MSC 1991 World Users' Conference Proceedings

The conference proceedings for the 1991 World Users' Conference are now available on-line in Adobe Acrobat PDF format. (The Adobe Acrobat Reader software is available for free download from Adobe's web site at www.adobe.com).

MASSIVELY PARALLEL SOLUTION FOR FEA (Acrobat 388K) #3491, 7 pgs.
Joseph L. Walsh, President -- FEGS, Inc., Duluth, Georgia

ABSTRACT: The past few years have seen the development of Parallel Processing computer hardware systems utilizing both minor and massive parallelism. Massive parallelism utilizing distributed memory processors, such as the INMOSS Transputers, offers a tremendous potential reduction in computation time for FEA applications. This paper outlines the differences between minor and massive parallelism and the special issues involved in massive parallelism.
This paper also describes the results of software research performed by FEGS, Limited regarding the use of massive parellelism for Finite Element Analysis and Finite Element Modeling as well as the current availability of Massively Parallel hardware and Software for Finite Element applications.

FAST ITERATIVE SOLVER FOR FINITE ELEMENTS USING INCOMPLETE ELIMINATION
 (Acrobat 1.42MB) #3591, 16 pgs.
Jan Mandel -- University of Colorado at Denver, Denver, Colorado

ABSTRACT: The preconditioned conjugate gradients method is used with a special preconditioning for large sparse systems of linear equations arising from finite elements. First the system is transformed by the elimination of selected nonzeros. The transformed system is then preconditioned by a block diagonal matrix that includes a coarse discretization of the same problem. The selection of the block diagonal is adaptive, which makes the method flexible and efficient for problems with a complicated geometry. The method is illustrated on systems arising from the p-version finite element method for three-dimensional elasticity and a test implementation is described. Computational results show that the iterative solver outperforms significantly the state-of-the-art direct sparse solver used in MSC/PROBE for real-world test problems with distorted elements both in terms of CPU time and storage. The advantage of the iterative solver increases with the size of the problem.

LARGE ORDER MODAL ANALYSIS MODULE IN THE AEROELASTIC DESIGN OPTIMIZATION PROGRAM (ADOP) (Acrobat 1.42MB) #3691, 17 pgs.
George T.J. Tzong, Gregory D. Sikes and Alan J. Dodd -- Douglas Aircraft Company, Long Beach, CA

ABSTRACT: Two advanced mode extraction methods, the block Lanczos and the accelerated subspace iteration methods, have been implemented in the Aeroelastic Design Optimization Program, a structural optimization program developed at McDonnell Douglas Corporation. Numerical errors most commonly observed in modal analysis have been overcome in both methods, using partial and selective orthogonalization schemes in the Lanczos method, and a selective technique in the subspace iteration method. Vibration modes for medium and large structural models are computed to demonstrate the ADOP modal analysis capability. In the paper a comparison between the block Lanczos and the subspace iteration methods is made in terms of CPU time usage. Since these two methods have never been compared on an equal basis before, i.e. using the same matrix storage format for the stiffness and mass matrices and the same routines to perform matrix-vector multiplication, and the numerical error treatments were not considered in the previous comparisons, this paper presents a more valid comparison.

EXPERIENCES WITH MSC/NASTRAN ON VARIOUS HARDWARE PLATFORMS (Acrobat 1.17MB) #3791, 15 pgs.
Mulji Patel -- FMC Corporation, Minneapolis, Minnesota

ABSTRACT: A number of production Finite Element analyses were run on different hardware platforms such as the Silicon Graphics workstation, IBM main frame and CRAY supercomputers using MSC/NASTRAN Versions 65 and 66. The study was conducted to find:
1. Elapsed time for various hardware platforms using MSC/NASTRAN Version 65 and 66 using real world FE analyses problems in a production type environment.
2. Effect of various hardware platforms on overall FE analysis turnaround including pre and post-processing time.
The study shows that the elapsed time is not directly proportional to the CPU rate, rather it is significantly affected by other factors such as memory size, I/O operations, cache memory utilization, software constructs, batch job queue, and general system parameters. The study also shows that significant time is required to interface software, hardware and communications media into a complete, usable system for pre and post processing and analysis as well as training the users when a change is made from one hardware platform to another.

