SAWE Technical Papers

@inproceedings{3442,

title = {3442. Knowledge Management in a 'Need to Know' Environment},

author = {Alan C. Jordan},

url = {https://www.sawe.org/product/paper-3442},

year  = {2008},

date = {2008-05-01},

booktitle = {67th Annual Conference, Seattle, Washington},

pages = {12},

address = {Seattle, Washington},

abstract = {Our capability within Engineering to capture and leverage useful knowledge is limited to our ability to protect information. Our goal is to maximize the amount of information we share and make available to those with 'need to know' and can add value. Focusing first on Information Protection and providing the tools to follow company policy will maximize the amount of information and knowledge we share. 

Our requirements were simple: 

1. The ability to segregate information by community providing a 'trusting' environment and enabling users to share more information to those who need it. 

2. The ability to mark and protect access to sensitive information based on company policy and government regulations. 

3. Ease of use and integration with desktop procedures and tools now used by engineers. 

This paper will discuss protecting and sharing information while collaborating within BCA Weight Engineering's implementation of a new KM tool from the AskMe Corporation (Ask BCA). The AskMe application, along with customized features specifically addressing our information protection requirements, will enable us to capture, share and leverage more knowledge and information based on 'need to know' without compromising information protection.},

keywords = {12. Weight Engineering - Computer Applications, 16. Weight Engineering - Organization},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3424,

title = {3424. Computer Aided Weight and Cost Management in Vehicle and Aircraft Industry},

author = {Hans-Peter Dahm},

url = {https://www.sawe.org/product/paper-3424},

year  = {2007},

date = {2007-05-01},

booktitle = {66th Annual Conference, Madrid, Spain},

pages = {23},

publisher = {Society of Allied Weight Engineers},

address = {Madrid, Spain},

organization = {Society of Allied Weight Engineers},

abstract = {At the present time, the time-to-market-process in R},

keywords = {12. Weight Engineering - Computer Applications, 28. Weight Reduction - Processes},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3389,

title = {3389. Managing Common Data Across Multiple Platforms},

author = {Kathleen Tolman and Peter Kniesel},

url = {https://www.sawe.org/product/paper-3389},

year  = {2006},

date = {2006-05-01},

booktitle = {65th Annual Conference, Valencia, California},

pages = {24},

publisher = {Society of Allied Weight Engineers},

address = {Valencia, California},

organization = {Society of Allied Weight Engineers},

abstract = {The Size, Weight, Power and Cooling (SWaP-C) attributes of common equipment in the Future Combat System (FCS) Program must be standardized in content and availability throughout all the platform Integrated Product Teams (IPTs). Under a traditional program-management approach, SWaP-C data would be informally managed and tracked by each vehicle platform IPT individually. But in the case of FCS–a highly decentralized program where development is proceeding at multiple geographic sites– such an approach posed potential risks. The results of employing a traditional approach to SWaP management, especially over several years of performance, could have included confusion about reporting responsibility, inconsistent use of the latest available estimates, and an environment in which IPTs would not maximize opportunities to share data and avoid duplication of tasks. To avoid such problems, a multi step approach has been instituted for FCS. Control of the data was assigned to a single, non-vehicle affiliated IPT (System of Systems Engineering and Integration (SSEI)), using a standard dataflow process and a dedicated, central, database. This approach provided a single source for all program SWaP-C Data with program wide visibility and unanimous IPT buy-in. The solution proved to be stable and effective, reducing confusion and inconsistent reporting practices. The processes described in this paper are uniquely applicable to System of Systems integration problems where complex, multi-product programs share common elements that need to be tracked in a central, visible manner by a Lead System Integrator.},

keywords = {12. Weight Engineering - Computer Applications, 22. Weight Engineering - Structural Design},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3391,

title = {3391. New Advances In Topology Optimization For Weight Reduction During Preliminary Design},

