Rotorcraft simulation fidelity: new methods for quantification and assessment

2013 ◽  
Vol 117 (1189) ◽  
pp. 235-282 ◽  
Author(s):  
P. Perfect ◽  
M. D. White ◽  
G. D. Padfield ◽  
A. W. Gubbels
Keyword(s):  
National Research Council ◽  
Flight Simulation ◽  
Flight Training ◽  
Pilot Training ◽  
Engineering Practice ◽  
Design Development ◽  
Simulation Fidelity ◽  
Handling Qualities ◽  
Fidelity Assessment ◽  
Research Aircraft

AbstractFlight simulators are integral to the design/development, testing/qualification, training and research communities and their utilisation is ever expanding. The use of flight simulation to provide a safe environment for pilot training, and in research and development, must be underpinned by quantification of simulator fidelity. While regulatory simulator standards exist for flight training simulators and new standards are in development, previous research has shown that current standards do not provide a fully quantitative approach for assessing simulation fidelity, especially in a research environment. This paper reports on progress made in a research project at the University of Liverpool (Lifting Standards), in which new predicted and perceptual measures of simulator fidelity have been developed. The new metrics have been derived from handling qualities engineering practice. Results from flight tests on the National Research Council (Canada) Bell 412 ASRA research aircraft and piloted simulation trials using the HELIFLIGHT-R simulator at Liverpool are presented to show the efficacy of adopting a handling qualities approach for fidelity assessment. Analysis of the new metrics has shown an appropriate degree of sensitivity to differences between flight and simulation.

Integrating CFD and piloted simulation to quantify ship-helicopter operating limits

2006 ◽  
Vol 110 (1109) ◽  
pp. 419-428 ◽  
Author(s):  
D. M. Roper ◽  
I. Owen ◽  
G. D. Padfield ◽  
S. J. Hodge
Keyword(s):  
National Research Council ◽  
Flight Simulation ◽  
Pilot Training ◽  
Helicopter Control ◽  
Numerical Predictions ◽  
Motion Simulator ◽  
Wide Range ◽  
Operating Limits ◽  
Wind Tunnel Data ◽  
Computational Fluid Dynamics Cfd

Abstract This paper describes a study which has been concerned with numerical predictions of the airwakes resulting from two simplified ship geometries: the internationally agreed Simple Frigate Shape, SFS1, and its successor, SFS2. Extensive steady-state simulations have been carried out for a wide range of wind conditions using Fluent, a commercially available Computational Fluid Dynamics (CFD) code. The CFD predictions have been partially validated against wind tunnel data produced by the National Research Council of Canada (NRC) and have shown good agreement. The resulting airwake velocity components have been exported from Fluent, interpolated onto suitable grids and attached to the FLIGHTLAB flight-simulation environment as look-up tables; piloted flight trials were then carried out using the Liverpool full-motion simulator. The pilot workload and helicopter control margins resulting from a range of wind-over-deck conditions have been used to develop the Ship-Helicopter Operating Limits (SHOL) for a Lynx-like helicopter and the SFS2. The workload was compared to the pilot’s experiences on a similar aircraft and a Type 23 Frigate and the simulated SHOL compared with SHOLs derived from sea trials. The results are very encouraging and open up further the long awaited prospect of such simulations being used in the future to reduce at-sea trials, and to provide a safe environment for pilot training.

Adaptive Training—An Application to Flight Simulation

1969 ◽  
Vol 11 (6) ◽  
pp. 569-576 ◽  
Author(s):  
Paul W. Caro
Keyword(s):  
Training System ◽  
Flight Simulation ◽  
Flight Training ◽  
Pilot Training ◽  
Adaptive Logic ◽  
Adaptive Training ◽  
Training Requirements ◽  
Training Techniques ◽  
Flight Simulators ◽  
Wide System

Army pilot training requirements, particularly in the helicopter area, are growing rapidly. To meet the increased training load, an Army-wide system of aircraft simulators, known as the Synthetic Flight Training System (SFTS), has been designed and is under development. A feature of the SFTS is the automation of many instructor functions normally associated with training in flight simulators. A portion of the automation involves the application of adaptive training techniques. This paper describes the SFTS and the rationale for the incorporation in it of adaptive training. The selection of appropriate adaptive variables, techniques for error measurement and for providing feedback to trainees, and the adaptive logic employed are discussed.