NONLINEAR STATIC ANALYSIS OF MCDONNELL DOUGLAS MD90 AIRCRAFT USING MSC/NASTRAN SUPERELEMENT DATABASE (Acrobat 946K) #3891, 13 pgs.
H.T. Wu and S.Q. Diep -- Douglas Aircraft, Long Beach, CA
V.K. Gupta -- Rockwell International, Canoga Park, CA

ABSTRACT: The new McDonnell Douglas MD90 aircraft engine/pylon/fuselage interface reactions, pylon stresses, and deflections were determined using MSC/NASTRAN nonlinear finite element analysis. The aft fuselage was modeled in detail using McDonnell Douglas interactive CGSA/CASD graphic software and reduced to a boundary stiffness matrix at the fuselage/pylon interface to minimize the cpu time in nonlinear iterations, design optimization, and evaluating multiple load conditions. MSC/NASTRAN was then used for SOL 66 nonlinear static analysis with the detailed engine model represented as one superelement, the pylon/fuselage model as another superelement, and the engine mount structures as residual structure. The engine mount structures were modeled by non-linear gap elements to evaluate the fail-safe design and by thermal elements to account for the preloads caused by engine expansion. The ultimate and fail-safe loading conditions were analyzed for emergency landing, arbitrary dynamic landing, arbitrary vertical gust, arbitrary lateral gust, engine seizure, reverse thrust rollback, take-off run, towing, and taxiing conditions. Fatigue design loads were generated from take-off to landing for one operation cycle. Engine fan blade-out analysis was also performed for the engine mount loads. Deflections of the engine/pylon/fuselage structure were generated to help designers investigate structural clearances for both ultimate and fail-safe design conditions.

SELF-ADAPTIVE GAP/FRICTION ELEMENT IN MSC/NASTRAN (Acrobat 1.98MB) #3991, 30 pgs.
Sang H. Lee and T.L. Lin -- MSC, Los Angeles, CA

ABSTRACT: One of the major areas in nonlinear analysis that poses difficulties in convergence is the application of GAP elements. This has been particularly true when friction is involved. Numerical difficulties is inherent in nature for the penalty method which is employed in the MSC/NASTRAN GAP element. Furthermore, the GAP element simulates a point-to-point contact, and is often used to simulate surface contact problems. Deficiencies of the penalty GAP elements are coped with by implementing an adaptive GAP element in Version 67 of MSC/NASTRAN. The adaptability is based on the subincremental scheme with a capability to update the stiffness at the appropriate time, bisect when the increment is excessive, and adjust penalty stiffnesses to the proper values in concert with the nonlinear and dynamic environment. In addition, the kinetic friction effect is introduced to simulate the physics more accurately by distinguishing stick-slip forces.

A PARAMETRIC STUDY TO OPTIMIZE A COMPLICATED STIFFENED PLATE STRUCTURE IN BUCKLING (Acrobat 923K) #4091, 18 pgs.
Khosrow Mehrzad, Structural Analyst -- Bombardier, Inc., Ville St.-Laurent, Quebec, Canada

ABSTRACT: The buckling of a stiffened plate with discontinuity of stringers is verified in this paper. For this purpose, the results of a finite element model analysed by MSC/NASTRAN, Solution 5, were compared with those of a test. While the theoretical critical load calculated by finite element is different from the measured value, as it is expected, the analysis locates the exact place of buckling and its principal mode shape. Afterwards, the finite element model has been used to optimize the structure.

FRACTURE MECHANICS COMPUTATIONS WITH MSC/PROBE (Acrobat 1.92MB) #4191, 25 pgs.
Michael J. Heskitt -- MSC, St Louis. Missouri

ABSTRACT: Methods based on linear elastic fracture mechanics are of great importance in evaluating the strength and durability of structural and mechanical systems. The Finite Element Method has become increasingly popular for fracture mechanics computations, and many commercial FEM packages now contain fracture mechanics capabilities. The fracture mechanics capabilities of the p-version finite element program, MSC/PROBE, are discussed and several example applications are used for illustration. Particular emphasis is placed on the quality of the results, and the methods that are available to verify the solution accuracy.