author = {Terence Smith and Harold Thomas},

year  = {2006},

date = {2006-05-01},

booktitle = {65th Annual Conference, Valencia, California},

pages = {-1},

publisher = {Society of Allied Weight Engineers},

address = {Valencia, California},

organization = {Society of Allied Weight Engineers},

abstract = {Weight reduction of current designs can be achieved through sizing optimization by reducing thicknesses with constraints on stress, stiffness, frequency, buckling factors, and dynamic loadings. Unfortunately, the weight reduction is usually just a few percent. A more effective approach to weight reduction is to define an optimum topology (layout) during the conceptual design stage. For example, three small diagonal reinforcement ribs may be more effective than two large horizontal ribs if the load path is diagonal. Another example is the number, size, and location of lightening holes. If the number and location of these holes is predetermined, weight reduction can only be achieved through changing the size of the holes. Much greater weight reduction can be achieved if the correct number of holes in the correct locations and of the correct sizes is used. Altair OptiStruct},

note = {Paper Missing},

keywords = {12. Weight Engineering - Computer Applications, 28. Weight Reduction - Processes},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3327,

title = {3327. Mass Properties In VTOL UAV Conceptual Design Software, Part 1: Overview and Beneral Algorithims},

author = {John Ohanian},

url = {https://www.sawe.org/product/paper-3327},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {26},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {The determination of an aircraft?s mass properties is critical during its conceptual design phase. Obtaining reliable mass property information early in the design of an aircraft can prevent design mistakes that can be extremely costly further along in the development process. 

In this paper, two methods are presented in order to automatically calculate the mass properties of aircraft structural components. The first method set forth calculates the mass properties of homogenous solids represented by polyhedral surface geometry. A newly developed method for calculating the mass properties of thin shell objects, given the same type of geometric representation, is derived and explained. Both of these methods apply to polyhedral geometry, which in many cases is used to approximate NURBS (Non-Uniform Rational B-Spline) surface geometry. This type of approximate representation is typically available in design software since this geometric format is conducive to graphically rendering three-dimensional geometry.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3328,

title = {3328. Mass Properties In VTOL USV Conceptual Design Software, Part II: Estimationg Fuel Mass Prooerties},

author = {John Ohanian},

url = {https://www.sawe.org/product/paper-3328},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {19},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {The determination of an aircraft?s mass properties is critical during its conceptual design phase. Obtaining reliable mass property information early in the design of an aircraft can prevent design mistakes that can be extremely costly further along in the development process. 

In this paper, a method for estimating the mass properties of liquid fuel in a tank that is suitable for conceptual design software is presented. The method calculates mass, center of gravity, and moments of inertia of the fuel at arbitrary tank fullness and rotation. The method is applied to polyhedral geometry, which in many cases is used to approximate NURBS (Non-Uniform Rational B-Spline) surface geometry. This type of approximate representation is typically available in design software since this geometric format is conducive to graphically rendering three-dimensional geometry. Results for an example case of a cylindrical fuel tank are presented.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3355,

title = {3355. Reference Models For Structural Technology Assessment and Weight Estimation},

author = {Jeffrey Cerro and Martinovic and Eldred},

url = {https://www.sawe.org/product/paper-3355},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {21},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {Previously the Exploration Concepts Branch of NASA Langley Research Center has developed techniques for automating the preliminary design level of launch vehicle airframe structural analysis for purposes of enhancing historical regression based mass estimating relationships. This past work was useful and greatly reduced design time, however its application area was very narrow in terms of being able to handle a large variety in structural and vehicle general arrangement alternatives. Features of that work such as the utilization of Object Oriented JAVA Programming and the incorporation of flexible commercial FEA and commercial structural design software are retained in this continuing work, but a new emphasis has been placed on making the integrating JAVA modules much more generic. The goal has been to develop a library of JAVA modules which when placed in the desired sequence facilitate the automated structural sizing of a greater variety of component and vehicle systems. The finite element procedures wrapped by JAVA routines now trend towards being more generic in the sense that the routine inputs are not as much design and FEA program specific as they are design and FEA process specific. A later goal in this analysis system development would be to arrive at a working group defined set of JAVA Interface Classes that describe input and output required for particular stages of analysis of automated structural design. Along with standardized input/output parameters there would also be a set of standard data processing functions, which are then useful to the structural designer in providing the flexibility required for designing numerous parts, sub-assemblies, and full vehicle configurations. In JAVA programming terminology these Class definitions become generic Interfaces which are then implementable at any corporate or academic organization utilizing internal and possibly proprietary procedures. Model data may be exchanged between these organizations and will be processable by any of the organizations which have implemented the defined standard Interface. Similar work is ongoing in the area of Simulation Based Acquisition (SBA) via the Simulation Interoperability Standards Organization (SISO) and particularly in the area of integrating distributed simulations by the High Level Architecture - Commercial off the shelf Simulation Package Interoperation Forum (HLA~CSPIF). For those more interested in preliminary design in a collaborative environment the NAVY NAVSEA division has pursued similar themes of modularity and multi-disciplinary interoperability by utilizing a CORBA and IDL (Interface Definition Language) based approach to Simulation Based Design (SBD). A quote from Optimization in the Simulations Based Design Environment by W. A. Kusmik shows the great utility of implementing a formal Simulation Based Design approach. 

