Pilot Visual Behavior as a Function of Navigation and Flight Control Modes in the Boeing 757/767

1982 ◽  
Vol 26 (5) ◽  
pp. 441-445 ◽  
Author(s):  
Richard E. Edwards ◽  
Philip Tolin ◽  
Gordon L. Jonsen
Keyword(s):  
Flight Control ◽  
Control Mode ◽  
Pictorial Representation ◽  
Visual Behavior ◽  
Electronic Map ◽  
Coupled Mode ◽  
Navigation Mode ◽  
The Impact ◽  
Scan Pattern ◽  
Manual Mode

This report presents data obtained from two line-oriented simulations conducted in the Boeing 757/767 simulators. The purpose of these simulations was to assess the impact of two navigation- and two flight control modes on pilot visual behavior during an entire flight, from takeoff to touchdown. The two navigation modes were the traditional VOR mode, in which a compass rose was presented on the HSI, and the MAP mode, in which a pictorial representation of the airplane's flight path was presented on the HSI. The flight control modes were manual and coupled flight. The results indicated that: (a) the electronic map did not alter the basic “T” scan pattern, (b) the pilots' basic scan pattern did not differ in the two navigation modes when flying manually, (c) pilot scan patterns did vary as a function of flight control condition, with the basic “T” scan pattern accurately characterizing pilot visual behavior in the manual mode but not in the coupled mode, (d) several visual performance measures were sensitive to changes in flight phase, navigation mode, and flight control mode, and (e) no differences in pilot scan patterns were observed between an EICAS- equipped cockpit and a cockpit with conventional engine instruments.

Automation Surprise

2017 ◽  
Vol 7 (1) ◽  
pp. 28-41 ◽  
Author(s):  
Robert J. de Boer ◽  
Karel Hurts
Keyword(s):  
Flight Control ◽  
Representative Sample ◽  
Aviation Safety ◽  
Control Mode ◽  
Cognitive Errors ◽  
Laboratory Studies ◽  
Airline Pilots ◽  
Flight Operations ◽  
Widespread Phenomenon ◽  
Few Data

Abstract. Automation surprise (AS) has often been associated with aviation safety incidents. Although numerous laboratory studies have been conducted, few data are available from routine flight operations. A survey among a representative sample of 200 Dutch airline pilots was used to determine the prevalence of AS and the severity of its consequences, and to test some of the factors leading to AS. Results show that AS is a relatively widespread phenomenon that occurs three times per year per pilot on average but rarely has serious consequences. In less than 10% of the AS cases that were reviewed, an undesired aircraft state was induced. Reportable occurrences are estimated to occur only once every 1–3 years per pilot. Factors leading to a higher prevalence of AS include less flying experience, increasing complexity of the flight control mode, and flight duty periods of over 8 hr. It is concluded that AS is a manifestation of system and interface complexity rather than cognitive errors.

Comparative crosstalk performance analysis of different configurations of heterogeneous multicore fiber

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Umar Farooque ◽  
Rakesh Ranjan
Keyword(s):  
Refractive Index ◽  
Mode Coupling ◽  
The Other ◽  
Heterogeneous Multicore ◽  
Coupled Mode ◽  
The Core ◽  
Bending Radius ◽  
Multicore Fiber ◽  
The Impact ◽  
Core Pitch