THE SUPERMESH: RUN-TIME MESHING FROM COARSE CAD MODELS USING MSGMESH
(Acrobat 1.26MB) #4291, 18 pgs.
Charles Lund, Structural Methods Specialist -- NWL Control Systems, Kalamazoo, Michigan

ABSTRACT: The generation of MSC/NASTRAN plate and solid element models is greatly speeded by combining any CAD mesh generator with MSGMESH (MSC's batch mode mesh generator). CAD models are developed only fine enough to sufficiently define the geometry; then MSGMESH is used to generate the elements and nodes at run time.

AN EXPLANATION OF TOPOLOGY BUILDING ALGORITHMS USED IN MSC/XLFROMCAD
(Acrobat 1.12MB) #4391, 14 pgs.
Martin Jones -- FEGS Limited, Cambridge, United Kingdom

ABSTRACT: MSC/XLfromCAD provides functionality to build geometric topology (faces, solids) ready for meshing from 3D wireframe data. This paper provides background on the technology used to build this topology along with hints and strategies for the user in the use of these algorithms.

DESCRIPTION OF AN INTERFACE BETWEEN MSC/NASTRAN AND THE MATRIX CONTROL DESIGN PROGRAM (Acrobat 952K) #4491, 13 pgs.
Scot Morrison -- Integrated Systems, Inc., Santa Clara, CA
John Caffrey -- MSC, Los Angeles, CA

ABSTRACT: This paper describes an existing interface which allows extraction of linear models from an MSC/NASTRAN output file and conversion into MATRIX readable format for control design and simulation. The interface is demonstrated using an MSC/NASTRAN model of a satellite microwave antenna.
In addition to the existing interface, a proposed expanded interface allowing additional information to be transferred from MSC/NASTRAN to MATRIX is presented. Candidate information includes component mass and stiffness matrices, and outputs from MSC/NASTRAN's Design Sensitivity Analysis package. This sensitivity data would allow open or closed loop robustness analysis, and simultaneous structural and controller design.

APPLICATION OF MSC/PAL 2 AND MSC/NASTRAN-WS TO DESIGN OF CEBAF EXPERIMENT STATIONS (Acrobat 986K) #4591, 11 pgs.
Atis A. Liepins, Hamid Nazemi, and Andre S. Lamontagne -- Simpson Gumpertz & Heger Inc, Arlington, Massachusetts

ABSTRACT: The use on personal computers of MSC/pal2 in the design and MSC/NASTRAN-WS in the redesign of CEBAF experiment stations is described. These stations are cylindrical tank type structures with spherical domes of reinforced concrete. Included are descriptions of the models employed, the features of the programs used to capture the important structural actions, and the problems encountered. Also included are welcome additions to both programs, both in structural modeling and display of results. The hardware used is given and run times of models with both programs are compared.

OBLIQUE PENETRATION IN DUCTILE PLATES (Acrobat 979K) #4691, 14 pgs.
H. Lenselink -- The MacNeal-Schwendler Corporation B.V. -- Gouda, The Netherlands

ABSTRACT: This paper presents the results of two three-dimensional coupled Euler-Lagrange simulations of oblique penetrations of a hard steel fragment in a copper plate. The computations are performed with the MSC/DYTRAN code and the computed penetration regime ranged from full ricochet to regular oblique perforation. In both computed cases the plate deforms severely by the cratering process of the penetrating fragment. By using a coupled Euler-Lagrange approach the fragment and the plate are modeled in the most accurate and efficient computational frame of reference. To model the highly non-linear material behavior, a Johnson and Cook yield model for the copper plate material has been used to take into account strain, strain rate and temperature effects. The computed penetration process, crater shapes and angle of exit of the fragment are compared with experimental data. A good agreement between the DYTRAN results and experiments was found.

