SAWE Technical Papers

@inproceedings{3724,

title = {3724. Methods and Processes for Robust Mass Properties Management in the Automotive Industry with a Main Focus on Mass Uncertainties},

author = {Marcus Stegmiller and Albert Albers},

url = {https://www.sawe.org/product/paper-3724},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {18},

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

address = {Norfolk, Virginia},

abstract = {The mass of an automobile represents a crucial parameter for development because it influences the design of the automobile as well as decisive purchasing characteristics such as driving dynamics, fuel consumption and range. The dimensioning effect of the automobile mass has so far led to the definition of challenging and fixed mass targets. Since the automotive industry is characterized by high cost pressure, product complexity (e.g. due to modular and platform strategies, supplier chains and manufacturing constraints), increasing product range and volatile boundary conditions (e.g. due to regulation) automobile masses are permanently changing during development. This can no longer be robustly controlled by fixed mass targets. In practice, this often results in late missed mass targets, which lead to heavy and costly countermeasures.Therefore, the specific requirements of the automotive industry demand a highly developed mass properties management (MPM). This paper presents such a MPM through a practice oriented and flexible methodology. The methodology is based on existing MPM approaches (including SAWE practices) and adapted to the automotive industry. It consists of a mass target framework enriched by a mass prognosis tool, an economic evaluation method for automobile mass scenarios, methods for identifying lightweight design measures and a phase-adequate determination of mass uncertainties. The methods are strongly based on the approach of PGE - Product Generation Engineering, which says that products are developed in generations and therefore information can be reused.This paper deals in particular with the determination of mass uncertainties. Five types of mass uncertainties are identified, compared to the SAWE mass change codes and quantified on the basis of real automobile projects. Since the uncertainties provide transparency on mass potentials and risks, a suitable approach corridor for mass target guidance is derived from them. Furthermore, approaches are presented how mass uncertainties can be interpreted as quality indicators of current MPM processes and how the entire method can be automated. Finally, the mentioned methods above are combined to form a process to derive and manage robust mass targets, buffers and design masses for automobile development.},

keywords = {31. Weight Engineering - Surface Transportation},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3721,

title = {3721. A Weight and Center of Gravity Instrument for Measuring Manned Spacecraft},

author = {Dan Otlowski},

url = {https://www.sawe.org/product/paper-3721},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {23},

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

address = {Norfolk, Virginia},

abstract = {Rocketry dynamics equations prescribe that the mass properties of spacecraft, particularly the spacecraft's mass and center of gravity (CG), be carefully choreographed throughout the launch, mission execution, and recovery stages. Mission design carefully selects CG locations for each of the spacecraft modules alone and in combinations, making CG verification an important step toward ensuring mission success. Measuring the CG of large spacecraft presents many of the typical problems associated with measuring CG of smaller objects. Some of these issues are commonly: constructing a measuring system with known geometry, maintaining the repeatability of said geometry under a wide array of load conditions, selecting force transducers with sensitivity appropriate to the verification tolerance, preserving that sensitivity throughout the measurement, and devising a method to relate the spacecraft's datum to the instrument's datum. A purpose-built, mass properties measurement solution that addresses all of these issues is the topic of this paper. In this paper, we will describe the form of the instrument, detail enabling technologies, explain performance drivers, and summarize our results.},

keywords = {09. Weighing Equipment},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3720,

title = {3720. A Practical and Proactive Way of Managing Weight & Center of Gravity Uncertainty Using the Successive Principle},

author = {Runar Aasen},

url = {https://www.sawe.org/product/paper-3720},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {18},

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

address = {Norfolk, Virginia},

abstract = {One of the challenges in mass properties is how to handle the uncertainty in an early stage estimate of weight and center of gravity (CG) and its impact throughout the life of the project. Risk is sometimes defined as the product of consequence multiplied by uncertainty, and for many shipbuilding projects the consequence of missing the mark on either the weight or CG can be dramatic. That makes reducing uncertainty essential to avoiding a high-risk project.Dr. Steen Lichtenberg started as early as the 1970's to develop a method for proactive management of uncertainty using the successive principle. The method is a practical way to manage opportunities and risk. The underlying philosophy states that realism in forecasts requires a qualitative phase as well as a quantitative phase. In the qualitative phase, an analysis group of people should be established, while the quantitative phase should establish a basic structure of main items, followed by a systematic detailing process and an action plan.While the method typically handles uncertainties related to the economics of large projects, this paper will look at how the principles and processes involved can be applied to the weight and CG challenges during ship design and construction. A general introduction to the successive principle will be given, the basic applications will be presented, and discussions and examples of use cases will be included. The goal is to add another tool to the toolbox of the weight engineer to help secure successful projects.},

