Network for innovative training on rotorcraft safety.


Programme of the NITROS International Workshop on Engineering for Rotorcraft Safety

Virtual Workshop 7-9 April 2021

To download a PDF version of the programme click here

Clicking on titles you will be able to download the extended abstracts

Day 1, April 7, 2021, Morning Chairman Pierangelo Masarati

09:30                    Giuseppe Quaranta, Politecnico di Milano

                             “Introduction to the NITROS Workshop on Engineering for Rotorcraft Safety”

09:40                    Fabio Nannoni, Senior Vice President Safety System Governance Leonardo

                           “Welcome to the participants by Leonardo Helicopter Division”

09:45                    Pierluigi Parente, Leonardo Helicopter Division                 

                           “PBN for RC operations: improved safety and unparalleled operational flexibility”

10:30                    Open discussion

10:50                    Coffee break

11:15                    D. Tilloca, Politecnico di Torino

                            “Hazard and risk analysis for helicopter aerial work mission profiles”

11:45                    D. Friesen, TU Delft and Politecnico di Milano

“Design and evaluation of a constraint-based helicopter display to support safe path planning”

12:15                    P. Masarati, Politecnico di Milano

“Helicopter emergency medical services (HEMS): higher availability calls for more stringent safety


Day 1, April 7, 2021, Afternoon Chairman Giuseppe Quaranta

14:00                    P. Scaramuzzino, TU Delft and Politecnico di Milano

                            “Autorotation transfer of training: effects of helicopter dynamics variation”

14:30                    M. Favale, Leonardo Helicopter Division                              

                           “Virtual sensors for prediction and monitoring”

15:00                    Coffee break

15:30                   N. Nabi, Politecnico di Milano and TU Delft

                           “Load alleviation in tiltrotor aircraft through incremental nonlinear control allocation”

16:00                    F. Marino, Robby Moto Engineering

                            “TEPS project”

16:30                    Wrap up

16:45                    End of day 1

Day 2, April 8, 2021, Morning Chairman Marilena Pavel

09:30                    G. Padfield, Emeritus Professor University of Liverpool

“The potential impact of critical aircraft pilot couplings on the safety of tilt-rotor operations”

10:15                    Open discussion

10:30                    A. Cocco, Politecnico di Milano

                            “Effect of control inceptors dynamics on helicopter vertical bounce proneness”

11:00                    Y. Yu, Tu Delft and Politecnico di Milano                              

“Analysis of rotorcraft pilot couplings from the perspective of RPC detection: a new multi-axes

distinguishable ROVER method”

11:30                    Coffee break

11:45                    M. Jump, University of Liverpool

“Preliminary piloted flight-simulation evaluation of autogiro operations in the presence of wind-

turbine wake”

12:15                    S. Henriquez Huecas, University of Liverpool and University of Glasgow

“Helicopter handling analysis using a synthetic eddy turbulence model”

12:45                    Lunch break

Day 2, April 8, 2021, Afternoon Chairman Mark White

14:00                    R. Bianco-Mengotti, Leonardo Helicopter Division

                            “The advantages of virtual engineering in rotorcraft flight mechanics design process”

14:30                    N. Taymourtash, Politecnico di Milano and University of Glasgow

“Aerodynamic load assessment of model-scale helicopter in shipboard operation”

15:00                    Coffee break

15:30                    S. Fasiello, Politecnico di Milano and University of Liverpool

                            “The effect of turbulence on RPC incipience and workload”

16:00                    Wrap-up

16:15                    End of day 2

Day 3, April 9, 2021, Morning Chairman George Barakos

09:30                    C. Audard, EASA Safety coordinator – VTOL

Rotorcraft safety roadmap and regulatory perspective on design safety improvements”

10:15                    Open Discussion

10:30                    F. Fonte, Leonardo Helicopter Division

“AW609 whirl flutter simulation, model validation and flight test for aeroelastic stability


11:00                    S. Ghiasvand, Politecnico di Milano and University of Liverpool

“Experimental and numerical investigation of matrix cracking and delamination interaction of

curved composite laminates by FBG sensors”

11:30                    Coffee break

11:45                    M. Filippi, Politecnico di Torino

“Multi-dimensional FE models for multifield analyses of composite realistic helicopter blade”

