The corporate presentation -The Airbus way
Transcript of The corporate presentation -The Airbus way
Airbus - 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 Aeronáuticas 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
EADS
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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 (more than 100.000 employees)
Astrium
Defence and security
Military Transport
Airbus
Eurocopter
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Welcome to Airbus
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a world of cultural diversity
AIRBUS Global Presence 2007
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20 languages
More than 5,000 aircraft delivered
57,000 employees (Airbus Spain 3000 employees)297 customers
more than 88 nationalities
Gross market share: 51 %
EVERY 3 SECONDS AN AIRBUS AIRCRAFT TAKES OFF OR LANDS SOMEWHERE IN THE WORLD
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A350-800
350
300
250
200
100
150
400
500
450
550
Range with full passenger load (nautical miles)
600 Typical seating
A300-600
A320
A319
A321A310-300
4,000 6,000 8,000 9,0007,0005,0003,000
A330-200
A330-300
A318
A340-500
A340-600
A380-800
A350XWB-800
A350XWB-900
A340-300
Airbus 2007 – Current Programmes
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ConceptPhase
DefinitionPhase Development Phase
FEASABILITY CONCEPT DEFINITION DEVELOPMENT SERIES
M3 M5 M7 M13
DEVELOP NEW AIRCRAFT PROCESS MILESTONES PLANIFICATION
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AIRCRAFT DEVELOPMENT
I. STRUCTURE
II. SYSTEMS
III. CABIN CONFIGURATION
IV. POWER PLANT
In the development of an aircraft the following points have a high importance for the design:
• Materials selection (metallic and non metallic).
• Industrial Manufacturing – Assembly.
• Weight.
• Costing.
• Harmonization and standardization (mechanics, systems, electrics).
• Technical issues: Corrosion prevention, lightning protection,…
• Technical and customer requirements.
• Testing.
• Resources (work sharing).
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STRUCTURE
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AERODYNAMIC SURFACES
A380 HTPA380 Rudder
Aerodynamic shape of the A/C for getting flight and performances requirements (lift, drag, noise, speed, etc.)
A380 REAR A380 Belly Fairing
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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 Section 19
A380 HTP
A380 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
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
A380 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
GENERAL AIRCRAFT BALANCE
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FEM AND STRESS ANALISYS
TYPICAL HTP PRELIMINARY FEM
HTP STRESS ANALISYS FEM
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 HTP FEM
PRELIMINARY RESERVE FACTOR ANALYSIS (IMPACT OF A NEW LOAD
LOOP)
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FEM AND STRESS ANALISYS
WING BOX BODY 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)
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
Design Review Design 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 & EQUIPMENTS
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SYSTEMS and EQUIPMENT LAY-OUT DEFINITION
Location of systems components on the structure, like fuel, water, hydraulic, 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 49 AUXILIARY POWER UNITATA 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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TEST PLANNING
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HTP A380
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S19 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 TRANSPORT
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Thank youfor your attention
Please visit www.airbus.com for more information