keywords = {21. Weight Engineering - Statistical Studies},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3718,

title = {3718. Center of Buoyancy and Center of Gravity Measurement of a Submersible Vehicle},

author = {James Blair},

url = {https://www.sawe.org/product/paper-3718},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {16},

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

address = {Norfolk, Virginia},

abstract = {Stability of submersible vehicles is dependent on the relationship between the center of gravity and center of buoyancy locations on the object. Improper relationships between the two can reduce performance and adversely affect the mission goals of the vehicle. Measuring these values can reveal variations from the designed values that may have been introduced during the manufacturing or assembly process. These values can also change in modular submersible vehicles which allow swapping or modifying components based on the needs of their mission. Errors associated with an improper relationship may not arise until sea testing, which may lead to the need for vehicle disassembly in order to shift or change ballast weights of the submersible.This paper examines a measurement system designed to measure the center of gravity and the center of buoyancy of a submersible object using a hanging weight and center of gravity instrument. The method demonstrated is applicable for vehicles ranging from a few pounds to upwards of 15 tons. With proper fixturing, the machine is capable of measuring center of buoyancy and center of gravity in all 3 axes, which can help determine lateral, longitudinal, and directional stability of a part. This paper outlines a process for measuring submersible vehicles (with negative or slightly positive buoyancy) to determine weight, buoyant force, center of gravity, and center of buoyancy.},

keywords = {21. Weight Engineering - Statistical Studies, Marine},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3717,

title = {3717. Evaluating a CoG Envelope Using a Probabilistic Approach},

author = {Robert J. Hundl},

url = {https://www.sawe.org/product/paper-3717},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {15},

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

address = {Norfolk, Virginia},

abstract = {In the Energy and Chemicals Construction Industry, many onshore projects are using modular construction. This type of construction requires that the modules be transported from the fabrication yard to the project site. The fabrication yard may be distant from the project site, thus requiring a combination of ocean transportation and land transportation. To verify the design, the structural analysis uses a given design weight limit and center of gravity (CoG) envelope for the various modes of transportation. The size of the CoG envelope can influence the strengthening requirements for the structure during the transportation phases. CoG envelopes are typically set as a percentage of the module length and width. In special cases, a probabilistic approach could be used to reduce the typical CoG envelope size for reducing the amount of strengthening requirements while also quantifying the risk to the project for reducing the size of the CoG envelope.},

keywords = {21. Weight Engineering - Statistical Studies, 35. Weight Engineering - Offshore, Marine},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3716,

title = {3716. A Methodology of Determining Parametric Equations from Data with a Worked Example},

author = {David Laurence Hansch},

url = {https://www.sawe.org/product/paper-3716},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {25},

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

address = {Norfolk, Virginia},

abstract = {The method of using multiple regression to determine parametric weight equations is discussed. A worked example based on 1930s to 1940s US submarines is given. In an appendix, the resulting equations are used for comparative naval architecture with contemporary British and German designs.},

keywords = {21. Weight Engineering - Statistical Studies},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3715,

title = {3715. Negligible Weight Quantification for Surface Ship Weight Surveys},

author = {Greg Roach},

url = {https://www.sawe.org/product/paper-3715},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {12},

