A380 Landing Gear System
Content
June 2008
Presented by
Andy Hebborn
Head of Landing Gear Systems
A380 Landing Gear and Systems – The feet of the Plane
DGLR – Hamburg 5th June 2008
DGLR Hamburg
A380 Landing Gear & Systems – An Overview Introduction
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Description of Landing Gears and Associated Systems
– Development of Gears Layout – Highlight new functions and technologies – Overview of Systems Architectures and Equipment
DGLR Hamburg
June 2008
Page 2
A380 Landing Gear & Systems – An Overview The Aircraft
The A380 • The A380 is a completely new, very high capacity, very long rang e commercial transport aircraft, powered by 4 RR Trent 900 or Engine Alliance GP7200 engines • Standard A380-800 accommodates 555 Passengers in threeclass long-range arrangement • MTOW 569 tonnes, MLW 391 tonnes • First flight 27 April 2005 • Entry into service Oct 2007, with Singapore Airlines • Delivery schedule for 2008: 13 A/C to Singapore, Qantas and Emirates
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 3
A380 Landing Gear Systems – An Overview Major Components and Systems
4ATA
Chapter 32 Landing Gear Systems 4Gears – Nose Landing Gear (2 Wheels) – Body Landing Gear x2 (Bogie Type, 6 Wheels - 4 Braked) – Wing Landing Gear x2 (Bogie Type, 4 Wheels - 4 Braked) 4Extension/Retraction System 4Braking Control System 4Steering Control System
– Nose Wheel Steering – Body Wheel Steering
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
4Wheels,
Tyres and Brakes (16 Braked Wheels) 4Monitoring Systems
– Tyre Pressure Indication System – Brake Temperature Monitoring System – Oleo Pressure Monitoring System
DGLR Hamburg
June 2008
Page 4
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
A380 Landing Gear Configuration Starting Point – 38 Alternatives
DGLR Hamburg June 2008 Page 5
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
First Down Selection: 2 Family Concepts for the gear and airframe
Longitudinal Bay
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Classical Bay
DGLR Hamburg June 2008 Page 6
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
Second Down Selection: - Family Concept Selected - Kinematic Options traded
Kinematic options
Bay concept selected
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Baseline configuration
DGLR Hamburg
June 2008
Page 7
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Main Gear Group: Installation in Wing & Fuselage
DGLR Hamburg
June 2008
Page 8
A380 Landing Gear Systems – An Overview Evolution ofgear Configuration Landing Gears
• Landing Gear Configuration – Basic Requirements
4 one concept philosophy for all aircraft
variants 4 each variant capable of optimization
4 concept capable of development to
•
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
•
significantly higher design weights 4 ACNs no worse than existing large aircraft 4 Nose gear to be compatible with towbarless towing Manoeuvring on ICAO code E and FAA group V airports 4 45m wide runways and 23m taxiways 4 U-turn on 60m wide runway possible Capable of growth beyond current a/c definitions
42
wheel or 4 wheel CLG installation possible
DGLR Hamburg
June 2008
Page 9
A380 Landing Gear Systems – An Overview Wing Landing Gear
Retract Actuator Hoses
Fwd Pintle Pin Retract Actuator Cardan Pin
Downlock Hoses Retract Actuator
Uplock Roller
Aft Pintle Pin
Drag Brace Lock Links
Upper Sidestay Unlock Actuator (with third Downlockspring) Ground Locking Pin Lower Sidestay Downlock Springs Fuse Pin Main Fitting Normal Brake System Alternate Brake System Sliding Piston Slave Links Bogie Trim Actuator Hydraulic Dressings Bogie Trim Actuator (BTA) Brake Hoses Retract Actuator (Ref) Torque Links Gear Rib 9 Fitting Lower Cardan Pin
Upper Cardan Pin
VIEW RETRACTED
Fwd Pintle Fitting
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
BTA Fuse
Bogie Beam Assy Brake Rods
VIEW LOOKING FORWARD ON WLG SPAR PLANE FWD VIEW LOOKING INBOARD ON PINTLE AXIS
Main Fitting
Cardan Pin Sidestay Fitting Sidestay Assy OUTBOARD FORWARD Wing Rear Spar (Ref)
Locklinks
DGLR Hamburg
June 2008
Page 10
A380 Landing Gear & Systems – An Overview Body Landing Gear
Upper Drag Brace Retract Actuator Lock Springs Ground Locking Pin Lock Links Unlock Actuator Lower Drag Brace Fuse Steering Lock Pin Springs Knuckle Joint Link Steering Wedge Lock Bogie Trim Actuator (BTA) Steering Locked Outer Cylinder Alternate Brake System Torque Links Steering System Steering Unlocked Steering Actuator and Steering Hydraulic Control Block Steering Unlock Actuator
STEERED AXLE DETAIL
Upper Drag Brace
Uplock Roller Alternate Brake Manifold Upper Panel Lower Panel
Lower Panel Normal Brake Manifold Normal Brake System Slave Links
‘G2’ FITTING ‘G1’ FITTING
LH BLG VIEW LOOKING AFT
‘C’ FITTING
Sliding Piston Bogie Beam Assy
Brake Rods
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
LH BLG VIEW LOOKING INBOARD
Steered Axle
