Clean Sky 2. LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels th December 2012 OUTLINE

Transcription

1 Clean Sky 2 LifeCraft Demonstrationt (IADP RC 2 & ITDs) Consultation meetings Brussels th December LifeCraft - The Compound Demo OUTLINE Presentation of the Compound R/C Concept Impact & Objectives Schedule Major Technical Challenges Components & Subsystems 2 2 1

2 LifeCraft - The Compound formula A new, game-changing rotorcraft Not an airplane, not a helicopter, but a compound VTOL architecture that retains the best of both aircraft types Features: Fixed wing for energy efficient lift Open propellers for high speed propulsion Main rotor for energy efficient vertical flight Anti-torque & yaw control with propellers No tail rotor Variable speed rotor and props Unique capabilities: Vertical flight with same agility as helicopter Cruise speed up to 220 kts(410 km/h) eco speed Flight experience started with X3 3 3 High Level Objectives for Compound R/C concept (LifeCraft /RC2) Time efficiency & mission productivity: Emergency evacuation 200 km in less than 30 min Travel 550 km gate-to-gate in less than 90 min (to/from remote areas) Greening: Acoustic footprint (SEL) less than conventional H/C in same class Fuel/ CO 2 per kilometer Eco-friendly materials & industrial processes EU competitiveness & growth: De-risk the compound rotorcraft concept ; Enable development & marketing prior non-eu competitors to secure growth 4 4 2

3 Demo Development Plan CDR Prelim Studies, Architecture, Specifications TR-FC CleanSky results Components & subsystems development & testing(*) Flight testing, Demo op. envir t TRL6 CDR Prelim Studies, Architecture, Specifications TR-FC Components & subsystems development & testing(*) Flight testing, Demo operat. envir t (*) NB: Components & subsystems development may be performed partly in ITDs TRL6 5 5 Major Technical Challenges Weight, weight, and weight Even more crucial than for helicopters, why? Addit al components: wing, props, gearboxes, shafts Stronger airframe for high speed: dynamic pressure, bird impact Fully stowable landing gear High power engines and transmission chain Aerodynamic efficiency: Take-Off Weight capability Lift-to-Drag ratio in cruise Anti-torque function and yaw control in hover Control & optimisation of: Attitude, RPM, Lift/Thrust split across flight envelope 6 6 3

4 CS2 LifeCraft Components & Subsystems Dynamic systems (rotor, props, main gear box, suspension system, hydraulics & controls) Project coordination, architecture, performance, specification, general engin., final assy,ground/flight testing Engines - adaptation & installation Propellers tail boom & tail surfaces Electrical power generation, distribution, elec actuators Fuselage Flight control, AFCS, nav systems Landing gear Wing Tip nacelles, gearboxes, shafts In IADP R/C In IADP R/C or ITDs (T.B.C.) 7 7 Subsystem: Fuselage & Cabin Partly based on existing H/C structural elements (as possible) Many parts fully re-designed or deeply modified: Rear part to fit junction with specific tail Canopy, doors & windows Main frames, mechanical deck, upper cowlings Landing gear Non pressurized cabin, large access doors as needed for typical rescue tasks Strong structure for high dynamic pressure and impact resistance: bird strike Fully stowable landing gear: specific architecture, electrical actuation (possible option) Aerodynamic cleanliness: shape, excrescence elimination, smooth joints, etc 8 8 4

5 Subsystem: Wing Wing structure Simple trailing edge flaps Internal arrangement (harnesses, shaft protection, fuel tank?) Provision for de-icing system (not implemented in demo). Short span, minimum thickness (for internal shaft) Minimum download in hover (interference with rotor downwash) Maximum fineness at high speed (L/D), using TE flap for camber adaptation High stiffness for aeroelastic stability and internal shaft protection 9 9 Subsystem: Tail unit Tail cone Empennage & fins Rudder & elevator Provision for de-icing system (not implemented in demo). Configuration optimised for low drag, stability in whole flight domain Mechanical vs. electrical actuation: option to be studied and decided

6 Subsystem: Dynamic assemblies Main rotor Suspension Main Gear Box Transmission shafts, Propeller blades, hubs, Prop Gear Boxes Engines (adaptation & installation) RPM variation for low noise and performance: adaptation low/high speed flight Hydraulic vs. electrical actuation for props: option to be studied and decided Propellers: quiet design to meet dual functions: antitorque & prop efficiency Powerful gear boxes, high speed shafts tolerant to wing deflection Subsystem: On-board energy & systems Hydraulic & electrical power generation & network Flight control system, including actuation Flight management, avionic equipment More Electrical A/C vs. hydraulic actuation: multiple options possible Advanced FCS: many actuators, broad flight domain, smooth transitions vehicle monitoring system: to be modified flight management/avionics: implementation of earlier research i.e. H/C flight procedures

7 General Demo Project Activities General Demo Project Activities Technical Project Coordination General architecture, prelim. design & specs General engineering studies Validation & Verification Demonstrator final assembly, ground & flight testing Organisation 40% of overall work to be performed by ; 60% allocated thru open competition (Core Partners, Partners) Tight schedule to fly demonstrator in 2018 Core partners expected to commit & deliver timely for overall programme completion components/systems compliant with aero prototyping standards, with docs needed for Permit-to-Fly Extensive use of state-of-art simulation tools in a concurrent engineering approach e.g. numerical wind tunnel Successful Demo will pave the way to sustainable leadership & growth in EU