'High Potential was evidenced by the ability to integrate high-fidelity modeling and simulation tools to provide insight into overarching system-level performance attributes and the ability of the integration process itself to promote informal collaboration between various domain experts.' 

These too are the features being encouraged and developed within the Exploration Concepts Branch to enable functionally and organizationally collaborative multidisciplinary design for the purposes of defining and building vehicle elements which best help us achieve the nation's vision for manned space exploration.},

keywords = {12. Weight Engineering - Computer Applications, 19. Weight Engineering - Spacecraft Estimation},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3360,

title = {3360. Are You Sure? - Uncertainty in Mass Properties Engineering},

author = {Robert L. Zimmerman and Nakai},

url = {https://www.sawe.org/product/paper-3360},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {36},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {The Mass Property Engineer?s role in the engineering organization is ultimately to report the mass properties of the organization?s vehicle, so that the vehicle?s performance can be characterized. It is insufficient merely to report the mass properties as a discrete entity ? the characterization of performance requires the possible variations of the vehicle?s mass properties also be determined and reported by the Mass Property Engineer to the team. Mass Property Engineers have an expectation, based on precision computerized drafting and manufacturing equipment, electronic mass property tallying, and high accuracy measurement equipment, that the reported mass properties will be very close to the vehicle?s actual mass properties. This paper will unveil the proposition that the carefully determined mass properties reported by the Mass Properties group has far greater dispersions about the reported values than that expectation. The paper is divided into three parts. Part One expands on basic statistical concepts required to determine mass property parameter dispersions. Part Two derives the algorithms necessary to determine overall vehicle mass property uncertainties. Part Three illustrates Parts One and Two using an example, and produces some representative computer code to implement the algorithms.},

note = {L. R. 'Mike' Hackney Award},

keywords = {12. Weight Engineering - Computer Applications, 21. Weight Engineering - Statistical Studies, Mike Hackney Best Paper Award},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3372,

title = {3372. Applications of Topology Optimization for Weight Reduction During Preliminary Design},

author = {Harold Thomas},

url = {https://www.sawe.org/product/paper-3372},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {19},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {Weight reduction of current designs can be achieved through sizing optimization by reducing thicknesses with constraints on stress; stiffness, and frequency. Unfortunately, the weight reduction is usually just a few percent. A more effective approach to weight reduction is to define an optimum topology (layout) during the preliminary design stage. For example, three small diagonal reinforcement ribs may be more effective than two large horizontal ribs if the load path is diagonal. Another example is the number, size, and location of lightening holes. If the number and location of these holes is predetermined, weight reduction can only be achieved through changing the size of the holes. Much greater weight reduction can be achieved if the correct number of holes in the correct locations and of the correct sizes is used. 

In this paper a finite element based structural topology optimization software program, Altair OptiStruct?. is used to detennine optimum layouts for aerospace, automotive, and consumer goods structures. This software program determines optimum topologies of components subject to weight, stiffness, and frequency limits. Examples will be shown and the weight reduction and cost benefits discussed. The impact of manufacturing constraints, such as stamping die and casting mold removal will be discussed. In addition, the optimal design of stamped ribs in sheet metal structures (topography optimization) will be introduced. 