‘A’ FITTING UPLOCK FITTING FR 63
‘J’ FITTING
‘H’ FITTING
VIEW RETRACTED
FWD
DGLR Hamburg June 2008 Page 11
A380 Landing Gear & Systems – An Overview Nose Landing Gear
Nose Wheel Steering (NWS): Towing Angle is +/- 60° Hydraulic Steering Angle is +/- 70° Mechanical Stop Angle is +/- 75° ‘Push-to-retract’ gear actuator
Single stage oleo
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Steering Disconnect Panel HVOF-coated slider
60/70°
Maintenance Panel on Leg
FWD
DGLR Hamburg June 2008
60/70°
Page 12
A380 Landing Gear & Systems – An Overview Landing Gear Structure
Weight / Cost / Size / Timescale Trade -offs
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
High Strength Steel (300M), except:Titanium Aluminium
DGLR Hamburg
June 2008
Page 13
A380 Landing Gear Systems – An Overview Gears Retraction Animation
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 14
A380 Landing Gear Systems – An Overview Main Wheel, Tyre and Brake
Honeywell Wheel & Brake: Braked Wheel •Deep Cavity A-Frame •2014-T6 Aluminium Alloy •23 inch rim size •11 Vent Holes •11 Drive keys •22 Iconel Tie Bolts •Segmented Heat-shield •Stainless Steel Axle Sleeve • Non-Braked Wheel •Symmetric A-Frame • Brake •5 Rotor Carbenix® 4000 heat-sink •1.59inch wear pin •23 spline titanium torque tube •Aluminium 7050 piston housing •6 x Ø1.805” pistons (split-ball adjuster) •Integral Lug and steel torque pin • Bridgestone Tyre •1400x530 R23 40PR Lightweight Radial
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 15
A380 Landing Gear Systems – An Overview Nose Wheel and Tyre
•Honeywell Wheel •Wheel
•Symmetric A-Frame •2014-T6 Aluminium Alloy •22 inch rim size •Iconel Tie Bolts •Light-weight Aluminium Axle Sleeve • Bridgestone Tyre •1270x455 R22 32PR Lightweight Radial
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 16
A380 Landing Gear Systems – An Overview Power Systems Architecture • Hydraulic architecture :
45000
psi 42 A/C circuit (Green & Yellow) 4Segregation Between Green and Yellow :
– BLGs ATA32 function on Yellow circuit only – WLGs & NLG ATA32 function on Green circuit only
4All
hydraulic back-up functions ensured by local hydraulic generation system (LEHGS) owned by the function system
• Electrical Architecture :
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
4AC
: 4DC:
115V Variable frequency 28V with no power transients 2 segregated Normal DC : 1 Emergency DC : 1 DC Service Bus
DC1 & DC2 DC essential
DGLR Hamburg
June 2008
Page 17
A380 Landing Gear Systems – An Overview Local Hydraulic Power Generation System • Redundancy of hydraulic power for Braking
and Nose Wheel Steering provided by LEHGS
• Features:
4 Re-pressurises
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
the HP accumulators to 350 bar throughout the flight 4 Low pressure reservoir with LVDT for level sensing and visual indicator 4 Electric motor-pump 4 Incorporates health monitoring (fluid and motor temperature sensing, filter clog detection)
DGLR Hamburg
June 2008
Page 18
A380 Landing Gear Systems – An Overview System Avionics Architecture
1) Normal ATA32 functions controlled by shared avionics units for a ll systems
Core Processor Input Output Module (Integrated Modular Avionics) CPIOM-G (IMA): All ATA32 System functions – Control functions and indication management – Central monitoring functions (BITE) – Main interfaces to other A/C systems 4 Remote Data Concentrator Landing Gear RDCs : Extension/Retraction (LGERS) and Monitoring (LGMS) – Specific Systems sensors Acquisitions – Ext/Ret Valves and Actuators second order control – Local monitoring Iinterface RDCs : Braking and Steering (BSCS) – A/SKID and pressure control loop function – Specific Systems sensors Acquisitions – Local monitoring Emergency ATA32 functions controlled by specific analogue units, independent of IMA and AFDX avionics technology 4 Brake Control : Emergency Brake Control (EBCU) 4 Ext/Ret Free Fall : Free-Fall Control (FFCM)
4
DGLR Hamburg June 2008 Page 19
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
2)
A380 Landing Gear Systems – An Overview Oleo Pressure Monitoring System
• Oleo pressure is monitored simultaneously on all landing gear shock absorbers and any warning is passed on to the Flight Warning System. Prevents departure with mis-serviced Landing Gear Accurate Check - performed once per flight, after gear extension Gross Check - continuous monitoring Combined Pressure and Temperature sensor mounted on each Shock Absorber
• • • •
OPMS is designed to: • •
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Provide a warning when one or more L/G oleo pressure is outside defined limits. Provide a warning when there is an OPMS equipment failure. Provide L/G oleo pressure status to the flight and maintenance c rew. Provide other aircraft systems with L/G oleo pressure status & e quipment information via AFDX. OPMS removes the need for carrying out pre-flight oleo pressure checks by the maintenance crew.
