Browse Topic: Geometric design and tolerancing (GD&T)

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testing new software productSAE-SUP-TEST134/1/2026
Software Diagram https://wcm14-tst.cld.sae.org/site/binaries/content/gallery/mobilus-brx/digital-supplements/software-diagram.png/software-diagram.png/sae%3Amedium
Arinc Automation Document - Standard Characteristic - PageCount less than 45KJH003-26 (Current)12/23/2025
Arinc Automation Document - Standard Characteristic - PageCount less than 45
Aviation Maintenance Committee, Airlines Electronic Engineering Committee
Arinc Automation Document - Standard Characteristic - PageCount less than 45KJH003 (Historical)12/19/2024
Arinc Automation Document - Standard Characteristic - PageCount less than 45
Aviation Maintenance Committee, Airlines Electronic Engineering Committee
test for kevin SAAS ingestionarinc-kjh (Current)11/1/2024
test
Aviation Maintenance Committee
asdgjmsaldkfgjalkerjtw (Current)8/29/2024
asdg
Airlines Electronic Engineering Committee
Automation Title for Group Code D23PC-Auto-1715022264466 (Current)5/6/2024
Automation Abstract for Group Code D23
Automation Title for Group Code D22PC-Auto-1715022197983 (Current)5/6/2024
Automation Abstract for Group Code D22
Automation Title for Group Code D21: Updated in Authoring: 5/03/24PC-Auto-1714611830430 (Current)5/2/2024
Automation Abstract for Group Code D21. Updated in Authoring: 5/03/24
Automation Title for Group Code D22PC-Auto-1713447343633 (Current)4/18/2024
Automation Abstract for Group Code D22
Airlines Electronic Engineering Committee
Automation Title for Group Code D21PC-Auto-1713447321320 (Current)4/18/2024
Automation Abstract for Group Code D21
Airlines Electronic Engineering Committee
Automation Title for Group Code D21PC-CUR-1232 (Current)4/18/2024
Automation Abstract for Group Code D21
Airlines Electronic Engineering Committee
Automation Title for Group Code D23PC-Auto-1713447365379 (Current)4/18/2024
Automation Abstract for Group Code D23
Flight Simulator Engineering and Maintenance Committee
An eleventh one for CUR-1174PC11-CUR-1174 (Current)4/2/2024
Italic
Flight Simulator Engineering and Maintenance Committee
A sixth one for CUR-1174PC6-CUR-1174 (Current)3/26/2024
N/A
testing tasksSAE-PP-092253/21/2024
3rd task
Mutagaana, Festo
This is an Information Report, Test-4jms-informationreport4 (Historical)3/13/2024
information report information report information report information report
Airlines Electronic Engineering Committee
specification test 3specification3 (Historical)3/12/2024
specification test 3
Airlines Electronic Engineering Committee
characteristic test 3characteristic3 (Historical)3/12/2024
characteristic test 3
Aviation Maintenance Committee
Characteristic Test 2 jms-characteristic2 (Historical)3/12/2024
Characteristic Test 2
Airlines Electronic Engineering Committee
information report test 3informationreport3 (Historical)3/12/2024
information report test 3
Aviation Maintenance Committee
Characteristic Testjms-characteristic1 (Historical)3/11/2024
Characteristic Test
Airlines Electronic Engineering Committee
Information Report Testjms-informationreport1 (Historical)3/11/2024
Information Report Test
Aviation Maintenance Committee
TEST - 800P1 Cabin Connectors and Cables, Part 1, Description and OverviewARINC800P1-CSP (Historical)2/23/2024
This document is the first of a multi-part specification that will provide a catalog of cabin connector and cables that may be used in ARINC Standard cabin systems, including In-Flight Entertainment. Part 1 describes connector and cable requirements and evaluation criteria for the interface components used in the integration of cabin systems. Future releases will define connectors, contacts, and termination methods in Part 2. Cables will be specified in Part 3.
