SAWE SAWE Technical Papers

3763. MauSPAF: Design of an Open-Source Mass Properties Management Framework

Nuño, M.; Schröder, K.

In: 81st Annual Conference, Savannah, Georgia, pp. 18, Society of Allied Weight Engineers, Inc., Savannah, Georgia, 2022.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, Student Papers

3762. Artificial Intelligence Techniques for Ship Weight Estimation and Calculation

Malla, Upendra

In: 2021 SAWE Tech Fair, pp. 9, Society of Allied Weight Engineers, Inc., Virtual Conference, 2021.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

3726. Toolchain Integration For Space Habitat Design

DeVoe, Maxwell; Tokarz, Ariel; Park, Samuel

In: 78th Annual Conference, Norfolk, VA, pp. 11, Society of Allied Weight Engineers, Inc., Norfolk, Virginia, 2019.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, 34. Advanced Design

3694. Using Knowledge Analytics to Search and Characterize Mass Properties Aerospace Data

Cerro, Jeffrey; Sidehamer, Theodore; Notarnicola, Dorthy

In: 77th Annual Conference, Irving, Texas, pp. 25, Society of Allied Weight Engineers, Inc., Irving, Texas, 2018.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

3671. Model Based Mass Properties Engineering at JPL

IV, Morgan Hendry; Gross, Johannes

In: 75th Annual Conference, Denver, Colorado, pp. 11, Society of Allied Weight Engineers, Inc., Denver, Colorado, 2016.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, 24. Weight Engineering - System Design

3630. Design Patterns in Object Oriented Programming

Rosal, Sal

In: 73rd Annual Conference, Long Beach California, pp. 10, Society of Allied Weight Engineers, Inc., Long Beach, California, 2014.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

3595. Calculating Mass Properties from a Triangulated Solid

Sinclair, Dr. Paul

In: 72nd Annual Conference, St. Louis, Missouri, pp. 10, Society of Allied Weight Engineers, Inc., Saint Louis, Missouri, 2013.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

@inproceedings{3595,

title = {3595. Calculating Mass Properties from a Triangulated Solid},

author = {Dr. Paul Sinclair},

url = {https://www.sawe.org/product/paper-3595},

year = {2013},

date = {2013-05-01},

booktitle = {72nd Annual Conference, St. Louis, Missouri},

pages = {10},

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

address = {Saint Louis, Missouri},

abstract = {The introduction of solid modelling in Computer—Aided Design (CAD) tools has proven to be a tremendous boon to weight engineering. Analysis of the solid models provides weight, center of gravity, and inertia data with an ease and precision undreamt of by earlier generations. However, CAD packages such as Dassault's Catia and SolidWorks are designed for a wide range of applications. As a result, the models are highly complex and even simple operations require a significant amount of resources. This can make sophisticated weights analyses slow and unwieldly, and occasionally prone to error.

Alternative means of representing solid objects

can address these problems. One of the simplest

representations of a solid is by triangulation: the

surface of the solid is approximated by adjoining

triangles. The representation is not exact, but can

be refined to any desired level of precision. By

Stoke's theorem, any quantity that can be

expressed by an integration of a well—behaved

function over the volume of a solid can also be

expressed by an integration of a related function

over the solid's surface. So, for a given mass

distribution, it is only necessary to know the surface of the solid in order to do mass properties calculations. Representations such as this are the heart of Finite Element Modelling (FEM), and various sophisticated software packages are also available to perform analysis on FE models. However, sometimes a custom application may be preferable. Since FEM is widely used, CAD packages commonly support the extraction of FE models from their solids, making the creation of these models easy to accomplish. Once created, the data for the FE model can be made available to other applications by exporting it to a text file. Although analysis packages exist that can handle triangulated solids, very little information [1][2][3] is publicly available on how the analysis is done. This article attempts to fill this hole by developing the necessary formulas and procedures.

For the author, the genesis of this article was a new routine for simulating the ditching of an aircraft in water. The routine worked by tracking the movement of water as it flowed into various parts of the aircraft. I originally attempted to craft a Catia macro, but quickly ran into problems. The routine required splitting solids by planes representing the water surface. Regularly, Catia would encounter errors in attempting the splits. I had to add special handling to work around these errors by estimating the results. When I finally produced a working program, it took over 8 hours to produce a very coarse simulation. And to my surprise, Catia had filled over 12 gigabytes of virtual memory, forcing me to reboot. It was clear that another approach would be needed to make this simulation viable. Rather than licensing and learning an existing FEM package, which might have its own computation overhead issues, I chose to program it on my own.