• • •
DGLR Hamburg
June 2008
Page 21
A380 Landing Gear Systems – An Overview Brake Temperature Monitoring System
BTMS (Brake Temperature Monitoring System) :
- Prevents take-off with a hot brake - Prevent landing gear retraction with a hot brake - Monitors for residual braking due to a dragging brake
Equipment:
Brake Temperature Compensation Module Brake Temperature Sensor located next to the brake heat pack.
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 22
A380 Landing Gear Systems – An Overview Tyre Pressure Monitoring System (TPIS)
Tyre pressures are monitored simultaneously on all wheels and any warning is passed on to the Flight Warning System.
TPIS is designed to: Provide other aircraft systems with tyre pressures & equipment s tatus information. Provide tyre pressure information to the flight and maintenance crew. Provide an alert when the pressure in one or more tyres is outsi de defined limits. Provide an alert when the differential pressure between any two tyres on the same axle differs by an amount beyond defined limits.
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
TPIS can be used to carry out daily tyre pressure checks.
DGLR Hamburg
June 2008
Page 23
A380 Landing Gear Systems – An Overview Tyre Pressure Monitoring System (TPIS)
Depending on the flight phase, a warning will be triggered if a tyre pressure is detected below a given percentage of the nominal tyre pressure ( for 5 seconds continuously). Likewise, a warning will be triggered if a differential pressure above a given percentage is detected across tyres on the same axle (measured f rom the tyre with the higher pressure). A ‘TYRE PRESS LO’ message will be displayed on the E/WD if a Low or Differential tyre pressure condition is triggered.
Pressure Sensor
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Hubcap Rotating Antenna Static Antenna Electronic Module
DGLR Hamburg
June 2008
Page 24
A380 Landing Gear Systems – An Overview Steering Control System
Steering is mainly effected on the NLG Wheel Pair by classic push-pull design (Nose Wheel Steering)
NWS
L R
FORWARD
1 2 3 4
5
6 9 10 11 12
7
8
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
13
14
15
16
20
17
18
19
BWS
Aft Axle of BLG is steerable to ensure better manoeuvrability for small radius turn (Body Wheel Steering)
DGLR Hamburg June 2008 Page 25
A380 Landing Gear Systems – An Overview Steering Control System Architecture
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 26
A380 Landing Gear Systems – An Overview NWS Control – Gear Mounted Components
ROTARY CHANGEOVER VALVE
HYDRAULIC CONTROL BLOCK
UPPER STATIONARY FLANGE
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
STEERING ACTUATOR
ROTARY COLLAR
LOWER STATIONARY FLANGE
DGLR Hamburg
June 2008
Page 28
A380 Landing Gear Systems – An Overview Body Wheel Steering – Gear Mounted Components
Lock and Steering Selector Valves HCB Lock Actuator
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Pressure Switch Lock Proximity Sensors
EHSV
Steering Actuator
DGLR Hamburg
June 2008
Page 29
A380 Landing Gear Systems – An Overview Brake Control System
NORMAL / ALTN BRAKING
• Body Landing Gear (BLG) & Wing Landing Gear (WLG) attached to se parate hydraulic
systems
4 BLG
– Yellow WLG – Green Yellow,
4 Single Cavity Brakes 4 Servo Valve per Wheel Pair
• LEHGS (Local electro-hydraulic generation supply)
4 Electric
motor driven pump supply Alternate hydraulics
AUTO-BRAKE • Autobrake function available in Normal & Alternate Braking mode • Comfortable & symmetric disconnect
• Provision for Brake to Vacate function
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
4 Adapts
deceleration rates to runway exits
DGLR Hamburg
June 2008
Page 30
A380 Landing Gear Systems – An Overview Brake Control System
WLG GROUP
FORWARD
Left Hand Wing Gear
1 2 3 4
5
6
Right Hand Wing Gear
7
8
Left Hand Body Gear LBLG WHEEL GROUP
9
10
11
12
13
14
15
16
Right Hand Body Gear RBLG WHEELGROUP
17
18
19
20
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
The Braking System architecture is divided into three groups lin ked to the three wheel groups : > WLG (8 wheel braked) > BLG (8 wheel braked- aft axle wheels not braked)
DGLR Hamburg
June 2008
Page 31
A380 Landing Gear Systems – An Overview Brake Control System Architecture
AFDX
A/C Green Hydraulics WLG LEHGS
COM1
ARINC 429 links
RDC1
Side 1
MON3
RDC3
COM2
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Side 2
MON4
RDC2
EBCU
A/C Yellow Hydraulics BLG LEHGS
DGLR Hamburg
June 2008
Page 32
A380 Landing Gear Systems – An Overview Brake Control System – Braking Modes
Braking Modes available per wheel group.
