200608-1

The MathWorksThe MathWorksAerospace & Defense Conference Aerospace & Defense Conference

Reston, VirginiaReston, VirginiaJune 14June 14--15, 200615, 2006

First Civilian First Civilian TiltrotorTiltrotor Takes FlightTakes Flight

David KingDavid KingBell HelicopterBell Helicopter

BA609 Analytical Integration LeaderBA609 Analytical Integration Leader

RESTRICTED DISCLOSURE NOTICE

The drawings, specifications, descriptions, and other technical data attached hereto are proprietary to Bell Helicopter Textron Inc. and constitute trade secrets for the purposes of the Trade Secret and Freedom of Information Acts. No disclosure to others, either in the United States or abroad, or reproduction of any part of the information supplied is to be made, and no manufacture, sale, or use of any invention or discovery disclosed herein shall be made, except by written authorization of Bell Helicopter Textron Inc.. This notice will not operate to nullify or limit rights granted by contract. The data subject to this restriction is contained in all sheets and is disclosed to Bell Helicopter Textron Inc. personnel or other parties involved with the 609 program for the purpose of internal use and distribution only.

COPYRIGHT NOTICE

Copyright ©2006Bell ® Helicopter Textron Inc.Unpublished - all rights reserved

200608-2

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-3

OUTLINEOUTLINE

•• What is the BA609 What is the BA609 TiltrotorTiltrotor??•• What can it do?What can it do?

–– Flight test resultsFlight test results–– VideoVideo

•• How was it developed?How was it developed?–– Systems engineering processSystems engineering process–– Extensive use of ModelExtensive use of Model--Based Design & Based Design &

simulation using The MathWorks toolssimulation using The MathWorks tools–– Example: Carefree Maneuvering functionsExample: Carefree Maneuvering functions

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-4

Bell-Agusta 609: The World’s First Civil Tiltrotor

First Flight on 20 March 2003 in Arlington, TX

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-5

PropulsionPowerplants (2)P&W PT6C-67A 1940 shp ea.

WeightsMax Gross Weight 16,800 lbEmpty weight 11,300 lbUseful Load 5,500 lb

CapacitiesRequired crew 2Passenger seating 6-9Baggage compartment 50 ft3

PerformanceMaximum cruise speed 275 ktasMaximum range 700 nmiOperational Ceiling 25,000 ft.

General DataGeneral Data

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-6

609 Interiors609 Interiors

Standard UtilityStandard Utility

Standard ClubStandard Club

ExecutiveExecutive

Air MedicalAir Medical

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-7

Flight Control SystemFlight Control SystemFeaturesFeatures

Pro Line 21Pro Line 21IFR Glass CockpitIFR Glass Cockpit

Triply RedundantTriply RedundantFlyFly--byby--WireWire

Flight ControlFlight ControlSystemSystem

Integrated Integrated Flight & Engine Flight & Engine

ControlsControls

InterconnectedInterconnectedSemiSemi--automaticautomatic

Conversion ControlConversion Control

Integrated Integrated Carefree Carefree

Maneuvering Maneuvering FunctionsFunctions

ArtificialArtificialForceForce--FeelFeel

InterconnectedInterconnectedSemiSemi--automaticautomatic

Conversion ControlConversion Control

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-8

BA609 Front OfficeBA609 Front Office

Flight Deck Arrangement

200608-9

FLIGHT TEST FLIGHT TEST ACCOMPLISHMENTSACCOMPLISHMENTS

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-10

25000 Feet25000 Feet

First Fully Pressurized Rotorcraft

Flight into known icing to be demonstrated

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-11

304 Knots True Airspeed304 Knots True Airspeed

Fastest Civil VTOL Aircraft

350 MPH

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-12

Video of Demo Flight atVideo of Demo Flight at2006 2006 HeliHeli--ExpoExpo

200608-13

DEVELOPMENTDEVELOPMENTPROCESSPROCESS

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-14

CLEAN SHEET OF PAPER CLEAN SHEET OF PAPER Development ChallengesDevelopment Challenges

•• How can first flight risk of a new type of How can first flight risk of a new type of aircraft be reduced?aircraft be reduced?

•• How will the complex, highly integrated How will the complex, highly integrated systems be certified?systems be certified?

•• How can the development time and How can the development time and cost be reduced?cost be reduced?

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-15

SAFE, EFFECTIVE, & AFFORDABLE

Requirements Development

Design Synthesis & Integration

System Test & Evaluation

Certification & Customer

Acceptance

Trade Study Analysis

Tools & Processes by The

MathWorks

• Modeling• Analysis• Simulation• Test Cases• Drawing

Control

Stakeholderneeds &wants

SYSTEMS ENGINEERING SYSTEMS ENGINEERING APPROACHAPPROACH

•• ModelModel--Based Based Design Design expedites expedites developmentdevelopment

•• Iterative trade Iterative trade study analyses study analyses to develop to develop requirementsrequirements

•• Structured, Structured, iterative design iterative design process heavily process heavily reliant on reliant on simulationsimulation

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-16

RISK REDUCTION RISK REDUCTION Extensive Use of SimulationExtensive Use of Simulation