I would like to express my appreciation to Patrick Brown and especially to Victor Graham, who assisted me in the preparation of this paper.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

Close

The introduction of solid modelling in Computer—Aided Design (CAD) tools has proven to be a tremendous boon to weight engineering. Analysis of the solid models provides weight, center of gravity, and inertia data with an ease and precision undreamt of by earlier generations. However, CAD packages such as Dassault's Catia and SolidWorks are designed for a wide range of applications. As a result, the models are highly complex and even simple operations require a significant amount of resources. This can make sophisticated weights analyses slow and unwieldly, and occasionally prone to error.
Alternative means of representing solid objects
can address these problems. One of the simplest
representations of a solid is by triangulation: the
surface of the solid is approximated by adjoining
triangles. The representation is not exact, but can
be refined to any desired level of precision. By
Stoke's theorem, any quantity that can be
expressed by an integration of a well—behaved
function over the volume of a solid can also be
expressed by an integration of a related function
over the solid's surface. So, for a given mass
distribution, it is only necessary to know the surface of the solid in order to do mass properties calculations. Representations such as this are the heart of Finite Element Modelling (FEM), and various sophisticated software packages are also available to perform analysis on FE models. However, sometimes a custom application may be preferable. Since FEM is widely used, CAD packages commonly support the extraction of FE models from their solids, making the creation of these models easy to accomplish. Once created, the data for the FE model can be made available to other applications by exporting it to a text file. Although analysis packages exist that can handle triangulated solids, very little information [1][2][3] is publicly available on how the analysis is done. This article attempts to fill this hole by developing the necessary formulas and procedures.
For the author, the genesis of this article was a new routine for simulating the ditching of an aircraft in water. The routine worked by tracking the movement of water as it flowed into various parts of the aircraft. I originally attempted to craft a Catia macro, but quickly ran into problems. The routine required splitting solids by planes representing the water surface. Regularly, Catia would encounter errors in attempting the splits. I had to add special handling to work around these errors by estimating the results. When I finally produced a working program, it took over 8 hours to produce a very coarse simulation. And to my surprise, Catia had filled over 12 gigabytes of virtual memory, forcing me to reboot. It was clear that another approach would be needed to make this simulation viable. Rather than licensing and learning an existing FEM package, which might have its own computation overhead issues, I chose to program it on my own.
I would like to express my appreciation to Patrick Brown and especially to Victor Graham, who assisted me in the preparation of this paper.

Close

3600. Autonomous Mass Properties Tracking Database Attributes

Burt, Edd

In: 72nd Annual Conference, St. Louis, Missouri, pp. 30, Society of Allied Weight Engineers, Inc., Saint Louis, Missouri, 2013.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

@inproceedings{3600,

title = {3600. Autonomous Mass Properties Tracking Database Attributes},

author = {Edd Burt},

url = {https://www.sawe.org/product/paper-3600},

year = {2013},

date = {2013-05-01},

booktitle = {72nd Annual Conference, St. Louis, Missouri},

pages = {30},

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

address = {Saint Louis, Missouri},

abstract = {Gulfstream has made some interesting discoveries while deploying our autonomous mass properties tracking database. Design attributes long used in manually updated databases are not always conducive to the design of an autonomous self-updating database. This technical paper intends to explore some of the more enlightening challenges and elegant solutions discovered while making our transition to an autonomous database.

Many obstacles to the development of an autonomous database have been cited. When does the weight of a part get verified if there is no engineer calculating the weight? Even if a part's weight is 100% perfect; that does not stop the 100% error from just one missing or extra quantity of it in the database. How do we verify the drawing tree is complete when there is no engineer inputting it? Will the computer make up drawing numbers for multiple use assemblies? How will we input delta actual weights when some program might come along behind us and mess them up? Design groups don't use the five RP$#$8 material codes; so how does an RP$#$8 report get generated from an autonomous database? Can a computer input the half-dozen other codes we also need to generate reports? Will someone have to re-write our programs every time CATIA releases a new version? We track airplanes designed long before V5 or electronic drawing release and all our airplane data, old and new, need to be viewed together. So tell me, just how is some database going to do all that for us, and make me confident in the answers?

