Boeing Defense, Space & Security PhantomWorks OSST-II Overview Presenter: Doug Knapp Distribution Statement A: Approved for public release; distribution is unlimited. Society of Reliability Engineers (SRE) Huntsville Chapter, RAM VII Workshop 04 Nov 2014 This research was partially funded by the Government under Agreement No. W911W6-11-2-0003. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. Copyright © 2014 Boeing. All rights reserved. 1 Operations Support and Sustainment Technologies Phase II (OSST-II) BDS | PhantomWorks Background: Army desires to transition aviation fleet to Condition Based Maintenance (CBM) Purpose: Technology development and demonstration to TRL4 (component and/or breadboard validation in laboratory environment) Objectives: Continue development and demonstrate 2016 Army S&T O&S metrics Scope: Electrical Project Propulsion Project VMS Project (Vehicle Management System) Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 2 CBM Program Objectives and Key Enablers BDS | PhantomWorks OSST-II Program supports Army CBM Program Courtesy U.S. Army Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 3 Metrics BDS | PhantomWorks (2005 Fielded Aircraft Baseline) (V) VMS 2016 S&T O&S Metric Goals (E) Electrical Contribution to 2016 Metric Goals (%) (P) Propulsion Predicted contributions to 2016 Metric Goals high low high medium medium medium medium medium medium high high high high high high medium medium high medium medium nil 65% Reduction in Inspections/Flight Hour 15% Reduction in Maintenance Labor/Flight Hour 20% Increase Component Mean Time Between Removals Less than 3% False Removal Rates 25 Hour Detection Time Before Failure 10% Reduction in System and Installation Cost 10% Reduction in System Weight high (>50%) medium (20-50%) low (<20%) nil (no contribution, or negative contribution) Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 4 Transition (2011 Outlook) BDS | PhantomWorks Technology demo Boeing product capability Rotorcraft platforms Courtesy U.S. Army, AATD 2011 Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 5 Transition Lookahead BDS | PhantomWorks Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 6 Electrical System ‒ Vision BDS | PhantomWorks Leverage the ubiquitous nature of the electrical system to create a CBM communications infrastructure to enable low cost, minimally intrusive and pervasive health management (HM) for the vehicle. Make the CBM infrastructure open and easy to use to provide the flexibility and adaptability required for growth. Develop CBM applications for selected subsystems based on their inherent benefit and to demonstrate the utility of the infrastructure. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 7 Electrical System ‒ Tech Approach BDS | PhantomWorks Electronic circuit breakers (ECBs) in a solid state power distribution system (PDS) is leveraged to monitor electrical loads. Ultra Wideband over Wire (Ultra WoW) to implement a virtual bus to communicate CBM data from line replaceable units (LRUs) that have a bus interface (e.g., Mil-Std1553). Power line communications (PLC) to move data from LRUs or major components that do not support a bus interface. CBM system built upon an open, partitioned, plug and play software infrastructure to reduce development and integration costs, and provide a platform for future growth. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 8 Electrical System ‒ Apache Applications BDS | PhantomWorks Three (3) CBM Demonstration Threads Generator Electrical generator bearing Blower ECS (Environmental Control System) Blower motor bearing and foreign object damage (FOD) Electronics Power supply and inverter Distance to fault for wiring Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 9 Electrical System Project Plan BDS | PhantomWorks Industry Partners; Leverage SBIR, IRAD funded technologies Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 10 Electrical System Demonstration BDS | PhantomWorks Demonstration Threads Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 11 Electrical System Demonstration BDS | PhantomWorks Boeing test stand Aircraft equipment Bearing Cage front half Rivet Generator Drive Stand Driveshaft Aircraft Equipment Rack Test Bench Operator’s Station AC and DC Load Banks Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 12 Electrical Power Demonstration System BDS | PhantomWorks Demonstration Threads CBM Application Enabling Technology PDS as a Sensor Generator Bearing Blower Motor Bearing Monitor motor current for health indicator. CBM System Copyright © 2014 Boeing. All rights reserved. Distance to Fault Provide data to distinguish arcing from load characteristics. Potential to host DTF electronics. Communicated sensor/processed data for health indicator. Ultra WoW Powerline Communications Power Supply and Inverter Communicated sensor data over main power feeder. Common open, partitioned, Plug and play infrastructure. Communicated sensor data over existing power wire. Common open, partitioned, Plug and play infrastructure. Common open, partitioned, Plug and play infrastructure. Distribution Statement A: Approved for public release; distribution is unlimited. Common open, partitioned, Plug and play infrastructure. 