Projects



En cours

PROJET 18: AERODYNAMICS STUDIES FOR RADARS
In this project, realized in collaboration with FLIR company in Montreal, radar systems are tested in the subsonic Price-Paidoussis wind tunnel at the LARCASE.

PROJET 17: OPTIMISATION OF AIRCRAFT FLIGHTS
In this project, realized in collaboration with the Romanian Airline TAROM in Romania, aircraft flight trajectories are optimized for their use by pilots in the real flight of aircraft.

PROJECT 16: FLIGHT MANAGEMENT PERFORMANCE OPTIMISATION II
In this project, realized in collaboration with CMC Electronics-Esterline, the main objective is to optimize the vertical and horizontal path of the aircraft within the Flight Management System by taking into account the Required Time of Arrival, the wind grids and meteorological conditions. The main motivation of the project is to reduce overall carbon emissions and flight costs. This project is funded by the Green Aviation Research Development Business Led Network GARDN in its second round.
PROJET 15: CRIAQ MDO-505 - MORPHING ARCHITECTURES AND RELATED TECHNOLOGIES FOR WING EFFICIENCY IMPROVEMENT
In this project, realized in collaboration with Thales, Bombardier Aerospace, École Polytechnique, IAR-CNRC, and also with italian researchers from Frederico II Naples University, CIRA and Alenia, a wing-aileron prototype will be designed, tested and validated using win tunnel tests at IAR-NRC. The aim of the project will consist in the improvement of the aerodynamic performances of this prototype.

In Canada, the university collaborators are : Profs Simon Joncas (ETS) and Eric Laurendeau (École Polytechnique), the industrial collaborators are : Mr Philippe Molaret (Thales Canada), Dr Patrick Germain and Dr Fassi Kafyeke (Bombardier Aerospace). The collaborators at IAR-CNRC are: Mr Mahmood Mamou, Dr Youssef Mebarki and Mr Brian Jahrhaus (IAR-CNRC).

In Italy, the collaborators are : the professors Leonardo Lecce and Rosario Pecora from Naples University, Dr Antonio Concilio from CIRA and Dr Salvatore Russo (Alenia).


Canada Team 2012

Italy Team 2012

PROJECT 14: CANADA RESEARCH CHAIR IN TECHNOLOGIES FOR AIRCRAFT MODELING AND SIMULATION
The Chair’s activities, that started on 1st of January 2011, will revolve around two main research axes: (1) aircraft and helicopter flight dynamics and control; and (2) active control technologies for deformable aircraft.

In the first axis, new modeling and simulation methodologies for aircraft and helicopter flight dynamics and control will be designed. Using flight test data, non-linear optimization algorithms will be developed to identify and validate aircraft and helicopters.

In the second axis, the LARCASE team will use geometric data to analyze aircraft stability. The shape of wings and other geometric surfaces of autonomous aerial systems will be modified using active control systems, to enhance the aerodynamic performance of aircraft.

The subsonic blown down wind tunnel Price-Païdoussis (please see the photo in project 12) and the aircraft research flight simulator(please see the photo in project 9) and an unmanned aerial system UAS designed and manufactured by Hydra Technologies (please see the next photo) will be used in axes 1 and 2 of the Canada Research Chair.

The UAS was obtained with research funds from Canadian Foundation for Innovation CFI, Ministère du Développement économique, innovation et exportation MDEIE and Hydra. The research performed on the UAS will be realized in collaboration with Hydra.


Hight Performance Reserach UAV Hydra Technologies S4

PROJECT 12: VALIDATION OF AEROELASTICITY STUDIES USING THE PRICE-PAIDOUSSIS BLOWN DOWN WIND TUNNEL
Following the donation of the Blown Down Subsonic Wind Tunnel by the Emeritus Profesor Michael P. Païdoussis from McGill University to Dr Botez, aeroservoelastic (aeroelasticity and control) studies will be done at LARCASE. This wind tunnel was designed and obtained with FCAR and NSERC research funds by both professors Stuart Price et Michael P. Païdoussis, two experts in fluids-structure interactions, vibrations and nonlinear dynamics, aeroelasticity and aeroservoelasticity.The wind tunnel will be useful for collaborations between professors Ruxandra Botez and Michael Païdoussis.

