28 results on '"Jump, Michael"'
Search Results
2. Prospective sky guides : developing future pilot vision aids
- Author
-
Jump, Michael
- Subjects
629.13 - Abstract
Airline transport operations are carried out in a wide range of visual and instrument meteorological conditions. For all but the most limiting of degraded visibility situations, the pilot can choose to fly the approach to the airfield and land the aircraft manually. S/he does this using the visual cues available through the cockpit windshield. The answer to the question - how is this achieved may seem rather obvious, but has actually challenged researchers for some time. The optical flow theory of visual perception offers solutions in terms of the way pilots pick up motion from the environment in which they move. In a relatively recent incarnation, flow theory transforms motion into the temporal, time-to-contact parameter, τ, defined as the time to close the motion gap to a surface or object at the instantaneous closure rate. This thesis reports on the development of novel display formats, using τ theory as a basis, for the fixed wing jet transport approach and landing manoeuvres. A simulation model of a generic large jet transport aircraft is constructed and a number of repeatable flight test manoeuvres developed. Using these as a start point, a number of flight test trials are conducted. The first two of these is to establish whether or not coherent τ-based relationships exist for a series of motion gaps identified for each flight test manoeuvre. Here, it is discovered that for the localiser capture, glide slope capture and flare manoeuvre, pilots use constant rate of change of τ (τ̇) guidance strategies to close the motion gaps of interest. The use of such strategies is consistent with the pilots coupling onto the τ-guides that τ theory postulates. This result is consistent with previous work conducted using rotary wing aircraft. Based upon the results obtained, a number of concept displays are developed. First, a two-dimensional lead aircraft concept is developed. Here, the pilot must overlay a prediction of the aircraft position at some near-future time with that of the desired position. Speed cueing is provided by the lead aircraft 'looming' if there is a difference between desired and actual airspeed. Second, a flare command display is developed. It provides a commanded flight path angle to achieve a desired τ̇ of height. Again, the pilot must overlay the actual aircraft flight path with desired. In order that these display designs could be finalised, the values of a number of parameters had to be established. A display development trial was conducted for this purpose. The specific values of interest and their final values were: optimum look-ahead time for a lead aircraft to guide the pilot along a given trajectory was found to be 2 seconds; for the localiser capture manoeuvre, the gap closure τ̇ was set at 0.6 and the gap closure duration fixed at 10 seconds; for the glide slope capture manoeuvre the gap closure τ̇ was also set at 0.6 and the duration at 5 seconds; for the flare command display, the τ̇ commanded was 0.75 and the initiation τ at 3.5 seconds. The novel display formats were tested by comparing them with a conventional head-down primary flight display, a 'state-of-the-art' head up display and a highway-in-the-sky concept. The comparison was performed using objective measurement of actual and desired trajectories and subjective measurement using the NASA display flyability rating scale and the Bedford workload scale. During this testing, the looming cue was found to be insufficient for the purposes of accurate speed control. However, the lead aircraft concept is shown to provide superior trajectory tracking over the alternative display formats in both good and degraded visual environments. The improved performance comes at the expense of slightly higher pilot-perceived workload. The τ-based flare command display is shown to provide landing touchdown performance as least as good as a current state-of-the-art head-up display in both good and degraded visual environments. Based upon the design process followed and the results obtained, a number of conclusions are drawn. The most important is that τ-based motion gap closure strategies are a fundamental means by which pilots guide aircraft through the environment. As such, the future display designers should incorporate the methods and approach discussed in this thesis.
- Published
- 2007
- Full Text
- View/download PDF
3. Tau Theory-Based Flare Control in Autonomous Helicopter Autorotation.
- Author
-
Saetti, Umberto, Rogers, Jonathan, Alam, Mushfiqul, and Jump, Michael
- Subjects
ROTORCRAFT ,HELICOPTERS ,AUTOMATIC control systems ,AIR travel ,COMPUTER simulation ,ALTITUDES - Abstract
A novel trajectory generation and control architecture for fully autonomous autorotative flare that combines rapid path generation with model-based control is proposed. The trajectory generation component uses optical Tau theory to compute flare trajectories for both longitudinal and vertical speed. These flare trajectories are tracked using a nonlinear dynamic inversion (NDI) control law. One convenient feature of NDI is that it inverts the plant model in its feedback linearization loop, which eliminates the need for gain scheduling. However, the plant model used for feedback linearization still needs to be scheduled with the flight condition. This key aspect is leveraged to derive a control law that is scheduled with linearized models of the rotorcraft flight dynamics obtained in steady-state autorotation, while relying on a single set of gains. Computer simulations are used to demonstrate that the NDI control law is able to successfully execute autorotative flare in the UH-60 aircraft. Autonomous flare trajectories are compared to piloted simulation data to assess similarities and discrepancies between piloted and automatic control approaches. Trade studies examine which combinations of downrange distances and altitudes at flare initiation result in successful autorotative landings. [ABSTRACT FROM AUTHOR]
- Published
- 2024
- Full Text
- View/download PDF
4. Towards the development of a flight training programme for future personal aerial vehicle users
- Author
-
Perfect, Philip, Jump, Michael, and White, Mark D.
