Detection, Identification and Estimation of Surface Damage/Actuator Failure for High Performance Aircraft

Çağlayan, Alper; Rahnamai, Kourosh; Allen, S.M.

doi:10.23919/acc.1988.4790091

Cited by 24 publications

(15 citation statements)

References 3 publications

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“…12 A few recent works have utilized the linear model following method. 13,14 However, the performances of the existing control recon guration methodologies depend on the accuracy of system identi cation that must be performed online.…”

Section: Robust Variable Structure Controller Design For Fault Toleramentioning

confidence: 99%

Robust Variable Structure Controller Design for Fault Tolerant Flight Control

Kim

2000

Journal of Guidance, Control, and Dynamics

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A model following control scheme is proposed that possesses fault detection and isolation capabilities as well as a fault tolerance property. The proposed model following controller is designed based on a variable structure control (VSC), and the scheme does not require the parameter estimation process for recon gurable control. The main idea of the proposed algorithm stems from the fact that the nonlinear control of VSC counteracts external disturbances. The proposed algorithm is shown to be very useful for the case of control surface damage in aircraft, where the parameter change and external fault signal satisfy the matching conditions. The nonlinear control action that suppresses the fault effect can be used to determine how serious the damage is. Numerical results show the applicability of the proposed algorithm. Nomenclature A= system matrix A m , B m = system/output matrix of the model to be followed a = gain parameter for discontinuous control input B = input matrix b(t) = bounding function of k n 1 (t )k C = output matrix C 1 , C 2 = partitioned matrices of C T T d a = ratio of lateral elevator location to aileron location from the body c.g.gain for output error feedback Dohyeon Kim was born in Seoul, Korea, in 1970. He received his B.S., M.S., and Ph.D. degrees in aerospace engineering from Seoul National University in 1993, 1995, and 1998, respectively. Since 1999, he has been with the Department of Automotive Engineering at Woosuk University where he is now a faculty member. Prior to joining the university, he worked on a risk management system as a consultant at The Boston Consulting Group, Inc. His research interests include the application of modern control theory to the aerospace and ground vehicles, modeling and control of economic and mechanical systems, and fault tolerant control. He is a member of AIAA. Youdan Kim is an Associate Professor in the . He also works for the Institute of Advanced Machinery and Design (IAMD), Seoul NationalUniversity. He received his B.S. and M.S. degrees in Aeronautical Engineering from Seoul NationalUniversity, and Ph.D. degree in Aerospace Engineering from Texas A&M University, in 1983, 1985, and 1990, respectively. From 1990 to 1991, he worked as research associate at Texas A&M University, before he joined the faculty of the Seoul National University in 1992. His current research interests include the control system design for aircraft and spacecraft, trajectory optimization, and exible structure control. He is a senior member of AIAA. K m = gain for output error feedback L a = stability derivative of roll moment with respect to a M = basis of left annihilator of C 2 m ail , m rud , m ele = signals to be monitored to diagnose control surface damage N a = stability derivative of roll moment with respect to a p(x, t ) = m £ n matrix i.e. D A = Bp r = yaw rate S a , S r , S v , S w = areas of aileron, rudder, vertical n, wing s = sliding variable T = transformation matrix t s = time at which sliding motion starts u d = discontinuous control input u eq = equivalent ...

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Section: Robust Variable Structure Controller Design For Fault Toleramentioning

confidence: 99%

Robust Variable Structure Controller Design for Fault Tolerant Flight Control

Kim

2000

Journal of Guidance, Control, and Dynamics

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“…GE chose an approach developed by Alphatech for the SIDC, which generated and filtered actuator and aircraft acceleration sensor residuals and then used a log-likelihood test to detect surface failures and SPRT to verify and classify a stuck or floating surface. The surface-damage detection approach by CRA included a no-fail filter to generate residuals, a bank of filters to compensate the residuals based on partial surface loss estimates and expected modelling errors, a bank of likelihood ratios to compute the likelihood of each surface-damage hypothesis, and a modified multiple hypothesis test to make detection and isolation decisions [23,24].…”

Section: Early Approaches Based On Failure Detection Isolation and mentioning

confidence: 99%

Historical Overview of Research in Reconfigurable Flight Control

Steinberg

2005

Proceedings of the Institution of Mechanical Engineers, Part G:

113

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This article presents a historical overview of research in reconfigurable flight control. For the purpose of this article, the term 'reconfigurable flight control' is used to refer to software algorithms designed specifically to compensate for failures or damage of flight control effectors or lifting surfaces, using the remaining effectors to generate compensating forces and moments. This article will discuss initial research and flight testing of approaches based on explicit fault detection, isolation, and estimation, as well as later approaches based on continuously adaptive and intelligent control algorithms. In addition, approaches for trajectory reshaping of an impaired aircraft with reconfigurable inner loop control laws will be briefly discussed. Finally, there will be some discussion on current implementations of reconfigurable control to improve safety on production and flight test aircraft and remaining challenges to enable broader use of the technology, such as the difficulties of flight certification of these types of approaches.

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“…Wu, Zhang and Zhou [2] studied the fault diagnosis and performance detection for the control system by using the control effectiveness factor. In 1998, Caglayan, and Rahnamai introduced the effectiveness factors into the flight control systems, and they illuminated the degree of damage of the control surface through the attenuation degree of the control effectiveness factor [8]. In ref.…”

Section: Introductionmentioning

confidence: 99%