DRESS Distributed and Redundant Electro-mechanical nose wheel - - PowerPoint PPT Presentation

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DRESS

Distributed and Redundant Electro-mechanical nose wheel Steering System

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This document and the information contained are Messier-Bugatti property and shall not be copied or disclosed to any third party without Messier-Bugatti prior written authorization

DRESS CHARACTERISTICS AND OBJECTIVES

European Commission funded project (FP6 - 3rd call - submitted in July 2005)

• Schedule:

Kick Off : June 2006 End : December 2009

• Consortium: 13 partners from 8 countries

4 Industries (Airbus, Messier-Dowty, Messier-Bugatti, Saab) 1 Research Institute (Institute of Aviation) 5 Universities (INSA, UHA, UCL, UCV, BUTE) 3 SMEs (TTTech, Equipaero, Stridsberg)

• Budget

Global total budget: 4 040 786 € Total funding: 2 460 892 €

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DRESS CHARACTERISTICS AND OBJECTIVES

Objectives:

• Study & Validate a redundant electromechanical actuator
• Study & Validate the control system based on a distributed architecture
• Particular attention to be paid to shimmy phenomenon (new system stiffness and

damping of oscillations with an electromechanical system)

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DRESS GENERAL PRESENTATION

Background on nose wheel steering actuation:

• Hydraulically actuated steering systems used on current commercial aircraft
• Current probability for nose wheel steering system loss is low (10-5 / FH). In case of

failure, the pilot can safely regain manual control using differential braking Current system safe, but limited if minimum visibility required (no CATIIIC landing) No potential automatic guidance relying on steering system

• Trend:
• Effort to improve ATM (Air Traffic Management)
• Move towards MEA (More Electric Aircraft)

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DRESS TECHNICAL SPECIFICATIONS

Functional analysis performed to identify the needs without focusing on solutions Main technical specifications, basis of DRESS design

• Maximum torque ≈

≈ ≈ ≈ 7000Nm

• Maximum angular speed ≈

≈ ≈ ≈ 20° /sec

• Towing mode capability (free to castor)
• Robust behavior regarding shimmy
• Total loss of steering event: objective 10-9/FH

Limit

20 40 60 80 100 120 20 40 60 80 100 Rate @ wheel (% spec. rate max) Torque @ turning tube (% spec. torque max)

• Spec. min. actuator's

transient capability Restricted torque area Bldc Motor Reducer Power 110% Ratio 900

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DESCRIPTION OF DRESS SOLUTION

Actuator architecture

• 2 identical path to apply torque at turning tube level
• Each path composed of
• 1 electric motor with its associated control unit
• 1 prime reducer (cyclodrive)
• 1 clutch
• 1 end reducer (worm gear)
• Normal configuration

⇒ Each path provide half of the demanded torque (torque summing)

• Failure of one path

⇒ Remaining path provide the full torque (sizing for a limited number of

• ccurrences)

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DESCRIPTION OF DRESS SOLUTION

AFDX COCKPIT AVIONICS BAY NOSE LANDING GEAR BAY NOSE LANDING GEAR EMCU EMCU ATA 32 Local Field Bus T TP CHA+CHB

PWM PWM A/C Avionics Bus AFDX Commo n to ATA 32 System Specific to ATA 32 Braking Co ntrol System BCS Specific to ATA 32 Steering Co ntrol System SCS Specific to ATA 32 L G E xtensio n Retraction System L GERS CAPT Tiller CAPT Brake Ped als F/O Tiller F/O Brake Ped als

Sp ec ific to ATA 32 Mo nito ring Contro l System MS BCS SCS LGERS MS CPM ATA 32 BCS SCS LGERS MS CPM ATA 32 BCS SCS LGERS MS CPM ATA 32 BCS SCS LGERS MS RDC ATA 32 SCS LGE RS MS RDC ATA 32 SCS LGE RS MS RDC ATA 32 SCS LGE RS MS RDC ATA 32 BCS SCS L GERS RDC ATA 32 BCS SCS L GERS

RDC ATA 32 BCS SCS L GERS Lan din g G ear Lever

A/SKID Sw itch

Park Brake 2 CBGs

System architecture (for potential future aircraft)

• based on field bus TTP

(time trigger protocole)

• 3 cockpit RDC (acquisition node)
• 3 CPM (computation node)
• 3 Landing gear RDC

(acquisition node)

• 2 EMCU (motor control unit)
• 3 angular sensors

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DRESS PROTOTYPE

Motor Key Characteristics

• Stritorque motor, embedding resolver position sensor, power off brake, temperature

monitoring.

• Spline interface towards the transmission for bearing lifetime.

EMCU Key Characteristics

• Motor torque control
• 270 VDC, 28 VDC
• Redundant, isolated RS-485 with Time-

Triggered Protocol by TTTech.

• PWM motor drive with field-oriented

control.

• The prototype EMCU overrated for the

application.

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DRESS PROTOTYPE

ACTUATOR

• Cyclo reducer
• Clutch
• Worm gear
• Sized to withstand –55°

C to 85° C

NODE

• A TTP module board (provided by

TTTECH) dedicated to manage TTP communications and to host the applicative software Clutch

• An IO-Board (HW and SW) developed

by MB) dedicated to acquire sensors data (cockpit, VDTs, discrete, analog…) and controls actuators (Clutch, Brakes, …).

worm worm

LGL

gear Aircraft front

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ACTUATOR RIG

Actuator mounting frame with actuator load device The objective of this rig is to test the DRESS actuator under several conditions (load, temperature…)

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SYSTEM RIG (ATCSS CONFIGURATION)

The objective of this rig is to test the DRESS system (steering precision and dynamic, avionic behavior, TTP functionality…)

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SYSTEM RIG (DCSS CONFIGURATION)

The objective of this rig is to identify the system response to dynamic (up to 60Hz) excitation and allow a shimmy study(by modelisation).

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OUTCOME OF DRESS

Specification and design sizing case associated to an electromechanical steering system Electromechanical solution for steering actuation Improvement of safety objectives for a steering system (compliance with CATIIIC landings or automatic guidance system ) Shimmy damping with an electromechanical actuator Control of an active/active redundant actuator Use of a distributed architecture for system control Redundant and fail safe design of all electric aircraft systems

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CONCLUSION

DRESS solution not optimized for aircraft but generating lots of information Will enable accurate decisions for design choices on next aircraft generation (New Short Range)