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Airbus ESDZ - José J. Jareño Diz-Lois
APPLICATIONSof the
ENGINEERINGin the
AERONAUTICS
PRESENTED BY: José Juan Jareño Diz-Lois
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Date of foundation: July 10, 2000Foundation companies: Aerospatiale Matra SA
CASA (Construcciones Aeronaúticas SA)DaimlerChrysler Aerospace AG
Gerhard Schröder
José María Aznar
Lionel Jospin
The heads of government in 2000 confirm the extension of EADS to integrate the three bounding partners
EADS today is the second-largest group in the global aerospace and defence industry, with a unique range of products and services
The Consortium
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EADS
EADS
36.4
51.6
68.2
69.3
92.9
16.6
18.7
24.4
Finmeccanica*
Thales
Raytheon
General Dynamics
Northrop-Grumman
Lockheed Martin
BAE Systems
Boeing**
179.3
18.2
23.2
28.2
44.8
16.1
10.6
6.3
14.7
Finmeccanica*
Thales
General Dynamics
Raytheon
BAE Systems
Northrop-Grumman
Lockheed Martin
Boeing
30.1
Revenuesbn €
Order Bookbn €
* Aerospace and defence activities** Commercial aviation based on catalogue prices for EADS, contractual prices for Boeing
Competitive PositionBased on 2003 average exchange rates €/$: 1.128 €/£: 0.691
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A Global Leader
Mil.Transport Aircraft
No.3
AIRBUS Commercial Aircraft
Helicopters
Commercial Launch Vehicles
Missile Systems
Satellites
Military Aircraft
No.1
No.1
No.1
No.2
No.4
No.3
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EADS Structure
Aeronautics EADSSPACE DefenceMilitary
TransportAirbus
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EADS-Employees by Divisions as 2005
Total Spain 8700 Employees
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a world of cultural diversity
Global Presence
Page 7
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Welcometo the world of Airbus
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Airbus 2005 – Current Programmes
300
200
100
400
500
600Seats
73 74 75 76 77 78 79
A310
A330-200
A340
A31889 90
ILFC
91 92 93 94 97 9895 96
SPAIN
70 71 7269
FRANCE
GERMANY
GREAT BRITAIN
80 81 82 83 84 85 86 87 88
EADS
BAESYSTEMS
AIRBUSINTEGRATED
COMPANY
01
AIRBUS
A300
A320
A330
A321
A319
A340-600
A340-500
87 88 94 98
A380
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ConceptPhase
DefinitionPhase Development Phase
FEASABILITY CONCEPT DEFINITION DEVELOPMENT SERIES
M3M3 M5M5 M7M7 M13
DEVELOP NEW AIRCRAFT PROCESS MILESTONES PLANIFICATION
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AIRCRAFT DEVELOPMENT
I. STRUCTURE
II. SYSTEMS
III. CABIN CONFIGURATION
IV. ENGINES
In the development of an aircraft the following points have a high importance for the design:
• Materials selection (metallic and non metallic)
• Manufacturing
• Standard parts (mechanics, systems, electrics)
• Corrosion prevention
• Requirements and specifications, weight, costs,…
• Testing
• Resources (work sharing)
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STRUCTURE
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AERODYNAMIC SURFACES
A380 Belly Fairing A380 Section 19 A380 Section 19.1
A380 HTP A380 Rudder A380 Wing
Aerodynamic shape of the A/C for getting flight and performances requirements (lift, drag, noise, speed, etc.)
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PRESSURES DISTRIBUTION
Euler algorithm Panels method
Analytical studies aimed to estimate the pressure coefficient on each part of the aircraft surfaces in a wide range of flight conditions and configuration cases
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PRESSURES DISTRIBUTION
RANS (Reynolds Averaged Navier-Stokes) Method
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STRUCTURAL ARRANGEMENT
A380 Belly FairingA380 Section 19
A380 HTPA380 Wing
Geometrical references of aircraft external and internal shapes, and the major co-ordinate systems and datum lines
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DESIGN STUDIES AND ALTERNATIVES
CENTER JOINT
LATERAL BOX
WITH CENTER JOINT (NO CENTER BOX)WITH CENTER BOX
LATERAL BOX
CENTER BOX
Different possibilities of a technical solution to be evaluated by the involved departments that meet one or several requirements which aim at defining the optimised solution at the lower cost in the shortest time.
