Evaluating Strategies to Mitigate Jamming in Electromechanical Actuators for Safety Critical Applications
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Published
Jul 14, 2017
Yameen M. Hussain
Stephen Burrow
Leigh Henson
Patrick Keogh
Abstract
In this paper various techniques to mitigate jamming in Electromechanical Actuators (EMA) for safety critical applications in aerospace are evaluated. This paper highlights and assesses what has already been achieved and the
challenges still to be addressed. Through Hierarchical Process Modelling (HPM), it was identified that Prognostics and Health Monitoring (PHM) and achieving fault tolerant designs in EMAs could be considered as means to mitigate jamming. The evaluation of past research revealed that achieving a fault tolerant EMA system through a reliable and robust anti-jamming system is currently at an early development stage for implementation within safety critical systems due to the increased design complexity (the antijamming system may even require PHM functionality itself). It was concluded that a hybrid diagnostic approach to predict the onset of jamming would be the most optimal approach by using a combination of model based and data-driven techniques to capture any discrepancies between the predicted and observed behaviour to isolate and identify faults. Furthermore, in order to achieve a robust and reliable hybrid diagnostics functionality (to mitigate EMA ballscrew jamming), recommendations were made to improve modelling fidelity and test stand analysis methodology, these are discussed in more detail in this paper.
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Keywords
Prognostics, Health Monitoring, Aerospace, Ballscrew, Electromechanical Actuators, Jamming
References
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AIR5713. (2008). In-service Reliability Data of Continuously Active Ballscrew and Geared Flight Control Actuation Systems. SAE.
Balaban, E., Bansal, P., Stoelting, P., Saxena, A., Goebel, K., & Curran, S. (2009). A Diagnostic Approach for Electro-Mechanical Actuators in Aerospace Systems. IEEE Aerospace.
Balaban, E., Saxena, A., Goebel, K., Byington, C., Watson, M., Bharadwaj, S., & Smith, M. (2009). Experimental Data Collection and Modelling for Nominal and Fault Conditions on Electromechanical Actuators. IJPHM.
Balaban, E., Saxena, A., Narasimhan, S., Roychoudhury, I., Goebel, K., & Koopmans, M. (2010). Airborne Electro-Mechanical Actuator Test Stand for Development of Prognostic Health Management Systems. Annual Conference of the Prognostics and Health Management Society 2010. PHM.
Bennett, J. (2010). Fault Tolerant Electromechanical Actuators for Aircraft. Newcastle University.
Bennett, J., Mecrow, B., Atkinson, D., & Atkinson, G. (2011). Safety-critical Design of Electromechanical Actuation Systems in Commercial Aircraft. IET Electric Power Applications, 37-47.
Bodden, D., Clements, S., Schley, B., & Jenney, G. (2007). Seeded Failure Testing and Analysis of an Electromechanical Actuator. Aerospace Conference (pp. 1-8). IEEE.
Byington, C., & Stoelting, P. (2004). A Model-Based Approach to Prognostics and Health Management for Flight Control Actuators. 2004 IEEE Aerospace Conference (pp. 3551-3562). IEEE.
Checkland, P., & Poulter, J. (2007). Learning for Action: A Short Definitive Account of Soft Systems Methodology, and itsd use for Practitioners, Teachers and Students. John Wiley.
Churn, P., Maxwell, C., Schofield, N., Howe, D., & Powell, D. (1998). Electro-hydraulic Actuation of Primary Flight Control Surfaces. IEE Colloquium on All Electric Aircraft, (pp. 3/1-3/5).
Collins, A., & Sunstrand, H. (2004). USA Patent No. US 6776376 B2.
Cooper, M. (2014). Simulating Actuator Energy Demands of an Aircraft in Flight. Cranfield University.
Croke, S., & Herrenschmidt, J. (1994). More Electric Initiative - Power by Wire Actuation Alternatives. IEEE Proceedings of the National Aerospace and Electronics Conference (pp. 1338-1346). IEEE.
Cronin, M. (1985). USA Patent No. US 4530271A. Department of Defense. (1980). Procedures for Performing a Failure Mode, Effects and Criticality Analysis. Department of Defense, USA.