- Published
- 2017
- Full Text
- View/download PDF
5. Dynamic Inversion-Based Flare Control Law for Autonomous Helicopter Autorotation
- Author
-
Saetti, Umberto, Rogers, Jonathan, Alam, Mushfiqul, Cameron, Neil, and Jump, Michael
- Abstract
A novel trajectory generation and control architecture for fully autonomous autorotative flare is proposed that combines rapid path generation with model-based control. The trajectory generation component uses optical Tau theory to compute flare trajectories for both longitudinal and vertical vertical speed. These flare trajectories are tracked by a nonlinear dynamic inversion (NDI) control law. One convenient feature of NDI is that it inverts the plant model in its feedback linearization loop, which eliminates the need for gain scheduling. However, the plant model used for feedback linearization still needs to be scheduled with the flight condition. This key aspect is leveraged to derive a control law that is scheduled with linearized models of the rotorcraft flight dynamics obtained in steady-state autorotation while relying on a single set of gains. Computer simulations are used to demonstrate that the NDI control law is able to successfully execute autorotative flare in the UH-60 aircraft. Autonomous flare trajectories are compared to piloted simulation data to assess similarities and discrepancies between piloted and automatic control approaches. Trade studies examine which combinations of downrange distances and altitudes at flare initiation result in successful autorotative landings.
- Published
- 2022
6. A closed loop experiment of collective bounce aeroelastic Rotorcraft–Pilot Coupling
- Author
-
Masarati, Pierangelo, Quaranta, Giuseppe, Lu, Linghai, and Jump, Michael
- Published
- 2014
- Full Text
- View/download PDF
7. Progress in the development of guidance strategies for the landing flare manoeuvre using tau‐based parameters
- Author
-
Jump, Michael and Padfield, Gareth D.
- Published
- 2006
- Full Text
- View/download PDF
8. A Method to Define a Scalable Turbulence Response Model for the Ship Helicopter Dynamic Interface
- Author
-
Fell, Thomas, Jump, Michael, White, Mark, Owen, ieaun, and Finlay, Bryan
- Published
- 2021
9. Can Time-To-Contact Be Used To Model A Helicopter Autorotation?
- Author
-
Alam, MM, Jump, Michael, and Cameron, Neil
- Published
- 2019
10. Surviving the Ship Airwake Towards a Scalable Turbulence Response Model For the Helicopter-Ship Dynamic Interface RAeS International Power Lift Conference
- Author
-
White, Mark D, Owen, Ieuan, Fell, Thomas, and Jump, Michael
- Published
- 2018
- Full Text
- View/download PDF
11. Predicting On-axis Rotorcraft Dynamic Responses Using Machine Learning Techniques.
- Author
-
Jackson, Ryan D., Jump, Michael, and Green, Peter L.
- Subjects
- *
MACHINE learning , *ROTORCRAFT , *GAUSSIAN processes , *AUTOREGRESSIVE models , *FORECASTING , *DATA reduction , *FLIGHT simulators - Abstract
Physical-law-based models are widely utilized in the aerospace industry. One such use is to provide flight dynamics models for use in flight simulators. For human-in-the-loop use, such simulators must run in real-time. Owing to the complex physics of rotorcraft flight, to meet this real-time requirement, simplifications to the underlying physics sometimes have to be applied to the model, leading to errors in the model's predictions of the real vehicle's response. This study investigated whether a machine-learning technique could be employed to provide rotorcraft dynamic response predictions. Machine learning was facilitated using a Gaussian process (GP) nonlinear autoregressive model, which predicted the on-axis pitch rate, roll rate, yaw rate, and heave responses of a Bo105 rotorcraft. A variational sparse GP model was then developed to reduce the computational cost of implementing the approach on large datasets. It was found that both of the GP models were able to provide accurate on-axis response predictions, particularly when the model input contained all four control inceptors and one lagged on-axis response term. The predictions made showed improvement compared to a corresponding physics-based model. The reduction of training data to one-third (rotational axes) or one-half (heave axis) resulted in only minor degradation of the sparse GP model predictions. [ABSTRACT FROM AUTHOR]
- Published
- 2020
- Full Text
- View/download PDF
12. Development of a Generic Time-to-Contact Pilot Guidance Model.
- Author
-
Linghai Lu, Jump, Michael, and Padfield, Gareth D.