Blown Down Subsonic Wind Tunnel

PROJECT 11: FLSIM FOR BUSINESS AIRCRAFT MODELING
FLSIM software will be used for the flight dynamic studies for business aircraft in collaboration with Presagis


PRESAGIS - ETS LARCASE

PROJECT 10: GREEN AIRCRAFT TRAJECTORIES OPTIMIZATION STUDIES
This project, in collaboration with CMC Electronics - Esterline is part of the new Excellence Center Network directed by the Green Aviation Research and Development Network(GARDN) recently funded by the Canadian Government. In this project, the aircraft trajectories will be analyzed for the reduction of the fuel consomption and the polluant emmissions in order to realize green aircraft studies. The industrial collaborators on this project are Mr Rex Hygate, Mr Dominique Labour, Mr Hugo Houde, Mr Reza Neshat, Mr Claude Provencas et Mr Michael Gordon Smith from CMC Electronique - Esterline.


CMC Electronique - ETS LARCASE - GARDN

PROJECT 9: CESSNA CITATION X AIRCAFT STABILITY ANALYSIS BASED ON ITS GEOMETRICAL DATA - VALIDATION WITH LEVEL D RESEARCH AIRCRAFT SIMULATOR FLIGHT TESTS
A new methodology and code for the Cessna Citation X will be conceived for the determination of the stability derivatives from the aircraft geometrical data and will be used in the preliminary aircraft design. In this preliminary phase od deisgn and conception of new aircraft, the aeronautical companies would minimize thier decision time on the geometrical aircraft design. The main industrial collaborators on this project are Mr Ken Dustin, Mr Denis Pelletier, Mrs Alexandra Savidis, Mr Peter Jarvis and other engineers: Allan Cofin, Cleo Fontaine - Lavoie, Christian Hould, Mitchel Golemic, and others.

The flight simulator (IPT) for the Cessna Citation X aircraft which is the fastest business aircraft, is equipped with a modifiable aerodynamical model for reseach purposes. This simulator was conceived by CAE Inc. and was obtained through the Canadian Funds for Innovation CFI, Ministère du Développement économique, innovation et exportation MDEIE and CAE Inc. Its orginal conception will allow the LARCASE team to perform different research projects in collaboration with CAE Inc.

CAE IPT Level D Simulator at LARCASE
Cessna Citation X


Completed

PROJECT 8: CRIAQ 7.1 - CONTROLLER DESIGN AND VALIDATION FOR LAMINAR FLOW IMPROVEMENT ON A MORPHING RESEARCH WING - VALIDATION OF NUMERICAL STUDIES WITH WIND TUNNEL TESTS
In this CRIAQ 7.1 project lauched during the second CRIAQ round, called Improvement of laminar flow on a research wing, the laminar to turbulent flow transition on a wing with a flexible skin on its upper surface will be controlled and therefore delayed by use of kulite pressure sensors and smart actuators in a wind tunnel. This project is realized in collaboration with Thales Avionics, Bombardier Aerospace, Ecole Polytechnique and LAMSI team at ETS.

The LARCASE team conceived, integrated and validated a controller for the transition delay on a Morphing Wing which changed its shape, by use of Smart Material Actuators and pressure sensors. The controller was validated by LARCASE team using Wind Tunnel Tests at the Institute of Aerospace Research ((IAR) - The National Research Council (NRC). The industrial collaborators in this project are Mr Philippe Molaret (Thales Canada), Dr Eric Laurendeau and Dr Fassi Kafyeke (Bombardier Aerospace), Mr Mahmood Mamou, Dr Youssef Mebarki and Mr Brian Jahrhaus (IAR-NRC).

Team in the beginning of the project in 2006
 
Team partners at the IAR-NRC Wind Tunnel
Wing used during the first Wind Tunnel tests for transition detection by use of optical sensors
 
 
Andrei Vladimir Popov and Lucian Teodor Grigorie - Bench controller tests at LAMSI
 
NRC and LARCASE teams at the IAR-NRC Wind Tunnel

PhD student Andrei Vladimir Popov - LARCASE


The first film (1ST WTTs) shows a sequence from the first wind tunnel tests on the morphing wing equipped with optical and kulite sensors, as well as with SMAs. We can see the optical sensors pressure system, the wing in the wind tunnel, the cases shown on the screen, as well as the teams.
 
 
 
The second film (2ND WTTS) shows a sequence from the second wind tunnel tests on the morphing wing equipped with kulite sensors and SMAs. We can see the controller system, the wing in the wind tunnel, the cases shown on the screen, as well as the teams.
 

The third film (3RD WTTS) shows only the morphing wing concept in the IAR-NRC WInd Tunnel.
 

