university of illinois at urbana-champaign university of illinois at urbana-champaign (uiuc)...

University of Illinois at Urbana-Champaign

UNIVERSITY OF ILLINOIS at URBANA-CHAMPAIGN (UIUC)

NATIONAL CENTER FOR SUPERCOMPUTING APPLICATIONS (NCSA)

ASC PET CSM REVIEW and ASC PET CSM REVIEW and CY4 & CY5 PLANNINGCY4 & CY5 PLANNING

Briefing Document October 7, 1999

Harry H. HiltonProfessor Emeritus of Aeronautical & Astronautical Engineering, UIUC

ASC CSM Senior Academic Lead, NCSA(217-333-2653 [email protected])


NCSA CSM ASC Personnel

Harry Hilton - Senior Academic Lead (25%)

Cristina Beldica - Research Scientist (95%)

LeRay Dandy - Senior System Programmer (15%)

Dave O’Neal - On-Site Lead (100%)

Seid Koric - Graduate Student (50%) *§

Gyuseok Kwak - Graduate Student (50%) *

Youngjin Woo - Graduate Student (50%) *§_______________* Funded by NCSA§ Till July 1999


NCSA CSM ASC Personnel

Tom I. PrudhommeSenior Associate Director

E. J. GrabertASC / ARL Program Manager

Harry H. HiltonSenior Academic Lead

Cristina E. BeldicaResearch Scientist

LeRay T. DandySr. System Programmer

David C. O’NealOn-Site Lead

CSM - THE THREE COMPONENTS


STRUCTURAL / SOLIDMECHANICS

COMPUTATIONALSCIENCE

MATERIALSCIENCE


CSM - PET Program Benefits to DoD


ASC & NCSA Personnel Collaborations

UIUC faculty is engaged in leading edge research and offers world class new ideas and solutions to DoD, ASC, ARL and the industry

Development of and modifications to existing codes for portable parallel computing and integrated visualization

New and unique analytical research and computational protocols in fundamental areas with applications to materials and composite flight structures under aeroelastic loads


ASC & NCSA Collaborations (cont’d)Promoting and executing unified cross CTA research and development projects through multidisciplinary analytical modeling, analyses and computational simulations

Advancing levels of interaction between groups, directorates and MSRCs through integration of multiprocessor application codes that traverse and ultimately span MSRCs (metacomputing)

Training, short courses and workshops tailored to specific CSM interests of DoD, ASC, ARL, HBUC & MI researchers, scientists and engineers

None of this work is being done elsewhere


ASC CSM CY4 & CY5 PROJECTS

CSM 1 Outreach, Training & Support (Funded)

CSM 2 Visualization (Funded)

CSM 3 Tool Development (Funded)

CSM 4 A 3 D Structural Solver for FDL3DI CFD Code (F)

CSM 5 Light Weight Advanced Composite Structures (F)

CSM 6 Portability and Performance Improvement of the Micromechanics Damage Models (Proposal)

CSM 7 Multidisciplinary Outreach Program UIUC & UNM (P)


Summary of CY 3 - 5 Cooperative Projects

• Code Parallelization for Damage Model (Materials Lab)

• Multidisciplinary Collaboration CSM-CFD Code Integration (Flight Dynamics) • Air Vehicle Survivability Study (VAVS)

• Investigation and Implementation of Multidisciplinary Techniques (AFRL)

• Analytical and Computational Modeling of Advanced Composite Flight Structures and Materials (AFRL)

• Diversified CSM On-site Training Efforts, Conferences, Workshops, Short Courses and Symposia (ASC/ARL)


Current Cooperative NCSA - ASC CSM Projects

• Axisymmetric Damage Model (Materials Lab) Multithread porting project

Performance optimization through integration into iSightDoD Users Group Conferences and SC’98 presentation

• Multidisciplinary Collaboration (Flight Dynamics) Integration of 3D FEM solver into CFD research codeParametric finite element model of an aircraft wing

