Annual Report Summary Green Regional Aircraft (GRA) The Green Regional Aircraft ITD

Transcription

1 Annual Report Summary Green Regional Aircraft (GRA) The Green Regional Aircraft ITD Green Regional Aircraft ITD is organised so as to: 1. develop the most promising mainstream technologies regarding Low Weight Configurations (LWC) and Low Noise Configurations (LNC) best fitting the requirement of greening the regional aircraft; 2. integrate technical solutions from the mainstream technologies and from other technology domains (Energy Management, Mission & Trajectory Management (MTM), Advanced Engines, Eco Design, New Configurations) in the Demonstrators of the Green Regional Aircraft, using a multidisciplinary approach. The following schematic is the high level WBS of the GRA Project. GRA GRA LNC LWC integration Integration New A/C a/c Configurations All Electric a/c A/C Mission & Trajectory Mgmt

2 Achievements The GRA work plan in 2011 focused on the following activities: - Requirements for the definition of the generic future regional aircraft and for ground and flight Demonstration; structural definition of peculiar items of advanced aircraft configurations; test report for all developed technologies for multilayer materials has been completed. The development of methodologies for probabilistic structural real design is still ongoing and will be completed in next six months; final evaluation of the analysis and tests results of developed nanomaterial. Flat large panels with different technologies selected after the first down selection test article design has been performed, started the manufacturing. Definition of technical solutions on empennage, wing, fuselage/cockpit of the future generic regional aircraft utilising the selected technologies is progressing. Definition of structure components to be tested in flight has been completed; engineering and manufacturing data to prepare the test article for flight test is started and in progress; the activities for providing lay out and installation of advanced components to be tested in flight and manufacturing; plan of advanced components and the definition of a preliminary flight test plan is also started. Design & Manufacturing preparation of test rig and test article is started. - First down-selection of High-Lift Devices (HLD) Technologies tailored to Natural Laminar Flow (NLF) wing (130-seat rear-mounted engine Green Regional A/C) and Turbo Prop (90-seat) Regional A/C wing configurations, by taking into account high-lift performance, noise impact, actuation/ kinematics concepts. Both conventional architectures (single and double-slotted T/E flap, Krueger slat) and innovative concepts (smart droop nose and morphing T/E flap), as well as active flow control (synthetic jets) and low-noise passive solutions (flap side-edge fence, acoustic liners), have been assessed on a multidisciplinary basis, considering results from aerodynamic and aero-acoustic CFD/CAA analyses, virtual modelling of kinematic system, structural/ actuation testing on small mechanical prototypes, etc. Further development and assessment of Load Control & Alleviation (LC&A) Technologies, considering both conventional and innovative wing control movables, to reduce induced drag, through optimal wing load distribution (LC function), and wing structural loads (wing bending and torsion moment) from gust and manoeuvre (LA function).to this aim, wing trailing edge devices, split ailerons, ailerons symmetric deflections, mini tabs, are among those concepts sized to a NLF wing configuration under study in a multi-physics view (LC&A performance evaluation, actuation system conceptual design, structural integration, etc.) by means of advanced CFD/CSM tools, CAD/CAE, FEM models, etc. In this context, aero-elastic tailoring parametric studies, implying dynamic modal analyses, steady (divergence) and unsteady (flutter) aeroelasticity checks, have been performed both in cruise and high load factor conditions to assess the sensitivity of LC&A devices performance to wing box structural stiffness.

3 Furthermore, modelling of Control Laws, Loads Estimator, Sensors and Actuators has been carried out for designing the preliminary architecture of an active loads control system for gust load alleviation. First part of aerodynamic and aero-acoustic Wind-Tunnel Tests campaign on Wing / High-Lift Devices 2D models in INCAS subsonic facility. Such testing activity is aimed at validating high-lift performance and low-noise solutions of HLD for NLF wing (130 seat A/C) and Turbo-Prop (90 seat A/C) configurations. Manufacturing of full-size test articles of NLF wing flap morphing structures is in progress. Relevant mechanical tests are going to validate the two actuation concepts addressed, respectively Deeply Embedded Smart Actuators and Smart Actuated Compliant Mechanisms. Definition of general requirements for the Wind-Tunnel Experimental Validation of NLF wing and LC&A integrated technologies through an innovative wing flexible scaled model, representative of the full-size wing structural deformation under aerodynamic loads. Such tests are aimed at validating wing aerodynamic design and steady aero-elastic performances of LC&A devices at transonic speed and high Reynolds number, close to in-flight conditions. This activity is planned to be performed through a project under CfP. The relevant Topic Description (JTI-CS GRA ) has been published on January 13 th, Workshops have been held beforehand, at Alenia plant and at Clean Sky JU premises, in order to present to potential Partners objectives and content of this challenging collaborative project. Aerodynamic Design of a Transonic Natural Laminar Flow Wing, sized to a Green Regional rear-mounted engine 130-seat Aircraft, relying on experience and achievements of a NLF wing concept addressed in the technologies maturation phase. Trade-off studies are on going to optimise wing plan form (AR, sweep,..) and wing profiles at specified design points (Mach, CL), looking for the best compromise between aerodynamic efficiency in cruise condition and low-speed performance, and to also account for impact on structural weight. - AEA (All Electrical Aircraft) requirements & architectures: Final Updating of Integration requirements and Architecture of the On-Board Systems for Future Green Regional Aircraft and for ground and flight Demonstration; Final V&V plan for energy management demonstration into GRA. AEA technologies for Systems (Methods & Tools): Implementation of the Level 1 (Architectural) and Level 2 (Functional) GRA AEA systems simulation and cabin thermal models and of the Shared Simulation Environment (SSE). Application studies: Analysis of function and performance of the on board systems either for All Electrical future regional A/C and for to the on ground and in flight demonstration of the Energy Management. Detailed Definition of the Systems modifications to be introduced on Demo a/c and preparation of Modification technical dossiers.

