Demonstrating the Third Generation Tiltrotor This research was partially funded by the Government under agreement No. W911W6-13-2-0001. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation thereon. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the Aviation Applied Technology Directorate or the U.S. Government. Society of Experimental Test Pilots | 25 October 2014

Definitions JMR – Joint Multi-Role FVL – Future Vertical Lift V-280 Valor is the Bell Naming Convention for 3rd Gen Tiltrotor Effort JMR – Joint Multi-Role FVL – Future Vertical Lift TIA BAA MPS FVL ICD Program of Record (PoR) Science & Technology (S&T) MPS Model Performance Specification AVCD Air Vehicle Concept Demonstrator JMR TD REDUCES RISK FOR FVL

Industrial Base - Teammates Teammates bringing the engineering resources, capabilities, and critical thinking to advance the design and technology maturation. Mission System Architecture and Mission Equipment Packages Flight Control System Engine Support Elastomerics Hydraulics V-Tails Fuselage Over-Wing Fairing Electrical Fuel

Bell’s TECHNOLOGY DEMONSTRATOR To Address these capabilities Voice of the Customer Science & Technology (S&T) Speed, Range, Payload, Reliability, Survivability Affordability Hover Maneuverability High Hot Operations Sustainability Commonality Program of Record Bell’s TECHNOLOGY DEMONSTRATOR To Address these capabilities

TRANSFORMATIONAL AGILITY vs. UH-60 Radius at 6kft/95ºF TRANSFORMATIONAL AGILITY Ó 2014 Bell Helicopter Textron Inc.

TRANSFORMATIONAL REACH vs. UH-60 Range at Sea Level Ó 2014 Bell Helicopter Textron Inc.

Footprint Comparison

MPS & Variants MPS Updates Attack Marinized Common Fuselage 30 mm nose gun Internal Weapons Bays Fwd Bay – Fwd Firing, Deploys Outboard 2 Aft Bays - Lateral Firing Marinized

Advanced Rotor and Drive System Concept Demonstrator Superior Low-Speed Maneuverability Advanced Rotor and Drive System Low Disk Loading 2 Pilots / 2 FTEs Fly-By-Wire Non-Rotating Fixed Engines Large Side Door Conventional Retractable Landing Gear Vtol Mode

Concept Demonstrator CRUISE Mode V-Tail with Ruddervators High Aspect Ratio, Straight Wing (Large Cell Carbon Core) Cruises at 280 knots Turboprop-like Ride Quality Advanced Composite Fuselage Superior High-Speed Handling Qualities CRUISE Mode

Wing Design for Manufacture Affordability Characteristics Semi-Monocoque design (large cell carbon core) No skin stiffening details/ fasteners Straight wing (few splice details) Broad goods lay up with reduced pad ups Bonded continuous skin assemblies Minimal ply drops Bonded LCCC rib assembly Tooled interfaces – reduced shimming Determinate assembly Point of use material dispensing Minimal compactions REDUCED COMPLEXITY, Fewer PARTS, LOWER COST

Rotor- Building on Experience Proven Configuration Key Technologies 3 Bladed Stiff In-plane Underslung Gimbaled hub Variable speed Lightweight carbon blades 25% cost savings Broad goods yoke 40% cost savings Advanced Technology improves value and performance of combat proven rotor configuration

Flight Control System - Overview Full-authority digital fly-by-wire flight control system Triplex electronic & hydraulic systems Systems Integration Lab development & testing ADS-33 Level I handling qualities (low-speed operations) Flight envelope protection Structural load limiting Conversion corridor protection Sidearm Controls Swashplate Control Pylon Conversion Active Rotor Flapping Control For Low Speed Maneuverability Tail Wheel Steering Integrated Engine Control Flight Control Computers Flaperon Ruddervator

Hover / Low Speed Maneuver Hover Yaw Quickness: Based on Control Power/Inertia ratio Tiltrotor configuration = large Izz Increased control power – Meets anticipated ADS-33 Level 1 yaw quickness Low Speed Maneuverability: MPS Requirement is 1.4g (45 bank) constant altitude turn at 80 kt, with reserve to accelerate Requirement intended to size rotor & engine Tiltrotor solution utilizes wing lift and thrust vectoring to meet spec with lightest rotor and minimum power required

Demonstrator Mission 229 nm mission radius Crew: 4 Payload: MPS Representative 229 nm mission radius

Demonstration Goals In priority order: Accomplish First Flight Demo 280 KTAS Expand to 6K/95 HOGE Evaluate agility, loads, and vibes Demo high altitude VTOL capability Validate mission performance radius and range capability Perform demo flights Demo operational capabilities – simulated fast rope, slung loads, PDAS situational awareness, MTEs, slope landings, simulated air refueling Demo STOL with build-up to MTOGW Collect additional data for model validation – high altitude, high speed, cg extremes Env Exp 1 Env Exp 2 Demo

Flight Envelope Build-up Approach

Third Generation Tiltrotor Exceptional capability Speed, range, payload, survivability Manageable technical risk Proven technology Major cost and performance improvements Total ownership cost Unprecedented fuel efficiency Greatest operational productivity Proven commonality with variants The Next generation of Vertical Lift: Twice as fast, twice as far

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