EXAMPLE A340/600EXAMPLE A330/340
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SPACE ALLOCATION MOCK-UP
A380 Belly Fairing A380 Section 19.1
Simplified envelope volumes for structure and system parts (including installation) allowing to allocate space between structures and systems and to validate structure and systems architectures
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SPACE ALLOCATION MOCK-UP
A380 Section 19A380 HTP
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DESIGN - STRESS Design loop (Metallic or CFRP parts)
DESIGN STRESS
Design concept FEM with loads
Stress results
New dimensioning
Two new Flanges: thickness = 3.5 mm
Without Hole
Without Hole
New proposal
Definitive part
Official part drawing
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FEM AND STRESS ANALISYS
AIRCRAFT C.G.AIRCRAFT LIFT LOAD
APPLICATION POINT (EXCEPT HORIZONTAL TAILPLANE)
HORIZONTAL TAILPLANE FORCE APPLICATION POINT
AIRCRAFT C.G.AIRCRAFT LIFT LOAD
APPLICATION POINT (EXCEPT HORIZONTAL TAILPLANE)
HORIZONTAL TAILPLANE FORCE APPLICATION POINT
GENERAL AIRCRAFT BALANCE
TOTAL FUSELAGE WEIGHT FWD OFTOTAL FUSELAGE WEIGHT AFT OFTOTAL FUSELAGE WEIGHT FWD OFTOTAL FUSELAGE WEIGHT AFT OF
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FEM AND STRESS ANALISYS
TYPICAL HTP PRELIMINARY FEM
HTP STRESS ANALISYS
Model of one A/C component simulating its geometry, materials properties, types of attachment, constraints, etc
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FEM AND STRESS ANALISYS
SECTION 19 AND 19.1. FINITE ELEMENT MODEL (FEM)
PRELIMINARY RESERVE FACTOR ANALYSIS (IMPACT OF A NEW LOAD LOOP)
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FEM AND STRESS ANALISYS
HTP AND SECTION 19. FINITE ELEMENT MODEL (FEM)
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PRELIMINARY SIZING (A380 Example)
Section 19 Lateral Upper panel thickness distribution
SK239
Baseline providing minimum data (basic dimensions and thickness) to start production of 3D models
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PRELIMINARY SIZING (A380 Example)
Actual frame sectionMouse hole sectionSkin panel
Linner
Ld
Hweb
Lst
Section 19 composite frame
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PRELIMINARY SIZING (A380 Example)
2 columns of rivets at each side of the joint
3 rivets at each side of the joint A
A
Section 19 metallic frames joint
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DESIGN PRINCIPLES
Technical solutions to the A/C that meets the applicable requirements.
It presents detailed information in order to demonstrate that the design fulfil all the requirements (stress, production, economy, reparability, supportability,…) and to enable the validation of the design by all the stake holders through a maturity process
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DESIGN PRINCIPLES (Maturity levels A, B, C)
DPCompleted
DPCompleted
CONFIDENCE Enhanc
ement
CONFIDENCE Enhanc
ement
Design ReviewDesign Review Design ReviewDesign Review
Maturities provide information about the progress status (real and planned) of a definition, and consequently about the level of confidence in the proposed solution.
DefinitionConceptM3 M7
DefinitionM5
MaturityLevel A
MaturityLevel C
MaturityLevel B
Many solutions are studied and discussed
One solution is selected and validated
Sum up good ideasRealise Feasibility
studies
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SYSTEMS
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SYSTEMS and EQUIPMENT LAY-OUT DEFINITION
Location of systems components on the structure, like fuel, water, hydraulic pipes, mechanical commands (rods, cables, etc.), electrical harnesses, etc. The attachment of those components to structure (brackets) is also part of Systems Lay-out.
ATA 21. AIR CONDITIONING/VENTILATIONATA 25. SUPPLEMENTAL COOLINGATA 27. FLIGHT CONTROLSATA 28. FUELATA 29. HYDRAULICSATA 32. LANDING GEARSATA 33. LIGHTSATA 36. BLEEDATA 38. WATER & WASTEATA 25 & 38. DRAINAGEATA 92. ELECTRICS
Location of equipments on the structure, like landing gears, electronic bays, electric/hydraulic/pneumatic equipments, actuators, etc. The linking elements between them are part of the Systems Installation
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BLEED AIR
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FLIGHT CONTROLS
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LANDING GEAR
Body landing gear
Nose landing gear
Wing landing gear
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CABIN CONFIGURATION
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CABIN CONFIGURATION
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HTP A380
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S19 A380
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COCKPIT A380
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WING BOX BODY A380
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S18 A380
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A380
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A380
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Thank youfor your attention
Please visit www.airbus.com for more information
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