AbstractIn order to select the heterogeneous multicore fiber (MCF) configuration with ultra-low crosstalk and low peak bending radius, comparative crosstalk analysis have been done for the three possible core configurations, namely, Configuration 1 - different refractive index (R.I.) and different radius, Configuration 2 - different R.I., and Configuration 3 - different radius. Using the coupled mode equation and the simplified expressions of mode coupling coefficient (MCC) for different configurations of heterogeneous cores, the crosstalk performance of all the heterogeneous MCF configurations along with the homogeneous MCF have been investigated analytically with respect to core pitch (D) and fiber bending radius (${R}_{b}$). Further, these expressions of MCC have been extended to obtain the simplified expressions of MCC for the estimation of crosstalk levels in respective trench-assisted (TA) heterogeneous MCF configurations. It is observed from the analysis that in Configuration 1, crosstalk level is lowest and the rate of decrease in the crosstalk with respect to the core pitch is highest compared to the other configurations of heterogeneous MCF. The values of crosstalk obtained analytically have been validated by comparing it with the values obtained from finite element method (FEM) based numerical simulation results. Further, we have investigated the impact of a fixed percent change (5%) in the core parameters (radius and/or R.I.) of one of the core of a homogeneous MCF, to realize the different heterogeneous MCF configurations, on the variations in crosstalk levels, difference in the mode effective refractive index of the core 1 and core 2 ($\Delta {n}_{eff}={n}_{eff1}-{n}_{eff2}$), and the peak bending radius (${R}_{pk}$). For the same percent variations (5%) in the core parameters (radius and/or R.I.) of different configurations of cores (Config. 1-Config. 3), Config. 1 MCF has highest variation in $\Delta {n}_{eff}$ value compared to other configurations of MCF. Further, this highest variation in $\Delta {n}_{eff}$ value of Config. 1 MCF results in smallest peak bending radius. The smaller value of peak bending radius allows MCF to bend into smaller radius. Therefore, Configuration 1 is the potential choice for the design of MCF with smaller peak bending radius and ultra-low crosstalk level compared to the other configurations of SI-heterogeneous MCF.

scholarly journals Assessment of the perceived burden associated with Malignant Melanoma with Pictorial Representation of Illness and Self Measure (PRISM) and Melanoma Concerns Questionnaire (MCQ-28)

2022 ◽  
Author(s):  
Alessandro Borghi ◽  
Maria Elena Flacco ◽  
Alberto Monti ◽  
Lucrezia Pacetti ◽  
Michela Tabanelli ◽  
...  
Keyword(s):  
Malignant Melanoma ◽  
Well Being ◽  
Cross Sectional Study ◽  
Pictorial Representation ◽  
Cross Sectional ◽  
Prism Score ◽  
Related Data ◽  
Perceived Burden ◽  
Study Population ◽  
The Impact

Abstract Purpose The impact of malignant melanoma (MM) on patients’ psychophysical well-being has been poorly addressed. We aimed to assess the perceived burden in patients with a diagnosis of MM, using two different tools, one generic and one specific for MM, such as Pictorial Representation of Illness and Self Measure (PRISM) and Melanoma Concerns Questionnaire (MCQ-28), respectively. The correlation between PRISM and MCQ-28 subscales and the relevance of disease and patient-related variables were also investigated. Methods This single-centre, cross-sectional study included all adult consecutive MM patients who attended our Dermatology Unit from December 2020 to June 2021. Demographics and disease-related data were recorded. PRISM and MCQ-28 were administered. Results One hundred and seventy-one patients were included (mean age: 59.5 ±14.9 years.; 48.0% males). Median time from MM diagnosis to inclusion was 36 months. Nearly 80% of the patients had in situ or stage I MM. Overall, 22.2% of the patients reported a PRISM score <100mm and similar percentages provided scores indicating impaired quality of life, as assessed with MCQ-28 subscales. A weak, albeit significant, correlation was found between PRISM scores and ACP, CON and SOC2 subscales. The most relevant association found was that between lower PRISM scores and higher-stage MM. Conclusions In the study population, mostly affected with superficial MM, their perception of the burden associated with MM did not appear either particularly dramatic or disabling. PRISM seems a reliable system for capturing and quantifying the domains correlated with the emotive dimension of MM, especially MM-related concerns and willingness to face life

Algorithmic support of low-altitude aircraft flight based on the hazard analysis of the flight situation

2021 ◽  
Author(s):  
V.A. Malyshev ◽  
A.S. Leontyev ◽  
S.P. Poluektov ◽  
Е.М. Volotov
Keyword(s):  
Adaptive Control ◽  
Flight Control ◽  
Control Algorithm ◽  
Hazard Analysis ◽  
Critical Value ◽  
Control Mode ◽  
Manual Control ◽  
Flight Safety ◽  
Low Altitude ◽  
Adaptive Control Algorithm