BRAKING NORMAL ALTERNATE (WITH ANTI-SKID) ALTERNATE EMERGENCY EMERGENCY
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
HYDRAULICS
•YELLOW – BLG •GREEN – WLG
CONTROL UNIT
IMA
ACTIVATION
•AUTOBRAKE •PEDALS
FUNCTIONS
•ANTI-SKID •PEDALS •AUTOBRAKE •ANTI-SKID •PEDALS •AUTOBRAKE •NO ANTI-SKID •PEDALS with limited pressure •NO ANTISKID •PEDALS with limited pressure •BRAKING ON ALL WHEELS
•LEHGS + ACCU
IMA
•AUTOBRAKE •PEDALS
•LEHGS + ACCU Or •ACCU •LEHGS + ACCU Or •ACCU •LEHGS + ACCU Or •ACCU •NORMAL Or •LEHGS + ACCU
IMA
•PEDALS
(Same as above, but with EBCU control)
EBCU
•PEDALS
ULTIMATE
EBCU
•PARK SWITCH ONLY
PARK
-
•PARK SWITCH ONLY
•BRAKING ON BLG ONLY
DGLR Hamburg
June 2008
Page 33
A380 Landing Gear & Systems – An Overview Extension/Retraction System The Landing Gear Extension and Retraction System is made up of three sub-systems: The Normal System:
Landing Gear Control and Indication System (LGCIS) Side 1 and 2, implemented in IMA Nose and Wing Landing Gear and Doors - Green Hydraulic System Body Landing Gear and Doors - Yellow Hydraulic System
An Independent Freefall System for Emergency operation
Independent of IMA Dedicated uplock electrical actuators and valves Uses dissimilar technologies where possible to avoid common-mode failures Uses different wiring routes
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
An Auxiliary Ground Door Opening System
Allows on-ground access to each landing gear bay for maintenance purposes Electrically operated and controlled from GDO Panels
DGLR Hamburg
June 2008
Page 34
A380 Landing Gear & Systems – An Overview Extension/Retraction System Equipment
Vent Valve Landing Gear Selector Valve
Dual Valve Actuator
Door By-Pass Valve
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Cut-Out Valve
DGLR Hamburg
June 2008
Page 35
A380 Landing Gear & Systems – An Overview Extension/Retraction System Equipment
NLG Door Uplock
Emergency Unlock Actuator Normal Unlock Actuator
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Wing Landing Gear Uplock
DGLR Hamburg
June 2008
Page 36
A380 Landing Gear & Systems – An Overview Ext/Ret - Ground Door Opening
• System operation is from a Control Panel, which is accessible fr om outside the
aircraft and located near the operated door(s). There is a Control Panel for; 4 NLG (both doors) 4 L WLG (one door) 4 R WLG (one door) 4 L BLG (outer door only) 4 R BLG (outer door only)
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
• Operation of system commands isolation of the Gear Door Actuator via a ByPass Valve and release of the Door Uplock via the Side B EUA, allowing it open by gravity.
DGLR Hamburg
June 2008
Page 38
A380 Landing Gear & Systems – An Overview Cockpit Controls and Indications
Independent Landing Gear Position Lights Brake Pressure Triple Gauge
Landing Gear Emergency Extension Switches Brake Pedal Transmitters
Normal BPTU ( Normal and Alternate Braking)
Anti-Skid selector switch
Landing Mode Rotary Selector Switch
Emergency BPTU (Emergency Braking)
Landing Gear Selector
Spring Rod
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Steering Tiller
Spring Rod Adjustable Rod
Parking Brake Selector
DGLR Hamburg June 2008
Systems Display (Wheel Page)
Page 39
A380 Landing Gear & Systems – An Overview Flight Test Highlights
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 41
A380 Landing Gear & Systems – An Overview Questions?
Any Questions?
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 42
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS UK LTD. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS UK LTD. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS UK LTD will be pleased to explain the basis thereof. AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks.
