Green Regional Aircraft ITD

Transcription

1 Green Regional Aircraft ITD Prepared by Rocco Pinto (AleniaAermacchi) Clean Sky Call 13 Info Day Paris, 6 th July 2012

2 Clean Sky - General Technical Organization Vehicle ITD Eco-design For Airframe and Systems Smart Fixed-Wing Aircraft Green Regional Aircraft Green Rotorcraft Leaders: Dassault Aviation & Fraunhofer Institute Leaders: Airbus & SAAB Leaders: Alenia & EADS CASA Leaders: Eurocopter & AgustaWestland Transverse ITD for all vehicles Sustainable and Green Engines Leaders: Rolls- Royce & Safran Systems for Green Operations Clean Sky Technology Evaluator Leaders: Liebherr & Thales ITD: Integrated Technology Demonstrator 2

3 GRA Team : ITD Leaders ALENIA AERONAUTICA EADS - CASA ALENIA AERONAUTICA affiliates: Alenia Aermacchi Alenia Sia Alenia Improvement SuperJet International Fraunhofer-Gesellschaft LIEBHERR ROLLS ROYCE SAFRAN THALES ROLLS ROYCE affiliate: Rolls Royce Deutschland SAFRAN affiliates: Snecma Messier-Dowty Hispano-Suiza THALES AVIONICS affiliate: Thales Avionics Electrical System 3

4 GRA Team : Associates AIR GREEN Cluster with following members: Piaggio, Italy, single-voice Cluster's representative Polo delle S&T, Univ. Naples, Italy Centro Sviluppo Materiali (CSM), Italy IMAST, Italy (technological district) FoxBit, Italy Sicamb, Italy Politech. Turin, Italy Univ. Bologna/Forlì, Italy Univ. Pisa, Italy ATR CIRA PLUS Cluster with following members: CIRA, Italy, single voice Cluster's representative Dema, Italy Aerosoft, Italy INCAS, Romania Elsis, Lithuania A sizeable amount of activities are reserved to Call for Proposals open to European Institutions and Industry HELLENIC AEROSPACE INDUSTRY ONERA 4

5 GRA ITD - Headquarters members : Map Liebherr Atr Eads-Casa Madrid Rolls Royce London C-130 compatible loading system Safran Thales Paris & Neuilly Onera Chatillon Toulouse Fraunhofer Munc hen Vilnius Cira Plus (Elsis ) AirGreen ( Poli To) AirGreen Cira Plus (Incas) (Piaggio, CSM, Turin Bologna Sicamb ) Bucharest AirGreen (UniBo) Alenia Aeronutica Pisa Air Green (Imast, Foxbit, UniNa) AirGreen (UniPI) Cira Plus - (Cira/Dema/Aerosoft ) Romea Foggi a Naples Schimatari Landing gear b for unprepared strips Toulouse uilt 16 cockpit windows provide excellent visibility Hellenic Aerospace 5

6 GRA Overview GRA program was launched on 1 st September 2008 (GRA Kick-Off: October, 7 th -8 th 2008), and will allow future regional aircraft to obtain weight reduction, aerodynamics efficiency and an higher level of operative performance w.r.t. year 2000 technology level. In order to achieve these so challenging results, the aircraft will be entirely revisited in all of its aspects. In fact GRA consists of five technological domains: Low Weight Configuration (LWC), Low Noise Configuration (LNC), All Electric Aircraft (AEA), Mission & Trajectory Management (MTM) and New Configuration (NC). 6

7 Low Weight Configurations Enabling Technology A multifunctional single layer is a structure in which different materials are integrated - in order to assure several functions - in a way that is impossible to identify them as separate layers A multifunctional multi-layer is a structure in which different materials are integrated, in order to absolve several functions WEIGHT REDUCTION Multifunctional Multilayer Multifunctional Layer Noise Damping Flame Smoke and Toxicity resistance Environment barrier Lightning strike Protection Self-healing Impact resistance Structural property GRA-LWC Technologies WEIGHT REDUCTION Carbon nanotube strengthened epoxy resin for increased compression and interlaminar shear strength in composites (fuselage and wing) Nanomaterials Nanotubes Self-healing Sensors: Fiber Optic Bragg Grating (FOBG) Structural property Conductive BRAGG GRATING Damping Flame resistant FIBER OPTIC TERMINATION Cobonded J-spar with embedded FOBG sensors 10

8 Low Noise Configurations Load Control Low Noise Configuration Low noise aircraft configuration, consisting of the innovative solutions of the wing high lift devices and of the landing gear installation enabling the generation of less aerodynamic noise while performing their other basic functions at a high level of efficiency. Innovative Technologies: Active Load Control concepts for Load alleviation and highly-efficient aerodynamics Passive flow control Technologies HLD Low Noise Technologies MLG & NLG Low Noise Technologies Laminar flow concept Load Control Technology Wing advanced load control concepts aimed at improving aerodynamic efficiency and alleviate loads over the entire flight envelope will be addressed. 11

9 Low Noise Configurations Natural Laminar Flow A Natural Laminar Flow (NLF) Wing will be designed as baseline configuration for the further technology development integrating loads control, passive flow control and HLD low-noise concepts The NLF wing will be sized to be compliant with a next-generation, 130 pax A/C at M=0.74 cruising flight condition CFD mesh TURBULENT TRANSITION UPPER LOWER 12

10 Low Noise Configurations Passive Flow Control Advanced concepts, based on passive flow control devices, aimed at reducing skin friction on NLF wings at cruising flight conditions will be pursued. Following technologies will be considered: micro-riblets in the turbulent flow region to reduce turbulent skin friction innovative surface treatments (micro-roughness) to delay laminar-turbulent flow transition 13