• Air Vehicle Survivability Study (VAVS)Parametric finite element analysis of structural damage

in aircraft wings due to internal explosionsGrand Challenge project proposal for prediction of

aircraft wing damage due to ballistic impacts


• Investigation and Implementation of Multidisciplinary Techniques

Software evaluation (CAPTools, Physica, MDICE, iSight)Organized MAPINT’98 & ‘99

• Modeling of Advanced Flight Structures & Materials (AFRL)Performance evaluations of massively parallel viscoelastic FE / FD computations for compositesStructural reliability & probability of failure analysesStructural health monitoring of flight structuresAnisotropic thermo-viscoelastic FE / FD analyses of

composites (manufacturing & service conditions)Piezoelectric control of aero-viscoelastic structural

phenomena (divergence, flutter, control surface effectiveness, aerodynamic noise, damping)

Analytical material characterization (optimum properties)Analytical & computational design of material property

determination experiments


CSM Outreach, Training & Conferences

• Diversified CSM On-site and Cross-site Training Efforts

• Workshops, Short Courses, Conferences and Symposia

Presentations at conferences organized by DoD or with direct DoD involvement

Participation in conferences outside DoD sponsored by national & international scientific societies

Papers published in archival scientific / engineering journals & conference proceedings

Posting research publications and results on the CSM PET web site

Millennium NCSA-PET Workshop on CSM Strategic Planning for the next Quarter Century


UIUC/NCSA CSM ASC Research Activities

1997 1998 1999 Archival journals andproceedings papers

Published or accepted 16 25 23

Submitted, not yet accepted 11

Presentations at nationaland international 11 17 12Conferences (not all trips charged to PET)


CSM Core Support Ongoing Activities

Web Pages Development and Support • Promote user productivity through web based access to

information, tools and training

• Local interrelated sites on NCSA, ASC, ARL, DoD, HBUC & MI web servers

• Showcase for PET projects and accomplishments

• Provide links to resources for DoD researchers, scientists and engineers

Software and hardware available at NCSA and the MSRCsCalendar of conferences, workshops and training eventsPublications and presentations by NCSA PET members


• SoftwareCommercial codesFree research softwareScientific librariesManualsPerformance evaluations

• PublicationsAuthored by members of the PET CSM groupCollaborations with ASC, ARL, industry scientific

staffs and university faculties at Clark Atlanta, Delaware, Florida Atlantic, New Mexico, Ohio State, Rice, UIUC, Greenwich, Singapore

Original papers in archival journals & proceedings

• Other web resources

ASC CSM MULTIDISCIPLINARY PROJECTS

AEROELASTICITY & MATERIAL DAMPING

STRUCTURAL 3D SOLVER FOR FDL3DI CFD CODE

PIEZOELECTRIC & STRUCTURAL CONTROL

MULTISCALE CCM & CSM MATERIAL MODELING

MULTIDISCIPLINARY OUTREACH PROGRAMS at UIUC & UNM and UIUC & CAU


Cristina Beldica, Harry Hilton, Seid Koric & David O’Neal - UIUC NCSA

Nicholas Pagano - AFRL

David Veazie - Clark Atlanta U

Jack Vinson - U of Delaware

Sung Yi - Nanyang Technological U, Singapore

CSM 5: AEROELASTIC, PIEZO-VISCOELASTIC &

STRUCTURAL CONTROL OF COMPOSITE

FLIGHT STRUCTURES


• Objective: To make use of smart composite materials to regulate deformations, stresses & failure probabilities through structural, material and piezoelectric control

• Methodology: Multiphase and multidisciplinary analytical formulations and computational simulations of viscoelastic material and piezoelectric constitutive relations and actual scientific and engineering problems

• Results: Deterministic and probabilistic stress, defor-mation and failure solutions for flight vehicle metal and composite structures to avoid excessive vibrations, noise transmission and undesirable aeroelastic effects and to predict structural survival times. (See web site)

• Significance: Provide realistic modern analytical and computational models and protocols to dampen un-wanted deformations and noise responses and to furnish structural survival probabilities and times to failure to be used by DoD, ARL and ASC researchers and designers

CSM 5: Viscoelastic Material & Piezoelectric Damping

-25

-20

-15

-10

-5

0

-0.2 0 0.2 0.4 0.6 0.8 1

PROBABILITY OF DELAMINATION ONSET

PIEZO CONTROL @ 800C

NO CONTROL @ 200C

PIEZO CONTROL @ 200C

NO CONTROL @ 800C

LO

G (D

ELA

MIN

ATIO

N P

RO

BA

BIL

ITY

)