Gulfstream has faced and overcome these and many more challenges in the pursuit of an autonomous self-updating database. The tradition of storing the weight of a part was abandoned in favor of storing the bill of materials it is calculated from. Our database sums a part weight like an assembly weight. The exception is it totals materials and finishes instead of parts and sub-assemblies. Like back in school - the database shows its work. This simple design allows the database to record how much of the real materials and finishes, found in the drawing release system, build the weight. It does not pick from a list of made-up codes. Volumes, areas and lengths come from a database where they are stored for certification purposes by design groups. This is done in the drawing review and release processes. CATIA is not touched by Mass Properties software to calculate the weight of a part; so new releases do not affect our weight calculations. Drawing release materials and finishes are built from the five RP$#$8 materials. So densities are recorded in the database and RP$#$8 reports can be run from the database. This allows a simple database design where installations, assemblies, parts, materials, finishes and RP$#$8 materials are all stored together. Those many types of components, stored in a single component table, build up to total airplanes in a single bill of materials table. This is accomplished by coupling the Quantity field with a Unit of Measure field. The Unit of Measure contains units like 'Each', 'IN^3', 'IN^2' and 'IN'. Only five components are to have the unit of measure called 'Pound' - the five RP$#$8 materials - and they are the very bottom callout in every branch of every bill of materials. It was also discovered that all the codes used to report mass properties can be derived from a matrix of just two available attributes. Gulfstream hopes you find the advances we are making as exciting to you as they are to us when you read and study this technical paper.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

Close

Gulfstream has made some interesting discoveries while deploying our autonomous mass properties tracking database. Design attributes long used in manually updated databases are not always conducive to the design of an autonomous self-updating database. This technical paper intends to explore some of the more enlightening challenges and elegant solutions discovered while making our transition to an autonomous database.
Many obstacles to the development of an autonomous database have been cited. When does the weight of a part get verified if there is no engineer calculating the weight? Even if a part's weight is 100% perfect; that does not stop the 100% error from just one missing or extra quantity of it in the database. How do we verify the drawing tree is complete when there is no engineer inputting it? Will the computer make up drawing numbers for multiple use assemblies? How will we input delta actual weights when some program might come along behind us and mess them up? Design groups don't use the five RP$#$8 material codes; so how does an RP$#$8 report get generated from an autonomous database? Can a computer input the half-dozen other codes we also need to generate reports? Will someone have to re-write our programs every time CATIA releases a new version? We track airplanes designed long before V5 or electronic drawing release and all our airplane data, old and new, need to be viewed together. So tell me, just how is some database going to do all that for us, and make me confident in the answers?
Gulfstream has faced and overcome these and many more challenges in the pursuit of an autonomous self-updating database. The tradition of storing the weight of a part was abandoned in favor of storing the bill of materials it is calculated from. Our database sums a part weight like an assembly weight. The exception is it totals materials and finishes instead of parts and sub-assemblies. Like back in school - the database shows its work. This simple design allows the database to record how much of the real materials and finishes, found in the drawing release system, build the weight. It does not pick from a list of made-up codes. Volumes, areas and lengths come from a database where they are stored for certification purposes by design groups. This is done in the drawing review and release processes. CATIA is not touched by Mass Properties software to calculate the weight of a part; so new releases do not affect our weight calculations. Drawing release materials and finishes are built from the five RP$#$8 materials. So densities are recorded in the database and RP$#$8 reports can be run from the database. This allows a simple database design where installations, assemblies, parts, materials, finishes and RP$#$8 materials are all stored together. Those many types of components, stored in a single component table, build up to total airplanes in a single bill of materials table. This is accomplished by coupling the Quantity field with a Unit of Measure field. The Unit of Measure contains units like 'Each', 'IN^3', 'IN^2' and 'IN'. Only five components are to have the unit of measure called 'Pound' - the five RP$#$8 materials - and they are the very bottom callout in every branch of every bill of materials. It was also discovered that all the codes used to report mass properties can be derived from a matrix of just two available attributes. Gulfstream hopes you find the advances we are making as exciting to you as they are to us when you read and study this technical paper.