12:15                    C. Paciello, Step Sud Mare S.r.l

“Crashworthiness of a tiltrotor fuel tank bay”

12:45                    Lunch break

Day 3, April 9, 2021, Afternoon Chairman Giuseppe Quaranta

14:00                    Francesco De Domenico, Leonardo Helicopter Division

                           “Rotorcraft ice protection in LHD”

14:30                    M. Morelli, Politecnico di Milano and University of Glasgow

“High-fidelity numerical ice prediction on rotors”

15:00                    Coffee break

15:30                    F. Di Caprio, CIRA

“Numerical evaluation of the damage scenario due to a bird strike on the wing leading edge of a


16:00                    F. Rovere, University of Glasgow and Politecnico di Milano

                            “Brown-out simulations of model-rotors”

16:30                    Wrap-up

16:45                    End of day 3

Helicopter Pilots Training through Flight Simulators. Basic Flying Skills: Hover. Paolo Scaramuzzino

The importance of rotorcraft safety has received significant recognition in recent years. The dramatically larger accident rate for rotary-wing aircraft compared to fixed-wing aircraft was interpreted by the technical community as a call to action. In 2005, the International Helicopter Safety Team (IHST) was established with the ambitious goal of reducing helicopter accident rates by 80% within 10 years. 

The analysis of accident data was the first step to identify the main causes and define priorities in terms of recommended interventions to enhance safety. The analyses carried out by the U.S. Joint Helicopter Safety Analysis Team (JHSAT) and the European Helicopter Safety Analysis Team (EHSAT) both highlight the same issues of concern and the same improvement actions. Training/Instructional interventions were recognized to be of prime interest for rotorcraft safety, since most of the accidents in the data set were the result of pilot-related factors (e.g., pilot judgement and actions, ground duties and pilot situational awareness). The in-depth analysis performed by the U.S. JHSAT pointed out that many efforts need to be dedicated to develop standard training program on autorotation and emergency aircraft handling and to improve simulator training for basic and advanced manoeuvres. 

Thus, pilots training and flight simulators play a crucial role in rotorcraft safety. The combination of simulator and in-flight training is desirable, especially during the training of hazardous scenarios. The variety of conditions that the pilot may face during an emergency situation requires experience and judgement in order to react promptly and avoid many possible types of error. Thus, extensive practice is necessary to acquire robust and flexible piloting skills. Unfortunately, extensive in-flight training of advanced manoeuvres is expensive and risky, and therefore simulator training is the only valid alternative. However, in order to avoid unrealistic training and negative transfer of skills when similar situations are encountered during actual flight, there is the need to bridge the gap between simulator scenarios and reality for edge-of-the-envelope and outside-of-the-envelope flight conditions.

The first part of my research was devoted to assess the effectiveness of a low-fidelity simulator on the initial training of a basic flying task, i.e. hover, using the part-task training program presented in the video. 

The results of this study can be found at the following link:

ESR 8 presentation at UK Vertical Lift Network

The UK Vertical Lift Network is a consortium of academic institutions and aerospace research groups. The shared aims are to promote the vertical lift sector, facilitate collaborative research and attract funding.  (

The 4th Technical WorkShop organized by UK VLN took place on the 7th-9th of April 2019 at Shrigley Hall, Cheshire. This event is organized in order to give to the network members the opportunity to present their research, exchange ideas and promote the vertical lift research sector.
During one of the sessions of the Workshop, ESR #08 Federico Rovere, introduced the NITROS project and his work about Modelling of Brown-out/White-out to the attendants.

Federico gave a brief introduction about the literature survey carried out so far, pointing out how Brown-out and White-out afflict helicopter safety.
The presentation included also the work done so far for the prediction the rotorcraft wake using CFD (Computational Fluid Dynamics): an accurate simulation of the rotor wake features is fundamental in order to predict properly the particle dispersion in the helicopter environment in case of Brown-out or White-out.

Revealing adverse Rotorcraft-Pilot Coupling induced by Flight Control Systems, by ESR10, Ying Yu

This video presents some general concepts of pilot induced oscillation (PIO), including the classification of PIO, examples of Aircraft pilot coupling (APC) and Rotorcraft pilot coupling (RPC). Description of Cat. III PIO and potential trigger events of Cat. III PIO is presented as well. Finally, the Flight simulation facilities that will be used in the following research is shown in the video.

