An Advanced Extensible Parametric Geometry Engine for Multi-Fidelity and Multi-Physics Analysis in Conceptual Design

Transcription

1 An Advanced Extensible Parametric Geometry Engine for Multi-Fidelity and Multi-Physics Analysis in Conceptual Design Rob McDonald & David Marshall Cal Poly Andy Ko. JR Gloudemans NASA Glenn July 23, 2012

2 2.2 Robust Aircraft Conceptual Design Geometric Modeling Objective Motivation The objective of this topic is to enhance the ability to employ higher-order, physics-based analysis during conceptual design through robust, easy to create geometry models. The research goal is to automate the rigorous steps required for intelligent conversion of a conceptual level parametric geometry model into the detailed representation necessary for higher-order analysis. Conceptual design is the starting point for a new engine or aircraft development. A successful design is highly dependent on accurate geometric representations, since they are used throughout the computational engineering process. Over the past several decades computational capability has drastically improved as has the understanding of human-computer interfaces. These advances have enabled less experienced users to perform far more sophisticated tasks without the requirement of extensive training time. More accurate geometry representations will advance the state-of-art in conceptual design by enabling more routine use of higher-order analysis tools. Approach A key need of conceptual design is the ability to quickly articulate ideas and engineering concepts into a digital 3-D database. While this can be accomplished through building a CAD (computer aided design) model of the geometry, it would be valuable to have the ability to parameterize the geometry s characteristics. Parametric overlays to CAD programs can be performed, but there can be negative implications to this approach. For instance, it requires users to obtain often expensive software, and there can be inherent limitations with a given CAD package. Therefore, a prerequisite of any valuable conceptual design geometry solution is that it be parametric-input based and use aircraft design terminology to communicate effectively with the user (e.g., span, aspect ratio, chord). Currently, there are no accepted standards for parametric-based geometry representations to facilitate sharing of geometry. There is a need to create a generalized standard for parametric geometry and an approach to transfer geometry models in that standard to CADbased models. These new approaches to streamline the conversion of conceptual geometry to the geometry representation needs of more detailed analysis, however, should not diminish the ability to rapidly explore the conceptual design space using a parametric geometry tool. NASA has made prior investments in the development of a parametric geometry tool for conceptual design [i.e., Vehicle Sketch Pad (VSP)]. There is a need, however, to create better coupling between higher-order engineering analysis codes and geometry tools like VSP. The developed geometry methods should be flexible in nature and must be compatible with, and support, NASA s existing ModelCenter-based systems analysis and conceptual design process. An overview of the tools used in a ModelCenter environment is available in the Other Documents section at: Expected Outcome The new capability shall provide parametric-based geometry modeling and analysis methodologies that enable conceptual designers to accomplish analyses in a faster, easier manner. In addition, the geometric representation will enable transferring of key geometry for use with higher-order aerodynamics, structural, mass properties, propulsion, control, aeroelastic, aeroacoustic, and aeropropulsive tools. However, developing an export capability/linkage to another tool is not sufficient. The goal is to embed in the tools the rigorous steps required for intelligent conversion of the geometric database into the necessary information for the higher-order analysis. This typically involves modification of the geometry through meshing to meet specific needs. Currently these intermediate steps are very time consuming and transitioning between tools loses necessary parametric definitions that could provide valuable sensitivity analyses. Being able to accomplish these steps in more intelligent ways, with less labor would provide timely access to more sophisticated tools. Such capability is not merely about attaching geometry interfaces to the most powerful CFD (computational fluid dynamics) or FEA (finite element analysis) tools it is about bringing all levels of analysis capability to the designer in an easier and more rapid fashion, with less data loss from geometric translations. 2