PROJECT 7: AEROSERVOELASTIC INTERACTIONS STUDIES FOR THE F/A-18 SRA, ATW AND AAW - VALIDATION WITH FLIGHT FLUTTER TESTS (PROJECT SINCE 1998)

The aeroservoelasticity works are realized in collaboration with NASA Dryden Flight Research Center (DFRC)in 3 well known aeroservoelasticty projects using the flight data for the following airplanes: F/A-18 Systems Research Aircraft(SRA), the Aerostructures Test Wing (ATW) and the F/A-18 Active Aeroelastic Wing (AAW). The industrial collaborator in this project is Mr Marty Brenner from NASA DFRC. Other collaborators from NASA DFRC between 1998 and 2003 are: Dr Kajal Gupta, Mr Tim Doyle, Mr Ed Hahn, Mr Roger Truax andt Dr Can Bach.

These flight test data are used for:
  1. the validation of new methods of conversion of aerodynamic forces from the frequency domain into the Laplace domain,
  2. the conception of new algorithms for the ’interactions between aircraft rigid, elastic and control modes and
  3. the elaboration of new parameter estimation methods by use of fuzzy logic, neural network, etc.


This research work is mainly funded by FQRNT and NSERC in the period of time 1998-2002 and since 2002 by MDEIE and NSERC.

NASA DFRC researchers Mr Sunil Kukreja and Mr Marty Brenner visits and presentations at ETS
 


Video on the aeroservoelastic interactions analysis on the F/A-18 SRA

This video shows the results of the research on the interaction of rigid, control and elastic modes on the F/A-18. There are two parts in this video. In the case when this interaction is not well analyzed, the aircraft has a non-realistic and unstable behaviour. In the case when the interaction is well done, the aircraft becomes stable. For details on this research, please see article 10 in the section 'Accepted Publications''. Dr Lucian Grigorie and Dr Adrian Hiliuta reaized this video.
 
 

PROJECT 6: MODELING AND SIMULATION OF UNDERWATER UNMANNED VEHICLES (UUVs)
This project, started in 2008, and is realized in collaboration with Dr Ioana Triandaf from US Naval Research Institute in Alexandria, USA.. Main objectifs of this project are:

The Firts objectives are:
  • The determination of the kinematic model and its equations of motion
  • The hydrodynamic forces calculations
  • The implementation of the UUV model and its automatic pilote

The 2nd objectives are:
  • The constrained energy optimisation
  • Planning of the optimal trajectories for the low energy research,
  • Optimal surface by use of Multiples UUV's


Ottawa 2009
 

PROJECT 5: X-31 AIRCRAFT STABILITY ANALYSIS FROM ITS GEOMETRICAL DATA - VALIDATION WITH WIND TUNNEL TESTS
This research work is part of the global NATO international project entitled Prediction methods of stability and control of aerial and marine vehicles, realized in collaboration with participants from DLR, US Air Force Academy, NASA Langley Research Center, ONERA, FOI, NW-NWB, EADS, UNIVERIST BRAUNSCHWEIG, NWB LSWT, NAL, TAI-ODTU, DSTL, BAE-SYSTEMS, NANGIA AERO RESEARCH, UNIVERSITY OF LIVERPOOL, IIHR-HYDROSCIENCES  & ENGINEERING, OINETIQ, etc. The industrial leaders of this project are Dr Andreas Schutte from DLR Germany and Dr Russ Cummings (US Air Force Academy).

The LARCASE team will calculate the stability and control derivatives will be calculated for the military X-31 aircraft, by use of its geometrical data and Wind Tunnel Test results (realized at DLR and Nasa Langley Research Center). Research on this project started in 2008.


  La maquette de l'avion X-31 en soufflerie

PROJECT 4: STABILITY ANALYSIS FOR THE HAWKER 800 XP AIRCRAFT FROM ITS GEOMETRICAL DATA - VALIDATION WITH FLIGHT TEST DATA
In the CRIAQ 3.2 project (first CRIAQ round) entitled Integration of the flight real time simuation with the Computational Flight Dynamics, new methods of stability derivatives were conceived by Concordia and McGill Universities team, using CFD knowledge. The LARCASE team conceived a new code and algorithm based on semi-empirical references from the literature (instead CFD) to obtain the stability derivatives.

This project was funded by CAE Inc. and CRIAQ. Research on this project started in 2003. The industrial project leader of this project is Mr Peter Jarvis from CAE Inc.