Airlines Electronic Engineering Committee
TEST - 791P2-2: Mark I Aviation Ku-Band and Ka-Band Satellite Communication System, Part 2, Electrical Interfaces and Functional Equipment DescriptionARINC791P2-2-CSP (Historical)2/23/2024
This document (ARINC Characteristic 791, Part 2) provides the non-networking interface definition of the Mark I (ARINC 791) and Mark II (ARINC 792) Ku-Band and Ka-Band Satellite Communication (satcom) system intended for passenger entertainment on commercial transport aircraft. ARINC Characteristic 791 Part 1 of this document provides an overview of Ku-band and Ka-band satcom systems. System provisions, including Line Replaceable Unit (LRU) form factors, attachments, cooling, and inter-system wiring, are defined. Signals between the Modem/Modem Manager (Modman) and the Antenna Subsystem are described to permit interchangeability between any Modman and any Antenna Subsystem. ARINC Characteristic 791 Part 2 of this document provides the non-networking interface definition of the satcom system. Any signal crossing into or out of the communication system is documented to ease aircraft integration. Signals within the satcom system, and in particular, between the Modman and the Antenna Subsystem, are described to permit interchangeability between any Modman and any Antenna Subsystem. ARINC Characteristic 791 Part 3 of this document provides the networking interface definition of the satcom system. Any signal crossing into or out of the communication system is documented to ease aircraft integration.
Airlines Electronic Engineering Committee
TEST - Designing for Long Life with ElastomersAIR1412E-CSP (Historical)2/23/2024
This document lists those guidelines recognized as being essential for consideration by the designer who is preparing to select an elastomer as part of an aerospace design.
Airlines Electronic Engineering Committee
Attacking vehicles with ransomware: Watch the horizon2022-01-04413/29/2022
Ransomware use is rampant throughout most industries. With the number of successful ransomware attacks through the industrial economy, this feels like a tsunami of attacks. These attacks seemingly originate from anywhere with an internet connection. There are vast numbers of bad actors creating these attacks, all focused on your systems. With the large number of attacks, it is granted there have been many breaches. While there have been a large number of successful attacks, each attack’s objectives have varied. These have historically been to generate revenue in the form of fees for the decrypt key or a promise not to publish exfiltrated data. The landscape has become saturated with ransomware attacks on consumers and the enterprise. There has been extensive training for staff in an effort to mitigate these issues. The next potential targets are vehicles and ground systems. These, as targets, have not been evaluated via a full risk assessment to the recommended extent. While not widely exploited, this has the distinct potential to be a significant issue. With the criticality of these systems for the troops along with the DoD, the risk for nation-state attacks cannot be dismissed or ignored. The impact of a coordinated attack would be significant. As the vehicles increase their connectivity and level of autonomy, the risks continue to grow. The compromised ground vehicle systems may lead to the vehicles inoperable, the supply chain stopping to the soldiers in the field, and distribution systems (goods and soldiers) ceasing. The paper will analyze ransomware threats, creation, pivots from present attacks, and attack methodologies.
Parker, Charles
Flexure for Self-AssemblyTBMG-359982/1/2020
Conventional fastening mechanisms like nails, bolts, and welds are subject to manufacturing and inspection tolerances, differential thermal growth, and other sources of error that lead to over-constraint, among other challenges, for manufacturers and assemblers. Sandia researchers have developed a versatile flexure design that resolves common issues such as over-constraint while providing more sophisticated control of freedom of movement, stiffness, configuration, and constraint and compliance features. This level of control and versatility is valuable in advanced or self-assembling manufacturing settings, particularly for large or complex systems.
A Novel Compliance Constrained Mass Optimization Framework for Vehicle Suspension Subframe Structures10-04-02-00081/27/2020
Traditionally, vehicle subframe mass optimization process is achieved by an iterative process, which is usually conducted with virtual test using an initial flexible suspension structure while satisfying compliance constraints via multibody dynamic simulation software. The optimization process is typically performed via a multibody dynamic simulation software, and ideally, with an adequate flexible subframe model, the design problem is formulated and solved via a traditional optimization procedure. In reality with a complex model, optimization is in general extremely cumbersome, time-consuming, and with no guarantee of an optimal solution. For this reason, this article presents a novel, rapid, and accurate design framework for vehicle subframe structural mass optimization consisting of five main components: (1) a meta-model is constructed to directly approximate the relationship between the subframe geometry and compliance characteristics of the corresponding suspension. (2) An optimization search is performed on the meta-model directly to identify the subframe geometry with minimal mass and satisfied compliance constraint. In the meta-model, the geometric dimensions of the subframe and suspension compliances are formulated respectively as design variables and constraints in the optimization process. (3) Global sensitivity analysis is then performed to reduce the insignificant design variables of the meta-model. (4) Using discriminant classification analysis, the compliance constraint is modeled as a function of subframe stiffness at the attachment point. (5) The attachment stiffness is a combination of the real bushing element and the equivalent stiffness, which is due to the flexibility of the subframe and can be determined from a finite element analysis based on the geometry. The results presented in this article indicate that a reduction in mass of the optimized geometry can always be achieved despite the initial design and constraint level.