By using mathematical optimization techniques in conjunction with finite element based structural analysis, the optimal topology and topography of designs can be achieved. By using this approach during the preliminary design phase, significant weight can cost reductions can be achieved.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3374,

title = {3374. MassMorph},

author = {Mark Beyer},

url = {https://www.sawe.org/product/paper-3374},

year  = {2005},

date = {2005-05-01},

booktitle = {64th Annual Conference, Annapolis, Maryland},

pages = {14},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Annapolis, Maryland},

abstract = {MassMorph is a technical innovation that has revolutionized Cessna's Advanced Design Weights processes. It is a flexible and robust process which speeds design by morphing highly detailed legacy mass properties and finite element models into new product designs. It provides an immediate head start in design and analysis, enabling timely review of alternate design approaches, and closes automation gaps for multi-disciplinary analysis and optimization. It can readily blend morphed mass properties from legacy aircraft databases and new analysis of engineering CAD models to support any phase of product development. The process produces a detailed report of target weights and CGs by functional group, mass properties for Loads, Dynamics, and Aeroelastic Stability functions, and conforms mass properties to detailed finite element models for structural analysis. The process provides extensive query capabilities by functional group, part, next higher assembly, inertial bay, volume, and/or FEM grid using regular expressions, which makes it a good research tool for legacy aircraft databases. The process is being expanded to facilitate morphing financial cost models. The process leverages Cessna's hierarchal functional group (formally Army-Navy codes) methods. The morphing process relies on mass particulation to transform both mass data to the target aircraft, and performs transformations in homogeneous coordinates (four-dimensions) to accommodate linear transformations for taper in addition to translation, rotation, shear, and scaling.},

keywords = {11. Weight Engineering - Aircraft Estimation, 12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3330,

title = {3330. Weight Optimization Of Filament-Wound Pressure Vessels},

author = {Dr. Myles L. Baker},

url = {https://www.sawe.org/product/paper-3330},

year  = {2004},

date = {2004-05-01},

booktitle = {63rd Annual Conference, Newport, California},

pages = {12},

address = {Newport, California},

abstract = {A software suite tailored to the analysis and optimization of filament wound composite pressure vessels has been developed. The software has been applied with success to simple pressure vessels, as well as to solid rocket motor cases. The optimization process employed is a mixed low-fidelity/high-fidelity approach, in which the basic pressure vessel geometry and winding angles are determined using a low fidelity model based on laminate theory. These results are then used as a starting point for a high fidelity optimization where the details of the winding schedule are tailored to provide the lightest possible bottle. The high fidelity component of the optimization is performed using a detailed winding simulation (COBSTRAN) and a composite progressive failure analysis (GENOA). The software is very easy to use, and provides a useful tool for pressure vessel design.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3307,

title = {3307. Next Generation - Aircraft Product Development Weight Control Tools for Hydraulic Power System},

author = {Corrie E. Gowland and Robert M. Bond and Arun K. Trikha and Reid M. Wakefield},

url = {https://www.sawe.org/product/paper-3307},

year  = {2003},

date = {2003-05-01},

booktitle = {62nd Annual Conference, New Haven, Connecticut},

pages = {21},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {New Haven, Connecticut},

abstract = {Boeing?s Sonic Cruiser was identified as a design challenge from the beginning. New materials, technologies, and systems architectures were needed to meet the very challenging performance requirements set by the program. The hydraulic system would require a new architecture utilizing new technologies. Weight engineers would need a design and analysis tool to quickly develop a configuration and perform weight assessments. Weight engineering needed a flexible tool with the sensitivity and adaptability to quickly guide the configuration. 

Boeing?s previous efforts led to work on a new weight estimation tool for hydraulic systems and the work continued on to the Sonic Cruiser. Support from the mechanical hydraulics systems organization was solicited to develop a rules-based method incorporating their existing tools and processes. Integration with their tools and processes also made discussions with them more productive because the focus could be on the design and architecture, not on the weight estimation tool. Excel and Visual Basic were used to keep the tool flexible and allowed for continuous incorporation of new requirements and capabilities as needed. 

The benefits of the new tool include reduced analysis cycle time and isolation of different aspects of the hydraulic systems for trade studies. Hydraulic components and tubing are distributed in three-dimensional space using design-based rules ? in seconds ? replacing a non-repeatable process, previously requiring days to execute. Weight engineers can now perform and support trade studies between architectures, components, materials, pressures, and geometry. When all data are available, a full weight analysis, previously taking two to three days can now be executed in under an hour! 