- Subjects
AIR pilots ,DYNAMICAL systems ,SIMULATION methods & models - Abstract
The time-to-contact t theory posits that purposeful actions can be conducted by coupling the actor's motion onto the so-called τ guides generated internally by their central nervous system. Although significant advances have been made in the application of t for flight control purposes, little research has been conducted to investigate how pilots are able to adapt their τ-guidance strategy to different aircraft dynamics, or how a τ-guide-based pilot-aircraft model might be used to represent control behavior. This paper reports on the development of such a model to characterize the adaptation of pilot guidance to variations in aircraft dynamics using data obtained from a clinical pilot-in-the-loop flight simulation experiment. The results indicate that pilots tend to maintain a constant coupling between the dynamic system's motion and the r guide across a range of different configuration parameters. Simultaneously, the pilot modulates the guidance maneuver period to adapt to these different aircraft dynamics that result in changes in workload. Modeling the complete pilot stabilization and guidance function as a regulator plus inverter yields good comparative results between the pilot-aircraft model and simulator trajectory data, and it supports the hypothesis that the following r-based guidance strategies suppress an aircraft's natural dynamics. [ABSTRACT FROM AUTHOR]
- Published
- 2018
- Full Text
- View/download PDF
13. Development of Occupant-Preferred Landing Profiles for Personal Aerial Vehicles.
- Author
-
Linghai Lu, Jump, Michael, White, Mark, and Perfect, Philip
- Subjects
DRONE aircraft ,FLIGHT control systems ,AUTONOMOUS vehicles ,TRAJECTORY optimization ,AERODYNAMICS - Abstract
With recent increased interest in autonomous vehicles and the associated technology, the prospect of realizing a personal aerial vehicle seems closer than ever. However, there is likely to be a continued requirement for any occupant of an air vehicle to be comfortable with both the automated portions of the flight and their ability to take manual control as and when required. This paper, using the approach to landing as an example maneuver, examines what a comfortable trajectory for personal aerial vehicle occupants might look like. Based upon simulated flight data, a "natural" flight trajectory is designed and then compared to constant deceleration and constant optic flow descent profdes. It is found that personal aerial vehicle occupants with limited flight training and no artificial guidance follow the same longitudinal trajectory as has been found for professionally trained helicopter pilots. Further, the final stages of the approach to hover can be well described using the Tau theory. For automatic flight, personal aerial vehicle occupants prefer a constant deceleration profile. For approaches flown manually, the newly designed natural profile is preferred. [ABSTRACT FROM AUTHOR]
- Published
- 2016
- Full Text
- View/download PDF
14. Prediction and Simulator Verification of Roll/Lateral Adverse Aeroservoelastic Rotorcraft-Pilot Couplings.
- Author
-
Muscarello, Vincenzo, Quaranta, Giuseppe, Masarati, Pierangelo, Linghai Lu, Jones, Michael, and Jump, Michael
- Subjects
FLIGHT simulators ,AEROSERVOELASTICITY ,ROTORCRAFT ,AIR pilots ,FLIGHT testing - Abstract
The involuntary interaction of a pilot with an aircraft can be described as pilot-assisted oscillations. Such phenomena are usually only addressed late in the design process when they manifest themselves during ground/flight testing. Methods to be able to predict such phenomena as early as possible are therefore useful. This work describes a technique to predict the adverse aeroservoelastic rotorcraft-pilot couplings, specifically between a rotorcraft's roll motion and the resultant involuntary pilot lateral cyclic motion. By coupling linear vehicle aeroservoelastic models and experimentally identified pilot biodynamic models, pilot-assisted oscillations and no-pilot-assisted oscillation conditions have been numerically predicted for a soft-in-plane hingeless helicopter with a lightly damped regressive lead-lag mode that strongly interacts with the roll mode at a frequency within the biodynamic band of the pilots. These predictions have then been verified using real-time flight-simulation experiments. The absence of any similar adverse couplings experienced while using only rigid-body models in the flight simulator verified that the observed phenomena were indeed aeroelastic in nature. The excellent agreement between the numerical predictions and the observed experimental results indicates that the techniques developed in this paper can be used to highlight the proneness of new or existing designs to pilot-assisted oscillations. [ABSTRACT FROM AUTHOR]
- Published
- 2016
- Full Text
- View/download PDF
15. Handling Qualities Requirements for Future Personal Aerial Vehicles.
- Author
-
Perfect, Philip, Jump, Michael, and White, Mark D.