Chen, Liang, Shen, Herman, Zhang, Xin, Gao, Jianghua
Unsettled Technology Domains in Aerospace Additive Manufacturing Concerning Safety, Airworthiness, and CertificationEPR201900812/23/2019
Additive manufacturing (AM) is currently being used to produce many certified aerospace components. However, significant advantages of AM are not exploited due to unresolved issues associated with process control, feedstock materials, surface finish, inspection, and cost. Components subject to fatigue must undergo surface finish improvements to enable inspection. This adds cost and limits the use of topology optimization. Continued development of process models is also required to enable optimization and understand the potential for defects in thin-walled and slender sections. Costs are high for powder-fed processes due to material costs, machine costs, and low deposition rates. Costs for wire-fed processes are high due to the extensive postprocess machining required. In addition, these processes are limited to low-complexity features. Incremental improvements in all of these areas are being made, but a step change could potentially be achieved by hybrid processes, which use wire feedstock to deposit the bulk of the part and powder for fine detail. NOTE: SAE EDGE™ Research Reports are intended to identify and illuminate key issues in emerging, but still unsettled, technologies of interest to the mobility industry. The goal of SAE EDGE™ Research Reports is to stimulate discussion and work in the hope of promoting and speeding resolution of identified issues. SAE EDGE™ Research Reports are not intended to resolve the issues they identify or close any topic to further scrutiny. Click here to access the full SAE EDGETM Research Report portfolio.
Muelaner, Jody
An Optimization Framework for Fixture Layout Design for Nonrigid Parts: An Automotive Perspective05-13-01-000111/19/2019
Abstract The inspection process of non-rigid parts during manufacturing and assembly is inherently challenging. This is exacerbated by the need for accurate real-time part data in the digital age. Although many ad hoc techniques exist, there are no rigorous methods to evaluate the quality of a fixture layout before final parts and gauges are available. This typically happens so late in the manufacturing process that errors found can scarcely be remedied. Additionally, the modifications to the gauge are usually costly and can result in significant delays, when performed this late in the process. This article proposes an optimization-driven mathematical approach tailored toward non-rigid parts to identify the best locator layout, early in the part design phase. A metric is proposed using robotic grasping theory to quantify the quality of the locating scheme and serves as the objective of optimization. The proposed method is implemented using a tolerancing software that performs finite element analysis (FEA) on the parts to predict its state given the force and torque inputs, including the effect of gravity. An evolutionary algorithm is used that optimizes the performance of the fixture layout. We demonstrate a significant improvement in gauge repeatability when compared with an arbitrary layout scheme on two design problems. The first problem is a representative design problem using a sheet metal part, while the second one is an actual automotive production part. General recommendations regarding fixture layout design for non-rigid parts are made, as well as directions for future work are provided.
