Source: Virginia Polytechnic

• Take advantage of advances in electrical systems

technology (power electronics in particular) to enhance

operational efficiency of aircraft

• Utilize bleedless engines and replace hydraulic and

pneumatic actuation systems by electrical drives where

possible

• Provide a technological springboard for “all-electric”

aircraft

By Rolf Wallner (from Wikipedia)

By BriYYZ (from Wikipedia/Flickr)

• Electric Environment Control System

• Electrical Anti-Ice (EIPS)

• Electrical Power Generation and Distribution systems (incl. Starter/Generator and Centralized Power

Electronics)

• Bleedless Engine

• Bleedless APU

• Optimized Hydraulic System

• Power Electronics Cooling System

• Li-Ion Battery

• Electro-Mechanical Actuation for FBW Flight Controls, Secondary Flight Controls, & Landing Gear Systems

• Increased power demand (order of MW) necessitates the use of variable frequency generation coupled

with power electronics (conventional geared constant-speed drives will have large losses)

• Power quality (voltage sags, harmonics, transients during switching) and reliability are critical

• Electric Power Generation and Distribution Systems (EPGDS) need to be validated across a range of

loading conditions defined by flight operations, while interacting with all aircraft systems

• High cost and risk for flight test, simulation-based testing is essential for de-risking

• EPGDS needs to be validated in conjunction with all the systems that are electrically driven

• Systems need to be tested under nominal, off-design and fault modes (including redundancy)

• Interaction and communication between systems need to be verified

• Testing needs to be conducted up to entire aircraft level (including handling qualities in system failure

modes)

• Real-time simulation of multi-domain models with multiple time-scales

• Complex power distribution system with redundancy

• Large number of power-electronic converters need to be simulated at sub-microsecond time-steps to ensure simulation fidelity that allows accurate estimation of power quality

• Distributed/parallel simulation on multiple CPUs and FPGAs

• Implementation of models may require development of computationally efficient numerical methods

• Common platform to go from M/SiL to HiL

Electrical network

Virtual Aircraft

FPGA FPGA

FPGA FPGA

CPU

Real-time Simulator APU Control

Software under test

ECS Control

Engine Control

ETC….

CPU

CPU

CPU

Electrical network

Virtual Aircraft

FPGA FPGA

FPGA FPGA

CPU

Real-time Simulator APU Control

Hardware under test

ECS Control

Engine Control

ETC….

CPU

CPU

CPU

I/O and

Comm.

Buses

Throttle_R

20

Hagl_m

19

Mext

18

Zext

17

Rudder

16

Aileron

15

Elevator

14

Psi

13

Theta

12

Phi

11

Altitude_ft

10

Mach

9

Climb

8

Thrust

7

DeltaThrottle

6

Nz

5

Ny

4

Track

3

Beta

2

Gamma

1

KIAS

TP

Target_Points

Pioneer_Aircraft

FromNavlRU

FromNavADC

FromNavFSC

FromAutoPilot

FromControls

FromEqm

FromAtm

FromEngine

EQM_Out

TJetEng_Out

Atm_Out

Ctrl_Out

OpXPlane_out

Outputs

OpComm

Ts = 0.01

OpComm1

17

AutoPilotON

16

NoseWheel

15

Brake

14

Booster_ON

13

FuelCut_RH

12

FuelCut_LH

11

GearDown

10

VertWind

9

WindDir_Deg

8

WindSpeed_kt

7

Throttle_RH

6

Throttle_LH

5

TrimCmd

4

FlapSlatLever

3

Pedal

2

Wheel

1

Column

<VD_mps>

<Phi_deg>

<The_deg>

<Psi_deg>

<Gamma_deg>

<Track_deg>

<Ny>

<Nz>

<DeltaThr>

<KIAS>

<Beta>

<PresAlt_ft>

<Mach>

<Thrust_Kgf>

<Elev_deg>

<Ail_deg>

<Rud_deg>

<Zext>

<Mext>

<Hagl_m>

Col

Wheel

Pedal

FlapLev

Throttle_L

TargetPoints

Column

Wheel

Pedal

FlapSlatLev er

TrimCmd

Throttle_LH

Throttle_RH

GearDown

GearDown

Horiz_Wind_Speed

Horiz_Wind_Dir

Vert_Wind_Speed

FuelCut_LH

FuelCut_RH

BoosterON

Brake

NoseWheel

AutoPilotON

AutoPilot

• Bleedless Engines

• Bleedless APU

• Less Hydraulics/ Pneumatics -Electric Ancillaries

• More Electric Loads (Electrical Air conditioning, Electrical Anti-Ice)

• More Electric Power Generation

Source: https://www.linkedin.com/pulse/20140901080038-16008290-energy-conversion-system-mdo