Team project kick-off meeting at CAE in 2004
 


Vidéo du code concu au LARCASE pour le calcul des dérivées de stabilité en se basant sur la géometrie de l'avion

Ce vidéo, réalisé par l'étudiant à la maitrise Dumitru Popescu de LARCASE, montre les resultats obtenus par notre code in-house, conçu et développé pendant 5 ans, en Matlab - en se basant sur les références provenant de US Datcom et d'autres références plus récentes en aérodynamique. Nous utilisons pour ce film, les données géométriques d'un avion non-confidentiel. On peut voir qu'a partir d'un minimum des données géométriques pour un avion, les coefficients aérodynamiques de la portance, trainée, moment ainsi que les dérivées de stabilité sont rapidement calculés.

Pour ce projet, ces resultats ont été validés avec des données des essais en vol sur le Hawker 800 XP. Ce travail est utilisé pour: le design préliminaire des avions (et même de leur composantes séparées), ainsi que dans les analyses de stabilité des avions en se basant sur un minimum des données géométriques et même des essais en vol.
 
 

PROJECT 3: MULTIDISCIPLINARY OPTIMISATION MOSAIC - LOADS OPTIMISATION (2003-2006)
In this CRIAQ 4.1 project (lauched during the first CRIAQ round) MOSAIC, different universities and industriels worked together to optimize the aircraft, helicopters and engines design. Project team members were from Bombardier Aerospace, Bell Helicopter Textron and Pratt & Whitney, as well as from l’École Polytechnique and Concordia University. This project was funded by CRIAQ, Bombardier Aerospace, Bell Helicopter Textron and Pratt & Whitney. The academic leader of this project was Dr Jean Yves Trepanier from Ecole Polytechnique. The industrial collaborator for this project was Dr Francois Pepin from Bombardier Aerospace.

The LARCASE team conceived, in collaboration with Bombardier Aerospace team, a new optimization algorithm of load cases on the CL-604 aircraft,, to obtain the miinimum and most important load cases for the optimal design of the CL-604.


Team meeting at École Polytechnique in 2006

PROJECT 2: AERODYNAMIC FORCES CALCULATIONS FOR AEROSERVOELASTIC INTERACTIONS STUDIES (2004-2007)
This project was realized in collaboration with Bombardier Aerospace. A high number of new methods for the aerodynamic forces conversions from frequency to Laplace domain for the aeroservoelastic interaction studies on the CL-604 were conceived. This project was funded by Bombardier Aerospace and NSERC. Bombardier team validated the numerical algorithms in the McGill WInd Tunnel. The industrial collaborators are Mr Nicholas Stathopoulos, Mr Sylvain Therien, Mr Alexandre Rathe and Mr Martin Dickinson from Bombardier Aerospace.



Mr Sylvain Thérien, Bombardier, during his presentation
at the Students Aerospace Forum SAF in 2007

PROJECT 1: IMPLEMENTATION OF GLOBAL MODEL PARAMETER ESTIMATION TECHNOLOGY FOR THE BELL 427 - VALIDATON WITH FLIGHT TESTS
In the CRIAQ project 3.4, the LARCASE team in collaboration with NRC and BHT teams validated a methodology to analyze the aerodynamic critical cases for helicopters and to conceive a global model for the B-427 helicopter. These cases were the following: auto-rotation, transition, close manoeuvres to the flight envelope corners, ground dynamics, hover, forward flight and ground reaction which represent challenges for the experts in the parameter estimation methods. This methodology was validated by flight tests at BHT where was used for level D high fidelity simulator certification according to FAA rules. The industrial leaders are Mr Ed Lambert and Mr Joey Seto (Bell Helicopter Textron) and Mr Ken Hui (IAR-NRC)

The main avantage of this new methods resulted in an important reduction of flight test number, that reduced the cost and the time needed for the development of new helicopters. This new approach allowed the reduction of approximately 60% of the development cycle. This project was funded by Bell Helicopter Textron and CRIAQ. Research on this project started in 2003 and ended in 2009.



Team photo taken at BHT
Bell 427


Video of the Bell-427 flight simulation based on flight test data - by Mr Andrei Popov, PhD student at LARCASE
 
 

Video of the Bell-427 autorotation landing based on flight test data - by Mr Andrei Popov, PhD student at LARCASE
 

Ground dynamics for the Bell-427 based on flight tests - by Dr Michel Nadeau Beaulieu, CAE (PhD student graduated in 2007 at LARCASE)