- Subjects
PRIVATE planes ,AIRPLANES ,AIRPLANE piloting ,AIR pilots' licenses ,ROTORCRAFT - Abstract
This paper describes research to develop handling qualities guidelines and criteria for a new category of aircraft: the personal aerial vehicle, which it is envisaged will demand no more skill to fly than that associated with driving a car today. Testing of concept personal aerial vehicle response types has been conducted with inexperienced "pilots" ranging from private pilot's license holders through to those with no prior flight experience. The objective was to identify, for varying levels of flying skill, the personal aerial vehicle response type requirements that will ensure safe and precise flight. Conventional rotorcraft response types such as "rate command", "attitude command/attitude hold" are unsuitable for likely personal aerial vehicle pilots. However, response types such as "translational rate command" and "acceleration command, speed hold" permit "flight-naive" pilots to perform demanding tasks repeatably and with the required precision. [ABSTRACT FROM AUTHOR]
- Published
- 2015
- Full Text
- View/download PDF
16. Methods to Assess the Handling Qualities Requirements for Personal Aerial Vehicles.
- Author
-
Perfect, Philip, Jump, Michael, and White, Mark D.
- Subjects
VERTICALLY rising aircraft ,AIRPLANE piloting ,ROTORCRAFT ,FLIGHT control systems ,MARITIME pilots - Abstract
This paper describes the development of a methodology to assess the handling qualities requirements for vertical takeoff and landing-capable personal aerial vehicles. It is anticipated that such a personal aerial vehicle would be flown by a "flight-naïve" pilot who has received much less training than is typically received even by today's general aviation private pilots. The methodology used to determine handling requirements for a personal aerial vehicle cannot therefore be based entirely on existing best practice; the use of highly experienced test pilots in a conventional handling assessment limits the degree to which results apply to the flight-naïve pilot. Using rotary-wing handling qualities methods as a start point, this paper describes both existing and newly developed alternative methods to subjectively and objectively analyze the performance and workload of flight-naïve pilots in typical personal aerial vehicle tasks. A highly reconfigurable generic flight dynamics simulation model that has been used to validate the methodology is also described. Results that highlight the efficacy of the various methods used are presented, and their suitability for use with flight-naïve pilots demonstrated. [ABSTRACT FROM AUTHOR]
- Published
- 2015
- Full Text
- View/download PDF
17. Practises to identify and prevent adverse aircraft-and-rotorcraft-pilot couplings—A ground simulator perspective.
- Author
-
Pavel, Marilena D., Jump, Michael, Masarati, Pierangelo, Zaichik, Larisa, Dang-Vu, Binh, Smaili, Hafid, Quaranta, Giuseppe, Stroosma, Olaf, Yilmaz, Deniz, Johnes, Michael, Gennaretti, Massimmo, and Ionita, Achim
- Subjects
- *
AIR pilots , *ROTORCRAFT , *FLIGHT simulators , *VISUAL culture , *AIRPLANE design - Abstract
The aviation community relies heavily on flight simulators as a fundamental tool for research, pilot training and development of any new aircraft design. The goal of the present paper is to provide a review on how effective ground simulation is as an assessment tool for unmasking adverse Aircraft-and-Rotorcraft Pilot Couplings (APC/RPC). Although it is generally believed that simulators are not reliable in revealing the existence of A/RPC tendencies, the paper demonstrates that a proper selection of high-gain tasks combined with appropriate motion and visual cueing can reveal negative features of a particular aircraft that may lead to A/RPC. The paper discusses new methods for real-time A/RPC detection that can be used as a tool for unmasking adverse A/RPC. Although flight simulators will not achieve the level of reality of in-flight testing, exposing A/RPC tendencies in the simulator may be the only convenient safe place to evaluate the wide range of conditions that could produce hazardous A/RPC events. [ABSTRACT FROM AUTHOR]
- Published
- 2015
- Full Text
- View/download PDF
18. New Methods to Subjectively and Objectively Evaluate Adverse Pilot Couplings.
- Author
-
Jones, Michael and Jump, Michael
- Subjects
- *
COUPLINGS (Gearing) , *GEARING machinery , *MACHINERY , *AEROSPACE industries , *HIGH technology industries - Abstract
Unmasking aircraft pilot couplings (APCs) prior to vehicle entry into service have been a long standing challenge in the aerospace industry. APCs, often only exposed through unpredictable or very specific circumstances, have arisen throughout the history of manned powered flight and have required stopgap "fixes" to ensure system safety once a problem has been identified. This paper describes two newly created novel tools, one objective and one subjective, to detect and analyze APCs. The Phase Aggression Criterion is the objective assessment method and, in the advanced form described in this paper, is capable of APC detection in near real time. The innovative Adverse Pilot Coupling Scale is a subjective assessment method for APCs experienced during completion of closed-loop tasks. Results from the application of both of these tools are presented as well as the very good correlation between them. Furthermore, the application of the tools to simulated flight-test data has shown how existing handling qualities mission task element courses and their associated performance tolerances can be inadequate when used to unmask the proneness of a pilot-vehicle system to APC. [ABSTRACT FROM AUTHOR]