Introduction to NITROS and Career Counselling Session at Institute of Space Technology (IST), Islamabad, Pakistan

An introductory session about NITROS project and career counselling session was organized for the students of Institute of Space Technology (IST) in Islamabad, Pakistan on 2nd January 2018. The session was conducted by ESR # 03 Hafiz Noor Nabi, an alumnus of IST. Students from Aerospace, electrical and mechanical engineering and space sciences attended the session.

Noor gave a general introduction about the research activities within the NITROS project and specifically talked about his own research on flight dynamics modeling and control design for Tiltrotors. An introduction to Marie Skłodowska-Curie Actions scholarship opportunities was also given to the students. The students were encouraged to consider research career and how to apply and what to consider when applying for research/PhD positions.


Handling quality of the helicopter can be basically explained as helicopter stability (or instability) and controllability in flight, and pilot’s ability to maneuver the helicopter and their comfort. This is affected by a long list of parameters, hence there are certain requirements that need to be satisfied starting from the design stages of the helicopter. The existing handling quality requirements document for rotorcraft is the ADS-33. It is applicable to both augmented and unaugmented helicopters. These requirements are generally adapted from the fixed wing requirements and flying and handling quality criteria. However, rotorcraft are different from the fixed wing designs since they need to operate in difficult conditions and need to complete difficult tasks and maneuvers. Both design and pilot workload are affected from these difficult operating environments. Pilot workload starts to increase and helicopter design starts to include more moving parts and complex mechanisms which result in higher vibration levels. Vibrations can be categorized in many ways but mostly according to their frequency. The main idea of this research is to analyze main rotor induced vibrations and their effect on handling qualities. Vibrations can change according to the mission task. ADS 33 is essentially a mission oriented specification, with criteria depending on selected mission task elements (MTEs), response types and usable visual cue environments as in Figure 1

Figure 1: Requirements for moderate-amplitude pitch attitude changes – hover and low speed [1]

The research problem arises here, how to maintain high agility needed for high operational capability without developing high vibrational loads? This research uses multi-disciplinary approach to solve this problem because there is a trade-off between agility and performance required for a mission and the vibration. It is also important what is appreciated by pilots in terms of handling qualities. There is a matrix that involves different level of agilities and vibrational loads for every task and there are many research going on to reduce the rotor induced vibratory loads in design. Hovewer, which case is the most preferred one or the one that the pilot handles the helicopter more easily in that matrix is a question that this research will deal with. Last but not least, the aim is to make a connection between handling quality and vibration to make these rotary wing aircrafts safer and more comfortable.

ADS-33 is essentially a mission-oriented specification, with criteria depending on selected mission task elements (MTEs), response types, and usable visual cue environments. The strength of ADS-33 lies in the new criteria and metrics introduced to maximize mission effectiveness while not compromising safety. These criteria offer the designer the proper tools for designing helicopters capable of performing difficult operations. Performing difficult operations implies designing for high agility while at the same time optimizing for flight in degraded visual environments. High agility occurs at the boundaries of the performance where high vibratory loads are developed in the structure. Therefore, designing for high operational capability requires a trade-off between agility and vibration. One of the questions arising in the design when assessing a rotorcraft’s handling qualities (HQs) is: How can one at the same time tackle the aircraft maneuver performance and the vibratory loading problem? A new series of guidelines and tools are, therefore, needed, capable of dealing with the multi-disciplinary nature of such a complex question.

The present paper presents a new approach to multi-disciplinary optimization by developing a set of complementary metrics drawn from ADS-33, capable of being applied to a rotorcraft for both agility enhancement and structural load alleviation. In this sense, the paper will give an example how the new metrics can be further used in the design of control functions that utilize multi-harmonic inputs, properly phased for simultaneous performance enhancement and vibratory reduction. The paper concentrates on developing and exercizing the new approach to vertical-pitch maneuvers in forward flight. These types of maneuvers are a good example of how the agility and structural loading problems link with each other in maneuvering flight.