Slon, Christopher, Pandey, Vijitashwa
The Future of Airplane Factory: Digitally Optimized Intelligent Airplane AssemblyR-4665/28/2019
The Future of Airplane Factory: Digitally Optimized Intelligent Airplane Factory defines the architecture, key building blocks, and roadmap for actualizing a future airplane factory (FAF) that is digitally optimized for intelligent airplane assembly. They fit and integrate with other FAF building blocks that aggregate to a Digitally Optimized Intelligent Airplane Factory (DOIAF). The word "intelligent" refers to the ability of a system to make right decisions and take right action in the highly dynamic and fluid environment of the modern airplane manufacturing space. The event-driven dynamics inherent in the complexity of this environment drive the need for expert knowledge which resides in intelligence systems incorporating the experience of experts. Expert knowledge need not be smart, brilliant, or possess genius as long as the outcomes are derived from right decisions resulting in right actions-applied rapidly to sustain an optimized factory enterprise. Complete factory enterprise visibility requires a higher order of decision capability that current operating systems do not have. A highly visible factory collects and displays data and information as it happens-at a rate beyond the ability of humans and current systems to analyze, process, decide, and act upon. Expert systems are constructed to present humans with right decisions in the form of optimal choices for right actions by incorporating the knowledge of experts into the logic for the decision. Structured Knowledge-Based Expert Systems (SKBES) are incorporated in this book and defined as a critical component for full enterprise actionable visibility. The power of the Digitally Optimized Intelligent Airplane Factory not only is found in its ability to unify the factory, reduce touch labor, improve quality, and streamline throughput but it also enables a significant reduction in above-the-shop-floor support and management. Such an ecosystem frees the human to focus on the complexity of interpersonal responsibilities. If the use of a DOIAF can be viewed as a holistic mechanism, then the human can be the agent engaging with that mechanism; improving negotiations for pricing, contracts, or other person-to-person events that require instinct and relationship.
Bullen, George Nicholas
Design for Manufacturing: Tips for Molding Components in SiliconeTBMG-335601/1/2019
Device functionality is usually the starting point when designing devices. Another element that needs to be considered when designing devices and their subsequent components is their manu-facturability. Part design should also be focused on the ease of manufacturing because it can help reduce cost and lead to a robust and reliable process. Several aspects should be considered regarding manufacturabil-ity: part geometry, location, and size and shape of critical surfaces, among others. These may seem like more obvious characteristics, but there are a few others that can be overlooked, but should be considered just as important. These are material selection, dimensioning/tolerancing, and the selection of critical dimensions. To better understand the impact of these factors, this article explores each characteristic in detail.
The Fault-Augmented Approach for the Systematic Simulation of Fault Behavior in Multi-Domain Systems in Aerospace2018-01-191710/30/2018
A library for modelling faults in multi-domain physical systems is introduced. The library is based on the simulation of fault effects on the system’s behavior. The motivation of how and why to model faults systematically as well as a description of the Modelica®-based library structure with a wizard supporting the semi-automatic augmentation process of faults are outlined. The fault types are classified into continuous and discrete with dedicated type definitions. The application of the Fault library is exemplified in the field of aerospace electrohydraulic actuator. The actuator is equipped with hydromechanical, electrical and digital systems for mitigating failures, which should be tested at an early stage of design. To perform the tests, a multi-domain, dynamic system model is created, wherein failures are systematically simulated using a special approach for fault augmentation. In addition, several complementary tests are obtained by a variants simulation and the simulation results of the fault augmented model are analyzed and using supervised machine learning classifier are demonstrated. Different classification algorithms were compared to each other and analyzed. The accuracy of an appropriate machine learning classifier is analyzed in detail to classify several faults from different domains and to localize their impact by changing a control mode. The selection of relevant output values for the fault classification in the electrohydraulic control system is executed based on the extraction of the feature’s importance.
Kolesnikov, Artem, Andreev, Maxim, Abel, Andreas
Design and Safety Criteria for Passenger Boarding StairwaysAIR6133 (Current)9/21/2018
AGE-3 Aircraft Ground Support Equipment Committee
Challenges to develop a robust dimensional tolerancing management process in the automotive industry2018-36-01589/3/2018
Geometric Dimensioning and Tolerancing is a language used to describe and communicate the feature dimensional variations permitted according to the product design. The product development engineering team defines not only the tolerance, but also the symbols to be used in the dimensional specification of each component, inside the feature control frame. Every year, it becomes much more complex to define the dimensional tolerance and symbols for each feature. Failures in product specification may impact on the cost of production or require changes to the product after the launch. This paper aims to describe the challenges to develop a robust process for geometric dimensioning and tolerancing, within a knowledge management approach. Furthermore, a survey is presented about the dynamics of knowledge, confidence level and application of the current tolerancing process in the automotive industry.
Murari, Thiago B., Ungaretti, Paulo, Silva, Diogo, Nascimento, Filipe, Filho, Aloísio S. N., Moret, Marcelo A.
