Company GURUCAD GERMANY GmbH is specialized, since 2nd of April 2008, on delivering Engineering Work-Packages (Design, Stress & Certification Documentation) for Composites, Hybrid and Metallic Aerospace Structures to global Aerospace OEM’s and their suppliers worldwide during Preliminary, Detail and Development Phases until Serial Manufacturing Release:
Primary Structure (composites, hybrid, metallic): skins, frames, stringers, clips, cleats, stringer/frame couplings ... assembled as complete side / upper / lower shells or complete sections
Passenger / Cargo Floor-Grid Structure (composites, hybrid, metallic): crossbeams, seat-tracks/rails, floor panels, X-Struts ...
Passenger / Cargo / Emergency Door Structure (composites, hybrid, metallic): door skins, door frames, door beams, fittings, mechanisms ...
Secondary Structure / Brackets (composites, hybrid, metallic) for: structural reinforcements, fittings, couplings, insulation, systems (air conditioning, water, waste, vacuum, oxygen, pneumatic, hydraulic, fuel, electrical, bonding ...), cabin components (hatracks, ceilings, side wall panels, dado-panels, galleys, lavatories, stowages, crew-rest compartments, bars ...)
Structure Provisions for conversions from passenger aircrafts to corporate business jets or VVIP business jets
Structure Provisions for conversions from freighter aircrafts to corporate business jets or VVIP business jets
Structure Provisions for conversions from passenger aircrafts to freighter aircrafts
Structure Provisions for conversions from freighter aircrafts to passenger aircrafts
Company GURUCAD GERMANY GmbH delivered Work-Packages for Composites, Hybrid and Metallic Aerospace Structures on following Aircraft Programs:
Airbus A350XWB Family - Extra Wide Body: A350XWB-900 / A350XWB-1000
Airbus A320 Family - Single Aisle: A321XLR / A319neo / A320neo / A321neo / A319ceo / A320ceo / A321ceo / legacy: A318, A319, A320 and A321
Airbus A330 Family - Wide Body - Long-Range: A330neo / legacy A330 / A340
Airbus A380 Family - Double Deck: A380
Airbus Corporate Jets Family: A319ACJ / A320ACJ / A330ACJ / legacy A321 / legacy A330 / legacy A340 in VVIP configurations
Airbus Freighters: A350F / A330-200F / A321P2F / A330P2F / Beluga XL / Beluga ST / concept project A380F / legacy: A330F and A340F
Airbus Military Aircrafts: A400M Airlifter and A330 Multi-Role Tanker Transport (MRTT)
Boeing 787 Dreamliner
Boeing 777
Boeing legacy 767
Boeing 747: 747-8 Intercontinental and legacy B747
Boeing Business Jets: 787, 747-8 Intercontinental, legacy B747, legacy 777, legacy 767 in VVIP configurations
COMAC ARJ21-700 Xiangfeng / Rising Phoenix
Company GURUCAD GERMANY GmbH creates and delivers following engineering data in Work-Packages for Composites, Hybrid and Metallic Aerospace Structures:
3D CAD Models
Stacking and Staggering Data as Excel or Text-Files for Composites 3D CAD Models
Holes & Fasteners 3D CAD Models
CAD Catalogs with 3D CAD Models and 2D Drawings Details / Templates
2D CAD Drawings in form of manufacturing, assembly and installation drawings based on aviation or OEM's standards in ISO or DIN Formats
Bill of Materials (BoM's) as Excel, Text-Files, inside 2D CAD Drawings or inside customer PDM- / PLM- / ERP-Systems
Weight Reports and Delta Weight Reports as Excel, Text-Files or inside 2D CAD Drawings
Clash / Clearance / Segregation Detection Reports in PowerPoint, Excel, Text, HTML, XML-Formats
Vizualization 3D CAD Models of complete Aircraft Sections (3D data reduction, merging of 3D data)
Product Documentation (Technical Documentation, Assembly / Installation Instructions ...)
3D / 2D Data Migration between different formats
FEM - CAE Finite Element Models for Structure Static Stress Analysis
FEM - CAE Finite Element Models for Structure Fatigue and Damage Tolerance Analysis
FEM - CAE Finite Element Models for Structure Thermal Analysis
FEM - CAE Finite Element Models for Structure Optimization Analysis
Hand calculation (rivets, fasteners, buckling and stress justification) in form of Word, Excel, XML or HTML-Files
Static Stress Reports in Word or PDF-Format
Qualification / Certification Stress Reports in Word or PDF-Format
Justification Stress Reports in Word or PDF-Format
Substantiation Stress Reports in Word or PDF-Format
Interface Loads Reports in Word or PDF-Format
Windmilling Stress Reports in Word or PDF-Format
Engineering Test Plans in Word or PDF-Format
Engineering Test Reports in Word or PDF-Format
Static Test Plans in Word or PDF-Format
Static Test Reports in Word or PDF-Format
Qualification / Certification Test Plans in Word or PDF-Format
Qualification / Certification Test Reports in Word or PDF-Format
...