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

address = {Norfolk, Virginia},

abstract = {Shipboard weight surveys are routinely performed for surface vessels across the spectrum of marine industries from small pleasure craft to large surface combatants. These surveys are typically part of a vessel's stability test (weight survey & inclining experiment) usually required as part of the vessel's delivery/acceptance or during its service life to confirm the safety of the vessel and/or crew/passengers has not been compromised from post-delivery modifications or inevitable weight & KG growth. These stability tests may take a few days to a few weeks, with a large portion of the effort attributed to the weight survey itself. Further, a large portion of the survey consists of inventorying smaller items which typically constitute a relatively small portion of the overall weight nor may have any appreciable impact to the overall results of the stability test.To date (to the author's knowledge), no official guidance or recommendation(s) exists on what or how to quantify as negligible weight(s) for the purposes of a weight survey. This guidance, if available, may reduce the time required for survey and save considerable time and resources without appreciably changing the end result and/or conclusion.With limited availability/diversity of actual ship survey data, the analysis will focus on the required precision of the stability test based on accepted requirements documentation. This analysis will consider the size of the vessel which directly impacts the design's sensitivity to weight, as well as the practicalities associated with the existing practices of shipboard surveys such as availability of the vessel or qualified personnel. In addition, industry guidance on human engineering design will be used to establish 'rules of thumb' for determining item weights and/or their potential impact to the results to aid in shipboard surveys.},

keywords = {25. Weight Engineering - System Estimation, Marine},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3714,

title = {3714. Weight and Design Data for World War II - Era United States Military Aircraft},

author = {Dudley M Cate},

url = {https://www.sawe.org/product/paper-3714},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {39},

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

address = {Norfolk, Virginia},

abstract = {Sources of weight data for World War II-era U.S. military aircraft recently were located in the U.S. Federal Archives. The data is to the level of detail found in a short group weight statement. To the author's knowledge, the weight data has not heretofore been publicly available. It was felt to be worthwhile to electronically tabulate the data and then make it available via the SAWE.The paper begins with an introduction that identifies the groundrules and constraints associated with the material in the paper. The rest of the paper presents both weights and weight fractions for the weight empty groups and the useful load items for a wide range of aircraft. The aircraft are arranged by type (fighter, bomber, etc.), military service (Army or Navy), and, in general, chronologically by model (P-40, P-39, P-47, etc.). Also included for each aircraft are the weights of alternate fuel and payload items. For most of the aircraft, the weight empty and gross weight obtained from the archived data are validated by comparing them with weights found in open sources. Values for some of the weight-related design attributes for each aircraft are provided. Accompanying this data is a brief discussion of weight-related considerations for each aircraft.The large number of aircraft for which data are included presents a clear picture of how group and total weights and weight fractions changed with time (e.g., from the pre-war Boeing P-26 to the post-war Lockheed P-80). The data also permit comparison of the differences between, for example, radial-engined and in-line-engined fighters, between Army and Navy fighters, between Navy dive bombers and torpedo bombers, and between biplane and monoplane trainers, to mention just a few of the possibilities.},

keywords = {10. Weight Engineering - Aircraft Design, 30. Miscellaneous},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3713,

title = {3713. Inspiring Future Mass Properties Engineers: NASA's Orion Ascent Abort-2 Flight Test and the Office of Stem Engagement},

author = {Anne Weiss and Rosemary L. Smith},

url = {https://www.sawe.org/product/paper-3713},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {32},

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

address = {Norfolk, Virginia},

abstract = {In response to the National Academy of Engineering's 2004 report, Educating the Engineer of 2020, and two subsequent National Science Foundation research studies examining effective strategies for educating the next generation of engineers, U.S. K-12 general education and undergraduate engineering programs have undergone numerous reforms. Instead of concentrating solely on technical knowledge (e.g., statics, mechanics, fluid dynamics, etc.), formal and informal teachers should now also enhance their instructional practices through interdisciplinary, interactive and immersive experiences that meet students where they are and equip them with 21st-century workforce skills such as collaboration, ability to consider societal and global contexts, and technical writing and public speaking. To support educators' efforts and NASA's Orion Ascent Abort-2 flight test, education specialists in the Langley Research Center's Office of STEM Engagement partnered with the Flight Test Management and Public Affairs Offices to create a line of instructional products that help teachers and students to make connections between NASA-unique assets, STEM content, and careers in mass properties engineering. Using a mixed-methods research design, this paper documents initial results of that unique, highly collaborative interdisciplinary process: an educator professional development digital badge and a flipped classroom unit with standalone video interview. Although full-scale assessment has yet to occur, preliminary data indicates that responses from students, educators and the public to these resources have been overwhelmingly positive. Future ideas include webinars targeting K-12 teachers as well as virtual-reality technology 'field trips' for students - additional tools for achieving the goal of inspiring tomorrow's mass properties engineers.},

keywords = {30. Miscellaneous},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3711,

title = {3711. A Century of Submarine Mass Properties},

author = {David Tellet},

url = {https://www.sawe.org/product/paper-3711},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {41},