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 43
Presented by
Andy Hebborn
Head of Landing Gear Systems
A380 Landing Gear and Systems – The feet of the Plane
DGLR – Hamburg 5th June 2008
DGLR Hamburg
A380 Landing Gear & Systems – An Overview Introduction
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Description of Landing Gears and Associated Systems
– Development of Gears Layout – Highlight new functions and technologies – Overview of Systems Architectures and Equipment
DGLR Hamburg
June 2008
Page 2
A380 Landing Gear & Systems – An Overview The Aircraft
The A380 • The A380 is a completely new, very high capacity, very long rang e commercial transport aircraft, powered by 4 RR Trent 900 or Engine Alliance GP7200 engines • Standard A380-800 accommodates 555 Passengers in threeclass long-range arrangement • MTOW 569 tonnes, MLW 391 tonnes • First flight 27 April 2005 • Entry into service Oct 2007, with Singapore Airlines • Delivery schedule for 2008: 13 A/C to Singapore, Qantas and Emirates
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 3
A380 Landing Gear Systems – An Overview Major Components and Systems
4ATA
Chapter 32 Landing Gear Systems 4Gears – Nose Landing Gear (2 Wheels) – Body Landing Gear x2 (Bogie Type, 6 Wheels - 4 Braked) – Wing Landing Gear x2 (Bogie Type, 4 Wheels - 4 Braked) 4Extension/Retraction System 4Braking Control System 4Steering Control System
– Nose Wheel Steering – Body Wheel Steering
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
4Wheels,
Tyres and Brakes (16 Braked Wheels) 4Monitoring Systems
– Tyre Pressure Indication System – Brake Temperature Monitoring System – Oleo Pressure Monitoring System
DGLR Hamburg
June 2008
Page 4
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
A380 Landing Gear Configuration Starting Point – 38 Alternatives
DGLR Hamburg June 2008 Page 5
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
First Down Selection: 2 Family Concepts for the gear and airframe
Longitudinal Bay
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Classical Bay
DGLR Hamburg June 2008 Page 6
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
Second Down Selection: - Family Concept Selected - Kinematic Options traded
Kinematic options
Bay concept selected
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Baseline configuration
DGLR Hamburg
June 2008
Page 7
A380 Landing Gear & Systems – An Overview Evolution of Main Landing Gear Configuration
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Main Gear Group: Installation in Wing & Fuselage
DGLR Hamburg
June 2008
Page 8
A380 Landing Gear Systems – An Overview Evolution ofgear Configuration Landing Gears
• Landing Gear Configuration – Basic Requirements
4 one concept philosophy for all aircraft
variants 4 each variant capable of optimization
4 concept capable of development to
•
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
•
significantly higher design weights 4 ACNs no worse than existing large aircraft 4 Nose gear to be compatible with towbarless towing Manoeuvring on ICAO code E and FAA group V airports 4 45m wide runways and 23m taxiways 4 U-turn on 60m wide runway possible Capable of growth beyond current a/c definitions
42
wheel or 4 wheel CLG installation possible
DGLR Hamburg
June 2008
Page 9
A380 Landing Gear Systems – An Overview Wing Landing Gear
Retract Actuator Hoses
Fwd Pintle Pin Retract Actuator Cardan Pin
Downlock Hoses Retract Actuator
Uplock Roller
Aft Pintle Pin
Drag Brace Lock Links
Upper Sidestay Unlock Actuator (with third Downlockspring) Ground Locking Pin Lower Sidestay Downlock Springs Fuse Pin Main Fitting Normal Brake System Alternate Brake System Sliding Piston Slave Links Bogie Trim Actuator Hydraulic Dressings Bogie Trim Actuator (BTA) Brake Hoses Retract Actuator (Ref) Torque Links Gear Rib 9 Fitting Lower Cardan Pin
Upper Cardan Pin
VIEW RETRACTED
Fwd Pintle Fitting
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
BTA Fuse
Bogie Beam Assy Brake Rods
VIEW LOOKING FORWARD ON WLG SPAR PLANE FWD VIEW LOOKING INBOARD ON PINTLE AXIS
Main Fitting
Cardan Pin Sidestay Fitting Sidestay Assy OUTBOARD FORWARD Wing Rear Spar (Ref)
Locklinks
DGLR Hamburg
June 2008
Page 10
A380 Landing Gear & Systems – An Overview Body Landing Gear
Upper Drag Brace Retract Actuator Lock Springs Ground Locking Pin Lock Links Unlock Actuator Lower Drag Brace Fuse Steering Lock Pin Springs Knuckle Joint Link Steering Wedge Lock Bogie Trim Actuator (BTA) Steering Locked Outer Cylinder Alternate Brake System Torque Links Steering System Steering Unlocked Steering Actuator and Steering Hydraulic Control Block Steering Unlock Actuator
STEERED AXLE DETAIL
Upper Drag Brace
Uplock Roller Alternate Brake Manifold Upper Panel Lower Panel
Lower Panel Normal Brake Manifold Normal Brake System Slave Links
‘G2’ FITTING ‘G1’ FITTING
LH BLG VIEW LOOKING AFT
‘C’ FITTING
Sliding Piston Bogie Beam Assy
Brake Rods
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
LH BLG VIEW LOOKING INBOARD
