Structure Design. May Korea Aerospace Industries, Ltd.

Transcription

1 Structure Design May Korea Aerospace Industries, Ltd.

2 Contents Introduction of A350XWB Wing Configuration Design Procedure Manufacturing Requirement Q&A -1-

3 Introduction of A350XWB -2-

4 A350 Xtra Wide Body -3-

5 Seating & Range Comparison -4-

6 Material Composition Misc. Composites 53% 8% 19% Al/Al-Li 6% 14% A XWB Material Breakdown (%) Including Landing Gear Steel Titanium CFRP Wings Centre wing box and keel beam Tail cone Skin panels Frames, stringers and doublers Doors (Passenger & Cargo) Titanium High load frames Door surroundings Landing gear Pylon -5-

7 Technology The very latest in aerodynamics, design and advanced technologies. Fuselage More than 60 % of new materials, chosen for their superior weight and strength properties, Innovative use of all-new Carbon Fibre Reinforced Plastic (CFRP) Much easier maintenance and reparability. Weight savings via optimum fibre lay-up and skin thickness tailored to the requirements of the location. Wing The all-new composite wing design Cruise speed to Mach 0.85 (the cruise speed of the A380). Excellent aerodynamics, together with advanced high lift devices and advanced systems. Building on the A380 interactive cockpit and systems, the XWB Family will feature- modern functions such as an airport navigation system and the brake to vacate, a system designed to optimize braking for passenger comfort and better runway usage. Exemplary reliability in service with longer maintenance intervals and customised maintenance schedules to help provide airlines with higher operating productivity. A 21st Century solution for an aircraft in this size category. -6-

8 Extended Enterprise View -7-

9 Mapping Across Airbus Plants Wing Box Assembly & partial Equipping Broughton Stade Hamburg VTP Assembly & Equipping Section 16/18 panels Upper wing cover Bremen Section 13/14 Equipping+ Section 16/19 Assembly & Equipping Wing Equipping Saint Nazaire S 11/14 + S 15/21 assembly & Equipping Nantes Centre Wing Box Keel Beam & aft lower shell Toulouse Final Assembly Line Pylon assembly & Equipping Getafe S19 Manufacturing-Assembly-Partial Equipping HTP assembly & Equipping Lower wing cover Composite technologies Equipping & Assembly -8-

10 Wing Configuration -9-

11 Wing Rib Interface -10-

12 Wing Rib Interface Fixed Leading Edge -11-

13 Wing Rib Interface Front Spar Three pieces of Composite Spar -12-

14 Wing Rib Interface Inboard Fixed Trailing Edge (Inboard Flap Area) -13-

15 Wing Rib Interface Mid Fixed Trailing Edge (Outboard Flap Area) -14-

16 Wing Rib Interface Outboard Fixed Trailing Edge ( Aileron Area ) -15-

17 Wing Rib Interface Wing Tip -16-

18 Wing Rib Interface Upper Cover -17-

19 Wing Rib Interface Lower Cover -18-

20 Wing Rib & Diaphragm Layout -19-

21 Wing Rib & Diaphragm Baseline Summary Ribs 2, 2A & 9-33 Metallic T7651, for billets less than 100mm(rib 28, 29, 31-33) /7050 T7651, for billets greater than 100mm T7451, for billets greater than 200mm & mill capability limitation(rib 2, 9) Ribs 3-8 Metallic 2050 T84 Al_Li Double sided feet, single sided body features(except fuel tank boundaries) Metallic Fuel Tank Boundaries staggered along ribs 4-7 & 7-9 Intermediate Stiffener Ribs Pylon Diaphragm (aluminium forging Al7010- T7652) Surge Tank between Ribs Metallic 2024 T3 stringer seal plates Metallic 2024 T3 corner seal plates -20-

22 Wing Rib Configuration Rear Spar Interface Lightening Hole Stringer Cut-Out Horizontal Stiffener Front Spar Interface Rib Foot Castellation System Penetration Primary Vertical Stiffener Intermediate Vertical Stiffener Manhole Butterfly Foot Standard Foot (Dog Bone) -21-

23 Diaphragm Configuration Rib 10 Pylon Diaphragm Rib 4 Manhole Door Fuel Tank Boundary Diaphragm -22-

24 System Brackets -23-

25 Design Procedure -24-

26 Concept of Maturity A Maturity for the WP This maturity is used to prove the feasibility of the Work Package by allowing a divergence of zonal concepts. They are very much focused on significant structural interfaces and critical (high risk/problematic) zones. Several configurations or studies may be produced in order to meet the design requirements. A-Maturity Review (A-MAT) marks the end of A-Maturity. B Maturity for the WP This maturity demonstrates detail design principles for structure and system installation aspects and includes Geometric Dimension & Tolerance (GD & T) analysis and key Work Package characteristics. B-Maturity-Preliminary Design Review (B-MAT-PDR) marks the end of B-Maturity. C Maturity for the WP SAM is developed into the DMU to enable Work Package detail design in the context of Aircraft geometry, based on critical jig shape. This will enable the Frontier models to be used and updated. The maturities demonstrate detail design principles for Structure, Systems and installation aspects, including Flight Test Installation (FTI) that conforms to the build philosophy, datum and Key Characteristics previously agreed. C-Maturity-Critical Design Review (C-MAT-CDR) marks the end of this maturity level. -25-

27 Concept of Maturity -26-

28 Design Tool -27-

29 Drawing Set -28-

30 Release Process DDC : Definition Dossier Check -29-

31 Rib model Composition Upper Feet (-10 ~ -19) Body (-00 ~ -09) Lower Feet (-20 ~ -29) -30-

32 Rib Automation Tool -31-

33 Rib Automation Tool -32-

34 Master Geometry < Cover OML > < Strip Surface > < Rib DATUM> < Spar DATUM> < Stringer DATUM> -33-

35 User Defined Feature A User Defined Feature(UDF) has been created for each feature contained within a rib body solid These UDF s can then be instantiated on to the Wireframe geometry in order to remove material from the rib billet solid The result is a rib model that is generated in the same way as it will be machined This modelling method allows full geometry to be created and parametrically controlled quicker and easier than manual methods -34-

36 CATIA Tree Composition Master Geometry Wireframe part Sub model Wireframe Model -35-

37 Detail Design with ASD -36-

38 Detail Design with ASD -37-

39 Manufacturing Requirement -38-

40 Cutter Trace Line (CTL) -39-

41 Minimum Thickness & Length -40-

42 Flange Profile -41-

43 Flange Profile -42-

44 Butterfly Foot Landing -43-

45 Pad Up Thickness -44-

46 Metal Removal -45-

47 Pocket Step -46-

48 Acute Angle Machining -47-

49 Acute Angle Machining -48-

50 Obtuse Angle Machining -49-

51 Machining Example Area only for manufacturing -50-

52 Corner & Fillet Radius -51-

53 Corner Radius & Depth -52-

54 Rib 28 & Rib 6-53-

55 Rib Assembly -54-

56 Rib Assembly -55-