Application of a distributed MDAO framework to the design of a short- to medium-range aircraft
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1 Chart 1 > Lecture > Author Document > Date Application of a distributed MDAO framework to the design of a short- to medium-range aircraft Erwin Moerland, Thomas Zill, Björn Nagel DLR, Institute of Air Transportation Systems Holger Spangenberg, Holger Schumann, Peter Zamov DLR, Institute of Flight Systems
2 Chart 2 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Contents MDO Case study System-of-systems approach Design interfaces Initial integration setup Conclusion advancing multidisciplinary design & optimisation design study guiding the integration combining aircraft predesign & design of aircraft systems coupling both design methods aircraft design results, systems design approach conclusive remarks & future challenges
3 Power Equation LP Spool Power Equ. HP Sp. COM COM HPT Cooling Chart 3 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Multidisciplinary Design & Optimisation Definition introduced by Prof. I. Kroo and Prof. J.J. Alonso, Stanford University 1st generation analysis-based design computations 2nd generation Workflow management 3rd generation Optimisation assisted design in teams optimisation algorithms approximation techniques networked computing # disciplinary interfaces management of knowledge collaboration of engineers and tools
4 OAD knowledge Chart 4 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Actors within system-of-systems design approach Operators gather resources establish design teams Workflow integrators setup design workflows integrate analysis modules System experts provide disciplinary knowledge generate analysis modules Knowledge detail
5 Chart 5 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 configuration connection environmental impact Common Design Engine integration System- Layout
6 Chart 6 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Aircraft redesign for short ranges payload 190 [pax] 135 [kg] all economy class with 30 seat pitch range 1000 [NM] design range TOFL LFL cruise Mach 2000 [m] 1500 [m] level, MTOW, ISA +15 level, MLW, ISA +15 C span 36 [m] maximum altitude Selection of TLAR for the case study FL 350 FL 410 initial climb cruise Nearly 80%: missions with sector length < 1000 [NM] 1 1 Source: OAG Aviation - OAG Schedules Data, 2007
7 output conv. synth. analysis Level 0 Level 1 Level 2 Level 0 Level 1 Level 2 Level 3 systems preliminary design req. def. Chart 7 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Top Level Aircraft Requirements (TLAR) 1 high-lift concept minimum aircraft dataset System boundaries reference high-lift concepts 2 VAMPzero initial aircraft configuration (CPACS) ParADISE systems architecture (PrEMISE) 3 aircraft preliminary design source: boeing-727.com 4 5 mass converger feasibility & mass evaluation 6 final aircraft configuration (CPACS) final systems architecture (PrEMISE, CATIA)
8 output conv. synth. reiterate reiterate analysis systems preliminary design req. def. Chart 8 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Top Level Aircraft Requirements (TLAR) 1 high-lift concept minimum aircraft dataset interface System boundaries reference high-lift concepts 2 VAMPzero initial aircraft configuration (CPACS) 2 1 ParADISE systems architecture (PrEMISE) 3 aircraft preliminary design Aerodynamic polars Loadcase determination Aerodynamic forcedistributions WINGmass main wing second. struct. Engine performance map 3 input files (tool specific input format) kinematics actuation safety support structure Mission simulation 4 VAMPzero synthesis ParADISE synthesis 5 mass converger feasibility & mass evaluation 6 final aircraft configuration (CPACS) final systems architecture (PrEMISE, CATIA)
9 Chart 9 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 1/3: Data Exchange Format Common Parametric Aircraft Configuration Scheme (CPACS) XML based <tags>used to build hierarchic structure</tags>: name description reference fuselages header aircraft model 1 wings vehicles engine model 2 engines CPACS missions airports profiles struct.elem model N ldg. gear systems fleets materials global toolspecific composites analyses
10 Pairwise integration approach Chart 10 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 1/3: Data Exchange Format Common Parametric Aircraft Configuration Scheme (CPACS) Pragmatic Engineering Model for Integrated Systems Engineering (PrEMISE) and Integrated data model approach
11 tool wrapping Chart 11 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 1/3: Data Exchange Format Common Parametric Aircraft Configuration Scheme (CPACS) Pragmatic Engineering Model for Integrated Systems Engineering (PrEMISE) and CPACS extract convert to tool lang. write input write convert to CPACS read output disciplinary calculation wrapped disciplinary tool convert to tool lang. ParADISE PrEMISE convert to PrEMISE disciplinary calculation disciplinary tool central specific input file generation
12 Chart 12 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 2/3: aircraft design results Decentralised computation framework: RCE for CPACS Initiation Iterations until convergence Tools remain on owners servers. Exchange of input and output in CPACS format via the network. For a more elaborate discussion on RCE and collaborative data management, please see: D. Böhnke, Challenges for Collaborative Data Management in an MDAO Process (DLRK2012)
13 Chart 13 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 2/3: aircraft design Parametric interfaces between aircraft and systems predesign Aircraft design wing dimensions types of moveables and target settings secondary wing component: - dimensions - loads - weights CPACS geometry Level 0 Level 1 Level 2
14 Chart 14 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Interface 3/3: systems design Parametric interfaces between aircraft and systems predesign Systems design high-lift concept feasibility high-lift support structure: - locations - dimensions system properties: - weight - costs - power budget
15 output conv. synth. reiterate reiterate analysis systems preliminary design req. def. Chart 15 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Top Level Aircraft Requirements (TLAR) 1 high-lift concept minimum aircraft dataset interface System boundaries reference high-lift concepts 2 VAMPzero initial aircraft configuration (CPACS) 2 1 ParADISE systems architecture (PrEMISE) 3 aircraft preliminary design Aerodynamic polars Loadcase determination Aerodynamic forcedistributions WINGmass main wing second. struct. Engine performance map 3 input files (tool specific input format) kinematics actuation safety support structure Mission simulation 4 VAMPzero synthesis ParADISE synthesis 5 mass converger feasibility & mass evaluation 6 final aircraft configuration (CPACS) final systems architecture (PrEMISE, CATIA)
16 Chart 16 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Conclusion System-of-systems approach in preliminary design Proper disciplinary interfacing techniques Integration frameworks Large potential for increasing OAD knowledge in predesign phases Challenges Technical: connecting disciplinary analysis tools Non-technical: establishing effective communication more research focus on the organisational level of MDO
17 Chart 17 > Application of a distributed MDAO framework > Erwin Moerland DLRK2012 > 10 th of September 2012 Collaborative Design in the Integrated Design Lab
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