Steered Axle
‘A’ FITTING UPLOCK FITTING FR 63
‘J’ FITTING
‘H’ FITTING
VIEW RETRACTED
FWD
DGLR Hamburg June 2008 Page 11
A380 Landing Gear & Systems – An Overview Nose Landing Gear
Nose Wheel Steering (NWS): Towing Angle is +/- 60° Hydraulic Steering Angle is +/- 70° Mechanical Stop Angle is +/- 75° ‘Push-to-retract’ gear actuator
Single stage oleo
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Steering Disconnect Panel HVOF-coated slider
60/70°
Maintenance Panel on Leg
FWD
DGLR Hamburg June 2008
60/70°
Page 12
A380 Landing Gear & Systems – An Overview Landing Gear Structure
Weight / Cost / Size / Timescale Trade -offs
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
High Strength Steel (300M), except:Titanium Aluminium
DGLR Hamburg
June 2008
Page 13
A380 Landing Gear Systems – An Overview Gears Retraction Animation
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 14
A380 Landing Gear Systems – An Overview Main Wheel, Tyre and Brake
Honeywell Wheel & Brake: Braked Wheel •Deep Cavity A-Frame •2014-T6 Aluminium Alloy •23 inch rim size •11 Vent Holes •11 Drive keys •22 Iconel Tie Bolts •Segmented Heat-shield •Stainless Steel Axle Sleeve • Non-Braked Wheel •Symmetric A-Frame • Brake •5 Rotor Carbenix® 4000 heat-sink •1.59inch wear pin •23 spline titanium torque tube •Aluminium 7050 piston housing •6 x Ø1.805” pistons (split-ball adjuster) •Integral Lug and steel torque pin • Bridgestone Tyre •1400x530 R23 40PR Lightweight Radial
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 15
A380 Landing Gear Systems – An Overview Nose Wheel and Tyre
•Honeywell Wheel •Wheel
•Symmetric A-Frame •2014-T6 Aluminium Alloy •22 inch rim size •Iconel Tie Bolts •Light-weight Aluminium Axle Sleeve • Bridgestone Tyre •1270x455 R22 32PR Lightweight Radial
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 16
A380 Landing Gear Systems – An Overview Power Systems Architecture • Hydraulic architecture :
45000
psi 42 A/C circuit (Green & Yellow) 4Segregation Between Green and Yellow :
– BLGs ATA32 function on Yellow circuit only – WLGs & NLG ATA32 function on Green circuit only
4All
hydraulic back-up functions ensured by local hydraulic generation system (LEHGS) owned by the function system
• Electrical Architecture :
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
4AC
: 4DC:
115V Variable frequency 28V with no power transients 2 segregated Normal DC : 1 Emergency DC : 1 DC Service Bus
DC1 & DC2 DC essential
DGLR Hamburg
June 2008
Page 17
A380 Landing Gear Systems – An Overview Local Hydraulic Power Generation System • Redundancy of hydraulic power for Braking
and Nose Wheel Steering provided by LEHGS
• Features:
4 Re-pressurises
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the HP accumulators to 350 bar throughout the flight 4 Low pressure reservoir with LVDT for level sensing and visual indicator 4 Electric motor-pump 4 Incorporates health monitoring (fluid and motor temperature sensing, filter clog detection)
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June 2008
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A380 Landing Gear Systems – An Overview System Avionics Architecture
1) Normal ATA32 functions controlled by shared avionics units for a ll systems
Core Processor Input Output Module (Integrated Modular Avionics) CPIOM-G (IMA): All ATA32 System functions – Control functions and indication management – Central monitoring functions (BITE) – Main interfaces to other A/C systems 4 Remote Data Concentrator Landing Gear RDCs : Extension/Retraction (LGERS) and Monitoring (LGMS) – Specific Systems sensors Acquisitions – Ext/Ret Valves and Actuators second order control – Local monitoring Iinterface RDCs : Braking and Steering (BSCS) – A/SKID and pressure control loop function – Specific Systems sensors Acquisitions – Local monitoring Emergency ATA32 functions controlled by specific analogue units, independent of IMA and AFDX avionics technology 4 Brake Control : Emergency Brake Control (EBCU) 4 Ext/Ret Free Fall : Free-Fall Control (FFCM)
4
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2)
A380 Landing Gear Systems – An Overview Oleo Pressure Monitoring System
• Oleo pressure is monitored simultaneously on all landing gear shock absorbers and any warning is passed on to the Flight Warning System. Prevents departure with mis-serviced Landing Gear Accurate Check - performed once per flight, after gear extension Gross Check - continuous monitoring Combined Pressure and Temperature sensor mounted on each Shock Absorber
• • • •
OPMS is designed to: • •
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Provide a warning when one or more L/G oleo pressure is outside defined limits. Provide a warning when there is an OPMS equipment failure. Provide L/G oleo pressure status to the flight and maintenance c rew. Provide other aircraft systems with L/G oleo pressure status & e quipment information via AFDX. OPMS removes the need for carrying out pre-flight oleo pressure checks by the maintenance crew.
