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Piloted Simulator Evaluation Results of New Fault-Tolerant flight Control Algorithm

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2009年第6期32卷 1747-1765页

作者： Lombaerts, T. J. J. Smaili, M. H. Stroosma, O. Chu, Q. P. Mulder, J. A. Joosten, D. A. Delft Univ Technol Fac Aerosp Engn Control & Simulat Div NL-2600 GB Delft Netherlands Natl Aerosp Lab Training Human Factors & Cockpit Operat Dept NL-1006 BM Amsterdam Netherlands Delft Univ Technol Delft Ctr Syst & Control NL-2600 GB Delft Netherlands

A high-fidelity aircraft simulation model, reconstructed using the digital flight data recorder of the 1992 Amsterdam Bijlmermeer aircraft accident (flight 1862), has been used to evaluate a new fault-tolerant flight control algorithm in an online piloted evaluation. This paper focuses on the piloted simulator evaluation results. Reconfiguring control is implemented by making use of adaptive nonlinear dynamic inversion for manual fly-by-wire control. After discussing the modular adaptive controller setup, the experiment is described for a piloted simulator evaluation of this innovative reconfigurable control algorithm applied to a damaged civil transport aircraft. The evaluation scenario, measurements, and experimental design, as well as the real-time implementation are described. Finally, reconfiguration test results are shown for damaged aircraft models including component as well as structural failures. The evaluation shows that the fault-tolerant flight control algorithm is able to restore conventional control strategies after the aircraft configuration has changed dramatically due to these severe failures. The algorithm supports the pilot after a failure by lowering workload and allowing a safe return to the airport. For most failures, the handling qualities are shown to degrade less with a failure than the baseline classical control system does.

关键词： flight Control Algorithms Test Pilots Handling Qualities Transport Aircraft Control System Design Nonlinear Dynamic Inversion digital flight data recorder Aircraft Configurations Aircraft Accidents Control Algorithm

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New Application of data Analysis Using Aircraft Fault Record data

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JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2018年第5期15卷 297-306页

作者： Lee, Chang-Hun Shin, Hyo-Sang Tsourdos, Antonios Skaf, Zakwan Cranfield Univ Sch Aerosp Transport & Mfg Coll Rd Cranfield MK43 0AL Beds England Cranfield Univ Integrated Vehicle Hlth Monitoring Ctr Coll Rd Cranfield MK43 0AL Beds England

Researchers extend the concept of the research work and develop newmethods to extract useful information from the fault history record data. The key enablers for revealing the useful information will be selection of key features and data analysis approaches. The focus of the analysis is design of key features and selection of appropriate data analytics, given the fault record data. The baseline approach adapted in this study is pattern analysis of the fault occurrences. The pattern in this study refers to the distribution of aircraft fault frequency across the aircraft fleet for each fault type. The analysis then identifies the candidates of fault types exhibiting abnormal patterns in the *** this end, the pattern is first modeled as a probability mass function (PMF), and the similarity between PMFs is measured using the probability-based distance such as the Bhattacharyya distance. The pattern analysis results can provide information on whether there is a potential problem in the maintenance phase of the aircraft or whether a specific fault type is a fault associated with a specific aircraft only.

关键词： Commercial Aircraft data Analysis Techniques Aircraft Operations Aircraft Condition Monitoring System Sensitivity Analysis Aircraft Maintenance digital flight data recorder Discrete Probability Distributions Aerospace Industry data Analytics

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ANALYSIS OF WINDSHEAR FROM AIRLINE flight data

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JOURNAL OF AIRCRAFT 1989年第2期26卷 103-109页

作者： BACH, RE WINGROVE, RC NASA Ames Research Center Moffett Field California

Advanced analysis methods, applied to airline digital flight records and air traffic control radar tracking data, are providing new insight into atmospheric disturbances that cause serious operating problems for aircraft. Reviewed in this paper are performance-based methods for determining unmeasured flow angles and the possible influence of rain on lift and drag, and a state estimation procedure for determining winds along the flight path. The methods are applied to data records from the Delta Airlines flight 191 windshear accident at the Dallas-Ft. Worth Airport, Aug. 2, 1985, involving an L-1011 airliner on final approach. The results indicate that the aircraft encountered a strong downflow that exceeded 40ft/s along with a headwind-to-tailwind change that exceeded 100 ft/s. The outflow near the ground was accompanied by large, rapid changes in vertical wind, consistent with the presence of imbedded vortices. Although rain was present in the "downburst," the analysis showed no evidence of rain causing a loss in aircraft performance. © 1989 American Institute of Aeronautics and Astronautics, Inc.