11 Low Noise Configurations Airframe Low Noise HLD Low Noise Technologies HLD passive low-noise treatments (porous materials, brush-like devices) to reduce noise emissions due to flap side edge vortices and slat upper TE vortex shedding HLD low-noise design (conventional and gapless solutions) based on multi-element wing camber aerodynamic optimisation and innovative kinematics to reduce noise induced by slots & tracks HLD advanced low-noise concepts (morphing structures, smart actuation) HLD highly-efficient, low-noise design through active (synthetic jets) flow control MLG & NLG Low Noise Technologies MLG and NLG low-noise configurations addressing mature and innovative concepts (gear strut and wheel pack optimised shaping, vortex flow control, etc.) 14

12 All Electrical Aircraft Main objectives of AEA is to demonstrate the feasibility of on-board systems new technologies and architectures enabling the application of the All- Electric approach for a Regional airplane which aims: to completely delete the Pneumatic and Hydraulic power to enhance the Electrical power to apply new technologies which optimise the energy usage (Electrical and Thermal Energy Management) thus contributing to Specific Fuel Consumption reduction (estimated around 2-3%, based on previous preliminary studies) Main function/systems affected by AEA concept: Electrical Power Generation & Distribution Power electronics Electrical engine starting Electrically powered cooling/heating and compression (ECS, Ice Protection, equipment cooling) Electro-mechanical Actuation (EMA) 15

13 Mission & Trajectory Management Integration and validation of new optimised missions and trajectories by using of a flight simulator The architecture and advanced functions of avionics utilising the technical solutions studied in other Clean Sky ITD s for the advanced flight guidance and flight management functions 17 Clean Sky Info Day Toulouse 1rst February 2011

14 New Configurations Next generation of Regional A/C will be strongly affected by the Green Requirements ; New aircraft, systems architectures and advanced configurations might be necessary to accomplishing such requirements; Moreover integration of new technologies, propulsion in particular, will affect the overall A/C sizing; Careful assessment is required to evaluate eco benefits, and overall competitivity as well; 18

15 GRA - DEMONSTRATIONS Demonstration Advanced technologies will be assessed through a cost effective mix of ground and flight tests covering the technical solutions of integration of airframe, systems and engines at aircraft level. In this respect, full scale structural ground tests, large scale aerodynamic and aero-acoustics wind tunnel tests, and flight simulators have been considered. With reference to the generic regional aircraft type, the following Demonstrators will be produced: Cockpit Flight Demonstration Ground Demonstration Aerodynamic and Aeroacoustic WT test 21

16 GRA ITD Master Plan Basic CS-GRA MPP Reference Top-Down Schedule based on high level assumptions 22

17 List of Topics for Call 13 JTI-CS-GRA Clean Sky - Green Regional Aircraft 1 400, ,000 JTI-CS-GRA-01 Area-01 - Low weight configurations 400,000 JTI-CS GRA Methodology platform for prediction of damage event for self sensing curved composite panel subjected to real load conditions 400,000 JTI-CS-GRA-02 Area-02 - Low noise configurations 0 JTI-CS-GRA-03 Area-03 - All electric aircraft 0 JTI-CS-GRA-04 Area-04 - Mission and trajectory Management 0 JTI-CS-GRA-05 Area-05 - New configurations 0 23

18 JTI-CS GRA GRA : Methodology platform for prediction of damage event for self sensing curved composite panel subjected to real load conditions. Objectives: Main expectances To develop a methodology platform for impact and damage detection of a sensorised curved composite panel. All possible impact scenarios (hail, tool drop) and failure modes on a full scale crown fuselage panel have to be considered. Fundamental is the extension of existing state of the art SHM methodology platform for flat composite stiffened panel to large scale curved composite panel subjected to real load conditions To provide self-diagnostic capabilities platform: prior to its application, the health of the sensors and their connection will be checked to avoid any false alarm. The platform main functions are divided into three categories : 1) Passive sensing (for impact location and force magnitude detection) 2) Active sensing (for dimension damage detection, position and proper damage severity index evaluation) 3) Optimal sensor positioning (in terms of number, kind of sensor and probability of detection). To set test procedure for a flight test to collect SHM data and to compare experimental/predicted values. Application to be performed: 1)Modelling and simulating of a curved stiffened panel of size 5 m x 1.7 m with radius 4.5 m using FEM codes for both Passive / Active sensing and sensor position optimisation, 2)Integrate transducer models with the FEM to carry out the actuating and sensing in the damage characterisation code. 24

19 JTI-CS GRA Special skills: 1. Demonstrable experience and capabilities for modelling guided wave methods for aerospace composite stiffened panels, 2. Experience at modelling impact and damage in composite panels, 3. Knowledge and experience in large scale FE analysis, dynamic analysis and fracture mechanics, 4. Knowledge of the state of the art at European level research of methodologies developed in aircraft composite, 5. Knowledge of high level programming for developing interactive and open environments, 6. Previous track record in development of SHM methodologies / platform for composite stiffened Expected deliverables: Duration: 24 Months ; Topic value: 400 k 25

20 2012 by the CleanSky Leading Partners: Airbus, AgustaWestland, Alenia Aeronautica, Dassault Aviation, EADS-CASA, Eurocopter, Fraunhofer Institute, Liebherr Aerospace, Rolls-Royce, Saab AB, Safran Thales and the European Commission. Permission to copy, store electronically, or disseminate this presentation is hereby granted freely provided the source is recognized. No rights to modify the presentation are granted. 26