• • •
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June 2008
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A380 Landing Gear Systems – An Overview Brake Temperature Monitoring System
BTMS (Brake Temperature Monitoring System) :
- Prevents take-off with a hot brake - Prevent landing gear retraction with a hot brake - Monitors for residual braking due to a dragging brake
Equipment:
Brake Temperature Compensation Module Brake Temperature Sensor located next to the brake heat pack.
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DGLR Hamburg
June 2008
Page 22
A380 Landing Gear Systems – An Overview Tyre Pressure Monitoring System (TPIS)
Tyre pressures are monitored simultaneously on all wheels and any warning is passed on to the Flight Warning System.
TPIS is designed to: Provide other aircraft systems with tyre pressures & equipment s tatus information. Provide tyre pressure information to the flight and maintenance crew. Provide an alert when the pressure in one or more tyres is outsi de defined limits. Provide an alert when the differential pressure between any two tyres on the same axle differs by an amount beyond defined limits.
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
TPIS can be used to carry out daily tyre pressure checks.
DGLR Hamburg
June 2008
Page 23
A380 Landing Gear Systems – An Overview Tyre Pressure Monitoring System (TPIS)
Depending on the flight phase, a warning will be triggered if a tyre pressure is detected below a given percentage of the nominal tyre pressure ( for 5 seconds continuously). Likewise, a warning will be triggered if a differential pressure above a given percentage is detected across tyres on the same axle (measured f rom the tyre with the higher pressure). A ‘TYRE PRESS LO’ message will be displayed on the E/WD if a Low or Differential tyre pressure condition is triggered.
Pressure Sensor
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Hubcap Rotating Antenna Static Antenna Electronic Module
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June 2008
Page 24
A380 Landing Gear Systems – An Overview Steering Control System
Steering is mainly effected on the NLG Wheel Pair by classic push-pull design (Nose Wheel Steering)
NWS
L R
FORWARD
1 2 3 4
5
6 9 10 11 12
7
8
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13
14
15
16
20
17
18
19
BWS
Aft Axle of BLG is steerable to ensure better manoeuvrability for small radius turn (Body Wheel Steering)
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A380 Landing Gear Systems – An Overview Steering Control System Architecture
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
DGLR Hamburg
June 2008
Page 26
A380 Landing Gear Systems – An Overview NWS Control – Gear Mounted Components
ROTARY CHANGEOVER VALVE
HYDRAULIC CONTROL BLOCK
UPPER STATIONARY FLANGE
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STEERING ACTUATOR
ROTARY COLLAR
LOWER STATIONARY FLANGE
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June 2008
Page 28
A380 Landing Gear Systems – An Overview Body Wheel Steering – Gear Mounted Components
Lock and Steering Selector Valves HCB Lock Actuator
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Pressure Switch Lock Proximity Sensors
EHSV
Steering Actuator
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June 2008
Page 29
A380 Landing Gear Systems – An Overview Brake Control System
NORMAL / ALTN BRAKING
• Body Landing Gear (BLG) & Wing Landing Gear (WLG) attached to se parate hydraulic
systems
4 BLG
– Yellow WLG – Green Yellow,
4 Single Cavity Brakes 4 Servo Valve per Wheel Pair
• LEHGS (Local electro-hydraulic generation supply)
4 Electric
motor driven pump supply Alternate hydraulics
AUTO-BRAKE • Autobrake function available in Normal & Alternate Braking mode • Comfortable & symmetric disconnect
• Provision for Brake to Vacate function
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4 Adapts
deceleration rates to runway exits
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June 2008
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A380 Landing Gear Systems – An Overview Brake Control System
WLG GROUP
FORWARD
Left Hand Wing Gear
1 2 3 4
5
6
Right Hand Wing Gear
7
8
Left Hand Body Gear LBLG WHEEL GROUP
9
10
11
12
13
14
15
16
Right Hand Body Gear RBLG WHEELGROUP
17
18
19
20
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The Braking System architecture is divided into three groups lin ked to the three wheel groups : > WLG (8 wheel braked) > BLG (8 wheel braked- aft axle wheels not braked)
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June 2008
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A380 Landing Gear Systems – An Overview Brake Control System Architecture
AFDX
A/C Green Hydraulics WLG LEHGS
COM1
ARINC 429 links
RDC1
Side 1
MON3
RDC3
COM2
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Side 2
MON4
RDC2
EBCU
A/C Yellow Hydraulics BLG LEHGS
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June 2008
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A380 Landing Gear Systems – An Overview Brake Control System – Braking Modes
Braking Modes available per wheel group.