Company GURUCAD GERMANY GmbH uses following software to create engineering data in Work-Packages for Composites, Hybrid and Metallic Aerospace Structures:
CATIA V5 including Composites (Grid) Design Workbench and Generative Part / Assembly Structural Analysis (GPS / GAS)
3D Experience / CATIA V6
Q-Checker
Siemens NX
SolidWorks
Nastran-Patran
Hyperworks (HyperMesh / Radioss)
Femap / NX Nastran
COSMOS / FEM inside SolidWorks
Enovia VPM 3dcom
Teamcenter
SAP
PASS SSI
PDMLink SSCI-PSE / CC
Some of the Engineering Work-Packages (Design, Stress & Certification Documentation) for Composites, Hybrid and Metallic Aerospace Structures that company GURUCAD GERMANY GmbH delivered, since 2nd of April 2008 until today, to global Aerospace OEM’s and their suppliers worldwide during Preliminary, Detail, Development and Serial Manufacturing Release Phases are:
Development and Design of Primary Structure (composites, hybrid, metallic) for Sections 13-14 and 16-18 of Airbus A350XWB-900 and A350XWB-1000 aircrafts: skins, frames, stringers, clips, cleats, shearwebs, stringer/frame couplings ... using CATIA V5 Composites Grid Design, Aerospace Sheetmetal, Generative Shape Design, Part Design, Assembly Design and Drafting Workbenches and Airbus A350XWB Toolset. Project duration: 3 years. Following Engineering Data was delievered in this Work-Package inside Airbus Engineering Concurrent Collaborative Environment through Extended Enterprise Access Gate:
native CATIA V5 3D Models for single parts and their design solutions / assemblies inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Stacking and Staggering Data as Excel Files for CATIA V5 Composites - CPD 3D Models
Holes & Fasteners CATIA V5 3D Models inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Clash / Clearance / Segregation Detection Reports in MS PowerPoint and PDF Formats
native CATIA V5 2D Drawings in form of manufacturing / single parts and assembly drawings based on Airbus Standard in ISO Format inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Bill of Materials (BoM's) inside PDMLink SSCI-PSE / PASS SSI
Release / Validation process start and follow-up until Airbus release inside PDMLink SSCI-PSE / PASS SSI
Development, Design and Stress of Secondary Structure / Brackets (composites, hybrid, metallic, 3D-Print) for Airbus A350XWB-900 and A350XWB-1000 aircrafts: structural reinforcements, fittings, couplings, insulation, systems (air conditioning, water, waste, vacuum, oxygen, pneumatic, hydraulic, fuel, electrical, bonding ...), cabin components (hatracks, ceilings, side wall panels, dado-panels, galleys, lavatories, stowages, crew-rest compartments, bars ...) using CATIA V5 Composites Grid Design, Aerospace Sheetmetal, Generative Shape Design, Part Design, Assembly Design and Drafting Workbenches, Nastran-Patran and Airbus A350XWB Toolset. Project duration: 6 years. Following Engineering Data was delievered in this Work-Package inside Airbus Engineering Concurrent Collaborative Environment through Extended Enterprise Access Gate:
BDPC - Brackets Design Principle Catalog - native CATIA V5 3D Models for single parts and their mini-assemblies inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
native CATIA V5 3D Models for design solutions / assemblies inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Stacking and Staggering Data as Excel Files for CATIA V5 Composites - CPD 3D Models
Holes & Fasteners CATIA V5 3D Models inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Clash / Clearance / Segregation Detection Reports in MS PowerPoint and PDF Formats
native CATIA V5 2D Drawings in form of manufacturing / single parts, assembly and installation drawings based on Airbus Standard in ISO Format inside Enovia VPM 3dcom and their meta-data inside PDMLink SSCI-PSE / PASS SSI
Bill of Materials (BoM's) inside PDMLink SSCI-PSE / PASS SSI
Release / Validation process start and follow-up until Airbus release inside PDMLink SSCI-PSE / PASS SSI
FEM - CAE Finite Element Models for Structure Static Stress Analysis using Nastran-Patran
Hand calculation (rivets, fasteners, buckling and stress justification) in form of Word and Excel-Files
Static Stress Reports in Word and PDF-Format
Development and Design of:
Primary Structure (metallic): skins, frames, stringers, clips, cleats, stringer/frame couplings ... assembled as complete side / upper / lower shells and complete sections
Passenger / Cargo Floor-Grid Structure (metallic and composites): crossbeams, seat-tracks/rails, composites floor panels, X-Struts ...