[1] ADS-27A-SP and ADS-33

[2] A. Datta, I. Chopra, “Prediction of UH-60 Main Rotor Structural Loads using CFD/Comprehensive Analysis Coupling”, Presented at the 32nd European Rotorcraft Forum, Maastricht, The Netherlands, September 12-14, 2006.

[3] C. Ockier, “Flight Evaluation of the New Handling Qualities Criteria Using the BO105”, in American Helicopter Society, Missouri, 1993.

[4] M. D. Pavel and G. D. Padfield, “Defining Consistent ADS-33 – Metrics for Agility Enhancement and Structural Loads Alleviation “, in Annual Forum Proceedings of the American Helicopter Society, volume 58. American Helicopter Society, 2002.

[5] M. D. Pavel and G. D. Padfield, “The Extension of ADS-33—Metrics for Agility Enhancement and Structural Load Alleviation “, Journal of the American Helicopter Society, 51(4):319–330, 2006

[6] Northrop Grumman – UH-60L Black Hawk Helicopter Cockpit Digitization [720p] – YouTube


[8] Leonardo helicopters video from

Flight simulation for airwake encounters – an overview by Sergio Huercas (#ESR7)


Airwake hazards

Helicopters are some of the most flexible aircraft in existence, their ability to freely manoeuvre in almost any direction allows their employment in missions that no other vehicle can perform. Search and rescue missions between mountains or buildings, logistic support to remote offshore installations and naval operations from military vessels are only a few examples of the very diverse applications of helicopters.

Many of these missions require pilots to fly in very challenging environments, often under the airwake and turbulence shed by very close obstacles, for example the ship superstructure during deck landings. Sudden changes in the wind velocity surrounding the helicopter will result in upsets in the aircraft position, orientation and speed that can impair handling by the pilot or even lead to loss of control. Improving our understanding of these hazards is a requirement to achieve NITROS objective of enhancing helicopter safety.

Flight simulation as a first look on the problem

Flight simulation is proving to be a very valuable tool for this aim. Most people are familiar with the use of flight simulation for training, allowing pilots to virtually practise a task in order to prepare for real world flight training. But piloted and unmanned flight simulation (also known as online and offline flight simulation respectively) also has important applications in research and development.

For example, wind energy is proliferating across the globe with wind farms appearing near airfields and heliports, there are increasing risk for an encounter with the airwake of a wind turbine. There is almost no experimental data for these kind of scenarios [1] but flight simulation can be used in initial concept studies for operations, helping engineers to identify possible risks beforehand and to prepare flight test. Also if flight simulators can reproduce the underlying physical causes of such hazards, they might help in evaluating possible solutions before putting them into practice.

This was the objective of a series of tests [2] conducted at the University of Liverpool during which pilots flew a simulated accidental encounter between a general aviation airplane and the airwake of a small wind turbine. It was shown that the airwake of a wind turbine could lead to mild upsets in aircraft attitudes which should not impair handling. Encounters with the airwake of modern very large wind turbines might produce a different outcome however.

Also, due to their very different flight mechanics and handling, helicopters will probably react in a very different way than fixed wing aircraft. Since they are being used to provide logistical support to offshore wind energy installations [3] and might need to operate in their vicinity for search and rescue missions, knowing the effects of such an encounter is therefore of great interest [4].

Models and realism

But if flight simulators are to be useful in reducing the hazards from airwake encounters they must realistically reproduce their effects and for piloted flight simulation, it must do so in real time. This is no easy requirement. The simulator combines mathematical models that describe the behaviour of the aircraft and the aerodynamics of their environment and solves them together to determine how the aircraft behaves.

The accuracy of models and their coupling, as well as the obtained results, must be validated. Comparison against results of wind tunnel experiments, field measurements and flight tests as well as pilot feedback can be used to assess if a model is valid. Usually improvements in accuracy are obtained by including the effect of additional physical phenomena to the model.

But this comes at the cost of increasing complexity leading to longer computation times, as solving these models, especially the fluid dynamics equations that describe the behaviour of the airwake, requires a large number of calculations which have to be performed repeatedly. This would have been completely impossible without today’s computing technology. But even then, if flight simulation is to be feasible, simplifications in models or coupling must be found that still lead to accurate results.