3 2.2 Robust Aircraft Conceptual Design Geometric Modeling Objective Motivation The objective of this topic is to enhance the ability to employ higher-order, physics-based analysis during conceptual design through robust, easy to create geometry models. The research goal is to automate the rigorous steps required for intelligent conversion of a conceptual level parametric geometry model into the detailed representation 2.2 Robust necessary Aircraft for higher-order Conceptual analysis. Design design is the starting Geometric point for a new Modeling engine or aircraft development. A successful design is highly dependent on accurate geometric representations, since they are used throughout the computational engineering process. Over the past several decades computational capability has drastically improved as has the understanding of human-computer interfaces. These advances have enabled less experienced users to Objective perform far more sophisticated tasks without the requirement of extensive training time. More accurate geometry representations will advance the state-of-art in conceptual design by enabling more routine use of higher-order analysis tools. The objective of this topic is to enhance the ability to employ higher-order, physics-based analysis during conceptual design through robust, easy to create geometry models. The Approach A key need of conceptual design is the ability to quickly articulate ideas and engineering concepts into a digital 3-D database. While this can be accomplished through building research a CAD (computer goal aided is design) to model automate of the geometry, the it would rigorous be valuable steps to have the required ability to parameterize for intelligent the geometry s characteristics. conversion Parametric of a overlays to CAD programs can be performed, but there can be negative implications to this approach. For instance, it requires users to obtain often expensive software, conceptual and there can be level inherent parametric limitations with a given geometry CAD package. model Therefore, into a prerequisite the detailed of any valuable representation conceptual design geometry necessary solution is that it for be parametric-input based and use aircraft design terminology to communicate effectively with the user (e.g., span, aspect ratio, chord). Currently, there are no accepted standards higher-order for parametric-based analysis. geometry representations Conceptual to facilitate design sharing of is geometry. the There starting is a need point to create for a generalized a new standard engine for parametric or aircraft geometry and an approach to transfer geometry models in that standard to CADbased models. These new approaches to streamline the conversion of conceptual geometry to the development. geometry representation needs A of successful more detailed analysis, design however, should is not highly diminish the ability dependent to rapidly explore the on conceptual accurate design space geometric using a parametric geometry tool. representations, since they are used throughout the computational engineering process. Over the past several decades computational capability has drastically improved as has the NASA has made prior investments in the development of a parametric geometry tool for conceptual design [i.e., Vehicle Sketch Pad (VSP)]. There is a need, however, to create better coupling between higher-order engineering analysis codes and geometry tools like VSP. The developed geometry methods should be flexible nature must be compatible with, and support, NASA s existing ModelCenter-based systems analysis and conceptual design process. An overview of the understanding of human-computer interfaces. These advances have enabled less tools used in a ModelCenter environment is available in the Other Documents section at: Expected Outcome experienced users to perform far more sophisticated tasks without the requirement of extensive training time. More accurate geometry representations will advance the state-of- The new capability shall provide parametric-based geometry modeling and analysis methodologies that enable conceptual designers to accomplish analyses in a faster, easier manner. In addition, the geometric representation will enable transferring of key geometry for use with aerodynamics, structural, mass properties, art in propulsion, conceptual control, aeroelastic, design aeroacoustic, by enabling and aeropropulsive more tools. routine However, use developing of higher-order an export capability/linkage analysis to another tools. is not sufficient. The goal is to embed in the tools the rigorous steps required for intelligent conversion of the geometric database into the necessary information for the higher-order analysis. This typically involves modification of the geometry through meshing to meet specific needs. Currently these intermediate steps are very time consuming and transitioning between tools loses necessary parametric definitions that could provide valuable sensitivity analyses. Being able to accomplish these steps in more intelligent ways, with less labor would provide timely access to more sophisticated tools. Such capability is not merely about attaching geometry interfaces to the most powerful CFD (computational fluid dynamics) or FEA (finite element analysis) tools it is about bringing all levels of analysis capability to the designer in an easier and more rapid fashion, with less data loss from geometric translations. 3

4 Proposed Work 4

5 Task Breakdown VSP to CFD Validation CBAero/VSP Integration VSP Plug-In Updates Foster OpenVSP Community Cart3D/VSP Shape Optimization Separate Geometry Kernel From VSP GUI NASA Prioritized Features and Bug Fixes Multi-Fidelity, Multi-Physics Analysis VSP to CAD Interoperability Modularization and Development of API User Defined VSP Components Fuselage Structure Support Improved Wing Structure 5