TIME (t / )

0.017

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Defl

ecti

on

(in

)

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Time (sec)

00.2

0.40.6

0.81

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0.6

0.8

10

0.2

0.4

0.6

0.8

1

J1 / J1maxJ2 / J2max

J3 /

J3m

ax

Fig. 3 INVARIANT FAILURE SURFACE

• Objective: To formulate and evaluate performances of parallel computational protocols for linear and nonlinear viscoelastic stress, failure and structural control analyses

• Methodology: Commercial codes such as ANSYS and ABAQUS with modified subroutines are used for solving real engineering problems. For nonlinear viscoelasticity, new codes have to be written because no available commercial software has such capabilities

• Results: ABAQUS scales well for large number of DOF, but needs modifications to run efficiently on more than 16 parallel processors (See web site)

• Significance: Provide realistic modern efficient compu-tational protocols for structural analysis, survival probabilities and times to failure. Of interest to DoD, ARL, ASC & industry engineers and scientists

CSM 5: Massively Parallel Piezoelectric / Viscoelastic Simulations

0

1000

2000

3000

4000

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6000

-1

0

1

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PERFORMANCE EVALUATIONS FOR 201,000 DOF

CPU TIME - BENDINGCPU TIME - TORSION

SPEED UP - BENDINGSPEED UP - TORSION

TO

TA

L TIM

E (s

ec)

SP

EED

UP

NUMBER OF CPU

201,000 DOF FEM

1000

1500

2000

2500

3000

3500

4000

4500

-25

-20

-15

-10

-5

0

5

10

-4 -3 -2 -1 0 1 2

Fig. 4 CANTILEVER BEAM TOP FIBER STRESSES

11

PIEZO

11

BEAM

12

PIEZO

12

BEAM

BEN

DIN

G S

TR

ESS

ES

SH

EA

R S

TR

ESS

ES

LOG (TIME)

• Objective: To investigate applicability of viscoelastic damping & piezoelectric effects, torsional divergence, flutter, aerodynamic derivatives, aileron effectiveness and aerodynamic noise in composite structures

• Methodology: Employ analytical tools and large scale computational simulations to conduct feasibility studies of light weight, low power and inexpensive piezo devices to control undesirable aeroelastic effects including aero-dynamic and structural coupling

• Results: Studies demonstrate ability to control aeroelastic effects and flight vehicle motion by application of simple sensing and actuator piezoelectric devices. (See website)

• Significance: Provide realistic modern analytical and computational models for aeroelastic and structural control of composite structures. Of interest to DoD, ARL, ASC & industry engineers and scientists

CSM 5: Aeroelasticity with Piezo-Viscoelastic Control

90.0

100.0

110.0

120.0

130.0

140.0

150.0

160.0

10 100 1000 10000

MEASURED DELTA IV NOSE CONE NOISE LEVELS

EXTERNAL

INTERNALDAMPED

AC

OU

STIC

LEV

EL (d

B)

FREQUENCY (Hz)

0

2

4

6

8

10

12

0 5 10 15 20

Fig. 3 ELECTRIC POTENTIAL FOR FIXED ELECTRIC DISPLACEMENT

D = 2.5 degD = 5.0 degD = 7.5 degD = 10 degD = 25 deg

VO

LTA

GE E

(V)

TIME (t/1)

0

5

10

15

20

25

0 1 2 3 4 5

Fig. 1 MAXIMUM ANGLE OF TWIST

VISCOELASTIC NO CONTROL

VISCOELASTIC PIEZO CONTROL

ELASTIC NO CONTROL

TW

IST A

NG

LE

(t)

/ E

TIME

V < VD

E

• Objective: To investigate influences of ramp loading functions and rise time to full load on experimental material characterizations through computer simulations

• Methodology: Employ analytical tools and large scale computational simulations to conduct feasibility studies of experimental procedures for viscoelastic deterministic & random material characterizations

• Results: Loading patterns distinctly affect the determi-nation of viscoelastic material parameters, leading to possible erroneous or misleading characterizations. Procedure for real time (not Laplace Transform) characterization is developed. (See website)

• Significance: Provide realistic and proper analytical and computational tools for material characterization of advanced composite structures. Of interest to DoD, ARL, ASC & industry engineers,researchers and scientists

