RECOVER: A Benchmark for Integrated Fault Tolerant Flight Control Evaluation

Smaili, Hafid; Breeman, J.H.; Lombaerts, Thomas; Joosten, Diederick

doi:10.1007/978-3-642-11690-2_6

Cited by 15 publications

(8 citation statements)

References 6 publications

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“…For comparison, the flight manoeuvre used in the tests is also similar to the GARTEUR FM-AG16 benchmark problem [33], [34], [17]. Shortly after a right turn, the complete loss of all control surfaces occurs and all the control surfaces become inactive with flaps locked at 20 • extension.…”

Section: Simona Simulator Evaluation Resultsmentioning

confidence: 99%

“…The aircraft model running the SRS 6-DOF flight simulator, is a high fidelity nonlinear model of a civil aircraft based on the RECOVER benchmark model from the GARTEUR FM-AG16 programme [33]. For these tests the RECOVER model has been modified to include a total loss of all control surfaces scenario, which was not considered in the GARTEUR FM-AG16 programme.…”

Section: Srs Implementation Issuesmentioning

confidence: 99%

See 1 more Smart Citation

Sliding-Mode Propulsion-Control Tests on a Motion Flight Simulator

Alwi¹,

Edwards²,

Stroosma³

et al. 2015

Journal of Guidance, Control, and Dynamics

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This paper describes a fault tolerant sliding mode control allocation scheme capable of coping with the loss of all control surfaces, resulting from a failure of the hydraulics system, during which time the scheme only utilizes the engines to control the aircraft. The paper presents tests of the scheme implemented on a 6-DOF motion research flight simulator of Delft University of Technology, called SIMONA (acronym for SImulation MOtion and NAvigation) research simulator, using a realistic manoeuvre involving an emergency return to a near landing condition on a runway in response to the failure. The simulator results show that, not only does the controller provide high tracking performance during nominal fault-free conditions, this performance is also maintained after the total loss of all control surfaces. This shows the capability of the proposed sliding mode control allocation scheme to achieve and maintain desired performance levels using only propulsion, by redistributing the control signals to the engines when failures occur.

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Section: Simona Simulator Evaluation Resultsmentioning

confidence: 99%

Section: Srs Implementation Issuesmentioning

confidence: 99%

Sliding-Mode Propulsion-Control Tests on a Motion Flight Simulator

Alwi¹,

Edwards²,

Stroosma³

et al. 2015

Journal of Guidance, Control, and Dynamics

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show abstract

“…The model which runs under the Matlab and Simulink environment, has been extensively developed over many years by many different contributors (see for example [48], [49], [38] and more recently [50]) into a platform to test state of the art FTC and FDI schemes. In the recent…”

Section: A Recover Benchmark Modelmentioning

confidence: 99%

Fault tolerant longitudinal aircraft control using non‐linear integral sliding mode

Alwi

Edwards

2014

IET Control Theory & Applications

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This paper proposes a novel nonlinear fault tolerant scheme for longitudinal control of an aircraft system, comprising an integral sliding mode control allocation scheme and a backstepping structure. In fault free conditions, the closed loop system is governed by the backstepping controller and the integral sliding mode control allocation scheme only influences the performance if faults/failures occur in the primary control surfaces. In this situation the allocation scheme redistributes the control signals to the secondary control surfaces and the scheme is able to tolerate total failures in the primary actuator. A backstepping scheme taken from the existing literature is designed for flight path angle tracking (based on the nonlinear equations of motion) and this is used as the underlying baseline controller in nominal conditions. The efficacy of the scheme is demonstrated using a high fidelity aircraft benchmark model. Excellent results are obtained in the presence of plant/model uncertainty in both fault-free and faulty conditions.

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“…7,21 Despite the fatal outcomes, reconfigurable flight control might have been able to recover the aircraft by efficiently utilizing the remaining control inputs. 19 Piloted simulations of one reconfigurable method, Adaptive Nonlinear Dynamic Inversion (ANDI), do not only allow a safe landing with a post-failure aircraft, but also reduce the workload of the pilot. 15 However, the disadvantage of using adaptive control as a Fault-Tolerant Flight Controller (FTFC) is that they require a model identification algorithm for an aerodynamic model in order to compute the control actions.…”

Section: Introductionmentioning

confidence: 99%

“…The designed SB-NDI controller was implemented in the Reconfigurable Control for Vehicle Emergency Return (RECOVER) B747 100/200 model and evaluated with one pilot in the SRS. 7,19 The real-time flight performance and the fault-tolerant capabilities of the multi-loop SB-NDI controller are evaluated with an approach procedure with a vertical tail loss and the Flight1862 failure scenarios. Besides evaluating the flight trajectories in a qualitative way, the physical workload of the pilot is analyzed by calculating the Root Mean Square (RMS) values of the applied deflections.…”

Section: Introductionmentioning

confidence: 99%

Piloted Simulator Evaluation of a Model-Independent Fault-Tolerant Flight Control System

Tang

Pool

Stroosma

et al. 2016

AIAA Guidance, Navigation, and Control Conference

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This paper for the first time evaluates the real-time performance of a sensor-based nonlinear dynamic inversion (SB-NDI) controller by means of a piloted proof-of-concept evaluation in a six degree of freedom research flight simulator. This fault-tolerant controller is completely model-independent and as a result does not require online identification. The inner loop of the controller incorporates an approximate dynamic inversion controller in combination with Lyapunov stability within a nonlinear dynamic inversion (NDI) framework and results in an adaptive model-free controller. The real-time performance, the fault-tolerant capabilities and the required physical workload of the controller are evaluated in the SIMONA research flight simulator with two flight scenarios consisting of approach procedures for the Flight1862 aircraft configuration and a vertical tail loss. The results are compared with full manual control and with an NDI attitude rate controller with a fixed aerodynamic model taken from literature. The results of this evaluation indicates that the designed multi-loop SB-NDI controller is capable of extending the survivability of the aircraft beyond what is possible with the baseline NDI controller. It also shows that the SB-NDI reduces pilot workload after a significant failure to levels comparable to the nominal aircraft.

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RECOVER: A Benchmark for Integrated Fault Tolerant Flight Control Evaluation

Cited by 15 publications

References 6 publications

Sliding-Mode Propulsion-Control Tests on a Motion Flight Simulator

Sliding-Mode Propulsion-Control Tests on a Motion Flight Simulator

Fault tolerant longitudinal aircraft control using non‐linear integral sliding mode

Piloted Simulator Evaluation of a Model-Independent Fault-Tolerant Flight Control System

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