BRAKING NORMAL ALTERNATE (WITH ANTI-SKID) ALTERNATE EMERGENCY EMERGENCY
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HYDRAULICS
•YELLOW – BLG •GREEN – WLG
CONTROL UNIT
IMA
ACTIVATION
•AUTOBRAKE •PEDALS
FUNCTIONS
•ANTI-SKID •PEDALS •AUTOBRAKE •ANTI-SKID •PEDALS •AUTOBRAKE •NO ANTI-SKID •PEDALS with limited pressure •NO ANTISKID •PEDALS with limited pressure •BRAKING ON ALL WHEELS
•LEHGS + ACCU
IMA
•AUTOBRAKE •PEDALS
•LEHGS + ACCU Or •ACCU •LEHGS + ACCU Or •ACCU •LEHGS + ACCU Or •ACCU •NORMAL Or •LEHGS + ACCU
IMA
•PEDALS
(Same as above, but with EBCU control)
EBCU
•PEDALS
ULTIMATE
EBCU
•PARK SWITCH ONLY
PARK
-
•PARK SWITCH ONLY
•BRAKING ON BLG ONLY
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June 2008
Page 33
A380 Landing Gear & Systems – An Overview Extension/Retraction System The Landing Gear Extension and Retraction System is made up of three sub-systems: The Normal System:
Landing Gear Control and Indication System (LGCIS) Side 1 and 2, implemented in IMA Nose and Wing Landing Gear and Doors - Green Hydraulic System Body Landing Gear and Doors - Yellow Hydraulic System
An Independent Freefall System for Emergency operation
Independent of IMA Dedicated uplock electrical actuators and valves Uses dissimilar technologies where possible to avoid common-mode failures Uses different wiring routes
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
An Auxiliary Ground Door Opening System
Allows on-ground access to each landing gear bay for maintenance purposes Electrically operated and controlled from GDO Panels
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June 2008
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A380 Landing Gear & Systems – An Overview Extension/Retraction System Equipment
Vent Valve Landing Gear Selector Valve
Dual Valve Actuator
Door By-Pass Valve
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
Cut-Out Valve
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June 2008
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A380 Landing Gear & Systems – An Overview Extension/Retraction System Equipment
NLG Door Uplock
Emergency Unlock Actuator Normal Unlock Actuator
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Wing Landing Gear Uplock
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June 2008
Page 36
A380 Landing Gear & Systems – An Overview Ext/Ret - Ground Door Opening
• System operation is from a Control Panel, which is accessible fr om outside the
aircraft and located near the operated door(s). There is a Control Panel for; 4 NLG (both doors) 4 L WLG (one door) 4 R WLG (one door) 4 L BLG (outer door only) 4 R BLG (outer door only)
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document.
• Operation of system commands isolation of the Gear Door Actuator via a ByPass Valve and release of the Door Uplock via the Side B EUA, allowing it open by gravity.
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June 2008
Page 38
A380 Landing Gear & Systems – An Overview Cockpit Controls and Indications
Independent Landing Gear Position Lights Brake Pressure Triple Gauge
Landing Gear Emergency Extension Switches Brake Pedal Transmitters
Normal BPTU ( Normal and Alternate Braking)
Anti-Skid selector switch
Landing Mode Rotary Selector Switch
Emergency BPTU (Emergency Braking)
Landing Gear Selector
Spring Rod
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Steering Tiller
Spring Rod Adjustable Rod
Parking Brake Selector
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Systems Display (Wheel Page)
Page 39
A380 Landing Gear & Systems – An Overview Flight Test Highlights
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June 2008
Page 41
A380 Landing Gear & Systems – An Overview Questions?
Any Questions?
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June 2008
Page 42
© AIRBUS UK LTD. All rights reserved. Confidential and proprietary document. This document and all information contained herein is the sole property of AIRBUS UK LTD. No intellectual property rights are granted by the delivery of this document or the disclosure of its content. This document shall not be reproduced or disclosed to a third party without the express written consent of AIRBUS UK LTD. This document and its content shall not be used for any purpose other than that for which it is supplied. The statements made herein do not constitute an offer. They are based on the mentioned assumptions and are expressed in good faith. Where the supporting grounds for these statements are not shown, AIRBUS UK LTD will be pleased to explain the basis thereof. AIRBUS, its logo, A300, A310, A318, A319, A320, A321, A330, A340, A350, A380, A400M are registered trademarks.
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June 2008
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