Close

3556. Composite Tank Structure Dynamics Modeling Based On Finite Particles

Baeten, André

In: 71st Annual Conference, Bad Gögging, Germany, pp. 23, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

3559. Fuel Mass Properties Calculation with CATIA V5

Funk, Ralf

In: 71st Annual Conference, Bad Gögging, Germany, pp. 21, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 11. Weight Engineering - Aircraft Estimation, 12. Weight Engineering - Computer Applications

@inproceedings{3559,

title = {3559. Fuel Mass Properties Calculation with CATIA V5},

author = {Ralf Funk},

url = {https://www.sawe.org/product/paper-3559},

year  = {2012},

date = {2012-05-01},

booktitle = {71st Annual Conference, Bad Gögging, Germany},

pages = {21},

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

address = {Bad Gögging, Germany},

abstract = {Complex aircraft tank geometries due to challenging requirements are designed nowadays using CAD allowing analysis in a concise and cheap way. For fuel mass properties calculation inside CATIA V5 a corresponding feature has to be provided via fuel macro. 

This programme can be used in the various design and development phases of an aircraft. Hence this tool is qualified for analysis of simple cuboids in the Pre-Draft as well as positioned and optimised tank geometries with integrated pumps or pipes in the Pre-Design-Phase, Product-Design-Phase or In-Service-Phase. 

Fuel mass properties are essential for aircraft moments of inertia (MOI) determination, flight performance (Flight Control System) and mission performance evaluation. 

Processing with CATIA V5 is possible for CAD-solids, which are designed in the CATIA V4/ V5 environment or having a compatible file format. Before starting the analysis it is necessary to install the basic settings and to prepare the files with a powercopy providing the CAD-model with various parameters and geometry, thus the user of this programme requires a basic knowledge of CATIA V5. 

This paper gives an overview to run the fuel macro for individual tanks or tank groups for various configured fuel rundown sequences. The simplification of internal tank geometry is compensated by a feature of the tool which provides fuel density variation. Further input parameters are the flight attitude with individual air space and unusable fuel. 

The Log-File contains apart from fuel mass properties of tank geometries the input parameters and more detailed information for interpretation of results.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

Close

3560. Dummy Optimization Regarding Mass Properties for Shaker Test and Flight Test

Clermont, Jürgen

In: 71st Annual Conference, Bad Gögging, Germany, pp. 45, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, 30. Miscellaneous

@inproceedings{3560,

title = {3560. Dummy Optimization Regarding Mass Properties for Shaker Test and Flight Test},

author = {Jürgen Clermont},

url = {https://www.sawe.org/product/paper-3560},

year  = {2012},

date = {2012-05-01},

booktitle = {71st Annual Conference, Bad Gögging, Germany},

pages = {45},

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

address = {Bad Gögging, Germany},

abstract = {For shaker- and flight test in aircraft development, replacement bodies with similar physical properties as the real body (like a black box) have to be created. 

A body like this is called DUMMY and the meant properties are mass, center of gravity in x-, y- and z-direction, as well as inertias (in total 10 components). 

These dynamic tests are essential to generate adequate mountings/bearings or to reproduce the real behaviour of an airplane or a subsystem in flight. 

Dummies are used when the exact part is not (yet) available or the part is too expensive to destroy it by testing. 

To produce dummies, results within 10% deviation (per component) are necessary for dynamic similarity. By trial and error it is possible to create such a body, but it is either time intensive or the precision is not very high. The higher the accuracy of all 10 components of mass properties, the better is the similarity and the better will be the results for mountings and bearings. 

Based on an inertia program with shape code calculation capability, an iterative process to create a dummy was developed. By variation of at least 4 bodies it is possible to get first results in all components. Up to a variation of 8 bodies and more is possible. To get good results in acceptable time and effort, a well-thought-out code is essential. 

This iteration process produces a lot of data, but with effective code and modern computing hardware it is possible to create more than 100.000 iterations per hour, where one of it is a best fit within 5% deviation or better.},

keywords = {12. Weight Engineering - Computer Applications, 30. Miscellaneous},

pubstate = {published},

tppubtype = {inproceedings}

}

Close

3574. Updated SumMassProps A Comprehensive Excel-Based Mass Properties Solution

Zimmerman, Robert L.