- Published
- 2015
- Full Text
- View/download PDF
19. Multiloop Pilot Model for Boundary-Triggered Pilot-Induced Oscillation Investigations.
- Author
-
Linghai Lu and Jump, Michael
- Subjects
BOUNDARY element methods ,OSCILLATIONS ,COMMAND & control systems ,SIMULATION methods & models ,MARITIME pilots - Abstract
This paper presents the development of a multiloop pilot model for use in boundary-triggered pilot-induced oscillation investigations. In doing so, the point-tracking and boundary-avoidance elements of the pilot control strategy are assumed to act simultaneously for a point-tracking-dominant task during a boundary-avoidance tracking event. The theoretical analysis indicates that the essence of the boundary-avoidance tracking phenomenon consists of an additional requirement for the pilot to provide lead equalization as the boundary is approached as the task transitions from a full-attention point-tracking task to both a point-tracking and boundary-avoidance task. This process leads to a narrower open-loop system bandwidth and a larger tracking error, or the triggering of a pilot-induced oscillation. It is also found that the severity of the boundary-avoidance influence can be reduced by including the effects of vestibular and proprioceptive cues into the model. The boundary-avoidance tracking pilot model exhibits pilot-vehicle responses that are consistent with those observed in a piloted-simulation study and can therefore be considered to be representative of pilot activity. Consideration of the results in the round indicates that the boundary-triggered pilot-induced oscillation can be categorized as Category III pilot-induced oscillation within the existing recognized taxonomy. [ABSTRACT FROM AUTHOR]
- Published
- 2014
- Full Text
- View/download PDF
20. Adverse rotorcraft pilot couplings—Past, present and future challenges.
- Author
-
Pavel, Marilena D., Jump, Michael, Dang-Vu, Binh, Masarati, Pierangelo, Gennaretti, Massimo, Ionita, Achim, Zaichik, Larisa, Smaili, Hafid, Quaranta, Giuseppe, Yilmaz, Deniz, Jones, Michael, Serafini, Jacopo, and Malecki, Jacek
- Subjects
- *
AIRPLANE wings , *AIR pilots , *OSCILLATIONS , *FLIGHT control systems , *ALGORITHMS , *ROBUST stability analysis - Abstract
Abstract: Fixed and rotary wing pilots alike are familiar with potential instabilities or with annoying limit cycle oscillations that arise from the effort of controlling aircraft with high response actuation systems. Understanding, predicting and suppressing these inadvertent and sustained aircraft oscillations, known as aircraft (rotorcraft)-pilot couplings (A/RPCs) is a challenging problem for the designers. The goal of the present paper is to give an overview on the state-of-the-art in RPC problem, underlining the future challenges in this field. It is shown that, exactly as in the case of fixed wing APCs, RPCs existed from the beginning of rotorcraft development and that the problem of eliminating them is not yet solved: the current rotorcraft modelling for RPC analysis is rather limited to the particular case analysed and there is a lack of quantitative pilot behavioural models to analyse RPCs. The paper underlines the importance of involuntary pilot control actions, generally attributed to biodynamic couplings in predicting RPCs in rotorcraft. It is also shown that recent experiences demonstrate that modern rotorcraft seem to embed tendencies predisposing the flight control system FCS system towards dangerous RPCs. As the level of automation is likely to increase in future designs, extending to smaller aircraft and to different kinds of operation, the consequences of the pilot ‘fighting’ the FCS system and inducing A/RPCs needs to be eradicated. In Europe, the ARISTOTEL project (2010–2013) has been launched with the aim of understanding and predicting modern aircraft's susceptibility to A/RPC. The present paper gives an overview of future challenges to be solved for RPC-free design and some new solutions herein. [Copyright &y& Elsevier]
- Published
- 2013
- Full Text
- View/download PDF
21. Tau Coupling Investigation Using Positive Wavelet Analysis.
- Author
-
Linghai Lu, Jump, Michael, and Jones, Michael
- Subjects
WAVELETS (Mathematics) ,HARMONIC analysis (Mathematics) ,MAGNETIC coupling ,NUMERICAL calculations ,NUMERICAL analysis - Abstract
The investigation of motion guidance and its subsequent application using tau (T) theory relies on the accurate calculation of the coupling term between the T (time to contact) of the motion and the appropriate r guide. However, the traditional approach for this calculation can be numerically unstable, requires experience and skill to execute in a meaningful manner, is sensitive to the data selected, and has limited application when the motion information is incomplete or deviates from the ideal. To deal with these issues, a new approach, based on positive wavelet analysis, is proposed in this paper. The mother wavelet is constructed using the desired r-guide shapes, with its scale considered to be defined by the maneuver period. The scale and time information of interest are found by searching for the best local correlation within the whitened original signal. An inverse dewhitening process is then used to reconstruct an approximation to the original motion signal. The adequacy of the positive wavelet method has been demonstrated using data obtained from piloted simulation test campaigns. The results show that the approach is not only feasible, but it has better numerical stability, reliability, enhanced performance, and wider applicability than those that have been used to date. [ABSTRACT FROM AUTHOR]