An example of such a coupling of different models is being applied to train naval pilots in ship deck landings. The ship airwake is solved using computational fluid dynamics, and approach that can last between hours or days depending on the fidelity of the solution. The movement of the air over the ship deck is stored as if it were a movie and replayed in the flight simulator which then can calculate the effects of the airwake on the helicopter in real time. This approach produces very realistic airwakes when compared to experimental measurements and has shown to help in the preparation of flight trials and training of pilots by providing them with a first impression of how to approach the landing[5].

This is referred as one way coupling. The effects of the airwake on the helicopter are modelled very accurately, but not so the effects of the helicopter on the airwake, since the solution of the airwake has been computed and stored beforehand. If the airwake changes due to the presence of the helicopter, their effects on the helicopter might change too.

Complete coupling of aerodynamics and flight dynamics would require computing the aerodynamics of the airwake and the helicopter acting upon it, computing its effects on the movement of the helicopter and applying them and then starting the cycle again for the new position and orientation of the aircraft. With the computational technologies available today, it is impossible to perform these simulations fast enough for piloted simulations.

Research is being conducted in this regard for non-piloted flight simulation. Here the pilot is replaced by an automatic pilot model that emulates a human pilot attempting to perform the intended task. But future improvements in modelling techniques and computing technologies might allow to implement some of these methodologies to improve the accuracy of piloted flight simulation.


As we have seen, whenever models are being used to obtain predictions, care has to be taken in their evaluation and researcher and engineers must always be aware of the limitations and compromises of the methodology applied. But results obtained by flight simulation can help pilots to prepare for flight training and provide guidance to engineers to evaluate new designs, alert about possible risks and identify which conditions require further testing. Used correctly, flight simulators can lower costs and enhance safety by reducing required flight hours for testing and training and by allowing to better prepare for them beforehand. A great help in achieving NITROS objective of enhancing helicopter safety.


[1] Civil Aviation Authority, “CAA Policy and Guidelines on Wind Turbines,” pp. 1–45, 2016.

[2] Y. Wang, M. White, and G. N. Barakos, “Wind Turbine Wake Encounter Study,” 2015.

[3] R. Roorman, “Assessing Viability in Offshore Wind,” Rotor and Wind, 2018.

[4] “Objectives, HC / AG-23 : Wind Turbine Wakes and Helicopter Operations Programme  ”

[5] I. Owen, M. D. White, G. D. Padfield, and S. J. Hodge, “A virtual engineering approach to the ship-helicopter dynamic interface – A decade of modelling and simulation research at the University of Liverpool,” Aeronaut. J., vol. 121, no. 1246, pp. 1833–1857, 2017.

Tiltrotors & the Future Transformative VTOL Aircraft: Opportunities and Challenges by Noor Nabi (ESR#3)

From first successful flight by Wright brothers to Airbus A380, and from first flight of Sikorsky’s VS-300 to Boeing’s AH-64 Apache, the aerospace industry has made huge advances in both fixed-wing and rotary-wing aircraft.
Fixed wing allows an airplane to fly by generating lift through vehicle’s forward airspeed. On the other hand, helicopters do not need the vehicle’s forward speed; the lift is generated by the spinning rotary wings. Helicopters have the ability to vertically takeoff and land that allows them to takeoff and land virtually anywhere and access remote areas, however, it has limited capability in speed and range when compared to a conventional fixed-wing airplane. The ambition to combine best of both worlds i.e., an aircraft that has VTOL (Vertical Takeoff and Landing) capability of a helicopter, and speed and range of a fixed-wing airplane, led to the development of several hybrid configurations. Tiltrotor is one such example and is the only rotary convertiplane in service.
Tiltrotors are the ultimate transformers, because not only they transform from one configuration to another during flight, they are also transforming the future of aviation industry. Most of the modern transformative VTOL aircraft, such as Uber Elevate, Lilium jet, Vahana from A3 by Airbus, Project zero by Leonardo helicopters, are inspired by tiltrotors in one way or another.
The hybrid configuration of these transformative VTOL aircraft allows them to operate over a broad flight envelope and thus present a lot of opportunities. The ability to hover like a helicopter and at the same time to fly at relatively high cruise speeds and range make them an effective point-to-point fast means of transportations. Their multi-role capability not only make them ideal for urban air mobility but also for energy & medical services and search & rescue missions.
However, the multi-role capability with large flight envelope pose various technical challenges in designing an aircraft to perform adequately over a wide range of aircraft configurations. These technical challenges include: dramatic change in control strategies with flight conditions and aircraft configurations, Rotorcraft Pilot Coupling (RPC) and structural loads.
In conclusion, the modern rotary VTOL aircraft will be half airplane and half helicopter that will fly long distances at higher speeds. In order to ensure safety and take full advantage of the hybrid capabilities of future transformative VTOL aircraft, various technical challenges need to be addressed at the design phase of the aircraft.