6 VSP ModelCenter Integration The VSP plug-in is used to load an existing VSP model. The user exposes a set of parametric input variables, and exports a CART3D mesh. CART3D reads the mesh, executes, and generates a pressure field. A second instance of the VSP Plug-In is used to create a NASTRAN mesh from the underlying VSP geometry and to map the pressure loads from the CART3D mesh onto this NASTRAN mesh. The displacements computed by the NASTRAN could optionally be mapped back to the CART3D mesh. 6

7 User Defined Components 7

8 VSP To CAD Interoperability VSP Parameters AR, S, Λ, λ, t/c Assisted Parameterization Surface Mesh Smooth Surface Export Surface Mesh CAD Model / CFD Grid Gen 8

9 VSP Re-design Application Service API (C++) ModelCenter ModelCenter VSP VSP User VSP Geometry Engine VSP GUI Custom Application Custom Application 9

10 Fuselage Structures Representative fuselage structures Similar sophistication to current wing structure Model major fuselage structural features Bulkhead Floor No plan for complex features at this time Wing-body join 10

11 Modeling Approach Same question exists for wing structure Structural features Frame & Stringer Windows & Doublers Resolve Discretize into primitive elements Specify material properties Model Discretize into beam elements Specify material & beam properties Smear Ignore feature in discretization Specify equivalent material properties Hybrid Model frames & smear stringers Resolve web & model caps 11

12 Enhanced Wing Structure Mesh Trimming Automatic Rib Layout Modeling Questions User-Defined Mesh Rib Cutout Resolve / Model / Smear? Structural features Skin stiffeners Spar caps Flanges Non-planar Spar Mesh Trimming 12

13 VSP Open Sourcing & Support Foster Open Source Community Develop high quality project-centered web site & community Web server, hosting, maintenance, backups, etc. Distributed version control, mailing list, user/developer blogs, links, issue tracker, etc. Model database, application database, automated build & packaging, etc. Issue tracker maintenance, community participation, etc. VSP Meetings Workshop ASM Session Perform NASA prioritized fixes & upgrades Ultimate goal is to foster a self-sustaining community of VSP users and developers 13

14 Shape Optimization Formal Shape Optimization VSP Driven High-level parameters Complex configuration Quick baseline Cart3D (Euler) Adjoint sensitivities 14

15 VSP/Cart3D Shape Optimization Develop useful parametric shape optimization based on VSP & Cart3D Integrate VSP into Cart3D optimization framework Develop load distribution matching optimization Validate parametric optimization technique Elliptical wing planform driven to minimize CD Elliptical wing planform driven to match load distribution Sears Haack body driven to minimize CD Demonstrate parametric optimization on aircraft configurations Wing-body wing twist driven to match load distribution OWN integration driven to minimize CD 15

16 Task Breakdown Well Under Way VSP to CFD Validation CBAero/VSP Integration VSP Plug-In Updates Foster OpenVSP Community Cart3D/VSP Shape Optimization Separate Geometry Kernel From VSP GUI NASA Prioritized Features and Bug Fixes Initiated Multi-Fidelity, Multi-Physics Analysis VSP to CAD Interoperability Modularization and Development of API Out Years User Defined VSP Components Fuselage Structure Support Improved Wing Structure 16

17 Curvature Based Meshing 17

18 CBAero Wake Modeling 18

19 Inaugural OpenVSP Workshop August 22-24, San Luis Obispo CA Presentations & Hands-on Tutorial Sessions Modeling Meshing Cart3D CBAero Structures etc. Registration is Closed, we ve exceeded our cap (50) Industry Government Academia Small Business Boeing Lockheed Northrop Grumman Gulfstream Bell Helicopter Pratt & Whitney Rocketdyne General Atomics NASA ARC NASA DFRC NASA GRC NASA LaRC USAF AFRL USAF NASIC US Army AMRDEC Cal Poly GA Tech GT / NIA PSU UC Davis UT Austin VA Tech Desktop Aeronautics General Cryo Phoenix Integration ES Aero 19

20 Questions? 20