CSM 5: Analytical & Experimental Material Property Determinations

0.0

0.2

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0.8

1.0

1.2

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0.4

0.6

0.8

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-3 -2 -1 0 1 2

Fig. 1 LOADING FUNCTIONS & RELAXATION FUNCTIONS

RELA

XA

TIO

N FU

NC

TIO

NS

LO

AD

LOG (TIME)

L1 L

2

A(t)

B(t)

C(t)

t1

t0

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0.7

0.8

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1.0

1.1

-8

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-6

-5

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-3

-2

0 50 100 150 200

Fig. 2 TRUE AND APPARENT YOUNG'S MODULUS

TRUE E0

APPARENT E0

FOR t1 > t

0

t0

NO

RM

ALIZ

ED

YO

UN

G'S

M

OD

ULU

S (E

0)

LO

G (t0 )

TEMPERATURE (oC)

0.0

0.2

0.4

0.6

0.8

1.0

1.2

-4 -3 -2 -1 0 1 2

Fig. 3 LOAD RAM FUNCTIONS AND RELAXATION FUNCTION

LOAD = H ( t ) / F0

[t0 = 10-2 t

1 = 0]

t / t1 [t

0 = t

1 = 10-2]

.5 [1 - cos (* t / t1)] [t

0 = t

1 = 10-2]

( t ) / O

NO

RM

ALI

ZED

LO

AD

&

R

ELA

XA

TIO

N FU

NC

TIO

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LOG (TIME)

• Objective: Analytical formulations & computational simulations to determine optimum anisotropic viscoelastic designer material properties to be manufactured to meet specific structural service requirements

• Methodology: Solutions for composites are approached by an inverse method through examining individual effects of portions of relaxation modulus curves on creep and relaxation responses

• Results: A mechanistic understanding of viscoelastic responses to loading, moisture and temperature histories has been achieved which allow the designer to select tailored composite materials for actual service conditions. Protocols for proper experimental determination of material properties have also been formulated. (See website)

• Significance: Provide modern composite property models to allow ASC, ARL, DoD and industry engineering designers to select optimum tailored materials for specific structural service conditions

CSM 5: Viscoelastic Designer Materials

0.0

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-10 -8 -6 -4 -2 0 2

Fig. 1 - MASTER RELAXATION MODULUS

NO

RM

ALIZ

ED

R

ELA

XA

TIO

N M

OD

ULU

S

LOG (TIME)

A

B

C

DE

0

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4

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10

12

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-3 -2.5 -2 -1.5 -1 -0.5 0 0.5 1

Fig. 5 MODIFIED RELAXATION MODULI (C0

11) IN DIRECTION (1,1)

110% C011REF

120% C011REF

130% C011REF

140% C011REF

150% C011REF

RELA

TIV

E D

IFFER

EN

CE IN

D

ISS

PA

TED

EN

ER

GY

(%

)

LOG (TIME) (sec)

-5

-2.5

0

2.5

5

-4 -2 0 2 4 6

Fig. 8 MODIFIED RELAXATION MODULI IN DIRECTION (I,J)

(1,1)

(2,2)

(3,3)

(1,2)

(1,3)

(2,3)

RELA

TIV

E D

IFFER

EN

CE D

ISS

IPA

TED

EN

ER

GY

(%

)

LOG (TIME) (sec)

(SLOPE)NEW

= 0.5 (SLOPE)OLD


CSM Predictions of Aircraft Wing Damagedue to Ballistic Impact

Grand Challenge Proposal

J. Calcaterra - VAVS

R. Hinrichsen - Anteon Corp.

A. Palazotto - AFIT

B. Baron - AFRL

H. Hilton - UIUC NCSA


• Numerical simulations for evaluation and prediction of end damage due to ballistic impact

• 3-D hydrocode model coupled to an accurate structural solver

• Comprehensive failure criteria

• Interactive framework for design optimization

Fluid response at t=0.0002 sec after explosion

Prediction of Aircraft Wing Damagedue to Ballistic Impact


CSM 7: UIUC / NCSA & UNM / AHPCCMultidisciplinary CSM Outreach Program

A CSM Project Proposal

Harry Hilton, David O’Neal - UIUC NCSA

Andrew Pineda - UNM AHPCC


CSM 7: UIUC / NCSA & UNM / AHPCCMultidisciplinary CSM Outreach Program

A two stage approach will be used to accomplish the project objective.