•• Rapid prototyping and simulation/analysisRapid prototyping and simulation/analysis–– SimulinkSimulink®® modelsmodels–– MATLABMATLAB®® and Realand Real--Time WorkshopTime Workshop®® to evaluate to evaluate

performance vs. requirementsperformance vs. requirements•• Incremental buildIncremental build--up to full hardware in the up to full hardware in the

loop simulationloop simulation–– Stress testing of aircraft systems in a realistic, Stress testing of aircraft systems in a realistic,

closedclosed--loop mannerloop manner–– Piloted validation of emergency procedures and Piloted validation of emergency procedures and

failure mode responses failure mode responses

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-17

Electrical Generator Room

Electrical Sys Test Bench

Flight Control Test BenchesSwash Plate Actuator Rigs

Avionics Test Bench

Hydraulic Pump Room

Conversion Actuator Rigs

Full Capability HardwareFull Capability Hardware--inin--thethe--Loop (HIL) SimulationLoop (HIL) Simulation

Cockpit Rig

200608-18

PROCESS EXAMPLE:PROCESS EXAMPLE:

Development of Carefree Development of Carefree Maneuvering FunctionsManeuvering Functions

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-19

CAREFREE MANEUVERING:CAREFREE MANEUVERING:MotivationMotivation

•• 40% of helicopter piloting workload 40% of helicopter piloting workload derived from monitoring aircraft and flight derived from monitoring aircraft and flight envelope limitsenvelope limits

from G. D. from G. D. PadfieldPadfield, , Helicopter Flight Helicopter Flight DynamicsDynamics

•• Large # of rotorcraft accidents attributed Large # of rotorcraft accidents attributed to abrupt maneuvers, high pilot workload, to abrupt maneuvers, high pilot workload, or violation of limitsor violation of limits

from Harris, Kasper, and from Harris, Kasper, and IselerIseler, , ““U.S. Civil U.S. Civil Rotorcraft Accidents, 1963 to 1997Rotorcraft Accidents, 1963 to 1997””

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-20

Design Requirements defined via Simulation & Analysis

Loads criteria

Active load alleviation system

requirements

Tradeoffanalyses

Envelope & limitprotection system

requirements

Design envelope

Loads Criteria

Active loadAlleviation

Alloca

te to

System

TradeoffAnalyses

Envelope & Limit Prot.

Design Envelope

SYSTEM

STRUCTUREAir VehicleRequirements

Allocate toStructure

•• Iterative ModelIterative Model--Based Design to Based Design to attain proper balance of structural attain proper balance of structural strength vs. active system protectionstrength vs. active system protection

Rapid prototypingand simulation

using Real-Time Workshop

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-21

CFM Example: Flapping LimitingCFM Example: Flapping Limiting

DescriptionDescriptionRotor flapping is maintained within structural limits through acRotor flapping is maintained within structural limits through activetivecontrol of longitudinal cyclic command authoritycontrol of longitudinal cyclic command authority

..

Max Flappingconstrainedby structure

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-22

Flapping Limiter Model-Based Design

Tradeoffanalyses

High FidelitySimulation

Requirements BasedTest Cases

SimulinkPage 1.1

Real-TimeWorkshop

Iterative Model-BasedDesign

Rotor controlsAllow up to11ºflapping

Embedded control lawLimits flapping < 11 º

Cyclic control powerfor pitch maneuvers

Differential cyclic foryaw maneuvers

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-23

Flapping Limiting Control LawFlapping Limiting Control Law

Simulink Model

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-24

Flapping Limiting PerformanceFlapping Limiting Performance

0 3 6 9 12 15Time - sec

-4

0

4

8

12Fl

appi

ng/C

yclic

- de

g

Gimbaled rotorflapping limit of

11 deg.

Total hub flapping staysBelow limit for worst-case

maneuver

Longitudinalcyclic

command

Activelycontrolled

cycliclimit

Aggressive roll reversal in conversion mode

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-25

CFM EXAMPLE:CFM EXAMPLE:Conversion ProtectionConversion Protection

Nacelle Control

NacelleUpSwitch

NacelleDownSwitch

Emerg.UpSwitch

ConversionCorridorSchedules

ConversionProtection

3 deg/secTrim Rate

NacelleAngle

75600

Go ToDetentLogic

Airspeed

Lower A/S ErrorUpper A/S Error

8o/s-8o/s2o/s-2o/s

Trim RateSelector

Go to DetentMode Active

Manual / Emer.Nacelle Trim

Rate

s1

NacelleAngleCmd(deg)

UL LL

UL

LL

DetentSelector

Ground MaintInterlock

T

5

Off Downstop RPM 100%Off Downstop RPM 100%

VminVcon

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-26

CONVERSION PROTECTIONTIME HISTORY

-101030507090

0 10 20 30 40 50 60 70 80Time (s)

Nacelle Angle (deg)

050

100150200

0 10 20 30 40 50 60 70 80Time (s)

Airspeed andConversion

Corridor Limits (knots)

Maximum Airspeed (Vcon)

ComputedAirspeed

Minimum Airspeed (Vmin)

Aggressive re-conversion from 175 knots (HILS)

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-27

CONCLUDING REMARKSCONCLUDING REMARKS

•• The BA609The BA609----worldworld’’s first civil s first civil tiltrotortiltrotor----is flyingis flying•• Extensive use of iterative, ModelExtensive use of iterative, Model--Based Based

Design and simulation has minimized flight Design and simulation has minimized flight test surprisestest surprises–– SimulinkSimulink–– MATLABMATLAB–– RealReal--Time WorkshopTime Workshop

•• Carefree maneuvering functions have been Carefree maneuvering functions have been successfully implemented through Modelsuccessfully implemented through Model--Based DesignBased Design

Use or disclosure of data contained on this sheet is subject to the restriction on the disclosure notice of this document200608-28

Questions ?

Questions ?