Low-altitude flight of an aircraft is an effective, but at the same time, a very complex tactical technique, during which the crew does not always have the opportunity to timely recognize the occurrence of an abnormal case, determine the way out of it and counteract an aviation accident development. Despite many advantages of the automatic mode of low-altitude flight performing, its practical implementation is associated with a number of features and disadvantages, which determined the preference for the manual mode of low-altitude flight control. These are the presence of telltale factors, limited ability of performing flights at night and in difficult weather conditions, insufficient reliability etc. The considered features determined the relevance of the of low-altitude flight safety ensuring problem in relation to the manual control mode. As a result of an experimental study of the low-altitude flight performing process in a manual control mode, it was found that when performing manually-controlled low-altitude flight, a hazard assessment of the flight situation becomes pivotal. However the crew being under such conditions is not always able to correctly assess the flight situation hazard due to a combination of objective reasons. The current state of the adaptive and on-board flight safety systems theory makes it possible to increase the safety of the manuallycontrolled low-altitude flight by using adaptive control algorithms based on the flight situation hazard assessment. To solve this problem an adaptive control algorithm is proposed that ensures the formation of a security corridor in the longitudinal control channel, where the upper limit is determined by the critical value of the aircraft detection hazard, and the lower limit is determined by the critical value of the error in maintaining a given flight altitude. For a continuous assessment of the flight situation hazard and the timely formation of control signals the complex information about the current true flight altitude and the foreground is needed. Taking into account the peculiarities of low-altitude flight a digital terrain map containing data on natural and artificial obstacles along the flight route is a more rational source of information, that will make it possible to predict the development of the flight situation hazard. The above reasoning makes it possible to form an aircraft low-altitude flight adaptive control algorithm. A distinctive feature of the proposed algorithm is the implementation of a combined control variety where the pilot is provided with ample manual control opportunities within the security corridor, and the automatic flight control system is assigned the role of a safety subsystem that ensures control and timely return of the flight situation to normal flight conditions. The presented algorithm will allow to increase the crew logical-analytical activity information support during continuous analysis of the existing flight situation due to the formation of protective control actions based on the current flight situation hazard analysis.

Sensitivity of automatic control of emergency manoeuvre to parametric uncertainty of the airplane model

2019 ◽  
Vol 91 (3) ◽  
pp. 407-419
Author(s):  
Jerzy Graffstein ◽  
Piotr Maslowski
Keyword(s):  
Control System ◽  
Automatic Control ◽  
Flight Control ◽  
Parametric Uncertainty ◽  
Second Phase ◽  
Flight Control System ◽  
Content Type ◽  
Control Quality ◽  
Wide Range ◽  
The Impact

Purpose The main purpose of this work was elaboration and verification of a method of assessing the sensitivity of automatic control laws to parametric uncertainty of an airplane’s mathematical model. The linear quadratic regulator (LQR) methodology was used as an example design procedure for the automatic control of an emergency manoeuvre. Such a manoeuvre is assumed to be pre-designed for the selected airplane. Design/methodology/approach The presented method of investigating the control systems’ sensitivity comprises two main phases. The first one consists in computation of the largest variations of gain factors, defined as differences between their nominal values (defined for the assumed model) and the values obtained for the assumed range of parametric uncertainty. The second phase focuses on investigating the impact of the variations of these factors on the behaviour of automatic control in the manoeuvre considered. Findings The results obtained allow for a robustness assessment of automatic control based on an LQR design. Similar procedures can be used to assess in automatic control arrived at through varying design methods (including methods other than LQR) used to control various manoeuvres in a wide range of flight conditions. Practical implications It is expected that the presented methodology will contribute to improvement of automatic flight control quality. Moreover, such methods should reduce the costs of the mathematical nonlinear model of an airplane through determining the necessary accuracy of the model identification process, needed for assuring the assumed control quality. Originality/value The presented method allows for the investigation of the impact of the parametric uncertainty of the airplane’s model on the variations of the gain-factors of an automatic flight control system. This also allows for the observation of the effects of such variations on the course of the selected manoeuvre or phase of flight. This might be a useful tool for the design of crucial elements of an automatic flight control system.

scholarly journals Implementation, mechanisms of impact and key contextual factors involved in outcomes of the Modification of Diet, Exercise and Lifestyle (MODEL) randomised controlled trial in Australian adults: protocol for a mixed-method process evaluation

BMJ Open ◽  
2020 ◽  
Vol 10 (11) ◽  
pp. e036395
Author(s):  
Reindolf Anokye ◽  
Simone Radavelli-Bagatini ◽  
Catherine P Bondonno ◽  
Marc Sim ◽  
Lauren C Blekkenhorst ◽  
...  
Keyword(s):  
Process Evaluation ◽  
Mixed Method ◽  
Controlled Trial ◽  
Behavioural Change ◽  
Implementation Strategies ◽  
Pictorial Representation ◽  
Model Study ◽  
Study Results ◽  
Qualitative Component ◽  
The Impact