- Published
- 2013
- Full Text
- View/download PDF
22. Development of the Phase-Aggression Criterion for Rotorcraft--Pilot Coupling Detection.
- Author
-
Jones, Michael, Jump, Michael, and Linghai Lu
- Subjects
OSCILLATIONS ,AERODYNAMICS research ,CRITERION (Theory of knowledge) ,AIRPLANE control systems ,FLIGHT control systems - Abstract
Significant effort has been expended to develop criteria to predict the susceptibility of an air vehicle to so-called pilot-induced oscillations. Much of this work has been carried out for fixed-wing aircraft and it is only recently that their applicability to rotorcraft has started to be assessed. Real time pilot-induced oscillation identification methods provide an alternative means to at least warn the pilot that a pilot-induced oscillation is in progress so that preventative action can be taken. Existing methods, however, have some limitations and have rarely been used for rotary-wing purposes. Specifically, the existing methods assessed in this paper do not provide an indication of the severity of the event and mask the underlying data that are being used to generate the warning. This paper proposes and presents a new method to identify pilot-induced oscillations, either in near real time or as a postprocessing aid for recorded flight-test data, that addresses both of these issues. The new method, entitled "phase-aggression criterion," is compared with current methods. It is shown, for a specific set of test cases and a limited test pilot population, that not only can it provide more information about the pilot-induced oscillation but it can also provide an earlier warning of its onset. [ABSTRACT FROM AUTHOR]
- Published
- 2013
- Full Text
- View/download PDF
23. Experimental and numerical helicopter pilot characterization for aeroelastic rotorcraft–pilot coupling analysis.
- Author
-
Masarati, Pierangelo, Quaranta, Giuseppe, and Jump, Michael
- Subjects
HELICOPTER pilots ,AEROELASTICITY ,COUPLINGS (Gearing) ,HELICOPTER design & construction ,BIOMECHANICS - Abstract
Pilot–vehicle interaction represents a critical aspect of aircraft design. Very low-frequency, voluntary although unintentional interaction has been extensively investigated in fixed and rotary wing aeromechanics. Higher frequency, involuntary and thus passive interaction received similar attention in fixed wing aeromechanics, but not as much for rotary wing. The results of an experimental campaign for the characterization of the passive behaviour of rotorcraft pilots' biomechanics are presented. A flight simulator has been used to excite human subjects. The accelerations of their limbs and the motion induced by the vibrations of the limbs in the control inceptors have been recorded. The vertical, longitudinal and lateral directions have been independently excited, while measuring the motion of the arm directly involved in the control inceptor mostly affected by motion in each direction, namely the left and the right arms for the collective and the cyclic sticks, respectively. The frequency domain response has been evaluated; resulting noteworthy behaviour is discussed, addressing its relevance in modelling the passive behaviour of pilots within the bioaeroservoelastic rotorcraft analysis. The measurements of human body impedance, under realistic cockpit motion, are used to identify the direct transfer functions between the motion of the seat and the controls inadvertently fed back into the rotorcraft. [ABSTRACT FROM AUTHOR]
- Published
- 2013
- Full Text
- View/download PDF
24. Measuring decision accuracy and confidence of mock air defence operators
- Author
-
Adams-White, Jade E, Wheatcroft, Jacqueline M, and Jump, Michael
25. Measuring the decision accuracy and decision confidence of air defence operators
- Author
-
Adams-White, Jade Elizabeth, Jump, Michael, and Wheatcroft, Jacqueline
- Subjects
150 - Abstract
Air defence decision making is demanding, time pressured and complex. Operators must make complex and cognitively demanding decisions in dynamic and uncertain environments. This thesis sought to increase the understanding of, and measure, decision confidence and accuracy in air defence decision making. In doing so, a novel method was designed and developed which was based on an integration of Classical Decision Making (CDM) and Naturalistic Decision Making (NDM) theories of decision making. Decision making is dependent on an interaction between both the situational demands of the task as well as individual differences in the decision maker. In addition, two key elements of decision making are the accuracy of the decision taken and its associated confidence. The body of work contained in this thesis, therefore, examined the impact of both external factors relating to decision making which included Decision Criticality, Task Load, Time Pressure and Audio communication, as well as the internal factors of Personality, Cognitive Constructs and Video Game experience. These factors were considered in relation to decision accuracy, confidence and W-S C-A (a measure of metacognitive ability). The experimental stimulus was developed with