A Disciplined Approach to Minimize Rattle Issues in Automotive Glove Box Assembly2018-01-14816/13/2018
Nowadays, perception of automotive quality plays a crucial role in customer decision of vehicle purchase. Hence, automotive OEM’s are now working on the philosophy of “Quality Sound”. Out of all the Noise, Vibration & Harshness (NVH) issues identified in a vehicle, the ranking of Buzz, Squeak & Rattle (BSR) stands high and glove box rattle is one of the issues that is continuously observed in all customer verbatim. Specific issues like lid rattle and latch rattle are predominant and gets worse over mileage accumulation. Also minimizing BSR issues in glove box is difficult due to complex latch mechanism. While deciding the bump stop specifications more weightage is given to efforts. The bump stop is selected in a way as not to increase the glove box opening and closing efforts, but the selected bump stops will not provide enough preload to glove box lid leading to rattle issues. Also, the contradictory requirements between efforts and rattle makes the scenario more difficult to fine tune bump stop specifications. In the present study, an attempt is made to drive the glove box design from BSR point of view by carrying out rattle simulation on glove box assembly. The aim is to minimize the BSR issues in assembly without affecting glove box operating efforts. The methodology is implemented with realistic themes of finite element modelling and the analysis is performed by utilizing current software capabilities. Meaningful information has been extracted to analyze the influence of rubber bump stop design on glove box rattle issues. The bump stop pretension force (FP) and calculated dynamic force, (Fd) are key parameters in estimating the BSR performance of glove box assembly. The present work is limited to minimize the rattle issues at glove box lid and latch interface alone. Internal latch rattles are out of scope of this study. The non-linear behavior of bump stop is not considered because of small deformation values.
Chaudhari, Naresh, Mohammed, Riyazuddin, Raghavendran, Prasath
A Novel Approach to Create Dimensional Tolerance Requirements from Expert Knowledge2017-01-02413/28/2017
Geometric Dimensioning and Tolerancing is used to describe the allowed feature variations regarding the product design. Tolerance specification is important in many stages of all phases on product development. The product development engineering need to define the symbols to use on the Feature Control Frame of every component. Since the component function has an increment on its complexity year over year, it is not trivial to define those symbols anymore. The determination of dimensional tolerance shall be preceded by careful specification of the types of tolerance and symbols that will be applied in controlled features. Poor tolerance specifications can increase the production cost, require late product changes or lead to legal issues. In this scenario, this paper presents a method to evaluate this engineering information for a few number of GD&T technical experts in a specific system, like chassis or powertrain, and translate it into dimensional tolerance requirements to support the tolerance specification process using fuzzy logic. Also, the method suggests the best set of symbols based on the feature geometry, assembly and function analysis and classify these features to generate significant information on the automotive industry.
Murari, Thiago B., Ungaretti, Paulo, Moret, Marcelo A.
Comparison of the Far-Field Aerodynamic Wake Development for Three DrivAer Model Configurations using a Cost-Effective RANS Simulation2017-01-15143/28/2017
The flow field and body aerodynamic loads on the DrivAer reference model have been extensively investigated since its introduction in 2012. However, there is a relative lack of information relating to the models wake development resulting from the different rear-body configurations, particularly in the far-field. Given current interest in the aerodynamic interaction between two or more vehicles, the results from a preliminary CFD study are presented to address the development of the wake from the Fastback, Notchback, and Estateback DrivAer configurations. The primary focus is on the differences in the far-field wake and simulations are assessed in the range up to three vehicle lengths downstream, at Reynolds and Mach numbers of 5.2×106 and 0.13, respectively. Wake development is modelled using the results from a Reynolds-Averaged Navier-Stokes (RANS) simulation within a computational mesh having nominally 1.0×107 cells. This approach was chosen to reflect a simple, cost-effective solution, using an industry-standard CFD solver. Each vehicle configuration has a smooth underbody, with exterior rear-view mirrors. The computational modelling includes a ground simulation set, and all simulations are for zero freestream yaw angle. A mesh sensitivity study was undertaken and the simulation validated against published experimental data for the body pressure distribution and aerodynamic drag. Critical assessment of the results highlights the benefits of focussed mesh refinement and specific numerical strategies for optimum performance of the CFD solver. Comparison of the far-field aerodynamic wake for the three model configurations exhibits significant differences in both extent and structure within the wake region up to three vehicle lengths downstream of the base. Total pressure loss coefficient is used as the primary aerodynamic parameter for analysis. The study is an element of a larger programme related to vehicle wake simulation and strategies are identified for possible wake modelling using simplified, computationally and experimentally efficient, shapes.