Donald, S., Garg, S., Hunter, G., Guo, T., & Semega, K. (2004). Sensor Needs for Control and Health Management of Intelligent Aircraft Engines. NASA.
Gerada, C., & Bradley, K. (2008). Integrated PM Machine Design for and Aircraft EMA. IEEE TRANSACTIONS ON INDUSTRIAL ELECTRONICS, 3300-3306.
Hoffman, A., Hansen, I., Beach, R., Plencner, R., Dengler, R., Jefferies, K., & Frye, R. (1985). Advanced Secondary Power System for Transport Aircraft. NASA.
Jennions, I. (2012). Integrated Vehicle Health Management: Business Case Theory and Practice. SAE International.
Jeong, S., & Park, J. (1992). Thermal Expansion Analysis of the Ball Screw System by Finite Difference Methods. Journal of the Korean Society for Precision Engineering, 44-57.
Jones, R. I. (1999). The More Electric Aircraft: The Past and the Future? IEE Colloqium on Electrical Machines and Systems for the More Electric Aircraft, (pp. 1/1-1/4).
Landing Gear parts. (2015). Retrieved from Pininterest: https://uk.pinterest.com/pin/488359153317845635/
Leonard, J. (1984). All-Electric Fighter Airplane Flight Conrol Issues, Capabilities and Projections. IEEE Transactions on Aerospace and Electronics Systems, 234-242.
Maggiore, P., Vedova, M., Pace, L., & Desando, A. (2014). Definition of Parametric Methods for Fault Analysis applied to an Electromechanical Servomechanism affected by Multiple Failures. European Conference of the Prognostics and Health Management Society 2014. PHM.
Mare, J. (2016). Aerospace Actuators 1: Needs, Reliability and Hydraulic Power Solutions. Wiley-ISTE.
Min, B., Park, C., & Chung, S. (2016). Thermal Analysis of Ballscrew Systems by Explicit Finite Difference Method. Transactions of the Korean Society of Mechanical Engineers, Volume 40, 41-51.
Moir, I., & Seabridge, A. (2008). Aircraft Systems: Mechanical, electrical, and avionics subsystems integration. John Wiley and Sons, Ltd.
Narasimhan, S., Roychoudhury, I., Balaban, E., & Saxena, A. (2010). Combining Model-Based and Feature- Driven Diagnosis Approaches - A Case Study on Electromechanical Actuators. 21st International Workshop on Principles of Diagnosis.
Nguyen, D., Behar, B., & Mckay, T. (2014). USA Patent No. US 8794084 B2.
Norton, W. (1986). Advanced Electromechanical Actuation System (EMAS), Flight Test. USAF.
Park, R. (1929). Two Reaction Theory of Synchronous Machines. AIEE Transactions 48, 716-730.
Pidd, M. (2004). Systems Modelling: Theory and Practice.
Pillay, P., & Krishnan, R. (1991). Application Characteristics of Permanent Magnet Synchronous Motors and Brushless DC Motors for Servo Drives. IEEE Transactions on Industry Applications, 986-996.
Rea, J. (1993, August). Boeing 777 High Lift Control System. IEEE AES Systems Magazine, pp. 15-21.
Robelin, O. (2010, January). Maintenance Review Board Process (MRB) and Instructions for Continuied Airworthiness. Retrieved from EASA: https://www.easa.europa.eu/system/files/dfu/ws_prod-g-doc-Events-2010-jan-19-Ref-9.-MRBprocess.pdf
Sampath, M., Godambe, A., Jackson, E., & Mallow, E. (2003). USA Patent No. US6519552 B1.
Stridsberg, L. (2005). Low Weight, Highly Reliable Anti- Jamming Device for Electromechanical Actuators. Texas: SAE Technical Paper Series.
Todeschi, M. (2011). Airbus - EMAs for Flight Controls Actuation System - An Important Step Achieved in 2011. SAE International.
Vahid-Araghi, O., & Golnaraghi, F. (2011). Friction Induced Vibration in Lead Screw Drives. Springer.
Section
Regular Session Papers