Health Monitoring: the choppers nervous system by Sara Ghiasvand (ESR #2)

It happens to everyone that in some conditions of loading to your body, the body couldn’t tolerate the situation and it will be injured. Body of older persons or individuals with a previous injury are more vulnerable and they are at greater risk of injury. So how you realize that your body is in danger? The nervous system that is distributed all over the body will recognize the pain and brings all the data to the brain and then after analyzing the data your brain finds out what has happened to the body and will decide the next step and will trigger an immediate command before the failure of the body. For example, if body experiences pain inside the knee and this pain signal becomes amplified, the next step is to sit, otherwise it could cause the body to fall down.
Now consider that helicopter structure could sense what is going to happen like human body and could make decision before a complete failure. It means that the structure could sense if it has been strained to the point of damage and could reduce its load-carrying capacity, then report that information in real time before the structure’s safety is compromised or in the case of propagation of damage, pilots will be informed how much time he has left for landing. For many years, such a scenario was more like the stuff of science fiction than fact, but today, structural health monitoring (SHM) systems that can perform these tasks are closer to reality.
The damage tolerance and high strength-to-weight ratio of composites have motivated designers to expand the role of advanced materials in aircraft structures. This practice, however, further complicates inspection of flaws before it causes critical situation. As a result, the aviation industry has recognized the need for more sophisticated and more innovative ways to deploy them in situations where complex structural geometries create accessibility limitations that may impede efforts to locate and identify deeply hidden flaws. “The basic idea of SHM is to build a system similar to the human nervous system, with a network of sensors placed in critical areas where structural integrity must be maintained” says Holger Speckmann, who is the Co-Founder of the SHM-AISC (SHM – Aerospace Industry Steering Committee) (Bremen, Germany) [1].
In general, SHM is a method of integrity analysis of an object via real-time measurements of a set of parameters, which characterize the object’s integrity [2]. The main assignment of SHM system is to alert system operator in case of critical structure situation such as fibre strains or breakage and matrix cracks. The other benefit of damage detection is reduction in the cost of maintenance. Operation and maintenance which can account for more than half of a rotorcraft’s total cost, but health monitoring can reduce those maintenance costs by more than 15% and reduce unscheduled downtime by nearly 50%.
The most common measurement quantity which is used to detect the presence of damage is strain. Devices used for this measurement are commonly referred to as ‘sensors’, measuring a value linearly proportional to a quantity of interest such as deformation. Currently, most sensors employed in SHM systems are either optical fibres or piezoelectric devices [2].
Practically, fibre optic sensors form the most useful class of sensors for SHM systems. Employing an embedded FBG sensors for measurement of distributed stress and strain fields of the composite material has significant advantages. First of all, FBG sensors can be easily embedded into materials to provide damage detection or internal strain field mapping. The FBG sensors supposed to be located in fiber optic cable mounted in the sample. Furthermore, the key feature of FBGs sensors is that the information about perturbations is encoded in wavelength. Indeed, this type of sensor has fantastic compatibility with composite [3].
Although SHM is still immature, research and development has already yielded promising results. It will be hoped that in the near future this system could prevent all the accidents cause by structural failure and help to reduce the cost and time of maintenance.
[2] Fedorov A, Lazarev V, Makhrov I, Pozhar N, Anufriev M, Pnev A, Karasik V, Structural monitoring system with fibre Bragg grating sensors: Implementation and software solution, Journal of Physics: Conference Series, vol. 594, issue 1 (2015) Published by Institute of Physics Publishing
[3] Guo H, Xiao G, Mrad N, Yao J, Fibre optic sensors for structural health monitoring of air platforms, Sensors, vol. 11, issue 4 (2011) pp. 3687-3705