TRADITIONAL ELECTRIC GENERATION AND DISTRIBUTION - B767 MORE ELECTRIC ARCHITECTURE – B787

Source: https://www.wired.com/2013/01/boeing-787-electric-fire-grounding/

TRADITIONAL ELECTRIC GENERATION AND DISTRIBUTION - B767 MORE ELECTRIC ARCHITECTURE – B787

Source: www.boeing.com Source: http://alverstokeaviation.blogspot.ca/2016/03/the-alverstoke-aviation-society-guide_25.html#!/2016/03/the-alverstoke-aviation-society-guide_25.html

WEIGHT

RELIABILITY

MAINTENANCE

EFFICIENCY

WEIGHTMAINTENANCE

RELIABILITY EFFICIENCY

COST

WEIGHT

RELIABILITY

MAINTENANCE

EFFICIENCY

COST

VFSG

IDG

Cooling System

Source:https://card2brain.ch/box/electronics_?max=16&offset=356&accessCode=2&lang=fr

Source:http://www.boeing.com/commercial/aeromagazine/articles/2012_q3/2/

Source: Boeing

Source: Boeing

ELECTRICAL THERMAL LOSSES AND COOLING

POWER QUALITY AND HARMONICS DISTORTION

ELECTRIC LOAD ANALYSIS (ELA)

ELECTRIC STEADY-STATE AND TRANSIENT STABILITY

DIODES

IGBTs

Source: http://alverstokeaviation.blogspot.ca/2016/03/the-alverstoke-aviation-society-guide_25.html#!/2016/03/the-alverstoke-aviation-society-guide_25.html

Source: www.Thalesgroup.comSource: Assessment of Two-Phase Cooling of Power Electronics Using Roll-Bonded Condensers - Thomas B. Gradinger and Francesco Agostini

Source: H. Jimenez and D. N. Mavris, “Assessment of Technology Integration using Technology Readiness, Levels”,American Institute of Aeronautics and Astronautics, Texas, 2013.

Source: “NASA Systems Engineering Handbook”, Appendix G, SP-2007-6105, Rev1.

TEST RIG FOR THE BOMBARDIER CSERIES AIRCRAFT (Integrated Systems Test and Certification Rig (ISTCR))

Source: BOMBARDIER- http://ir.bombardier.com/en/press-releases/press-releases/39111-bombardier-cseries-aircraft-takes-virtual-flight

Requirements Integrated V&V

Integrated HIL Testing

Unit HIL Testing

Real-Time Implementation

Design Studies

Concept & System Modeling

Controllers

and

Plant Models

Faults insertion

Plant models (Engines, aircraft,electric systems, hydraulics,…)

Simulated ECUs replaced by actual controllers

Virtual environment

HIL environment

MappingBox

Source: www.opal-rt.com

• LESS HARDWARE AND EQUIPMENT

• FLEXIBLE

• AUTOMATED TESTING

• LOW MAINTENANCE

• Collaborative R&D project led by BOMBARDIER AEROSPACE and involving several aerospace OEMs.

• OPAL-RT involved in development of Multi Electric System Integrated Simulator (MESIS) as a TRL 6 virtual test rig demonstrator

MESIS OBJECTIVES MESIS EVOLUTION TIMELINE

Analytical proof of concept

Component Integrated

model

Relevant technology

models

Integrated HIL system

models

MESIS

Power QualityControl and Protection

Failure modes and

Malfunctions

Electric Systems

Interaction

2017 2018 2019 2020

MESIS

Power QualityControl and Protection

Failure modes and

Malfunctions

Electric Systems

Interaction

OPAL-RT(MODELING GAPS)

RT-LAB

MODELS

OEM 1

MODELS

OEM 2

MODELS

OEM n

MESIS Block Diagram Architecture

MESIS Block Diagram Architecture Real-Time Simulator

HW Architecture

CPU1

CPU2

Sou

rce:

ww

w.o

pal

-rt.

com

Sou

rce:

ww

w.o

pal

-rt.

com

MESIS Block Diagram Architecture Real-Time Simulator

HW Architecture

CPU1

CPU2

Sou

rce:

ww

w.o

pal

-rt.

com

Sou

rce:

ww

w.o

pal

-rt.

com

RECTIFIER / ECS MTC LOAD

EPGDS (CPU) MTC LOAD (FPGA)

EPGDS - MATRIX STRUCTURE EXAMPLE

CPU - Ts = 60 us

FPGA - Ts = 300 ns

• Competitive reality of MEA Technology

• Real-Time Simulation, a cost effective option for the validation of MEA Technology

• Modeling and Validation of electrical requirements and power quality analysis

• MEA models Co-Simulation is a challenge that isaddressed using specific tools or techniques

Alexandre Leboeuf, B. Eng.