关键词： flight data Radar Tracking ATC Aircraft Performance Delta Airlines Vortices Airliner Lift Coefficient digital flight data recorder True Airspeed

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Intelligent flight Control Systems Evaluation for Loss-of-Control Recovery and Prevention

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2017年第4期40卷 890-904页

作者： Smaili, M. H. Breeman, J. Lombaerts, T. J. J. Mulder, J. A. Chu, Q. P. Stroosma, O. NLR Netherlands Aerosp Ctr Aerosp Operat Cockpit & Flight Operat POB 90502 NL-1006 BM Amsterdam Netherlands NLR Netherlands Aerosp Ctr Aerospace Syst Aircraft Syst POB 90502 NL-1006 BM Amsterdam Netherlands NASA Ames Res Ctr Mail Stop 269-1 Moffett Field CA 94035 USA Delft Univ Technol Control & Simulat Div Fac Aerosp Engn POB 5058 NL-2600 GB Delft Netherlands

Recent developments in the field of loss-of-control recovery and prevention included improved pilot training, cockpit automation, and fault-tolerant control. The flight Mechanics Action Group on Fault-Tolerant Control of the Group for Aeronautical Research and Technology in Europe demonstrated the advantages of fault-tolerant "intelligent," flight control systems. The research enabled the improvement of the technology readiness level of these systems by evaluating one of them in realistic operational scenarios. The handling qualities results of a piloted flight simulator assessment with a damaged aircraft model showed that an online physical model identification approach contributed to improved pilot performance following potentially catastrophic structural and flight critical system failures. After the failures and subsequent control reconfiguration by the intelligent flight control system, airline and engineering test pilots experienced no difficulties in conducting a safe approach and landing.

关键词： Intelligent flight Control System Test Pilots Handling Qualities Aircraft Configurations Adaptive Control Algorithm Full flight Simulator flight Trajectory Technology Readiness Level Fly By Wire Control Systems digital flight data recorder

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Aircraft Performance Model Calibration and Validation for General Aviation Safety Analysis

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JOURNAL OF AIRCRAFT 2020年第4期57卷 678-688页

作者： Puranik, Tejas Harrison, Evan Chakraborty, Imon Mavris, Dimitri Georgia Inst Technol Aerosp Syst Design Lab Daniel Guggenheim Sch Aerosp Engn Atlanta GA 30332 USA Auburn Univ Sch Aerosp Engn Auburn AL 36849 USA Georgia Inst Technol Atlanta GA 30332 USA

Performance models facilitate a wide range of safety analyses in aviation. In an ideal scenario, the performance models would show inherently good agreement with the true performance of the aircraft. However, in reality, this is rarely the case: either owing to underlying simplifications or due to the limited fidelity of applicable tools or data. In such cases, calibration is required to fine-tune the behavior of the performance models. For point-mass steady-state performance models, challenges arise due to the fact that there is no obvious, unique metric or flight condition at which to assess the accuracy of the model predictions, as well as because a large number of model parameters may potentially influence model accuracy. This work presents a two-level approach to aircraft performance model calibration. The first level consists of using manufacturer-developed performance manuals for calibration, whereas the second level provides additional refinement when flight data are available. The performance models considered in this work consist of aerodynamic and propulsion models (performance curves) that are capable of predicting the nondimensional lift, drag, thrust, and torque at any given point in time. The framework is demonstrated on two representative general aviation aircraft. The demonstrated approach results in models that can predict critical energy-based safety metrics with improved accuracy for use in retrospective safety analyses.

关键词： Aircraft Performance General Aviation flight data Aviation Pilots Operating Handbook Aerodynamic Characteristics Cessna digital flight data recorder Total Energy Energy Management System

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Identification of Instantaneous Anomalies in General Aviation Operations Using Energy Metrics

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JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2020年第1期17卷 51-65页

作者： Puranik, Tejas G. Mavris, Dimitri N. Georgia Inst Technol Atlanta GA 30332 USA Daniel Guggenheim Sch Aerosp Engn Aerosp Syst Design Lab Atlanta GA 30332 USA Daniel Guggenheim Sch Aerosp Engn Atlanta GA USA

The quantification and improvement of safety is one of the most important objectives among the general aviation community. In recent years, machine learning techniques have emerged as an important enabler in the data-driven safety enhancement of aviation operations, with a number of techniques being applied to flight data to identify and isolate anomalous (and potentially unsafe) operations. Energy-based metrics provide measurable indications of the energy state of the aircraft and can be viewed as an objective currency to evaluate various safety-critical conditions across a heterogeneous fleet of aircraft and operations. In this paper, a novel method of identifying instantaneous anomalies for retrospective safety analysis in general aviation using energy-based metrics is proposed. Each flight data record is processed by a sliding window across the multivariate time series of evaluated metrics. A Gaussian mixture model using energy metrics and their variability within each window is fit in order to predict the probability of any instant during the flight being nominal. Instances during flights that deviate from the nominal are isolated to identify potential increased levels of risk. The identified anomalies are compared with traditional methods of safety assessment, such as exceedance detection to highlight the benefits of the developed method. The methodology is demonstrated using flight data records from two representative aircraft for critical phases of flight.