• First, a one day symposium will be organized featuring presentations by AHPCC and NCSA CSM teams augmented by research groups from AFRL Phillips AFB & WPAFB. Targeted applications will include aeroelasticity, composite structures, fracture mechanics, aerodynamics, multidisciplinary optimization and multiscale models.

• Secondly, a cross site project plan will then be completed by the NCSA and AHPCC teams to benefit research groups at Phillips and Wright-Patterson AFBs.


CSM 6: Portability and Performance Improvement of the

Micromechanics Damage Models (MDM)

A CSM PTES Project Proposal

Cristina Beldica, David O’Neal - UIUC NCSA

Richard Luczak - Rice U

Nicholas Pagano - AFRL


CSM 6: Portability and Performance Improvement of the

Micromechanics Damage Models (MDM)

• Execution of the MDM code suite has been restricted to HP plat- forms due to a fundamental portability problem. A solution to this problem was recently discovered by the NCSA CSM team and this project’s primary objective is to assist the AFRL development group in implementing portability onto high performance computers.

• Focused efforts will resolve portability problems while simultaneously yielding significant performance improvements. This is a collaborative project involving AFRL developers of the MDM codes, NCSA researchers and the PET CSM and PTES site leads at ASC.

Cristina Beldica, Harry Hilton, David O’Neal - UIUC NCSA

David Veazie - Clark Atlanta U.

Margaret Hurley, Gerry Lushington, Richard Pritchard -

Ohio State U. OSC

Multiscale Materials Modeling

A CCM-CSM Proposal for Multidisciplinary and Multisite Collaboration


• Objective: Construction of a prototyping tool capable of predicting continuum effects in composite materials from the molecular properties of the constituent materials.

• Methodology: The key to this project lies in the design of the mechanism used to bridge atomistic and continuum scale analysis tools. A materials database will also be used to validate new results, as well as catalog information associated with previous studies.

• Results: This project is still in planning. Related proposals for resources have been completed. Study of existing multiscale bridging techniques has been initiated.

• Significance: Multidisciplinary collaboration involving CCM and CSM CTAs and Clark Atlanta University. Huge potential associated with virtual prototyping.

CSM: Multiscale Materials Modeling

Microscopy experiments


CSM 5: THE AXISYMMETRIC DAMAGE MODEL (ADM)

Cristina Beldica, D. O’Neal - UIUC NCSA

N. Pagano, G. Shoeppner - AFRL

G. P. Tandon - AdTech

K. Flurchick - OSC


CSM 5: THE AXISYMMETRIC DAMAGE MODEL (ADM)

• Brittle Materials Lab code assist • Used to establish design properties of experimental composite materials • Current models have cut run time costs in half and enhanced post

processing capabilities • Potential for additional order of magnitude reductions in run time costs


CSM 4: Structural Solver for FDL3DI CFD Code

L. Dandy, D. O’Neal - UIUC NCSA

M. Visbal, R. Gordnier, R. Melville - AFRL

H. Thornburg, B. Soni - Mississippi State U


CSM 4: Structural Solver for FDL3DI CFD Code

• Objective: To integrate a compact portable 3D FE structural solver into the FDL3DI CFD code in order to predict flexible aircraft responses to aerodynamic loads and to properly couple aeroelastic phenomena

• Methodology: A linear elastic FE solver is being integrated into a high fidelity CFD code replacing the previous 1D modal solver

• Results: Linear elastic solvers are much more accurate than modal solvers in predicting structural responses of aircraft subjected to aerodynamic loads

• Significance: Provide accurate and realistic structural responses for aircraft under various aerodynamic loads and structural stiffnesses

Convergence Plot (S-S Plate w/ Conc. Load)

0.0590.06

0.0610.0620.0630.0640.0650.0660.0670.0680.069

16 36 144 400

Number of Elements

Disp

lace

men

t (in

.)

Exact

FEA

Convergence Plot (S-S Plate w/ Uniformly Distributed Load)

0.096

0.098

0.1

0.102

0.104

0.106

0.108

16 64 144 256

Number of ElementsDi

spla

cem

ent (

in.)