Integration Team Lead

OPAL-RT TECHNOLOGIES

Source: Virginia Polytechnic

• Electronic Systems Integration

• Hardware-in-the-loop

• Case Studies

• Typical Project Time Line

• Automation and Visual Aids

• Benefits and Features

• Team specifically dedicated to provide turnkey Tests & Validation solutions.

• Official creation March 2012, ISO 9001:2008 certification. Currently upgrading our certification to

ISO9001:2015.

Requirements Integrated V&V

Integrated HIL Testing

Unit HIL Testing

Real-Time Implementation

Design Studies

Concept & System Modeling

Purpose:

• Test the prototype controllers and their surrounding equipment.

• Test in a safe manner the 85+ % of lines of code that manage the

exceptions the UUT will see through its use by creating those

exceptions on purpose.

• Automate test sets to perform a great number of validation during a

short time frame or during the night.

• Diagnose specific inflight problems on the ground.

• Get credited certification flight hours on the ground while being super

cost effective

• Validate interconnected systems simultaneously.

Purpose:

• Add to standard HIL the power system validation for transients, HW

redundancies, power capacities, power control algorithm, stability, etc.

• APU controllers (7)

• Air Management Systems controllers (8)

• Main Engine controllers (4)

• Based on the aerospace project

management model.

• Adapted to retain critical milestones

while adding more flexibility.

• Defines a clear design to delivery

timeline that is typically between 12

to 18 weeks from PO to shipping.

• Involves the customer at each step.

Throttle_R

20

Hagl_m

19

Mext

18

Zext

17

Rudder

16

Aileron

15

Elevator

14

Psi

13

Theta

12

Phi

11

Altitude_ft

10

Mach

9

Climb

8

Thrust

7

DeltaThrottle

6

Nz

5

Ny

4

Track

3

Beta

2

Gamma

1

KIAS

TP

Target_Points

Pioneer_Aircraft

FromNavlRU

FromNavADC

FromNavFSC

FromAutoPilot

FromControls

FromEqm

FromAtm

FromEngine

EQM_Out

TJetEng_Out

Atm_Out

Ctrl_Out

OpXPlane_out

Outputs

OpComm

Ts = 0.01

OpComm1

17

AutoPilotON

16

NoseWheel

15

Brake

14

Booster_ON

13

FuelCut_RH

12

FuelCut_LH

11

GearDown

10

VertWind

9

WindDir_Deg

8

WindSpeed_kt

7

Throttle_RH

6

Throttle_LH

5

TrimCmd

4

FlapSlatLever

3

Pedal

2

Wheel

1

Column

<VD_mps>

<Phi_deg>

<The_deg>

<Psi_deg>

<Gamma_deg>

<Track_deg>

<Ny>

<Nz>

<DeltaThr>

<KIAS>

<Beta>

<PresAlt_ft>

<Mach>

<Thrust_Kgf>

<Elev_deg>

<Ail_deg>

<Rud_deg>

<Zext>

<Mext>

<Hagl_m>

Col

Wheel

Pedal

FlapLev

Throttle_L

TargetPoints

Column

Wheel

Pedal

FlapSlatLev er

TrimCmd

Throttle_LH

Throttle_RH

GearDown

GearDown

Horiz_Wind_Speed

Horiz_Wind_Dir

Vert_Wind_Speed

FuelCut_LH

FuelCut_RH

BoosterON

Brake

NoseWheel

AutoPilotON

AutoPilot

• New RT-LAB Python API

• New Python integrated librairies

• New RT-LAB Data Logger

• We control the full business chain: Systems Integration team has a direct influence on HW/SW designs in accordance with real customer

requirements.

Overheads are limited with in-house products and procurement.

Support is handled directly by OPAL-RT.

• Open architecture permitting easy interface with existing simulation solutions.

• Modular design provides the means to expand the system with controlled cost.

• HW/SW for power electronics simulation as a backbone to propel MEA test bench designs.

• Simplified project management provides complex system delivery in short time frames. (Typically 12 to 18 weeks)

• OPAL-RT offers turnkey tests and validation solutions which are easily automatable.

• Purpose of HIL and PHIL.

• Some of the tools available with OPAL-RT solutions.

Source: Virginia Polytechnic

RT17 - OPAL-RT’s 9th User Group Conference

• September 5th to 8th, 2017 // Montreal, QC, Canada

• Register now to benefit from the early bird deadline -www.opal-rt.com/rt17

• Celebrating OPAL-RT’s 20th anniversary!

SAE 2017 AeroTech Congress & Exhibition

• 26 Sep to 28 Sep 2017 // Forth Worth, United States

• Visit us at booth # 914

• Learn more at www.opal-rt.com/event/sae-2017-aerotech-congress-exhibition/

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