INFLATION OF FOLDED DRIVER AND PASSENGER AIRBAGS (Acrobat 1.32MB) #4791, 15 pgs.
A.J. Juijk and C.J.L. Florie -- The MacNeal-Schwendler Company B.V., Gouda, The Netherlands

ABSTRACT: The ever increasing requirements for enhanced passenger safety in cars has led to the fitting of airbags to reduce injury in front end impacts. This in turn has produced a need to accurately analyse the behavior of the airbag as it inflates, and the forces on the occupants as they interact with the airbag. Explicit, transient dynamics codes are ideally suited to solving these non-linear, short term events. In order to realistically simulate airbag-occupant interaction in safety studies, it is often required that the initial folded state of the airbag represents accurately the actual folded state. Even partially unfolded, the airbag does not normally fit in between the position of the occupant and the relevant parts of the vehicle interior. In MSC/DYTRAN a module has been implemented to compute the transient states of the airbag as it unfolds, taking into account the interaction of the airbag with itself and relevant external parts. The special contact algorithm in MSC/DYTRAN is an upgrade of the existing contact algorithm in MSC/DYNAN enabling the complex fold patterns to be dealt with as they occur in the unfolding process. MSC/DYTRAN includes a variety of ways of analyzing airbag inflation. At its simplest the airbag can be inflated using a simple uniform pressure model, where the pressure depends on the mass inflow and volume of the airbag. A more accurate approach, taking into account the inertia effects of the gas inside the airbag, is the inclusion of gas dynamics through Euler/Membrane interaction. This is verified by comparing passenger bag inflation calculations with experimental pendulum tests. The occupant interaction is modelled by coupling MSC/DYTRAN with the Crash Victim Simulation program MADYMO.

MESH GENERATION FOR FOLDED AUTOMOBILE AIRBAGS USING MSC/XL (Acrobat 1.03MB) #4891, 14 pgs.
M.T. Howe -- The MacNeal-Schwendler Company B.V., Gouda, The Netherlands

ABSTRACT: The preparation of meshes for the analysis of automobile airbags is a complex process and requires a number of advanced pre-processing features to enable the modelling of the initially folded configuration. This task has been performed using MSC/XL Version 2A, a powerful pre- and post-processor intended for use with MSC's finite element analysis software. It involves generating two circular surfaces, joining them at the edges and the folding-up of this bag into its initial square-like shape for an analysis involving MSC/DYTRAN. The type of problem to be analysed is broadly described before indicating the above-mentioned features and the sequence of actions necessary to generate this mesh.

ANALYSIS OF FAULTS IN DISTRIBUTION TRANSFORMERS WITH MSC/PISCES-2DELK (Acrobat 983K) #4991, 13 pgs.
Jean-Bernard Dastous and Marc Foata -- IREQ-Institut de Recherche d'Hydro-Quebec, Varennes, Quebec, Canada

ABSTRACT: The problem of explosions in oil-insulated distribution transformers, following an internal electrical fault, has been investigated with MSC/Pisces-2DELK. A user-defined routine was developed to model the mechanical effects of an electric arc in oil. Rupture modes and peak pressures have been evaluated and compared to experimental data from the literature. They show good agreement with the results of MSC/Pisces-2DELK.

UPDATING MSC/NASTRAN MODELS TO MATCH TEST DATA (Acrobat 1.08MB) #5091, 14 pgs.
Ken Blakely -- MSC, Los Angeles, CA

ABSTRACT: Because of modeling uncertainties, an MSC/NASTRAN model may not match test data acquired for the same structure. The Design Optimization capability, new in Version 66, can be used to update a model by minimizing the difference between computed results and test data. This paper shows how to use the equation capability in SOL 200 to update MSC/NASTRAN models, and shows application to a disk drive enclosure to match measured resonant frequencies.