13 Propulsion Project (Approach & Benefits) BDS | PhantomWorks OSST II Propulsion Design Targets 2013 Technology Goals and 2016 S&T O&S Metrics Develop sensor platform to measure multiple oil & component parameters. Integrate COTS sensor technology. Utilize wireless communications. Develop prognostics through embedded algorithms using dynamic model of components and fluid conduits. Bench test Advanced Sensor Platform. Demonstrate with MELB Engine and Transmission. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 14 Propulsion Project Plan BDS | PhantomWorks Industry Partners; Leverage SBIR, IRAD funded technologies Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 15 Sensor Parameters BDS | PhantomWorks *O=Oil Aging/Contamination, W=Water Contamination, B=Bearing/Gear Fatigue, G=Gear Pump Degradation, F=Filter Loading, P=Pressure Regulation, C=Cooler Performance, L=Line Restriction Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 16 Mapping System Features to Metrics BDS | PhantomWorks System Feature Multiparametric oil properties Critical oil debris Flow rate, RPM supply pressure Oil temperature Algorithms providing: Signal processing, Self-diagnostics, data fusion, physical/empirical models Specific Benefit OSST Impact Lubricant degradation, RUL Extended oil intervals Lubricant contamination Bearing/gear fatigue Lube pump performance, RUL Lube / scavenge filter loading, RUL Copyright © 2014 Boeing. All rights reserved. Earlier bearing/gear fault indication with less false-positives Localize pump faults, Improved maintenance scheduling Reduce inspection 65% per flight hour 15% reduction in labor 20% MTBR increase < 3% False removals Increased filter life utilization, improved maint. scheduling > 25 hr detection time before failure Localize cooler / bypass valve faults 10% reduction in installation cost Localize sensor faults 10% reduction in system weight Cooler performance Sensor built-in-test, self-accommodation Integrated nodes, Wireless hub Reduced oil inspections Related Metrics Reduced weight, integration effort Reduced weight, integration effort Distribution Statement A: Approved for public release; distribution is unlimited. 17 Test Plan Overview (MELB Transmission) BDS | PhantomWorks Test 1 – Initial Checkout and Acceptance Test 2 – Baseline Condition Test 3 – Fault Condition A: Water Contamination Test 4 – Fault Condition B: Bearing Debris, Static Flow Test 5 – Fault Condition C: Bearing Debris, Dynamic Flow Test 6 – Fault Condition D: Silica Dust, Dynamic Flow Test 7 – Fault Condition E: Gear Pump Wear Test 8 – Fault Condition F: Incorrect Lubricant Contamination Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 18 RR250-C30P Engine Demo BDS | PhantomWorks Hardware installed on RR250-C30 Supply-side Sensor Node Scavenge-side Sensor Node To Scav Filter Supply Pump Pressure Sensor RR 250-C30 Test Article From Engine Sensor nodes plumbed into flex lines Master hub mounting arrangement Injector port for dirt and steel chips Debris Chamber HM System Mounting Plate Master Hub Enclosure Sensor, Power, Comm Connections Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 19 MELB Main Transmission Demo BDS | PhantomWorks Hardware installed via plumb lines, master hub, injector port A C (A) MELB Transmission (retired on flight hours) (B) OSST-II hardware installation, showing master hub unit (C) OSST-II hardware installation, showing sensors and fluid connections B Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 20 MELB Main Transmission Demo BDS | PhantomWorks Hardware installed via plumb lines, master hub, injector port (A) OSST-II hardware installed in the vicinity of the slave gearbox unit. (B) Clearance measurement near pump inlet/outlet ports. (C) Fluid aeration within the gearbox sump while stopped. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 21 VMS Project (Approach & Benefits) BDS | PhantomWorks OSST II VMS Design Targets 2013 Technology Goals and 2016 S&T O&S Metrics OSST VMS Design CAPTURE & ADAPT ERDS Block-III Boeing Programs: CRAD IRAD CH-47 V-22 A160 LEVERAGE A H-64 Copyright © 2014 Boeing. All rights reserved. S-100 Contribution to 2016 Metric Goals (%) 2016 S&T O&S Metric Goals (2005 Fielded Aircraft Baseline) (V) VMS Emerging AED Findings • Selection of Higher Payoff CBM Applications • Analysis of No Fault Founds, Intermittents and Extended Troubleshooting • Data Mining • Performance Analysis of Actuators • Development of Health Indicators for Electro-mechanical and Hydraulic Actuator • Fault Patterns in Reasoner • Vehicle Level Integration • System Demonstration in Test Facilities (E) Electrical RAM DRIVERS (P) Propulsion Vehicle Field Data high low high medium medium medium medium medium medium high high high high high high medium medium high medium medium nil 65% Reduction in Inspections/Flight Hour 15% Reduction in Maintenance Labor/Flight Hour 20% Increase Component Mean Time Between Removals Less than 3% False Removal Rates 25 Hour Detection Time Before Failure 10% Reduction in System and Installation Cost 10% Reduction in System Weight high (>50%) medium (20-50%) low (<20%) nil (no contribution, or negative contribution) Distribution Statement A: Approved for public release; distribution is unlimited. 22 VMS Project Plan BDS | PhantomWorks Industry Partners; Leverage SBIR, IRAD funded technologies Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 23 VMS Focus Areas (application categories) BDS | PhantomWorks Health Management & Analysis Focus on No Fault Found (NFF) and maintenance event records Utilized academia (Univ Tennessee, Vanderbilt Univ) Yield relevant technology maturation for future development est. <TRL4 for Apache application Actuator Rigging est. TRL4 auto rigging to reduce O&S burden Actuator Prognostics est. TRL4 diagnostics/prognostics for stabilator actuator degradation Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 24 Actuator Prognostics Overview BDS | PhantomWorks Early Program Effort These “new technology” efforts concluded in 2012 Correlating Existing MDR and Unit Leven Logistics System Aviation (ULLSA) Data Actuator Life on Wing Distribution (many early removals indicates shot gun maintenance) Correlation of Fault Codes to Removals (weak correlation, no forensics) Estimating NFF Rate (extremely high) Characterizing Degrading Actuators Final objective and focus of 2013-2014 testing and analysis effort TRL4 prognostics may reduce instances of early removals and NFFs Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 25 Actuator Prognostics Overview BDS | PhantomWorks Final Objective — to use the rates as a measurement of degradation in the stabilator actuator, also known as ElectroMechanical Actuator (EMA) Approach By comparing the actuator commands and responses during the preflight IBIT test portion for the flight data that is available, determine whether or not there are observable degradations over time Assuming that there are observable degradations over time, incorporate this information into a failure prediction model Develop an automated script to compare the command versus the response and look at the margins in the test Data was convincing as useful for performance evaluation Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 26 Actuator Prognostics Overview BDS | PhantomWorks Stabilator Actuator on aircraft Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 27 Actuator Prognostics Overview BDS | PhantomWorks Stabilator Actuator components susceptible to wear Motor commutation Brushes DC motor bearings Gear train wear Gear train bearings Limit switch failure. Fault Modes 2 back-to-back Stabilator Actuators Typically slow degradation in actuator drive rate with (brush/bearing) wear out. Increasingly large variance in drive rate with wear out. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 28 Actuator Prognostics Overview BDS | PhantomWorks Stabilator Actuator in lab (bench test, tear down) Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 29 Acknowledgements BDS | PhantomWorks AATD Leadership: Mr. Ming Lau, Power Systems Division OSST II Program – AATD Team: Program Manager, Treven Baker Technical / Program Agent, Christopher Lyman Contracts, Kenneth Helms and Robert Waible Disclaimer: The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the Aviation Applied Technology Directorate or the U.S. Government. Copyright © 2014 Boeing. All rights reserved. Distribution Statement A: Approved for public release; distribution is unlimited. 30 Copyright © 2014 Boeing. All rights reserved. 31