IntroductionThe Modification of Diet, Exercise and Lifestyle (MODEL) study aims to examine the impact of providing visualisation and pictorial representation of advanced structural vascular disease (abdominal aortic calcification), on ‘healthful’ improvements to diet and lifestyle. This paper reports the protocol for the process evaluation for the MODEL study.Methods and analysisThe overall aim of the process evaluation is to understand the processes that took place during participation in the MODEL study trial and which elements were effective or ineffective for influencing ‘healthful’ behavioural change, and possible ways of improvement to inform wider implementation strategies. A mixed-method approach will be employed with the use of structured questionnaires and semistructured in-depth interviews. All 200 participants enrolled in the trial will undertake the quantitative component of the study and maximum variation sampling will be used to select a subsample for the qualitative component. The sample size for the qualitative component will be determined based on analytical saturation. Interviews will be digitally recorded and transcribed verbatim. Qualitative data will be analysed thematically and reported according to the Consolidated Criteria for Reporting Qualitative Research (COREQ) guidelines.Ethics and disseminationThe MODEL study process evaluation has received approval from Edith Cowan University Human Research Ethics Committee (Project Number: 20513 HODGSON). Written informed consent will be obtained from all participants before they are included in the study. The study results will be shared with the individuals and institutions associated with this study as well as academic audiences through peer-reviewed publication and probable presentation at conferences.Trial registration numberACTRN12618001087246.

scholarly journals Identification of In-Flight Wingtip Folding Effects on the Roll Characteristics of a Flexible Aircraft

Aerospace ◽  
2019 ◽  
Vol 6 (6) ◽  
pp. 63 ◽  
Author(s):  
Gaétan Dussart ◽  
Sezsy Yusuf ◽  
Mudassir Lone
Keyword(s):  
Time Domain ◽  
Flight Control ◽  
Dynamic Models ◽  
Direct Connection ◽  
Reduced Order ◽  
Transport Aircraft ◽  
Flight Simulators ◽  
Induced Drag ◽  
Generic Polynomial ◽  
The Impact

Wingtip folding is a means by which an aircraft’s wingspan can be extended, allowing designers to take advantage of the associated reduction in induced drag. This type of device can provide other benefits if used in flight, such as flight control and load alleviation. In this paper, the authors present a method to develop reduced order flight dynamic models for in-flight wingtip folding, which are suitable for implementation in real-time pilot-in-the-loop simulations. Aspects such as the impact of wingtip size and folding angle on aircraft roll dynamics are investigated along with failure scenarios using a time domain aeroservoelastic framework and an established system identification method. The process discussed in this paper helps remove the need for direct connection of complex physics based models to engineering flight simulators and the need for tedious programming of large look-up-tables in simulators. Instead, it has been shown that a generic polynomial model for roll aeroderivatives can be used in small roll perturbation conditions to simulate the roll characteristics of an aerodynamic derivative based large transport aircraft equipped with varying fold hinge lines and tip deflections. Moreover, the effects of wing flexibility are also considered.

A Manipulator for Medical Applications: Design and Control

2010 ◽  
Vol 4 (4) ◽  
Author(s):  
Basem Fayez Yousef ◽  
Rajni V. Patel ◽  
Mehrdad Moallem
Keyword(s):  
Control Mode ◽  
Robot Arm ◽  
Medical Interventions ◽  
Surgical Tools ◽  
Workspace Analysis ◽  
Robot Performance ◽  
Safety Features ◽  
Lock In ◽  
And Control ◽  
Manual Mode

An actuated robot arm is designed for use as a gross positioning macro-manipulator that can carry, appropriately orient, precisely position, and firmly “lock” in place different types of micro-robots and surgical tools necessary for applications in minimally invasive therapy. With a simple manipulation protocol, the clinician can easily operate the robot in manual mode. A remote control mode can also be enabled for teleoperation of the robot. The robot’s normally locked braking system and the simple quick-release joint enhance its safety features for emergencies and power shutdown. Robot workspace analysis showed that the singularity regions are outside the usable work envelope of the robot. Performance analysis showed that the robot operates with an average displacement accuracy of 0.58 mm and a roll, pitch, and yaw angular accuracies of 0.26 deg, 0.26 deg, and 0.38 deg, respectively. The sophisticated configuration and joint architecture of the arm enable it to perform and interact efficiently with the constrained and limited workspace of surgical environments. The special features of the proposed robot make it well suited for use with new surgical tools and micro-robots for a range of medical interventions.