the help of Subject Matter Experts. This included the development of a realistic computer-generated air defence scenario in which the Task Load (high, moderate, low) was varied. In addition, an appropriate range of classifiable decision options, which varied in Decision Criticality (high, medium, low) was also generated. Three-hundred novice participants and twenty-two experts took part across a range of experiments. The Experimental Work consisted of two sections. The first section contained the foundation and investigatory work. The second section assessed the application of this measure through the use of feedback/training and expert participants. The results highlight the impact that Decision Criticality, which is the level of consequence associated with a decision, has on individual decision making. Findings show that a decision which was higher in criticality impacted positively on the performance by increasing decision accuracy. Individual participants tended to be less confident in their decisions when responding to decision events of medium criticality. Higher Decision Criticality was also shown to increase metacognitive abilities. That is, individuals were better able to discriminate between their accurate and inaccurate responses. Decision confidence was found to be both relatively stable and high across the experiments, indicating high levels of confidence in decisions, regardless of any other experimental variables including Task Load, Time Pressure and Audio. Such confidence was heightened in individuals who played video games on a regular basis. Internal factors also suggest that there may be individual differences that relate to decision making. Indeed, a higher tolerance of ambiguity may be beneficial in helping individuals deal with uncertain environments, such as in air defence. Although results of personality trait were largely inconclusive, low neuroticism and high conscientiousness appear to be beneficial in critical environments. Additionally, through the introduction of a metacognitive feedback training element, the research investigated the application of the measure. The results from this study demonstrated that, with metacognitive instruction, individuals displayed improved metacognitive ability. The experimental work also contains the first research to apply this method using active Royal Navy air defence personnel. The results from this experiment replicated the findings of criticality in the novice participants. The results thereby identify how this approach could be applied to air defence settings, and, illustrate the increased ecological validity of the findings. Recommendations suggest the findings can be applied to training and decision support technology. Further, the outcomes generally support the potential use of more traditional experimental methods alongside naturalistic approaches in critical environments, and that such an approach is warranted. Researchers and practitioners need to consider new approaches to research design to examine decision making in critical environments going forward. Overall, this thesis further contributes to the air defence decision making domain by providing valuable insights into the external and internal factors that are significant and relate to air defence decision making. Importantly, the work clearly showed Decision Criticality as an important factor that needs to be addressed when investigating decision making in critical environments. Individual differences were also demonstrated to be an important consideration.
- Published
- 2019
- Full Text
- View/download PDF
26. Practices to identify and preclude adverse Aircraft-and-Rotorcraft-Pilot Couplings – A design perspective.
- Author
-
Pavel, Marilena D., Masarati, Pierangelo, Gennaretti, Massimo, Jump, Michael, Zaichik, Larisa, Dang-Vu, Binh, Lu, Linghai, Yilmaz, Deniz, Quaranta, Giuseppe, Ionita, Achim, and Serafini, Jacopo
- Subjects
- *
ROTORCRAFT , *AIRCRAFT industry , *AIR pilots , *AIRPLANE design , *AERODYNAMICS , *STRUCTURAL models - Abstract
Understanding, predicting and supressing the inadvertent aircraft oscillations caused by Aircraft/Rotorcraft Pilot Couplings (A/RPC) is a challenging problem for designers. These are potential instabilities that arise from the effort of controlling aircraft with high response actuation systems. The present paper reviews, updates and discusses desirable practices to be used during the design process for unmasking A/RPC phenomena. These practices are stemming from the European Commission project ARISTOTEL Aircraft and Rotorcraft Pilot Couplings – Tools and Techniques for Alleviation and Detection (2010–2013) and are mainly related to aerodynamic and structural modelling of the aircraft/rotorcraft, pilot modelling and A/RPC prediction criteria. The paper proposes new methodologies for precluding adverse A/RPCs events taking into account the aeroelasticity of the structure and pilot biodynamic interaction. It is demonstrated that high-frequency accelerations due to structural elasticity cause negative effects on pilot control, since they lead to involuntary body and limb-manipulator system displacements and interfere with pilot's deliberate control activity (biodynamic interaction) and, finally, worsen handling quality ratings. [ABSTRACT FROM AUTHOR]