This paper describes this weight estimation process and tool.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3245,

title = {3245. Stringer-Panel Optimization and Pitfalls},

author = {George Johnston},

url = {https://www.sawe.org/product/paper-3245},

year  = {2002},

date = {2002-05-01},

booktitle = {61st Annual Conference, Virginia Beach, Virginia, May 18-22},

pages = {16},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Virginia Beach, Virginia},

abstract = {Every vehicle deserves to have its structure optimized. Panel optimization programs minimize weight or increase stiffness. But the biggest advantage is to find the best panel designs sized to the applied load with the required dimensions (for example, stringer spacing) for the material selected with means to get them on the airplane with the assurance that the tests will be passed. Computers formerly limited the panel optimization programs. Now that computer capacity has increased by orders of magnitude, those who would develop new programs are urged to look at the whole problem. Assumptions, approximations and pitfalls are explained.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3155,

title = {3155. Simulation of the Cessna Citation Flight Profile},

author = {May Raisdana},

url = {https://www.sawe.org/product/paper-3155},

year  = {2001},

date = {2001-05-01},

booktitle = {60th Annual Conference, Arlington, Texas, May 19-23},

pages = {12},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Arlington, Texas},

abstract = {In today's competitive and complex manufacturing environment, companies should be aware of any technology that may help guide them and improve their performance to reach or exceed customer satisfaction. This paper discusses the philosophy of Computer Application using a Microsoft Excel spreadsheet and Visual Basic Programming Language to compute flight weight and balance. 

A series of Visual Basic Programming codes were written considering all the constraints pertaining to each Citation. These improvements have been noticed from using this software: 

1. Greater Accuracy 

2. Timesaving 

3. User friendly 

4. Loading flexibility 

This program allows the pilot to simulate the flight profile for a specific Citation over and over again on any computer with Microsoft Excel spreadsheet application.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3156,

title = {3156. ''Standard'' SAWE Mass Properties Calculation Software and Algorithms},

author = {Richard Boynton and Nakai and Wiener and Strom},

url = {https://www.sawe.org/product/paper-3156},

year  = {2001},

date = {2001-05-01},

booktitle = {60th Annual Conference, Arlington, Texas, May 19-23},

pages = {70},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Arlington, Texas},

abstract = {Although most CAD programs now include routines for calculating the mass properties of the various elements of a system or vehicle, there is still a use for basic mass properties calculation software. If such software were written in JAVA, then it could be easily shared by all members of the SAWE and would run on any type of computer. This software could be used when estimating the mass properties of new designs, or it could be used to make quick simplified mass properties calculations to verify that the results of the CAD programs are reasonable. In addition to describing the software, this paper is a tutorial on the calculation of mass properties (moment of inertia, centerof gravity, product of inertia). We have included a discussion of the coordinate transformation of inertias using tensors and have provided a number of simple mathematical tests that can be used to verify the reasonableness of calculated values. There are numerous textbooks on dynamics that devote a few pages to the theory of these properties. However, these textbooks quickly jump from a very brief description of these quantities to some general mathematical formulas without giving adequate examples or explaining in enough detail how to use these formulas. The purpose of this paper is to provide a detailed procedure for the calculation of mass properties for an engineer who is inexperienced in these calculations. This paper will also provide a convenient reference for those who are already familiar with this subject. This paper contains a number of specific examples with emphasis on units of measurement. The examples used are rockets and re-entry vehicles. The paper then describes the techniques for combining the mass properties of sub-assemblies to yield the composite mass properties of the total vehicle. Errors due to misalignment of the stages of a rocket are evaluated numerically. Methods for calculating mass property corrections are also explained. It was hoped that an outcome of this paper will be the generation of SAWE standard mass properties utility software written in JAVA that is available on the SAWE web site. Tutorial booklets could also be downloaded which would explain the use of the software and describe the process of making mass properties calculations. Unfortunately, due to concerns regarding United States export restrictions, the JAVA software described in this paper is currently only available for distribution and licensing to United States companies and citizens.},