4 Definition of the Preliminary Energy Management logics for an on-ground and in flight demonstration. - Updating of MTM functionalities and scenario analysis document in case of relevant input coming from SESAR; finalization of avionics architecture and basic prototyping tool architecture definition. - TLAR (Top Level A/c Requirements) last definition phase and power plant specifications (Loop 2). Validation and verification strategy and plan finalization: planning of activities oriented to verify the feasibility. Preliminary GTF (Geared Turbo-Fan) sizing under wing installation configuration definition. Relevant data (trajectories, mission results, etc.), noise and engine emissions evaluation for the Technology Evaluator for Green A/C (main results of Loop 1 activities). Green Power plant architecture, technology and modeling, performance and emission data started (2nd loop). Power plant / Airframe integration: analysis has been performed in order to evaluate adopted architectures integrated solutions foropen Rotor (OR) (1 st loop).

5 The main technical achievements in 2011 are: For LWC (Low Weight Configuration) Requirements for the definition of the generic future regional aircraft and for ground and flight Demonstration; Structural definition of peculiar items of advanced aircraft configurations; Coupon manufacturing, testing and results analysis of enabling technologies for the first down selection; Flat large panels with different technologies selected after the first down selection test article design has been performed; New Composite panel for Fuselage to be tested Al-Li laser welded panel for Wing to be tested

6 Lay out of advanced components installation to be tested in flight; General lay out of demonstrator to be tested in ground; For LNC (Low Noise Configuration) First down-selection of High-Lift Devices Technologies tailored to NLF wing (130-seat rear-mounted engine Green Regional A/C) and Turbo Prop (90-seat) Regional A/C wing configurations ; Further development and assessment of Load Control & Alleviation Technologies, considering both conventional and innovative wing control movables; First part of aerodynamic and aero-acoustic Wind-Tunnel Tests campaign on Wing / High-Lift Devices 2D models in INCAS subsonic facility; CADS Models Models parts manufactured

7 Definition of general requirements for the Wind-Tunnel Experimental Validation of NLF wing and LC&A integrated technologies through an innovative wing flexible scaled mode; Aerodynamic Design of a Transonic Natural Laminar Flow Wing, sized to a Green Regional rear-mounted engine 130-seat Aircraft. For AEA (All Electrical Aircraft) AEA requirements &architectures of the On-Board Systems for Future Green Regional Aircraft and for ground and flight Demonstration; AEA technologies for Systems (Methods & Tools); Application studies: Analysis of function and performance of the on board systems; Implementation, analysis and Integration of Energy Management Functional logics for Future Regional Aircraft and for the on ground and in flight demonstration; GRA AEA in-flight Demonstration Modification Detailed Definition in progress For MTM (Mission and Trajectory Management) Definition of Safety requirements (2 nd release); Definition of Avionics Architecture; Preparation of basic ATM scenario model; Preparation of upgraded advance communication model; Start of green FMS development; Finalization of Basic Prototyping tool;

8 Progressing on the activities relevant to the set-up of basic version of GRA flight simulator. GRA flight simulator in its basic configuration; Basic FMS have been integrated and tested For NC (New Configurations) GRA aircraft simulation model reference aircraft (TP & TF) 1 st release; (TP Turboprop, TF Turbofan) GRA aircraft simulation model (GRASM) green conceptual aircraft (TP & ATF) 1 st release; (ATF Advanced Turbofan) GRA aircraft simulation model green conceptual aircraft (GTF) spot points; GTF preliminary under wing integration studies; Analysis of Aerodynamic data-base for OR configuration.