FE MODEL REFINEMENT WITH ACTUAL FORCED RESPONSES OF AEROSPACE STRUCTURES (Acrobat 785K) #5191, 10 pgs.
Tienko Ting -- University of Bridgeport, Bridgeport, Connecticut
Timothy L.C. Chen -- Sirkorsky Aircraft, Stratford, Connecticut

ABSTRACT: Formulation and computer algorithm for FE model refinement based on correlation with frequency response test results have been developed. The proposed approach derives from the direct frequency response formulation for FE analysis of dynamic systems. The computer algorithm has been effectively implemented in MSC/NASTRAN's DMAP language.

APPLICATION OF MSC/NASTRAN FOR ASSURANCE OF FLIGHT SAFETY AND MISSION EFFECTIVENESS WITH REGARD TO VIBRATION UPON INSTALLATION OF THE STINGER MISSILE ON THE AH-64A #5291 (no text available)
Mark H. Morton, Research Engineer -- McDonnell Douglas Helicopter Company, Mesa, Arizona

STRESS CALCULATION FOR THE SANDIA 34-METER WIND TURBINE USING THE LOCAL CIRCULATION METHOD AND TURBULENT WIND (Acrobat 1.29MB) #5391, 14 pgs.
Bernard Masse and Henri Pastorel -- IREQ Institut de Recherche d'Hydro-Quebec, Varennes, Quebec, Canada

ABSTRACT: Stress calculation for wind turbine blades is an important task for the manufacturers of wind turbines. A good prediction for stress level is required to evaluate the fatigue life of the rotor. Design of critical blade joints is based on such calculations. Aerodynamic loads are responsible for much of the stress level, and atmospheric turbulence has been identified as an important factor in estimating fatigue damage. This paper describes a stress estimation procedure and its application for the Sandia DOE 34-meter wind turbine. The procedure uses the computer code developed at IREQ(MCL) for aerodynamic loads calculation including atmospheric turbulence. Aerodynamic loads are decomposed into modal components and applied to the structure using the general purpose finite element program MSC/NASTRAN. The stress distributions as functions of frequency are extracted for critical locations on the blade. Stress distributions are calculated for the first five harmonics of the rotational speed and for off-harmonic frequencies. Comparison with measured data is good but a few questions about damping factors and aeroelastic phenomena are raised.

IPTN IN-HOUSE UTILITY SOFTWARE FOR STRESS ANALYSIS PROCESS (Acrobat 693K) #5491, 11 pgs.
M. Mochajan, Trias Santoso, and John Herry Karo Karo -- Nusantara Aircraft Industry, Bandung, Indonesia

ABSTRACT: Stress analysis process using FEM, beginning from input data preparation, model checking, validation to final result and documentation, should be performed effectively, efficiently, and with good accuracy. This paper describes the experiences in making utility software to support MSC/NASTRAN to achieve the above goals. Using available software and hardware, the utility software is made mainly for stress analysis requirement. The significance of this software is its user friendliness. It is graphic display oriented and integrated on one network system, so that all stress analysis procedures can be performed at one terminal.

INTERNAST: A GATEWAY TO MSC/NASTRAN (Acrobat 898K) #5591, 12 pgs.
Mary L. Alcorn, Computer Systems Engineer and Dr. M. M. Moharir, Senior Engineering Specialist -- General Dynamics, San Diego, CA

ABSTRACT: INTERNAST is a user-friendly preprocessor to MSC/NASTRAN. For engineers, it relieves the burden of knowing complicated operating system commands. Also, no prior knowledge is necessary to generate the File Management Section newly added in MSC/NASTRAN. INTERNAST helps to save engineering hours and computer dollars by reducing the probability of execution errors.
INTERNAST generates appropriate Job Control Language commands to execute MSC/NASTRAN in a batch mode. The FMS commands generated by INTERNAST at user's discretion, are automatically inserted at their respective proper locations in the MSC/NASTRAN input desk.
The advanced features such as Split Database Technology of superelements, multiple databases, automatic restart in different solution sequences, DMAP-ALTER libraries, etc., are very efficiently handled by INTERNAST, sparing the engineer's time mainly for engineering work. It also scans for errors in user input, pre-empting the costly execution runs doomed for fatal termination.

