Abstract
Aircraft actuation system receives commands from the flight control computer and drives the plane surface to realize the aircraft flight attitude and flight trajectory control. The actuation system has a significant influence on the overall aircraft flight control performance and safety. This chapter presents the essential reliability characteristics of the redundancy aircraft actuation systems, and creates a reliability evaluation method for non-similar redundancy actuation systems. Section 1 summarizes the aircraft actuation system, and explains the interface between the flight control system(FCS) and the actuation system. Some typical aircraft hydraulic actuation system constructions in current commercial aircraft are provided in Sect. 2. Furthermore, Sect. 3 analyzes the architecture and characteristics of A380 aircraft actuation system, and provides the comprehensive reliability definition and the reliability calculation method. Afterward, the reliability of actuation system based on performance degradation is described. Finally, the integrated reliability evaluation case is provided for example of a HA/EHA system, in which HA operates actively and EHA follows under normal operating conditions.
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References
Moir I, Seabridge A (2008) Aircraft systems: electrical and avionics subsystems integration. Wiley
McLean D (2000) Flight control systems: practical issues in design and implementation. In: Pratt RW (ed) The institution of electrical engineers, Michael Faraday House, Six Hills Way, Stevenage, Herts, SG1 2AY. 2000. 382 pp. Illustrated. £59.00. ISBN 0-85296-766-7; Aeronaut J 104(1037):334–335 (1968)
Crane D (2020) Dictionary of aeronautical terms
SAE International (2007) SAE AIR 5273: 2007 actuation system failure detection methods
Collinson RPG (2011) Aerodynamics and aircraft control. In: Introduction to avionics systems. Springer, Dordrecht
Bossche DV, Airbus (2006) The a 380 flight control electrohydrostatic actuators, achievements and lessons learnt
Wang Y (2014) Aircraft flight control hydraulic servo actuator. Aeronautic Industry Press, Bei**g
Wang S, Tomovic M, Liu H (2015) Commercial aircraft hydraulic system. Shanghai Jiao Tong University Press
Frischemeier S (1997) Electrohydrostatic actuators for aircraft primary flight control—types, modelling and evaluation
Shi C, Wang S, Wang X, Wang J, Tomovic MM (2017) Active fault-tolerant control of dissimilar redundant actuation system based on performance degradation reference models. J Franklin Inst 354(2):1087–1108
Botten SL, Whitley CR, King AD (2000) Flight control actuation technology for next generation all-electric aircraft. Technol Rev J 8(2):55–68
Mei WH, Guo Y, Mang HY (2003) Practical counterexamples to AMSAA reliability growth model for multiple systems development in MIL-HDBK-189 and MIL-HDBK-781. In: Paper presented at the 8th ISSAT international conference on reliability and quality in design, proceedings
Cui X (2019) Energy based reliability modeling method and its application in aircraft flight control system, Beihang University
Li T, Wang S, Shi J, Zio E, Cui X (2020) An energy-based coupling degradation propagation model and its application to aviation actuation system. Chin J Aeronaut 33(4):1288–1298
Kołowrocki K, Soszyńska-Budny J (2011) Modeling reliability and safety of multistate systems with ageing components. In: Reliability and safety of complex technical systems and processes. Springer Series in Reliability Engineering. Springer, London
Wang S (2000) Reliability engineering. Bei**g University of Aeronautics and Astronautics Press
MIL-F—9490D (USAF) Military specification, flight control systems—design, installation and test of piloted aircraft, general specification for, June 6, 1975
Wang S, Cui X, Shi J, Tomovic MM, Jiao Z (2016) Modeling of reliability and performance assessment of a dissimilar redundancy actuation system with failure monitoring. Chin J Aeronaut 29(3):799–813
Cui X, Wang S, Li T, Shi J (2019) System reliability assessment based on energy dissipation: modeling and application in electro-hydrostatic actuation system. Energies 12(18):3572
Shi C (2018) Research on variable load failure mechanism and life prediction of load sensing electro-hydrostatic actuator, Beihang University
Shi C, Wang S, Wang X, Zhang Y (2018) Variable load failure mechanism for high-speed load sensing electro-hydrostatic actuator pump of aircraft. Chin J Aeronaut 31(5):949–964
Wang S, Tomovic MM, Liu H (2016) Chapter 4—new technology of aircraft hydraulic system
Yin Y (2022) Vector engine control system fault coupling mechanism and information fusion fault diagnosis method, Beihang University
Li Q, Wang S, Shi J, Wang X, Jiao Z (2014) Reliability modeling analysis for hydraulic/electro-hydrostatic dual redundant actuation system. In: Paper presented at the proceedings of 2014 IEEE Chinese guidance, navigation and control conference
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Wang, S., Shi, J., Qiao, Y. (2023). Comprehensive Reliability of Aircraft Actuation System. In: Liu, Y., Wang, D., Mi, J., Li, H. (eds) Advances in Reliability and Maintainability Methods and Engineering Applications. Springer Series in Reliability Engineering. Springer, Cham. https://doi.org/10.1007/978-3-031-28859-3_9
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DOI: https://doi.org/10.1007/978-3-031-28859-3_9
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