- Published
- 2015
- Full Text
- View/download PDF
27. Practises to identify and prevent adverse aircraft-and-rotorcraft-pilot couplings - A ground simulator perspective
- Author
-
A Ionita, Olaf Stroosma, Deniz Yilmaz, Pierangelo Masarati, Michael Johnes, Hafid Smaili, Giuseppe Quaranta, Binh Dang-Vu, Marilena D. Pavel, Michael Jump, Larisa Zaichik, Massimmo Gennaretti, Pavel, Marilena D, Jump, Michael, Masarati, Pierangelo, Zaichik, Larisa, Dang-Vu, Binh, Smaili, Hafid, Quaranta, Giuseppe, Stroosma, Olaf, Yilmaz, Deniz, Johnes, Michael, Gennaretti, Massimo, and Ionita, Achim
- Subjects
Motion Cues ,Control Loading ,Pilot Assisted Oscillations (PAO) ,Engineering ,Aircraft Pilot Coupling ,Aviation ,Aerospace Engineering ,Flight simulator ,Range (aeronautics) ,(APC) ,Aircraft Pilot Couplings ,Biodynamic Feedthrough ,Latency ,Pilot Induced Oscillations (PIO) ,Rotorcraft (RPC) ,Simulator Fidelity ,Time delay ,Visual Cues ,Mechanical Engineering ,Mechanics of Materials ,Pilot training ,Simulation ,business.industry ,Perspective (graphical) ,Motion cues ,Motion Cue ,Visual cueing ,business ,Visual Cue - Abstract
The aviation community relies heavily on flight simulators as a fundamental tool for research, pilot training and development of any new aircraft design. The goal of the present paper is to provide a review on how effective ground simulation is as an assessment tool for unmasking adverse Aircraft-and-Rotorcraft Pilot Couplings (APC/RPC). Although it is generally believed that simulators are not reliable in revealing the existence of A/RPC tendencies, the paper demonstrates that a proper selection of high-gain tasks combined with appropriate motion and visual cueing can reveal negative features of a particular aircraft that may lead to A/RPC. The paper discusses new methods for real-time A/RPC detection that can be used as a tool for unmasking adverse A/RPC. Although flight simulators will not achieve the level of reality of in-flight testing, exposing A/RPC tendencies in the simulator may be the only convenient safe place to evaluate the wide range of conditions that could produce hazardous A/RPC events.
- Published
- 2015
28. Practices to identify and preclude adverse Aircraft-and-Rotorcraft-Pilot Couplings - A design perspective
- Author
-
M Pavel, A Ionita, Larisa Zaichik, Deniz Yilmaz, Giuseppe Quaranta, Pierangelo Masarati, Linghai Lu, Michael Jump, Jacopo Serafini, Massimo Gennaretti, Binh Dang-Vu, Pavel, Marilena D, Masarati, Pierangelo, Gennaretti, Massimo, Jump, Michael, Zaichik, Larisa, Dang Vu, Binh, Lu, Linghai, Yilmaz, Deniz, Quaranta, Giuseppe, Ionita, Achim, and Serafini, Jacopo
- Subjects
Pilot inducedoscillations(PIO) ,0209 industrial biotechnology ,Engineering ,Pilot induced oscillations (PIO) ,media_common.quotation_subject ,Aircraft-Pilot Couplings (APC) ,Rotorcraft-Pilot Coupling (RPC) ,Conceptual design ,Preliminary design ,Flight control system design ,Pilot assisted oscillations (PAO) ,Automatic flight control system (AFCS) ,Aerospace Engineering ,02 engineering and technology ,Rotorcraft-PilotCoupling(RPC) ,020901 industrial engineering & automation ,0203 mechanical engineering ,Aeronautics ,Aircraft-Pilot Couplings(APC) ,Flight controlsystemdesign ,European commission ,Quality (business) ,Simulation ,media_common ,020301 aerospace & aeronautics ,business.industry ,Mechanical Engineering ,Perspective (graphical) ,Aeroelasticity ,Fly-by-wire ,Pilot assistedoscillations(PAO) ,Mechanics of Materials ,Engineering design process ,business ,Automatic flight controlsystem(AFCS) - Abstract
Understanding, predicting and supressing the inadvertent aircraft oscillations caused by Aircraft/Rotorcraft Pilot Couplings (A/RPC) is a challenging problem for designers. These are potential instabilities that arise from the effort of controlling aircraft with high response actuation systems. The present paper reviews, updates and discusses desirable practices to be used during the design process for unmasking A/RPC phenomena. These practices are stemming from the European Commission project ARISTOTEL Aircraft and Rotorcraft Pilot Couplings – Tools and Techniques for Alleviation and Detection (2010–2013) and are mainly related to aerodynamic and structural modelling of the aircraft/rotorcraft, pilot modelling and A/RPC prediction criteria. The paper proposes new methodologies for precluding adverse A/RPCs events taking into account the aeroelasticity of the structure and pilot biodynamic interaction. It is demonstrated that high-frequency accelerations due to structural elasticity cause negative effects on pilot control, since they lead to involuntary body and limb-manipulator system displacements and interfere with pilot's deliberate control activity (biodynamic interaction) and, finally, worsen handling quality ratings.
- Published
- 2015
Catalog
Discovery Service for Jio Institute Digital Library
For full access to our library's resources, please sign in.