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

address = {Norfolk, Virginia},

abstract = {This paper takes a chronological look at submarine milestones during the last century and discusses how the evolution of submarine design affected mass properties engineering including weight control processes, management of mass properties, technical authority, and stability and buoyancy requirements. The paper discusses how the movement of submarine design from boats that can submerge to submarines designed for near constant submergence changed performance requirements including mass property limits. It discusses how the Cold War and nuclear power influenced submarine design and how this affected mass properties requirements and practices including deliberate margin depletion and reduction in service life margins. The paper includes some thoughts on future submarine designs and how those may affect mass property management practices.},

keywords = {Marine},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3710,

title = {3710. Application of the Law of Propagation of Uncertainties to a Weight and CG},

author = {Anjie Emmett},

url = {https://www.sawe.org/product/paper-3710},

year  = {2019},

date = {2019-05-01},

booktitle = {78th Annual Conference, Norfolk, VA},

pages = {49},

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

address = {Norfolk, Virginia},

abstract = {In order to quantify potential errors in a measurement system, the uncertainties of all measurement sources must be combined to generate a total system uncertainty. This quantified measurement system uncertainty may be used as a decision-making tool to determine the required accuracy of measurement devices such as load cells, scales, and laser trackers.For NASA's Ascent Abort 2 (AA-2) Flight Test, such an uncertainty quantification was performed to ensure that the Ground Support Equipment (GSE) designed to measure the mass and center of gravity (CG) of a Crew Module (CM) would meet the accuracy requirements set forth by the program. The uncertainties of the load cells used were combined with the laser tracker system's positional uncertainty to determine the overall measurement system uncertainty, which met program requirements.},

keywords = {15. Weight Engineering - Missile Estimation, 21. Weight Engineering - Statistical Studies},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3708,

title = {3708. SAWE RP-8 Past, Present and Future},

author = {Paul Kachurak},

url = {https://www.sawe.org/product/paper-3708},

year  = {2018},

date = {2018-05-01},

booktitle = {77th Annual Conference, Irving, Texas},

pages = {10},

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

address = {Irving, Texas},

abstract = {SAWE Recommended Practice (RP) A-8 has been used in essence for the format of military aircraft mass properties for decades. RP A-8 forms the basis for effective communication within the mass properties community.The paper revisits the genesis of RP A-8, its importance, and makes recommendations for potential future changes to the RP in order to accommodate future aircraft design architectures.},

keywords = {17. Weight Engineering - Procedures},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3703,

title = {3703. DRIFT: Drone-Rover Integrated Fire Tracker System},

author = {Nur Rashid and Syaminmah Deen and Amber Bishop and Daniel Collins and Brandon Cott and Samantha Growley and Pierce Lieberman and Kelsey Owens and Anthony Stanco and Matthew Stoffle and Nick Wiemelt},

url = {https://www.sawe.org/product/paper-3703},

year  = {2018},

date = {2018-05-01},

booktitle = {77th Annual Conference, Irving, Texas},

pages = {11},

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

address = {Irving, Texas},

abstract = {Wildfire reconnaissance and mitigation efforts are a primary concern for the United States Department of the Interior and National Forest Service. The critical consequences of climate change are becoming more prevalent with longer fire seasons throughout the Western United States [1]. The fire seasons are characterized by hotter and drier conditions, allowing for a wildfire to easily start and rapidly spread with the potential to burn millions of acres and cause billions of dollars in property loss. The National Forest Service (NFS) predicts that it will spend over half of its budget in the fight against wildfires within the next decade [2]. Wildfires can have devastating impacts on communities, ecosystems and wildlife, but also pose a dangerous threat to the fire fighters responsible for their mitigation and containment. A Mother Rover-Child Drone Firetracker System will assist firefighters by traveling to locations at risk of wildfire and gather environmental data which it then transmits back to the designated ground station. This provides information on a fire's intensity, severity, and extent while firefighters remain a safe distance away from the threat. Team DRIFT is a group of eleven undergraduate Aerospace Engineering Sciences students at the University of Colorado Boulder currently developing the Mother-Rover for the Firetracker System with the purpose to secure and carry the Child Drone (Unmanned Aerial Vehicle) to a desired location of interest. The development of this Mother- Rover involves integrating the hardware and software of the already completed Child Drone and Landing Platform. The Mother Rover, approximately 46.3 by 58.9 inches, weighing 450 lbs and driven by a remote operator, is capable of traversing rough terrain, defined by small gravel, fine dirt, and slopes up to 20 degrees. Due to the image recognition system utilized on the landing platform for the autonomous landing of the Child Drone, the landing platform must be level to within 3.5 degrees in order for the child drone to safely take off and land. Therefore, the Mother Rover utilizes an internal leveling jack system to level in the landing platform to within 3.5 degrees if the child drone is to be deployed on a slope. The considerable weight of the Mother Rover presents a unique engineering challenge as it must be capable of traversing over the defined rough terrain while also maintaining the security of the onboard Child Drone. The design solution for this Mother Rover and associated leveling system will be discussed in this paper.},