Passenger / Cargo / Emergency Door Structure (metallic): door skins, door frames, door beams, fittings, mechanisms ...
Secondary Structure / Brackets (metallic) for: structural reinforcements, fittings, couplings, insulation, systems (air conditioning, water, waste, vacuum, oxygen, pneumatic, hydraulic, fuel, electrical, bonding ...), cabin components (hatracks, ceilings, side wall panels, dado-panels, galleys, lavatories, stowages, crew-rest compartments, bars ...)
for Sections 13-14 and 16-18 of Airbus Wide Body - Long-Range A330 / A340 aircrafts, using CATIA V5 Aerospace Sheetmetal, Generative Shape Design, Part Design, Assembly Design and Drafting Workbenches and Airbus Long-Range Toolset. Project duration: 3 years. Following Engineering Data was delievered in this Work-Package inside Airbus Engineering Concurrent Collaborative Environment through Extended Enterprise Access Gate:
native CATIA V5 3D Models for single parts and their design solutions / assemblies inside Enovia VPM 3dcom and their meta-data inside Airbus Taksy Tool
Holes & Fasteners CATIA V5 3D Models inside Enovia VPM 3dcom and their meta-data inside Airbus Taksy Tool
Clash / Clearance / Segregation Detection Reports in MS PowerPoint and PDF Formats
native CATIA V5 2D Drawings in form of manufacturing / single parts and assembly drawings based on Airbus Standard in ISO Format inside Enovia VPM 3dcom and their meta-data inside Airbus Taksy Tool
Bill of Materials (BoM's) inside Airbus Taksy Tool
Release / Validation process start and follow-up until Airbus release inside Airbus Taksy Tool
Design, Stress and Certification Documentation of Structural Provisions for the first Business Jet conversion of Chinese COMAC ARJ21-700 Xiangfeng / Rising Phoenix aircraft:
FWD Stowage Top and Bottom Attachments
Conference Dining Seats Bottom Attachments
Conference Dining Table Bottom Attachments
Private Suite Top and Bottom Attachments
VIP Seats Bottom Attachments
Credenzas Top and Bottom Attachments
Partition 1 Top and Bottom Attachments
Partition 2 Top and Bottom Attachments
Partition 3 Top Attachments
AFT Partition Wall Top and Bottom Attachments
Stowage AFT Bar Top and Bottom Attachments
AFT Bar Top and Bottom Attachments
AFT Lavatory Top and Bottom Attachments
Diplexer Satcom Top Attachments
SC Band Stub Antenna Top Attachments
Additional TRU Installation Structure and its Bottom Attachments
New Auxiliary Equipment Rack Structure and its Top and Bottom Attachments for additional Avionics and Electrical Equipments
using CATIA V5 Generative Shape Design, Part Design, Assembly Design and Drafting Workbenches and Nastran-Patran. Project duration: 2,5 years. Following Engineering Data was delievered in this Work-Package inside customer Data-Transfer Portal Server:
native CATIA V5 3D Models for single parts and their assemblies
Clash / Clearance / Segregation Detection Reports in MS PowerPoint and PDF Formats
native CATIA V5 2D Drawings in form of manufacturing / single parts, assembly and installation drawings based on COMAC Standard in DIN Format
Bill of Materials (BoM's) in MS Excel-Format
Weight Reports in MS Excel-Format
FEM - CAE Finite Element Models for Structure Static Stress Analysis using Nastran-Patran
Hand calculation (rivets, fasteners, buckling and stress justification) in form of Word and Excel-Files
Certification Static Stress Reports in Word and PDF-Format
Complete Aircraft Fuselage DMU creation for the first Business Jet conversion of Chinese COMAC ARJ21-700 Xiangfeng / Rising Phoenix aircraft: ATA21, ATA22, ATA23, ATA24, ATA25, ATA26, ATA27, ATA28, ATA29, ATA30, ATA31, ATA32, ATA33, ATA34, ATA35, ATA36, ATA38, ATA45, ATA49, ATA52, ATA53, ATA71, ATA78 and ATA88 using CATIA V5 DMU Space Analysis, DMU Navigator, Part Design and Assembly Design Workbenches. Project duration: 6 months. Following Engineering Data was delievered in this Work-Package inside customer Data-Transfer Portal Server:
Creation of CATIA V5 Vizualization 3D Models of complete Aircraft Fuselage ATA Chapters and complete Structure Sections (3D data reduction, merging of 3D data in cgr and stp formats)
Consistency Check of created CATIA V5 Vizualization 3D Models of complete Aircraft Fuselage ATA Chapters and complete Structure Sections, in cgr and stp formats, against native CATIA V5 data
... and more than 75 similar Design, Stress and Certification Documentation Work-Packages for Airbus, Boeing and COMAC Aircrafts.