ATC simulation for flight training: The missing link

2017 ◽  
Vol 08 (04) ◽  
pp. 1743001
Author(s):  
Nick Papadopoli
Keyword(s):  
Communication Skills ◽  
Flight Simulation ◽  
The State ◽  
Flight Training ◽  
Aviation Industry ◽  
Primary Reason ◽  
Missing Link ◽  
Simulation Fidelity ◽  
Training Tool ◽  
Research Communities

This paper presents the state of piloted flight simulation fidelity with a focus on the missing link needed to complete the flight simulation experience, namely the simulated ATC environment (SATCE). To date, there has been a great deal of effort invested in providing the highest level of flight realism possible. However, little investment has gone into systems which are used to improve communication skills with ATC while in a populated active airspace. It is important to note that the relatively few SATCEs is not due to the lack of technology, since such products have been available for about a decade. The primary reason for its absence is the inability and unwillingness for operators to justify the investment in such a training tool. In the meantime, the aviation industry has recognized that pilots need to have better communication skills while operating in various conditions. Consequently ICAO, with help from ARINC Industry Activities/FSEMC, has already taken steps to recommend the inclusion of SATCE characteristics in flight simulation devices. The aviation and research communities need to assist efforts by producing the necessary studies and metrics which can be used to evaluate and validate SATCEs used in the flight training.

Design and evaluation of the objective motion cueing test and criterion

2016 ◽  
Vol 120 (1227) ◽  
pp. 873-891 ◽  
Author(s):  
R. Hosman ◽  
S. Advani
Keyword(s):  
Flight Simulation ◽  
Flight Training ◽  
Pilot Training ◽  
Tuning Parameters ◽  
Flight Simulators ◽  
Flight Mode ◽  
Subjective Judgement ◽  
Motion Cueing ◽  
Simulator Motion ◽  
Mode Of Transport

ABSTRACTSince the introduction of hexapod-type motion systems for flight simulation in the 1970s, Motion Drive Algorithm tuning has been primarily based on the subjective judgement of experienced pilots. This subjective method is often not transparent and often leads to ambiguous process of adjustment of the tuning parameters. Consequently, there are large variations in the motion cueing characteristics of flight training devices, a variability that subsequently raises questions regarding the value of motion cueing for pilot training itself. The third revision of ICAO 9625 Manual of Criteria for the Qualification of Flight Simulation Training Devices offered the opportunity to take a closer look at simulator motion cueing requirements in general. This led to the concept of the objective motion cueing test (OMCT), which was reported in 2006. After the method was evaluated on three research flight simulators, the results were published in 2007, demonstrating a larger spread in dynamic behaviour of cueing algorithms than expected. After discussions with the simulator industry regarding the form and methodology of the OMCT, an evaluation of the test in cooperation with the industry started in 2011. This led to the final form of the OMCT and cueing parameter criterion for the in-flight mode of transport aircraft. This paper describes the OMCT, the evaluation results and the criterion.

scholarly journals Development of a Full Mission Simulator for Pilot Training of Fighter Aircraft

2018 ◽  
Vol 68 (5) ◽  
pp. 425-431 ◽  
Author(s):  
Shashidhara BP ◽  
Chandra Sekaran ◽  
Yashpal Bhatia ◽  
Magesh Kumar ◽  
Binesh Kumar ◽  
...  
Keyword(s):  
Air Force ◽  
Flight Simulation ◽  
Flight Training ◽  
Pilot Training ◽  
Significant Component ◽  
Fighter Aircraft ◽  
Waypoint Navigation ◽  
Glass Cockpit ◽  
Navigation Software ◽  
Insight Into