keywords = {Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3702,

title = {3702. Uncertainty Modelling in a Wing Weight Convergence Simulation Framework},

author = {T Ries and P Sartor and J Cooper and J Cheeseman},

url = {https://www.sawe.org/product/paper-3702},

year  = {2018},

date = {2018-05-01},

booktitle = {77th Annual Conference, Irving, Texas},

pages = {14},

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

address = {Irving, Texas},

abstract = {Weight is a key element in aircraft design, having a major influence on its performance and being a common factor to all disciplines involved in the decision making process, i.e. aero- dynamics, structural sizing, materials, loads, geometry, cost, manufacturing, etc. To ensure an optimal trade-off is achieved, alongside a smooth convergence to the desired final aircraft weight, it is essential to be able to model the aircraft weight estimation process throughout the design, including assessment of uncertainty and risk. Weight estimation processes and uncer- tainty analysis are well established bodies of literature. Yet, its unification into a framework that can deliver meaningful managerial information is a new research branch.This paper presents a new methodology for quantifying uncertainty and performing sensi- tivity studies on aircraft weight estimation. A framework has been developed that emulates the weight convergence corridor for an aircraft wing. It combines a traditional wing-box sizing method for primary weight with alternative methods for secondary weight. The alternative methods mimic the different phases of design in the aircraft development cycle. Maturity of design translates to the status of the information available, which translates to accuracy in the weight estimation method in use.This process incorporates uncertainty in the form of modelling the desired input parame- ters as probability density functions (PDFs). The uncertain input space may include wing and engine planform geometry, wing-box material properties, load cases, general aircraft weights and fuselage dimensions. Design features and aircraft components are correlated and there- fore an underlying dependency grid prevails. Combining the PDFs on the grid propagates the uncertainty towards an ultimate distribution of the total wing weight.This paper investigates the use of the framework developed for wing weight estimation by quantifying design sensitivities impact on wing weight. The methodology is demonstrated on a representative commercial jet airliner wing.},

keywords = {Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3696,

title = {3696. A Novel Approach for an Autonomous Weighing System through Fuselage Interface Loads},

author = {Oran Shachar},

url = {https://www.sawe.org/product/paper-3696},

year  = {2018},

date = {2018-05-01},

booktitle = {77th Annual Conference, Irving, Texas},

pages = {27},

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

address = {Irving, Texas},

abstract = {According to a N.A.L report, from May 2007 (G.W.H.van Es[ 4]), each year numerous aircraft accidents occur due to weight and balance issues, major factors in weight and balance accidents/incidents being errors in load sheet, cargo shifting, incorrect loading etc. This paper presents an ESL patented novel method and system for estimating an aircraft's weight while it is on the ground. Additionally, the system enables measuring the takeoff/landing weight profile, which includes information pertaining to weight/force as a function of time, including the time of contact with the ground. This enables various conditions such as heavy landing and the like to be identified.One of the main advantages of this development, over prior methods, is that this system measures loads above the landing gear, thus avoiding bias due to the flexibility of the landing gears. It also offers high repeatability of the measured load.The measurement subsystem includes sensors configured to measure a physical property (load/strain) at several locations near and/or at the fuselage interface with the landing gears. Such a sensor can be based on several technologies such as: strain gages, optical fibers (Bragg Gratings), load cells, etc.The specific solution and sensor implemented is a tailor-made design for each aircraft, taking into account the effect of the aircraft weight and desired sensitivity due to weight change on the results being measured.As part of the work done by ESL in developing the system, that for a given (existing) Hermes 900 fleet, an average of 1 flight hour can be saved.This paper presents the design and integration of such a system on ESL's Hermes 450 UAV, based on load cells. A proof-of-concept test was performed and is presented in this paper.The main test findings show, that the maximum deviation between the standard weighing procedure and ESL's system result is 0.6% at weight and 0.9% at COG.The conceptual methodology suggested here is still under development. Nevertheless, the integration of the sensor technology into the fuselage has its own promise to develop higher levels of safety of flight, while increasing the specific range of the aircraft.},