In: 71st Annual Conference, Bad Gögging, Germany, pp. 13, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

@inproceedings{3574,

title = {3574. Updated SumMassProps A Comprehensive Excel-Based Mass Properties Solution},

author = {Robert L. Zimmerman},

url = {https://www.sawe.org/product/paper-3574},

year  = {2012},

date = {2012-05-01},

booktitle = {71st Annual Conference, Bad Gögging, Germany},

pages = {13},

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

address = {Bad Gögging, Germany},

abstract = {In May 2003 at the Society of Allied Weight Engineers International Conference on Weight Engineering in New Haven Connecticut, the author presented the original release version of SumMassProps as part of SAWE Paper 3310. SumMassProps is an Excel-based add-in that provides within Microsoft Excel a comprehensive set of mass properties functions to sum component mass properties. In the intervening years, over 100 interface improvements, bug fixes, speed enhancements, and additional functionality changes have been made to this add-in. The resulting version of SumMassProps is now a fully functional mass properties database manipulator using modern programming and error prevention techniques. Many of the improvements specifically address ease-of-use and error proofing the functionality of the add-in. 

The present version of SumMassProps now creates the function prototypes for each of its menu-driven functions; performs full coordinate and inertia rotations; determines Principal Inertia Matrices and the corresponding Direction Cosine Matrix to arrive at the principal inertias; and incorporates the lessons of SAWE Paper 3360 depicting the correct derivation of mass property uncertainties. Additional functionality includes one click formula matrix filling; utilization of multiple mass properties formats; determination of ballast weights for dynamic balance; specific unit conversions; and the capability to undo any of SumMassProps' built-in functions. 

SumMassProps as it currently stands is what the author envisioned this comprehensive solution to be when this odyssey began. The functionality and user interface makes Version 9 a desirable tool in the Mass Properties Engineer's arsenal.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

Close

3576. Automation Methods Of Aircraft Weight Activities

Isikdogan, O; Kiper, T; Unay, E; Gurak, D.

In: 71st Annual Conference, Bad Gögging, Germany, pp. 12, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

@inproceedings{3576,

title = {3576. Automation Methods Of Aircraft Weight Activities},

author = {O Isikdogan and T Kiper and E Unay and D. Gurak},

url = {https://www.sawe.org/product/paper-3576},

year  = {2012},

date = {2012-05-01},

booktitle = {71st Annual Conference, Bad Gögging, Germany},

pages = {12},

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

address = {Bad Gögging, Germany},

abstract = {This paper presents the optimization and automation efforts for aircraft weight activities in aircraft design projects. Those weight activities involve monitoring the aircraft total weight and inertia, evaluation of weight breakdown and calculation of mass and inertia distribution. The results are then submitted to project management, flight mechanics, structural analyses and design groups. The methods and tools developed for this study provide less time-consuming process and more accurate results. The mass and inertia properties of the aircraft are subject to change progressively during an aircraft design process. The challenge is to monitor those changes and report their effects instantly. An integrated system is designed to make all those weight activities to be automatically performed and controlled. The system works simultaneously with Computer Aided Design (CAD) software and provides real time monitoring of weight properties and weight breakdown of aircraft. In addition, this system helps the weight data to be more accessible and updated. Also, mass and inertia distribution of aircraft is evaluated in this integrated system as the mass model, consisting of lumped masses, required from related analysis groups. The most common method for this mass distribution calculation is slicing functions of CAD software. However, the methods developed for the weight activities help overcome the inefficiencies of solely depending on CAD software for large assemblies consisting of thousands of detailed parts, sub-assemblies, equipments, harness, systems etc. These tools are designed to be used in all phases of the aircraft design process, from conceptual to detailed design. In conclusion, the integrated system developed for the automation of weight activities is mentioned and compared to common methods used in industry. The advantages and impact of those new methods and tools to aircraft design are presented.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

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3590. Optimized Mass Matrices Business Process

Zawadzki, Radoslaw; Hiersig, Michael

In: 71st Annual Conference, Bad Gögging, Germany, pp. 17, Society of Allied Weight Engineers, Inc., Bad Gögging, Germany, 2012.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

3530. Confidence Of Mass Properties (COMP) Tool

Smith, James

In: 70th Annual Conference, Houstion, Texas, pp. 14, Society of Allied Weight Engineers, Inc., Houston, Texas, 2011.