Exact

FEA


CSM 2: Visualization and

Job Monitoring of FDL3DI

L. Dandy, D. Semeraro, D. O’Neal - UIUC NCSA



CSM 2: Visualization and Job Monitoring of FDL3DI

• Objective: To build a portable infrastructure for monitoring the progress of FDL3DI jobs during simulations

• Methodology: CUMULVS will be integrated into the FDL3DI code to provide analysts with snapshots of job progress during simulations

• Results: Many codes (i.e., EPIC and FDL3DI) require many days to perform a typical simulation. With CUMULUS jobs may be monitored throughout the computation to determine accuracy of results or to restart with different physical parameters.

• Significance: Provides a substantial increase in HPC resource efficiency and allows the analyst to improve results by check pointing and restarting a job based on real time examination of results


CSM 4: Parametric Finite Element Model

of an Aircraft Wing

L. Dandy, G. Kwak - UIUC NCSA



Sample Calculation of Wing FEA Model - MSC/PATRANCompletely automatic with internal structure


CSM 4: Parametric Study of Structural

Damage due to Internal Explosions

L. Dandy, Y. Woo - UIUC NCSA

A. Mayer, G. Czarnecki, J. Calcaterra - VAVS

R

t1

L3

half span

L1 L2

t3

t2

Load

p2

p1

kspar2

Parametric Model

L4 - span to next spar

kspar1

NOT TO SCALE


CSM 4: Preferred damage path before and after optimization simulation

David O’Neal - UIUC NCSA

Ruth Pachter - ASC MSRC

Geoffrey Fox - Syracuse U


CSM 3: MAPINT’99 Symposium


CSM 3: MAPINT’99 Symposium

• Methodology: The MAPINT’99 agenda again promoted a cross-section of contemporary research projects and emerging technologies.

• Results: Collaborations with ARL MSRC, the University of Greenwich, and Engineous Software, Inc. have resulted directly from NCSA ASC CMS personnel participation in this event.

• Significance: The DoD supports the development of multidisciplinary frameworks and environments targeting more realistic simulations and analyses. The MAPINT Symposium provides a platform from which strategic academic, industrial, and government researchers may communicate their ideas and achievements.

• Objectives: Provide an overview of leading multidisciplinary programs, initiate interaction between developers and users and explore advanced computing systems where such applications are likely to be executed.


David O’Neal - UIUC NCSA

Mark Cross, Constantinos Ierothrou - U of Greenwich, UK

Michael White - Ohio Aerospace Institute


CSM 3: CAPTools Project


CSM 3: CAPTools Project

• Methodology: Semi-automatic dependency analysis and parallelization of FORTRAN source codes using the Computer Aided Parallelization Tools. Evaluation nearly completed. Steer development in a manner consistent with DoD HPC program goals. Produce portable message passing and OpenMP source codes.

• Results: Preliminary results describing performance and scaling attributes associated with a selected set of test applications were presented at the 1999 DoD HPC Users Group Conference in Monterey. Final results were presented at MAPINT’99. Five new multiprocessor codes (2 DoD) have been completed.

• Significance: Huge potential for legacy code modernization projects. Effects on utilization of HPC resources could be dramatic as improvement in job turnaround will encourage consideration of larger simulations.

• Objectives: Identify, evaluate, and deploy software tools that address the needs of the DoD research community. Transition CSM legacy codes to the high performance multiprocessor computing systems characteristic of the MSRCs.

LeRay Dandy, David O’Neal - UIUC NCSA

Jeffrey Calcaterra, Nicholas Pagano - AFRL

Juan Carlos Chavez - HPTi

Mark Ondracek - Engineous Software, Inc.

CSM 3: iSIGHT Project


CSM 3: iSIGHT Project

• Results: Acquisition of network licensed product supporting two concurrent users was recently finalized. Approval of funding for purchase of additional seats by ARL is imminent. A combined network licensing arrangement will be served from ASC, thus providing a model for cross-MSRC resource allocation. Two DoD related test applications were also completed during the evaluation phase.

• Significance: Benefits of combining discipline-specific analysis tools into coupled physics models will support simulation of the behavior of real-world weapons systems with unprecedented accuracy.