keywords = {09. Weighing Equipment},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3694,

title = {3694. Using Knowledge Analytics to Search and Characterize Mass Properties Aerospace Data},

author = {Jeffrey Cerro and Theodore Sidehamer and Dorthy Notarnicola},

url = {https://www.sawe.org/product/paper-3694},

year  = {2018},

date = {2018-05-01},

booktitle = {77th Annual Conference, Irving, Texas},

pages = {25},

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

address = {Irving, Texas},

abstract = {There is growing capability in the field of 'Big Data' and 'Data Analytics' which Mass Properties Engineers might like to take advantage of. This paper utilizes an implementation of the IBM Knowledge Analytics and Watson search capabilities to explore a corpus of material developed primarily with the interests of Mass Properties Engineers and vehicle concept developers at its forefront. The full collection of SAWE Technical Papers from 1939 thru 2015 is a major portion of the knowledge content. Additional aerospace vehicle design information includes metadata from AIAA (American Institute for Aeronautics and Astronautics), and INCOSE (International Council on Systems Engineering) as well as author provided personal search material. This data is processed with respect to certain expected content, data taxonomies and key words to become the core data in NASA Langley Research Center's 'Vehicle Analysis Analytics', IBM Watson Content. Processed data becomes the corpus of information which is interrogated to provide examples of finding data for mass regression analysis, technology impacts on MPE, mass properties control, standards, and other aspects of interest.},

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

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3692,

title = {3692. Aircraft Systems Physics-Based Weight Estimation Methods for Conceptual Design},

author = {Ali Tfaily and Dr. Susan Liscouët-Hanke},

url = {https://www.sawe.org/product/paper-3692},

year  = {2017},

date = {2017-05-01},

booktitle = {76th Annual Conference, Montreal, Canada},

pages = {12},

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

address = {Montreal, Canada},

abstract = {During the conceptual design phase of an aircraft, details regarding aircraft systems such as the detailed architecture and parts lists are not available. However, weight estimates for aircraft systems are needed very early for aircraft design and performance calculation. Several methods exist to predict system weights and most of these methods are empirical models correlated to top level aircraft parameters such as take- off weight, wingspan, etc. Even if the empirical methods have been sufficiently accurate in the past, they are not suitable for a more sophisticated multidisciplinary design optimization (MDO) approach implemented today in Bombardier's Advanced Design group. In addition, the empirical methods are not valid to predict the effect of new technologies. So called 'physics-based methods' are proposed, leading to a better understanding of technology and system architecture choice impact on the aircraft weight.The new weight estimation methods are implemented as integral part of a conceptual aircraft systems sizing framework. This framework enables the development of more mature aircraft concepts without comprising the calculation runtime. The proposed physics based models showed minimal errors when compared to actual data while capturing additional sensitivities that did not exist in previous methodologies. This paper illustrates the methodology for the example of the hydraulic power system.},

keywords = {11. Weight Engineering - Aircraft Estimation, 25. Weight Engineering - System Estimation, 34. Advanced Design},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3690,

title = {3690. Weight Optimization of Environmental Control System of Corporate Jets},