Abstract | Buy/Download | BibTeX | Tags: 07. Section Properties, 12. Weight Engineering - Computer Applications

3531. Weight Data Management for Completion of Corporate Jets

Mitry, Ragaa

In: 70th Annual Conference, Houstion, Texas, pp. 18, Society of Allied Weight Engineers, Inc., Houston, Texas, 2011.

Abstract | Buy/Download | BibTeX | Tags: 11. Weight Engineering - Aircraft Estimation, 12. Weight Engineering - Computer Applications

@inproceedings{3531,

title = {3531. Weight Data Management for Completion of Corporate Jets},

author = {Ragaa Mitry},

url = {https://www.sawe.org/product/paper-3531},

year = {2011},

date = {2011-05-01},

booktitle = {70th Annual Conference, Houstion, Texas},

pages = {18},

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

address = {Houston, Texas},

abstract = {Cabin Completion Engineering is a very crucial phase of the high-end business jet aircraft design. The interior of the aircraft, including all of its customer-oriented and advanced technology, is perhaps one of the most important factors in the decision-making process of a potential corporate aircraft buyer. Indeed, range, performance and operating costs are factors, but the customer is also buying privacy and functionality. With this mindset, the Original Equipment Manufacturer is prone to hold nothing back - to 'spare no expense' - in the development of a state-of-the-art aircraft interior.

In order to protect vehicle performance, the weight and center of gravity of the completions must be maintained. Completions engineering is no different when it comes to the need to properly identify, sort, and budget weights, all while correlating Computer-Aided Design models to the proper installations. This task can be somewhat automated using contemporary design tools and appropriate software.

This paper discusses how to build a matrix to track and manage the completion development weight. The matrix is a depletion schedule that sets the limits for each installation and/or assembly. Whenever a weight exceeds the preliminary estimated weight, it will be immediately flagged red, bringing the attention of the designers to a potential problem. The estimated weight is based on historical data adjusted to the new aircraft. The depletion schedule matrix allows the quick generation of tables and charts at any given time during the program, drastically reducing the effort required to compile and create weight status reports.

The matrix calculations output graphs can be interpreted to ensure that the weight status of the detail is not only dependent on the weight recorded but its developmental maturity. Also, it is helpful in determining whether there are some areas that are sufficiently reduced in weight allowing for the reallocation of weight budget - and its CG location - to another area or if weight savings can result in improved aircraft performance.

This data can then be used by the engineer and program to quickly pinpoint weight-critical design areas.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

Close

Cabin Completion Engineering is a very crucial phase of the high-end business jet aircraft design. The interior of the aircraft, including all of its customer-oriented and advanced technology, is perhaps one of the most important factors in the decision-making process of a potential corporate aircraft buyer. Indeed, range, performance and operating costs are factors, but the customer is also buying privacy and functionality. With this mindset, the Original Equipment Manufacturer is prone to hold nothing back - to 'spare no expense' - in the development of a state-of-the-art aircraft interior.
In order to protect vehicle performance, the weight and center of gravity of the completions must be maintained. Completions engineering is no different when it comes to the need to properly identify, sort, and budget weights, all while correlating Computer-Aided Design models to the proper installations. This task can be somewhat automated using contemporary design tools and appropriate software.
This paper discusses how to build a matrix to track and manage the completion development weight. The matrix is a depletion schedule that sets the limits for each installation and/or assembly. Whenever a weight exceeds the preliminary estimated weight, it will be immediately flagged red, bringing the attention of the designers to a potential problem. The estimated weight is based on historical data adjusted to the new aircraft. The depletion schedule matrix allows the quick generation of tables and charts at any given time during the program, drastically reducing the effort required to compile and create weight status reports.
The matrix calculations output graphs can be interpreted to ensure that the weight status of the detail is not only dependent on the weight recorded but its developmental maturity. Also, it is helpful in determining whether there are some areas that are sufficiently reduced in weight allowing for the reallocation of weight budget - and its CG location - to another area or if weight savings can result in improved aircraft performance.
This data can then be used by the engineer and program to quickly pinpoint weight-critical design areas.