With aircraft becoming more complex and avionics intensive and flight being almost autonomous based on waypoint navigation, software and displays becoming a significant component of the all glass cockpit of the modern day fighter aircraft, it is imperative that pilots are trained on missions using ground based full mission simulator (FMS) for routine flight as well as advanced missions. A flight simulator is as good as the real system only when it is able to mimic the physical system, both in terms of dynamics and layout so that the pilot gets the complete feel of the environment as encountered during actual sortie. The objective of this research paper is to provide a detailed insight into the various aspects of development of a FMS for pilot training with minimal maintenance operations for long hours of realistic flight training on ground. The approach followed by ADE in developing a FMS using a healthy mix of conventional flight simulation methodologies and novel approaches for various simulator sub-systems to tailor and meet the specific training needs, one presented. The FMS developed by ADE is presently being used by Indian Air Force for flight and mission critical training of squadron pilots.

scholarly journals Helicopter handling qualities: A study in pilot control compensation

2021 ◽  
pp. 1-35
Author(s):  
W.A. Memon ◽  
M.D. White ◽  
G.D. Padfield ◽  
N. Cameron ◽  
L. Lu
Keyword(s):  
Frequency Domain ◽  
Rating Scale ◽  
National Research Council ◽  
Subjective Assessment ◽  
Control Activity ◽  
Handling Qualities ◽  
Systems Research ◽  
Wide Range ◽  
Time Varying Frequency ◽  
Research Aircraft

Abstract The research reported in this paper is aimed at the development of a metric to quantify and predict the extent of pilot control compensation required to fly a wide range of mission task elements. To do this, the utility of a range of time- and frequency-domain measures to examine pilot control activity whilst flying hover/low-speed and forward flight tasks are explored. The tasks were performed by two test pilots using both the National Research Council (Canada)’s Bell 412 Advanced Systems Research Aircraft and the University of Liverpool’s HELIFLIGHT-R simulator. Handling qualities ratings were awarded for each of the tasks and compared with a newly developed weighted adaptive control compensation metric based on discrete pilot inputs, showing good correlation. Moreover, in combination with a time-varying frequency-domain exposure, the proposed metric is shown to be useful for understanding the relationship between the pilot’s subjective assessment, measured control activity and task performance. By collating the results from the subjective and objective metrics for a range of different mission task elements, compensation boundaries are proposed to predict and verify the subjective assessments from the Cooper-Harper Handling Qualities Rating scale.

Rotorcraft Lateral-Directional Oscillations: The Anatomy of a Nuisance Mode

2021 ◽  
Author(s):  
Dheeraj Agarwal ◽  
Linghai Lu ◽  
Gareth D. Padfield ◽  
Mark D. White ◽  
Neil Cameron
Keyword(s):  
Simulation Model ◽  
Simulation Models ◽  
Flight Test ◽  
Flight Simulation ◽  
Stability And Control ◽  
Systems Research ◽  
Control Derivatives ◽  
Research Aircraft ◽  
Level Of Understanding ◽  
And Control

High-fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. One such example is the difficulty in the prediction of the characteristics of the rotorcraft lateral-directional oscillation (LDO) mode in simulation. Achieving an acceptable level of the damping of this mode is a design challenge requiring simulation models with sufficient fidelity that reveal sources of destabilizing effects. This paper is focused on using System Identification to highlight such fidelity issues using Liverpool's FLIGHTLAB Bell 412 simulation model and in-flight LDO measurements from the bare airframe National Research Council's (Canada) Advanced Systems Research Aircraft. The simulation model was renovated to improve the fidelity of the model. The results show a close match between the identified models and flight test for the LDO mode frequency and damping. Comparison of identified stability and control derivatives with those predicted by the simulation model highlight areas of good and poor fidelity.

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