• Objectives: Justify and acquire iSIGHT framework software and optimization logic. Create cross site multidisciplinary applications. Document individual achievements in a public forum, e.g. the PET CSM web site and promote collaborations.

• Methodology: Facilitate implementation of user defined problem solving environments by fostering a collaborative approach and providing relevant training.


ARL & ASC JOINT CSM PROJECTS



CSM 1: Outreach, Training & Short Courses

• Objective: To disseminate newly developed information on structural analyses and large scale computational protocols as rapidly as possible to as wide and as diverse an audience as budgets permit through short courses and website course listings

• Methodology: 1 - To provide information and training through use of computerized instructional materials simultaneously to DoD and industry audiences at multiple locations through distance learning.2 - To provide current information on new research, development and associated results through seminars and short courses

• Results: The training and educational programs will be pervasive and cover numerous topics based on audience demand and new developments in universities, government laboratories, commercial codes, etc.

• Significance: This program will keep DoD personnel informed on current state of ongoing research efforts and on high performance computational protocols. It will also provide training for users to effectively execute advanced computer codes and to apply modern research results in a timely fashion


CSM 1: ARL & ASC Year 3 Training and Support

– CoMeT seminar July 7, 1998

– Aeroelastic Design for CFD Engineers July 13-14, 1998– Introduction to ANSYS January 19-21, 1999– Viscoelastic Constitutive Relationships February 22, 1999– Equation of State (EOS) Course March 17-19, 1999– Using ParaDyn/DYNA3D March 23-24, 1999– Introduction to LS-DYNA3D July 26-30, 1999– INGRID September 14-15, 99

Other Core Support

– Support for ARL & ASC software committees

– On-going user support and consulting

CSM 1: Computational Software Seminars & Short Courses

Topic Tentative Date Location

NASTRAN TBD ASC/ARL PATRAN TBD ASC/ARL CAP Tools Training (via D. L.) TBD ASC/ARL Advanced ANSYS TBD ARL/ASC EOS/CTH Course TBD ARL/ASCCTH - DICE training TBD ASC/ARL Advanced Paradyn trainingTBD ARL/ASC ISight (via D. L.) Fall 99 ASC/ARLGraphics & GUIs with MATLAB TBD ASC/ARL



Structural/Solid Mechanics Seminars & Short CoursesTopic Tentative Date LocationProbability & Statistics TBD ASC/ARLDeterministic & Probabilistic Failures TBD ASC/ARL Composite Delamination TBD ASC/ARLComposite Manufacturing TBD ASC/ARLComputational Optimum Control TBD ASC/ARLIntroduction to BEM TBD ARL/ASCBEM & Failure Analysis Fall 99 ARL/ASCFracture Mechanics (theory) Fall 99 ARL/ASCComputational Fracture Mechanics Spring 00 ARL/ASCHigh Strain Rates Fall 99 ARL/ASCStructural Health Monitoring Spring 00 ASC/ARLStructural Control Fall 00 ASC/ARLComposite Aging TBD ASC/ARL

Nonlinear & Stochastic FEM TBD ASC/ARL Smart Materials & Characterization TBD ASC/ARL


CSM for CY4 & Beyond


YR 1OUTREACH

YR 2 TRAINING

YR 3 PROJECTS

YR4 ADVANCEDPROJECTS

YR5META

SYSTEMS

YR5 ADVANCEDPROJECTS

YR 4 PROJECTS

YR 5 PROJECTS

YR 3 TRAINING

YR 4TRAINING

YR 5 TRAINING

PROGRAM YEARS03/29/99 Grabert / Smith

YR 2OUTREACH

YR 3OUTREACH

YR 4OUTREACH

YR 5OUTREACH

0 1 2 3 4 5 t

ARL and ASC PET STRATEGY&

5 - YEAR DEPLOYMENT

• Objective: 1 - To provide multidisciplinary computational protocols and codes to analyze and design next century lightweight structures for flight, surface and naval vehicles based on probabilistic and deterministic reliabilities, including aeroelastic capabilities. 2 - To make results widely available through training and/or short courses by electronic transmissions and web postings for all MSRCs and selected HBUCs & MIs.