note = {L. R. 'Mike' Hackney Award},

keywords = {12. Weight Engineering - Computer Applications, Mike Hackney Best Paper Award},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3157,

title = {3157. IMPACT - Innovative Mass Properties Analysis CATIA Tool or Weight and Balance 2.2 Customized Solution},

author = {Jean-Marc Flamand},

url = {https://www.sawe.org/product/paper-3157},

year  = {2001},

date = {2001-05-01},

booktitle = {60th Annual Conference, Arlington, Texas, May 19-23},

pages = {30},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Arlington, Texas},

abstract = {Impact is a mass property distribution tool developed by Bombardier Aerospace and ACT (Alliance Commercial and Technology). This new tool is a customized solution of the ACT Weight and Balance V3.2 application for CATIA. 

The new application includes the basic functionality of the W&B ACT application plus the following: 

- Ability analyze all CATIA models loaded in the user work session. 

- Cut most of the CATIA elements in a model(s) to extract, center of gravity, and inertia distribution data. The data is then use in the weight data for stress and dynamic analysis report. 

- Code each CATIA element to produce a detail weight statement (ref: SAWE recommended practice $#$8A) with an integrated code table. 

- Automatic code attribution for each CATIA element to produce a geographical weight statement. 

- User interface to validate data prior to the initiation of the compute process. 

- Result of analysis may be appended to an existing file or saved under a new file. 

- Output analysis data can be organized in an assembly drawing structure via the validation panel. 

- Analysis can be performed through an overnight batch process. Results and error log files are sent by e-mail to the user account.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2464,

title = {2464. Mass Properties Relational Database Manager - A Primary Element of the Mass Properties Tool Kit},

author = {A McGill},

url = {https://www.sawe.org/product/paper-2464},

year  = {1999},

date = {1999-05-01},

booktitle = {58th Annual Conference, San Jose, California, May 24-26},

pages = {77},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {San Jose, California},

abstract = {The mass properties tool kit is comprised of four powerful tools. Used together, these tools provide the capability to mathematically model the mass properties of a complex system. The Mass Properties Relational Database Manager tool is a preprocessor data manager. The other three tools sort, sum the mass properties, distribute the mass to finite element grids, and graphically display the data. The Mass Properties Relational Database Manager is the key in a suite of analysis software tools. It serves several purposes. It provides an interactive interface for the entry and maintenance of mass properties data. It is a library of part information. It manages the relationship between parts that build up assemblies. It extracts all this data to create an output file. This file is used as input for the other tools. The Moments of Inertia, Products of Inertia version 3 (MIPI3) mass properties analysis program is made up of several subroutines. They are used to manipulate the mass properties relational database output to obtain the summation of weights, centers of gravity, moments and products of inertia, principle axes, principle inertias, and uncertainties. The MIPI3 program also contains several preprocessors that can be used for sorting the mass properties relational database output to obtain a variety of other outputs. These sorting preprocessors utilize the columns in the mass properties relational database output and arrange that information in a specific order. MIPI3 also has the capability to utilize a transformation of coordinate axes. Therefore, the system is not limited to a rectangular coordinate system, but can also use cylindrical and spherical coordinate systems. The Mass Distribution (MASDIS) mass properties mass distribution program supports finite element structural analysis. This program distributes the mass properties relational database output to a set of finite element grid points. The subroutines divide each component's mass into pieces of user defined size. A search is then conducted to find the closest node for each subelement of mass. The mass properties of all the subelements are summed at each finite element node. The results are written to an output file in the CONM2 card format. This file serves as an input file for NASTRAN. The Mass Properties Plotter (MPPLOTX) displays the image of the data in the mass properties relational database output. It uses interactive 3-D color graphics and can be used as a visual check that the subject is modeled as intended. Common errors such as misplaced items, improperly sized items, reversed or misoriented shapes, or incorrect shapes can be identified quickly with this tool. It can also display the output of the MASDIS program. This provides a quick validation of the quality of the mass distribution. The mass properties tool kit addresses all phases of mass properties analysis requirements. It is designed to provide sophisticated modeling and visualization capabilities. Based on simple user inputs, the mass properties tool kit provides quick computation and reporting capabilities. This paper addresses only some of the highlights of the Mass Properties Database Manager. It is focused on the use of four basic forms, namely Part, Parts List, Location, and Extract. Emphasis is placed on the ease of using these forms to enter and edit mass properties data. Additional emphasis is placed on the vast capability this tool has in handling coordinate system transformations. An example is shown in the appendix to help illustrate these features. A hypothetical wagon train is used in the example for two reasons. The main reason is to ensure that no company proprietary data is inadvertently leaked in this paper. The other reason is symbolic. Let the pioneering spirit of the western settlers carry you to a better understanding of this new tool. Just as the wagon train led to a new epic in American history, the Mass Properties Relational Database Manager can shift the paradigm of mass properties analysis.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2465,

