DRESS Distributed and Redundant Electro-mechanical nose wheel Steering System 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 1
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 € 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 2
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) 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 3
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) 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 4
DRESS TECHNICAL SPECIFICATIONS � Functional analysis performed to identify the needs without focusing on solutions � Main technical specifications, basis of DRESS design Limit • Maximum torque ≈ ≈ ≈ ≈ 7000Nm 120 Torque @ turning tube (% spec. torque • Maximum angular speed ≈ ≈ ≈ ≈ 20° /sec Restricted torque area 100 Spec. min. actuator's transient capability 80 • Towing mode capability (free to castor) Bldc max) 60 Motor Reducer • Robust behavior regarding shimmy Power 110% Ratio 900 40 • Total loss of steering event: objective 10-9/FH 20 0 0 20 40 60 80 100 Rate @ wheel (% spec. rate max) 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 5
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 occurrences) 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 6
DESCRIPTION OF DRESS SOLUTION � System architecture (for potential future aircraft) Specific to ATA 32 Sp ec ific to ATA 32 BCS Commo n to ATA 32 Steering Co ntrol Mo nito ring Contro l System System System SCS SCS MS LGERS Specific to ATA 32 • based on field bus TTP Specific to ATA 32 L G E xtensio n MS Braking Co ntrol Retraction System System BCS L GERS (time trigger protocole) COCKPIT AVIONICS BAY NOSE LANDING GEAR BAY NOSE LANDING GEAR A/C Avionics Bus AFDX • 3 cockpit RDC (acquisition node) CPM ATA 32 BCS CAPT Tiller • 3 CPM (computation node) SCS LGERS ATA 32 Local RDC ATA 32 MS Field Bus T TP RDC ATA 32 BCS CAPT Brake CHA+CHB A NA LOGU E SCS SCS • 3 Landing gear RDC Ped als DIS C LGE RS L GERS D ISC MS and CPM ATA 32 TE PWM Lan din g LOGUE CRE EMCU BCS G ear Lever (acquisition node) DIS SCS A AN 2 CBGs LGERS O FF PAR K BRK RVDT RDC ATA 32 AFDX MS RDC ATA 32 MO T OR Park DIS C BCS SCS O N Brake • 2 EMCU (motor control unit) A NA LOGU E P U LL & TU R N SCS LGE RS RV DT ETE DIS C CR L GERS MS RVDT DIS MO T OR A /SKI D A/SKID CPM ATA 32 DIS C Sw itch O N • 3 angular sensors BCS PWM O FF EMCU SCS LGERS RDC ATA 32 RDC ATA 32 MS D ISC SCS BCS DIS C LGE RS F/O Tiller AN ALO GUE SCS MS L GERS F/O Brake Ped als 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 7
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. 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 8
DRESS PROTOTYPE � ACTUATOR • Cyclo reducer worm • Clutch • Worm gear Aircraft LGL • Sized to withstand –55° C to 85° C front gear worm � 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, …). 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 9
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…) 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 10
SYSTEM RIG (ATCSS CONFIGURATION) The objective of this rig is to test the DRESS system (steering precision and dynamic, avionic behavior, TTP functionality…) 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 11
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). 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 12
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 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 13
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) 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 14
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