author = {Ragaa Mitry},

url = {https://www.sawe.org/product/paper-3690},

year  = {2017},

date = {2017-05-01},

booktitle = {76th Annual Conference, Montreal, Canada},

pages = {20},

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

address = {Montreal, Canada},

abstract = {The environmental control system (ECS) is an essential system in the aircraft; it provides air supply, thermal, humidity, ventilation, and cabin pressurization for the crew and passengers. It is also used for engine anti-ice, main door sealing, avionic cooling, and smoke detection.ECS is sized to meet the aircraft mission. It is the highest power-consuming system on the aircraft.The basic designs of the ECS used on most aircraft, in both corporate jets and commercial airliners, are remarkably similar. In simplified terms, air is first compressed to high pressure and temperature in the engine compressors, cooled in a precooler before entering the fuselage then conditioned by an air cycle machine (ACM) where excess moisture is removed and the temperature necessary for heating or cooling the airplane is established. The conditioned air is then delivered to the cabin and cockpit through the duct distribution system to maintain a comfortable environment.To optimize the system from the weight point of view, a complete analysis of each component must be considered and evaluated. The weight of the ECS is driven by the bleed air pressure and temperature which determines the size of the precooler (Reference SAWE Paper $#$ 3648; Engine Integration to Aircraft of Corporate Jets).The thermal heating and cooling load will determine the extracted bleed airflow quantity, which in turn, will impact the ACM size and weight.Most of the ECS components are designed and provided by suppliers but the air distribution ducts are laid out by the airframers and that deserves more attention. The adverse effect of paying little attention to duct optimization is a weight penalty and cost increase. The ducts' layout, size, and shape can lead to increased cabin's noise which is usually treated by additional sound attenuation materials on the account of weight, cost, and maintainability. The duct noise can also lead to other problems such as vibration and passenger's discomfort.This paper will focus on addressing the air distribution duct design and layout as related to weight optimization.},

keywords = {10. Weight Engineering - Aircraft Design, 24. Weight Engineering - System Design},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3687,

title = {3687. An Updated Initial Parametric Weight Equation Compendium},

author = {David Hansch},

url = {https://www.sawe.org/product/paper-3687},

year  = {2017},

date = {2017-05-01},

booktitle = {76th Annual Conference, Montreal, Canada},

pages = {50},

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

address = {Montreal, Canada},

abstract = {When developing the initial weight estimate for a new vessel, the weight engineer or naval architect can produce his or her estimate either by scaling from a known, similar vessel, or by taking the weights of each portion of the vessel from parametric equations or by some combination of these two methods. The preferred source of a parent vessel to scale from or the data from which a parametric equation is derived is the past vessels designed by the naval architect's own firm; however, sometimes the firm may not have suitable designs in its portfolio to base a new design weight estimate upon. This paper seeks to collect as many previously published parametric weight equations for as wide a collection of vessel types as possible in order to provide a convenient reference for the times the naval architect's own data is insufficient to complete a weight estimate.This paper is not intended to be the definitive source of parametric weight equations, rather, the goal is to collect a critical mass of equations across the range of vessel types to start the conversation on the relative merits of the various equations and hopefully elicit new up-to-date equations from others. Ideally discussers will add equations based on their own data in addition to discussing the merits of those collected here. The end goal is the production of a SNAME T&R Bulletin, however much additional validation, updating and discussion is required to take the current paper to the point where it could be considered as a true draft for such a bulletin.In all cases, the reader is encouraged to consult the original source and attempt independent validation before using any of the equations collected herein.},

keywords = {Marine},

pubstate = {published},

tppubtype = {inproceedings}

}

@inproceedings{3685,

title = {3685. Design of an internal aerodynamic load cell for static for oscillating airfoils},

author = {Kamal Ben Miloud and Hachimi Fellouah},

url = {https://www.sawe.org/product/paper-3685},

year  = {2017},

date = {2017-05-01},

booktitle = {76th Annual Conference, Montreal, Canada},

pages = {7},

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

address = {Montreal, Canada},

abstract = {This project concerns the design of a three components internal aerodynamic load cell. This load cell will be used to measure the lift, drag and pitching moment in static or oscillating airfoils enduring air loads. The end objective is to study the complex unsteady 3 dimensional (3D) air flows interaction with airfoils. This interaction is often characterized by flow recirculation and massive flow separations that lead to reduction of both aerodynamic performance and structure fatigue.The Computer-aided design (CAD) of the internal load cell will be presented. Finite element analysis (FEA), through ANSYS software, is used to assess the design before its construction. The result shows the good response of the balance to simulated air loads.},

keywords = {11. Weight Engineering - Aircraft Estimation, Student Papers},

pubstate = {published},

tppubtype = {inproceedings}

}