title = {2465. Rapid Finite Element Modeling With RAMPAGE (Rapid Aircraft Mass Properties and Geometry Estimation)},

author = {D P Yanez},

url = {https://www.sawe.org/product/paper-2465},

year  = {1999},

date = {1999-05-01},

booktitle = {58th Annual Conference, San Jose, California, May 24-26},

pages = {12},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {San Jose, California},

abstract = {A process, called the Rapid Modeling System (RMS), is under development at The Boeing Company. This process uses a combination of Boeing developed software applications and commercially available modeling tools to greatly reduce the time and manpower required to create high fidelity finite element models. This allows three-dimensional finite element models to be used early in the structural design process. The Rapid Modeling System has been successfully used by many military aircraft projects at Boeing, and has become an integral part of the structural design and optimization process. One software tool that is an integral part of the RMS process is the RAMPAGE application. RAMPAGE allows the mass properties engineer to supply initial thickness, width, and mass factors to the structural geometry based upon historical data for similar parts. RAMPAGE also supplies a three-dimensional mass distribution, including system masses if desired, for the application of inertia loads to the finite element model. This paper provides an overview of the RMS process, highlighting the integration of mass properties analysis through RAMPAGE.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2413,

title = {2413. Rebuilding Your Company's Technology},

author = {G A Honea},

url = {https://www.sawe.org/product/paper-2413},

year  = {1998},

date = {1998-05-01},

booktitle = {57th Annual Conference, Wichita, Kansas, May 18-20},

pages = {5},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Wichita, Kansas},

abstract = {The internal development of a software tool to help in the standardization of mass properties determination and reporting can offset various costs if standards exist. Companies involved with weight and mass properties on a regular basis require standard tools and processes for many important reasons. However, cutbacks within the industry have taken a toll on many of these tools, with work-arounds becoming common place. Fortunately, organized groups have started to form strategies that will re- establish these lost tools and skills while remaining within budgetary constraints. Our everyday workplace is so filled with military standards and specifications, standard tools, and standard manufacturing processes that when a lack of them do occur it is very disconcerting. Society, in general, has grown to expect tools, devices, systems, and processes that perform the same way industry-wide. The personal computer industry is probably the most popular example and looming on the horizon is digital television. In the engineering world, people rely on standards for tools, compatibility of materials, and even presentation of results, to name a few. They are also important for internal communications, engineering productivity, and corporate efficiency. Standards can even assist in determining when analytical results are ''good enough.'' But without this basis for evaluation, things are left in the air. Typically it is not an internal decision to disregard the norm, but more of a reaction to the environment which includes corporate consolidation.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{2432,

title = {2432. Object Oriented Programming in Mass Properties Analysis},

author = {J H Nakai},

url = {https://www.sawe.org/product/paper-2432},

year  = {1998},

date = {1998-05-01},

booktitle = {57th Annual Conference, Wichita, Kansas, May 18-20},

pages = {69},

publisher = {Society of Allied Weight Engineers, Inc.},

address = {Wichita, Kansas},

abstract = {This paper provides an overview of object-oriented programming and summarizes reasons why object oriented programming (OOP) can be an attractive programming approach for mass properties analysis. It addresses the pros and cons of OOP when applied to the development of mass properties analysis code. This paper includes sample listings of C++ code used to create mass properties objects and related objects. Object class definitions include vectors, tensors, coordinate transformations, complex numbers, and mass properties.},

keywords = {12. Weight Engineering - Computer Applications},

pubstate = {published},

tppubtype = {inproceedings}

}