Relative Performance of a TGS for the Assay of Drummed Waste as Function of Collimator Opening

2007 ◽  
Author(s):  
S. C. Kane ◽  
S. Croft ◽  
P. McClay ◽  
R. Venkataraman ◽  
M. F. Villani
Keyword(s):  
Dynamic Range ◽  
Photon Emission ◽  
High Energy ◽  
General Purpose ◽  
Nuclear Industry ◽  
High Energy Resolution ◽  
Waste Forms ◽  
Trade Offs ◽  
The Impact ◽  
Scan Pattern

Improving the safety, accuracy and overall cost effectiveness of the processes and methods used to characterize and handle radioactive waste is an on-going mission for the nuclear industry. An important contributor to this goal is the development of superior non-destructive assay instruments. The Tomographic Gamma Scanner (TGS) is a case in point. The TGS applies low spatial resolution experimental computed tomograghy (CT) linear attenuation coefficient maps with three-dimensional high-energy resolution single photon emission reconstructions. The results are presented as quantitative matrix attenuation corrected images and assay values for gamma-emitting radionuclides. Depending on a number of operational factors, this extends the diversity of waste forms that can be assayed, to a given accuracy, to items containing more heterogeneous matrix distributions and less uniform emission activity distributions. Recent advances have significantly extended the capability to a broader range of matrix density and to a wider dynamic range of surface dose rate. Automated systems sense the operational conditions, including the container type, and configure themselves accordingly. The TGS also provides a flexible data acquisition platform and can be used to perform far-field style measurements, classical segmented gamma scanner measurements, or to implement hybrid methods, such as reconstructions that use a priori knowledge to constrain the image reconstruction or the underlying energy dependence of the attenuation. A single, yet flexible, general purpose instrument of this kind adds several tiers of strategic and tactical value to facilities challenged by a diverse and difficult to assay waste streams. The TGS is still in the early phase of industrial uptake. There are only a small number of general purpose TGS systems operating worldwide, most being configured to automatically select between a few configurations appropriate for routine operations. For special investigations, one may wish to widen the repertoire but there is currently little guidance as to the trade-offs involved. In this work, we address this weakness by studying the performance of a typical TGS arrangement as a function of collimator opening, scan pattern and scan time for a representative selection of simulated waste forms. Our focus is on assessing the impact on the precision and accuracy of the quantitative assay result but we also report the utility of the imaging information in confirming acceptable knowledge about the packages.

Range Prediction and Trajectory Correction of Long Range Rocket with Attitude Stabilization

2012 ◽  
Vol 232 ◽  
pp. 299-304
Author(s):  
Ke Yong Li ◽  
Fen Fen Xiong ◽  
Cheng Zhang ◽  
Shi Shi Chen
Keyword(s):  
Long Range ◽  
Prediction Method ◽  
Longitudinal Direction ◽  
Control Mode ◽  
Attitude Stabilization ◽  
Large Dispersion ◽  
Range Correction ◽  
And Control ◽  
Range Error ◽  
The Impact

The dispersion of long range rocket is significantly suppressed by the attitude stabilization in the boost phase. However, the attitude stabilization system cannot govern the propellant impulse error and mass error, which induces large dispersion in the longitudinal direction. Therefore, it is necessary to conduct range correction in the post-boost phase of flight trajectory. A range prediction method based on the elliptic ballistic theory is proposed in this paper. Elliptic ballistic equations and range estimation equations are derived and the modified range prediction method with correction factor is presented. It is verified that the proposed method can predict the residual flight range accurately. After that, the lateral pulse jets control is presented and utilized to correct the trajectory and eliminate the range error. A unique control law is reported that combines elliptic ballistic theory and control mode for lateral pulse jets. The impact point is directly controlled and rocket dispersion in the longitudinal direction is efficiently reduced.

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