Abstract:This paper presents piloted flight simulator results associated with the EL-AL flight 1862 scenario using a model reference-based sliding mode control allocation scheme for fault tolerant control. The proposed controller design was carried out without any knowledge of the type of failure, and in the absence of any fault detection and isolation strategy. This is motivated by the fact that the flight crew were unaware of the loss of the right engines. For this reason, the control allocation scheme which is propo… Show more
“…Edwards et al , which enables the results in this paper to be compared to the results presented in [4,5]. It should be noted that the altitude tracking control task would be switched into flight path angle command tracking mode at the 650 th second in order to mimic a landing process with fixed gliding slope (i.e.γ = −3 deg).…”
Section: B Overall Autopilot Flight Control Systemmentioning
“…To simplify the control allocation logic, some of the aircraft inputs can be combined and the following 19 equivalent control variables can be used instead [4,14,21]:…”
Section: B Rate Control Basis and Control Allocationmentioning
“…A number of FDI methods, as well as reconfiguring control approaches, have been proposed in the literature [4,. More recently, the work of Lombaerts et al , as a part of the GARTEUR FM-AG 16 program, has provided practical validation results of a piloted adaptive nonlinear dynamic inversion (ANDI) controller on the Simulation, Motion, and Navigation (SIMONA) research simulator (SRS).…”
“…The ANDI rate controller guarantees the stability of the postfailure aircraft and enables the pilot to land the aircraft safely. Thereafter, Alwi and Edwards et al  validated another type of reconfigurable control method on the SRS, which was designed using a model reference sliding mode control method together with a constant control allocation matrix.…”
Recently, an incremental type sensor based backstepping (SBB) control approach, based on singular perturbation theory and Tikhonov's theorem, has been proposed. This Lyapunov function based method uses measurements of control variables and less model knowledge, and it is not susceptible to the model uncertainty caused by fault scenarios. In this paper, the SBB method has been implemented on a fixed wing aircraft with its focus on handling structural changes caused by damages.
“…The idea is only to trigger the adaptive scheme if a fault is present and a degradation in the sliding motion begins to appear (Alwi et al, 2010). give a view of a virtual environment and a motion system moves the entire cabin to simulate aircraft motion.…”
Sliding mode methods have been historically studied because of their strong robustness properties with regard to a certain class of uncertainty, achieved by employing nonlinear control/injection signals to force the system trajectories to attain in finite time a motion along a surface in the state-space. This paper will consider how these ideas can be exploited for fault detection (specifically fault signal estimation) and subsequently fault tolerant control. It will also describe applications of these ideas to aerospace systems, including piloted flight simulator results associated with the GARTEUR AG16 Action Group on Fault Tolerant Control. The results demonstrate a successful real-time implementation of the proposed fault tolerant control scheme on a motion flight simulator configured to represent the post-failure EL-AL aircraft.
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