关键词： General Aviation flight data Gaussian Mixture Models Air Travel Aircraft Operations Critical Phases of flight data Mining Techniques Experimental Aircraft digital flight data recorder flight Record

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IDENTIFICATION OF VORTEX-INDUCED CLEAR AIR TURBULENCE USING AIRLINE flight RECORDS

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JOURNAL OF AIRCRAFT 1985年第2期22卷 124-129页

作者： PARKS, EK WINGROVE, RC BACH, RE MEHTA, RS University of Arizona Tucson Arizona NASA Ames Research Center Moffett Field California

The nature and cause of clear-air turbulence is being investigated in cooperation with the National Transportation Safety Board, using the flight records available from airline encounters with severe turbulence. This paper presents two case studies of severe turbulence which indicate that the airplanes involved encountered vortex arrays which were generated by destabilized wind-shear layers near the tropopause. In order to identify and analyze vortex patterns (i.e., vortex strength, size, and spacings), potential-flow models of vortex arrays were developed that describe reasonably well the wind patterns derived from the airliner flight records. The results of this analysis indicate that in the two cases studied, the vortex cores had diameters in the range of 900 to 1200 ft with tangential velocities in the range of 70 to 85 ft/s. This study presents the first identification and analysis of vortex arrays from airline flight data. The results are compared with theoretical predictions and previous observations. © 1985 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

关键词： Vortex Modeling Clear Air Turbulence Shear Layers Aeroplane Kelvin Helmholtz Instability digital flight data recorder True Airspeed Stratosphere Radar data Angle of Attack

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ROBUST flight RECONSTRUCTION FOR HELICOPTER SIMULATION AND TRAINING

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JOURNAL OF AIRCRAFT 1992年第3期29卷 421-428页

作者： KRISHNAKUMAR, K PRASANTH, RK BAILEY, JE University of Alabama Tuscaloosa Alabama 35487

The concept of using flight-recorded data for training via real-time simulator playback of flight maneuvers is introduced, and the requirements and technical methodology for simulator-based flight reconstruction are discussed. A robust Kalman filter design, which includes parametric uncertainties modeled as multiplicative white noise processes, is utilized as a state estimator flight simulator driver. Actual robust Kalman filter implementation utilizes a UH-60 helicopter nonlinear simulation (piecewise linear aerodynamics) for state propagation to facilitate easy transition between flight reconstruction and manual simulation. This robust technique is compared to the traditional linearized extended Kalman filter approach. Resulting flight data reconstruction system simulation, using computer-generated data and flight test data, demonstrates the flight payback insensitivity to helicopter model parameter changes. The study results indicate superior performance of the robust Kalman filter approach for the flight reconstruction for flight simulation (FRFFS) problem.

关键词： Helicopters Extended Kalman Filter digital flight data recorder Heading Angle Aircraft Training Mathematical Models Airspeed Linear Time Invariant System White Noise Aerodynamic Coefficients

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Wingrove parameter: A new turbulence metric

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JOURNAL OF AIRCRAFT 1996年第2期33卷 363-368页

作者： Chan, W Lester, PF Bach, RE San Jose State University San Jose California 95192 NASA Ames Research Center Moffett Field California 94035

This article discusses the development of a real-time turbulence metric called the Wingrove parameter. This metric is proportional to the turbulent kinetic energy of the vertical wind. It is computed from digital flight data recorder information after the application of a numerical filter to eliminate gust scales that do not contribute to aircraft turbulence. Preliminary results from this study show that the Wingrove parameter is able to eliminate long nonturbulent wave motions and to distinguish true atmospheric turbulence from maneuvering. There are some averaging problems because of the intermittent nature of turbulence events, and some simple procedures for eliminating them are presented. From these preliminary results it is concluded that the Wingrove parameter provides a substantial foundation for the development of a standardized, quantitative, real-time turbulence metric.

关键词： Atmospheric Turbulence digital flight data recorder Kinetic Energy Airliner Clear Air Turbulence Aircraft Tracking True Airspeed flight Attendant Power Spectral Density Shear Layers

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MODELING CLEAR-AIR TURBULENCE WITH VORTICES USING PARAMETER-IDENTIFICATION TECHNIQUES

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1987年第1期10卷 27-31页

作者： MEHTA, RS NASA Ames Research Center Moffett Field California

A vortex model of winds associated with clear-air turbulence is shown to be useful for characterizing actual airline encounters with severe turbulence. The model consists of an array of vortices with solid-body cores embedded in a potential flowfield. Parameters such as the size and strength of the vortices and their locations are identified using a modified Newton-Raphson algorithm. A manual identification startup scheme is used to minimize errors in the initial parameter estimates, and the identification algorithm is found to be robust in regard to the remaining errors. The analysis of a turbulence experience involving a commercial airliner demonstrates the success of the model and estimation procedure. The analysis finds vortices with core diameters of 1000 ft and tangential velocities of 87 ft/s in this encounter.

关键词： Vortex Modeling Clear Air Turbulence Airliner Commercial Aircraft Shear Layers digital flight data recorder ATC National Transportation Safety Board Kelvin Helmholtz Instability True Airspeed

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