APPLYING DISTRIBUTED COMPUTING TECHNOLOGY TO MSC SOFTWARE APPLICATIONS
(Acrobat 1.14MB) #5691, 16 pgs.
Brian Casey, Juliette Gutierrez, and Ken Peterson -- MSC, Los Angeles, CA

ABSTRACT: This paper describes ways in which MSC product users can enhance their productivity and efficiency through the use of distributed computing environments. These environments consist of protocols, interfaces, and services that permit both users and their applications to access data and resources across a heterogeneous network. Several components of distributed computing environments and their relevance to MSC product users are discussed. Sample distributed configurations are described along with their comparative benefits. A table is also provided that denotes four levels of "interoperability" attainable between MSC/XL platforms and selected MSC/NASTRAN platforms.

ADAPTIVE DATA MANAGEMENT- A PATH TO CAE INTEGRATION (Acrobat 774K) #5791, 14 pgs.
Joseph L. Walsh, President -- FEGS, Inc., Duluth, Georgia

ABSTRACT: Integration of Computer-Aided-Engineering activities is the major priority for the 1990's for both users and developers of CAE software. This paper outlines some of the issues and past approaches toward CAE integration and outlines a proposed approach toward integration utilizing a vendor independent "Object-Oriented" data base system with the ability to adapt the data format and structure to the specific application.

USING THE CQUAD4 ELEMENT TO MODEL THE INTERFACE BETWEEN SOLID AND SHELL FINITE ELEMENTS (Acrobat 1.16MB) #5891, 17 pgs.
David S. McCollum -- MicroMotion, Inc., Boulder, Colorado

ABSTRACT: The MSC/NASTRAN CQUAD4 shell element is used to facilitate the transition modelling at the interface between shell and solid elements. The CQUAD4 element is used in lieu of multi-point constraints or rigid elements. By "coating" the solid surface at the plane defining the transition interface, degree-of-freedom consistency is maintained. The element thickness t and the normalized bending intertia 12I/t^3 are also varied in order to study their effects on the transition modelling. The impetus for using CQUAD4 element arises from its ease of application at an interface, particularly when a graphics pre/post-processing program is used to construct the finite element model and when the model geometry is complex. The efficacy of using the CQUAD4 at a shell/solid transition interface is investigated for typical analysis problems.

GRID POINT STRESS CALCULATION, ERROR PREDICTION AND AUTOMATIC REMESHING PROCEDURE (Acrobat 1.32MB) #5991, 16 pgs.
J.C. Cheng, G.C. Campbell, and L.I. Nagy -- Ford Motor Company, Dearborn, Michigan

ABSTRACT: This paper describes the following three post-processing methods as applied to MSC/NASTRAN static analysis:
1. Grid point stress computation
2. Error prediction due to mesh discrepancy
3. Automatic remeshing procedure

A P-VERSION ELEMENT ERROR INDICATOR FOR MSC/PROBE (Acrobat 1.11MB) #6091, 16 pgs.
John E. Schiermeier, Engineering Applications Specialist -- MSC, St. Louis, Missouri

ABSTRACT: In this paper, the background of the p-version and the calculation of the p-version element error indicator will be discussed. The application and performance of the indicator will be demonstrated through examples. Related issues, such as the use of the indicator in an adaptive manner, will be explored.

FLEXIBLE RESULTS EVALUATION (Acrobat 560K) #6191, 10 pgs.
Joseph L. Walsh -- FEGS, Inc., Duluth, Georgia
Martin Jones -- FEGS Limited, Cambridge, United Kingdom

ABSTRACT: The evaluation of large amounts of MSC/NASTRAN results is becoming more and more common among MSC/NASTRAN users. The processing of this data can become a monumental task for the user without the proper tools. This paper discusses a flexible approach for results evaluation based on a hierarchical results database in which results are assigned as attributes to mesh entities and have assigned the results the attribute of their mathematical form. Since the mathematical form and relationship to mesh entities is stored in the hierarchical database any result entity may be converted to a different mathematical form and/or "averaged" to a different mesh entity. The results database stores all loadcases in one direct access file allowing for combination of load case values, and graphing of results across load cases or time steps. This paper outlines the hierarchical results data structure in FAM and the methodology of accessing and manipulating this result data.