• Methodology: Cross CTA and MSRC multiphase and multidisciplinary analytical formulations and massively parallel computational simulations of viscoelastic composite materials with or without piezoelectric structural control for linear and nonlinear structural and aeroelastic problems, including stress and failure analyses.

• Results: Deterministic and probabilistic stress, deformation and failure solutions for flight vehicle metal and composite structures including optimum material selection and material characterization based on massively parallel computational protocols for real material solid/fluid interaction problems.

• Significance: Provide DoD, ARL, ASC and industry researchers, engineers, scientists and designers with modern analytical and computational models and tools to give them the ability to create realistic structures based on survival probabilities and times to failure. To make software & results universally available through grids. (metacomputing)

CSM for CY4 and Beyond


National Computational Science Alliance

(The Alliance)

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National Computational Science Alliance

The National Science Foundation Partnership for Advanced Computational Infrastructure initiative supports the development of a powerful computational problem-solving environment for national scale, multidisciplinary, collaborative work.

The National Computational Science Alliance (Alliance) is a partnership among more than 50 U.S. universities and research institutions to prototype the computational and information infrastructure of the next century. The Alliance's National Technology Grid will consist of a broad range of high-end parallel computing systems located at NCSA and other leading-edge facilities within the Alliance -- the super nodes of the Grid.


Alliance Technology Roadmaps

• Building the Grid

• Capability Computing

• Science Portals

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Creating the Virtual Machine Room -Alliance National Scale Enterprise Testbeds

• High Speed Networking

• Connecting Multiple Vendor Supercomputers

– from Maui to Boston

• Common Web Interface to User

• Security/Authentication

• Accounting/Metacomputer Director Service

• Scheduling

• Access to Files and Distributed Data

• Remote I/O

• Quality of Service Reservations


• A 5-year Plan That Identifies the Services Necessary to Prototype the Grid

• The Alliance Grid Strategy Is Designed to Achieve the Following:

Seamlessly Integrate Alliance Hardware, Software, Data and People

Allow for Extensions to Other Grids Allow for Easy Incorporation of New Technologies

• The Grid Can Be Dissected Into Two Logical Grids: Computational Grid Access Grid

Building the Grid


Access Grid

Enabling Groups to Interact With Grid Resources

• Mural Displays • Cost Effective Multiple Projectors Base System < $50K Front or Back Projected Driven by PCs Software to Drive System Desktop Accessible • Audio Stereo, Quad, 3-D

Collaborations and Visualization

• Collaborations

Multiple Participants Share: Applications, Chat, White Boards, Presentations• Distance Training/Education• Visualization

Group Analysis of: Scientific Data, Virtual Reality, Instrument Steering


What is a Science Portal? A New Generation of Alliance Workbenches

• Built on an Alliance “Common Portal Architecture” Defined by Alliance Teams Using: Emerging Web Distributed Object, Component Technologies & Information Repositories Standards• Web Access to: Remote Computational Resources Data Discovery and Analysis Tools Alliance Collaboration Infrastructure• Drawing on Emerging Commercial Technologies Personalization Integration of Services Security


Science Portals are Gateways for the Computational Scientist

• Allow HPC Users to Interact With NCSA Queues & Globus Connected Supercomputers

• NCSA Is Developing a System to Report to Portal: System Allocations System Status (Up/Down, Capacity, Queues) Mass Store Status (Up/Down, HIPPI Connection Working?) Job Status (Where Job Is in Queue, Projected Run Date) Queue Information (Various Presentations) Account Statistics Project Statistics Usage and Patterns Billing Data • NCSA D2K is a Working Model of Science Portal


FOR ADDITIONAL INFORMATION PLEASE CONSULT:

http://www.asc.hpc.mil/PET/CSM/frame.html

http://www.ncsa.uiuc.edu/SCD/Science/PET/publications/

http://www.ncsa.uiuc.edu/SCD/Science/PET/presentations/

http://www.ncsa.uiuc.edu/SCD/Science/PET/conferences/


For further information please contact:

HARRY H. HILTON

Voice 217-333-2653 Fax 217-244-0720

Cellular 217-840-0358

h-hilton @ uiuc.edu

http://www.uiuc.edu/ph/www/h-hilton

university of illinois at urbana-champaign university of illinois at urbana-champaign (uiuc)...

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