed on military helicopters is both burdensome and error prone. Maintainers are required to follow static fault isolation procedures (i.e., fault trees), either paper or electronic, that detail a series of sequential test and repair steps. There is a lack of direct communication between embedded (on-board) fault diagnostics and ground based troubleshooting systems, which necessitates transferring information manually that could otherwise be attained digitally and without human error. Today, troubleshooting effectiveness is, at best, on the order of 50%. Removed components are often categorized as No Evidence of Failure (NEOF) when tested in the back shops and Reliability and Maintainability (R&M) data associated with the maintenance tasks is not easily accessible. To address the opportunity for improved troubleshooting efficiency, Honeywell and Impact Technologies, under an AATD sponsored Program, have developed and demonstrated a software package called ATEDS (Aviation Turbine Engine Diagnostic System). The targeted application is Honeywell's T55-GA-714A propulsion engine, subsystems and the CH-47 Auxiliary Power Unit. ATEDS 1) automatically collects diagnostic data from the digital electronic control unit (DECU) and facilitates the collection of observables from airframe crew and maintainers, 2) automatically aggregates the collection of this evidence, 3) uses an evidence-based Reasoner to fuse disparate diagnostic data and manual observations and prioritize the troubleshooting tasks having the greatest likelihood of success, 4) provides interactive, step-by-step fault tree navigation with direct link to the IETM and graphics, 5) tracks actions that have been performed to provide Reliability & Maintainability feedback, and 6) is capable of improving fault isolation performance through reinforcement learning. A fully functional ATEDS prototype system has been developed and demonstrated in several test cell evaluation events and through at-aircraft user trials, including flight testing. Honeywell's T55 Automated Power Assurance System was included in the prototype system, enabling the first flight demonstration of Automated Power Assurance and the integration of on- and off-board systems. Engine seeded-fault testing was performed in a test cell environment in October 2005. Operational Assessment Tests were successfully performed at Ft Carson, CO during 2005 and 2006 which included on-aircraft seeded fault and inflight Power Assurance tests. Successful field testing was also conducted in June 2006 at the US Army Aviation Logistics School (USAALS), Ft Eustis, VA, fulfilling the requirements of the ATEDS User Assessment Plan. The end result is a test equipment system that provides 'at aircraft' capability to fault isolate Honeywell's T55 propulsion engine, subsystems, DECU, electrical systems, and the CH-47 Auxiliary Power Unit (APU) with troubleshooting effectiveness approaching 95%. Most importantly, a Condition-Based Maintenance (CBM) system has been developed for a legacy propulsion system that applies state-of-the-art PHM and reasoner technologies similar to nextgeneration DoD platforms such as Joint Strike Fighter and Future Combat Systems, without requiring any new hardware, sensors or hardware modifications. This paper will describe the architecture and features of ATEDS and illustrates how it supports the Army's vision for Condition Based Maintenance through reduced maintenance support costs and improved mission readiness. Case studies are discussed that demonstrate ATEDS' performance capability and benefits, based on results from seeded fault engine tests and field trials. Also, results of a Cost-Benefit analysis will show that even basic features have a dramatic impact on reducing Operations & Support costs through the use of these technologies.


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    Titel :

    Aviation turbine engine diagnostic system (ATEDS) for the CH-47 helicopter


    Beteiligte:


    Erscheinungsdatum :

    2008


    Format / Umfang :

    12 Seiten, 2 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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