PRE- AND POSTPROCESSING LARGE DETAILED MSC/NASTRAN MODELS (Acrobat 1.05MB) #6291, 16 pgs.
Mike Farley -- McDonnell Douglas Helicopter Corporation, Mesa, Arizona

ABSTRACT: The advent of advanced pre and postprocessing techniques makes MSC/NASTRAN more viable in evaluating large detailed structures with unique geometry and characteristics. Discrete areas can be modeled in detail to evaluate effects such as stress concentration. Shell element analysis of laminated composite structure on a ply basis can be performed and the results postprocessed. The large output generally associated with PCOMP and MAT8 card images of such an analysis can be easily managed. Three dimensional ply representations, using solid HEX8 elements to evaluate interlaminar tension is practical. The technique of evaluating and postprocessing large detailed MSC/NASTRAN models is the topic of this paper.

LAPCAD, A MSC/NASTRAN AND MSC/PAL2 FRONT END ON THE PERSONAL COMPUTER
 (Acrobat 1.70MB) #6391, 20 pgs.
Gert M. Lundgren -- LAPCAD Engineering, Chula Vista, CA

ABSTRACT: The following example illustrates how LapCAD was used for the creation of a finite element model of an automotive suspension part. This model was output in the MSC/NASTRAN format, the primary file format of LapCAD. The model was transferred to a VAX mainframe, and the resulting F06 was taken back to the Macintosh and postprocessed in LapCAD. The model solution could have also been obtained via MSC/pal2, on the Macintosh, since the model has fewer than 2000 nodes. LapCAD allows creation of models up to 10,000 nodes or 60,000 degrees of freedom.

OVERVIEW OF MSC/XL V3 (Acrobat 180K) #6491, 3 pgs.
Don McLean, MSC/XL Program Manager -- MSC, Los Angeles, CA

ABSTRACT: V3 is the next version of MSC/XL that will be released. This paper presents an overview of the new capabilities in the areas of error correction, performance enhancements, hardcopy support, MSC/NASTRAN support and MSC/EMAS support.

OVERVIEW OF MSC/NASTRAN VERSION 67 (Acrobat 517K) #6591, 6 pgs.
Ken Blakely, MSC/NASTRAN Program Manager -- MSC, Los Angeles, CA

ABSTRACT: Version 67 is the next version of MSC/NASTRAN that will be released. This paper presents an overview of the new Version 67 capabilities in the areas of mesh error analysis, matrix solvers, nonlinear analysis, design sensitivity, acoustic analysis, heat transfer, and the executive system, among others.

OVERVIEW OF MSC/DYNA VERSIONS 2 AND 3 (Acrobat 456K) #6691, 7 pgs.
Roger Keene, Program Manager -- MSC ltd., Walton-on-Thames, United Kingdom

ABSTRACT: MSC/DYNA is MSC's explicit transient dynamic code designed for structural applications like automotive crash, ship collision, and metal forming. It compliments the other explicit codes MSC/PISCES and MSC/DYTRAN which are intended for applications involving fluid/structure interaction and extreme deformations.
MSC/DYNA Version 2 is the latest version of the code, currently available on a range of popular computers. It is a significant enhancement over Version 1 in terms of speed, capability and ease of use. MSC/DYNA Version 3 will further enhance the code. This paper presents an overview of the new capabilities in Version 2 and the enhancements that users can expect in Version 3.

OVERVIEW OF MSC/DYTRAN VERSION 1 (Acrobat 492K) #6791, 7 pgs.
Roger Keene, Program Manager -- MSC ltd., Walton-on-Thames, United Kingdom

ABSTRACT: MSC/DYTRAN is a new explicit transient dynamic code designed to solve large problems that involve the interaction of fluids and structure or the extreme deformation of materials. MSC/DYTRAN combines the technology of MSC/DYNA and MSC/PISCES in a modern, vectorized and very efficient code structure. It contains a Lagrangian processor to model the structural parts of the model, and an Eulerian processor for modelling fluids and materials undergoing very large deformations.