Close

3534. Mass Properties Requirements For Marine Design Software

Titcomb, Alan; Carter, Keith; Moore, Ronnie

In: 70th Annual Conference, Houstion, Texas, pp. 18, Society of Allied Weight Engineers, Inc., Houston, Texas, 2011.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, Marine

3495. Using PHP/MySQL to Manage Potential Mass Impacts

Hager, I. Benjamin

In: 69th Annual Conference, Virginia Beach, Virginia, pp. 20, Society of Allied Weight Engineers, Inc., Virginia Beach, Virginia, 2010.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications, 26. Weight Growth

@inproceedings{3495,

title = {3495. Using PHP/MySQL to Manage Potential Mass Impacts},

author = {I. Benjamin Hager},

url = {https://www.sawe.org/product/paper-3495},

year  = {2010},

date = {2010-05-01},

booktitle = {69th Annual Conference, Virginia Beach, Virginia},

pages = {20},

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

address = {Virginia Beach, Virginia},

abstract = {This paper presents a new application using commercially available software to manage mass properties 

for spaceflight vehicles. PHP/MySQL (PHP: Hypertext Preprocessor and My Structured Query 

Language) are a web scripting language and a database language commonly used in concert with each 

other. They open up new opportunities to develop cutting edge mass properties tools, and tools for the 

management of potential mass impacts (threats and opportunities). The paper begins by providing an 

overview of the functions and capabilities of PHP/MySQL. The focus of this paper is on how 

PHP/MySQL are being used to develop an advanced 'web accessible' database system for identifying 

and managing mass impacts on NASA's Ares I Upper Stage program, managed by the Marshall Space 

Flight Center. To fully describe this application, examples of the data, search, and view pages are 

provided to show, not only the function, but the security, ease of use, and simplicity of this new 

application. 

The premise behind this paper is that PHP/MySQL are software tools that are easy to use and readily 

available for the development of cutting edge mass properties applications. These tools are capable of 

providing 'real-time' searching and status of an active database, automated report generation, and other 

capabilities to streamline and enhance mass properties management application. By using 

PHP/MySQL, proven existing methods for managing mass properties can be adapted to present-day 

information technology to accelerate mass properties data gathering, analysis, and reporting, allowing 

mass property engineers, and the management they support, to keep pace with today's fast-pace design 

and development processes.},

keywords = {12. Weight Engineering - Computer Applications, 26. Weight Growth},

pubstate = {published},

tppubtype = {inproceedings}

}

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3498. Introduction of Mass Management Software - Our experiences

Rosenberger, Claudia

In: 69th Annual Conference, Virginia Beach, Virginia, pp. 16, Society of Allied Weight Engineers, Inc., Virginia Beach, Virginia, 2010.

Abstract | Buy/Download | BibTeX | Tags: 12. Weight Engineering - Computer Applications

@inproceedings{3498,

title = {3498. Introduction of Mass Management Software - Our experiences},

author = {Claudia Rosenberger},

url = {https://www.sawe.org/product/paper-3498},

year  = {2010},

date = {2010-05-01},

booktitle = {69th Annual Conference, Virginia Beach, Virginia},

pages = {16},

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

address = {Virginia Beach, Virginia},

abstract = {From the design to the in-service phase of products, managing mass properties is a running 

challenge. High technology products are becoming more and more complex, so time and 

resources necessary for a proper handling of mass properties are increasing considerably. 

Standard software products like MS Excel are meeting the limits of its capacities facing this 

request. 

In August 2009, EADS Germany decided to introduce the mass management system M3 of 

usb GmbH for all military projects like Tornado, Eurofighter and all future projects. 

This paper is written in cooperation of usb and EADS and will report our common 

experiences during the introduction of this software. The main points are: 

What are the reasons for EADS to choose M3? 

What are the main improvements compared to previous situation? 

What are the main steps and milestones during the introduction? 

These questions are answered in detail by this paper, describing the features of M3 and how 

these features support EADS Mass Properties department to make its work easier and more 

effective. Different projects in different production phases from early design up to in service 

phase are managed by M3. The paper shows, how these different requirements and algorithms 

are handled by the software. 

At the moment M3 replaces former software tools and is used as a standalone system. 

However, it is planned to apply its full capabilities as an open system to integrate other 

applications into the mass management processes. Therefore, data exchange with CATIA and 

the PLM System will be installed in the next steps. Automation of workflow avoids manual 

data entry, increases productivity and ensures quality of work.},

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

pubstate = {published},

tppubtype = {inproceedings}

}