Soares, Renan F., Garry, Kevin P., Holt, Jennifer
Proposed Validation Method for the Uncertainty Estimation of CMM Straightness Measurement Using PSO Algorithm and SMC Technique2016-01-02854/5/2016
Straightness uncertainty in dimensional metrology is an important parameter in precision engineering. Optimization in straightness measurement using soft algorithm techniques is widely encountered solution in coordinate metrology. In this work, we report on the uncertainty in the CMM measurement of straightness feature for a slab surface. Straightness points have been measured precisely in 3D using CMM at NIS. The straightness has been analyzed using a Particle Swarm Optimization (PSO) algorithm. The probability density distribution of the measured spatial straightness was developed using a Sequential Monte Carlo (SMC) technique; forming probability density histogram with 95% confidence level representing an uncertainty in the straightness measurement. Comparison with relevant reports showed and approved that our results are more accurate since we used a computationally efficient modified SMC technique and PSO algorithm. This work confirms that the developed strategic methodology can achieve validation method successfully for straightness uncertainty. Moreover, uncertainty in straightness measurement has been estimated and found to be suitable of the proposed validation method for CMM dimensional metrology.
Ali, Salah H. R., Khalafalla, Mohammed A. H., Naeim, Ihab H., Zahwi, Sarwat Z. A.
Light Weight Structures - Structural Analysis for Weight Optimization and Joining Techniques of Dissimilar Materials2016-01-13944/5/2016
Light weight structures give significant advantages to products in the Industrial sector. Component weight-saving plays a major role in improving the efficiency and performance of assembled systems. The introduction of lighter materials into products using dissimilar material joining techniques can create more weight savings and leads to lighter structures. Structural optimization is another method to optimize the material layout without affecting overall performance of the product. This paper discusses the methods to create lighter structures by the introduction of lighter materials in structures and structural optimization methods. Lighter materials are introduced in the structure using dissimilar material joining techniques. Joining processes such as thermal shrink-fit and mechanical press-fit are useful for metal to metal components. Similarly, adhesively bonded joints are useful for both metal and non-metal (plastics and composites) components. The aim of this study is to combine the advantages of introducing lighter material in structures and optimized design using structural optimization. In this paper detailed study on the structural analysis approach for some of the common dissimilar material joining techniques is presented. Topology optimization methodology is discussed in detail using a case study on a lighter body which is introduced through joining techniques. A parametric optimization method is proposed in this paper to consider the optimal percentage of weight saving and the overall cost of the structure which includes the material and manufacturing cost. This paper presents a novel approach of introducing lighter materials in combination with structural optimization.
Anand, Anuj, Konka, Hari Prasad, Fritz, Peter
Hydraulic Flange Clamps, 2-Screw Flange Connection to be used with SAE J518-1 (Code 61) Connections where Only Low Pressure is RequiredJ518/3_201511 (Historical)11/24/2015
This SAE standard outlines general and dimensional specifications for Code 61 flange clamps for use in low pressure applications with J518-1 connections. For port dimensions, port design considerations, and flange head dimensions, please refer to SAE J518-1. The rated working pressure of an assembly shall not exceed the least of all the component working pressure rated values. The following general specifications supplement the dimensional data contained in the tables with respect to all unspecified detail. Parts manufactured to this standard are also compatible with ISO 6162-1 port connections and flange heads.
Hydraulic Hose and Hose Fittings Committee
Predicting Alignment of Clutch Systems - A Case Study of Variation Simulation Analysis2015-01-28619/29/2015
Dimensional Variation Analysis (DVA) is a decision-making methodology for tolerance analysis, and is employed to evaluate assembly variations and identify problems in manufacturing assembly processes at early stages of design. In this study, the impact of component tolerances on manufacturing and assembly process variations is presented on a case study. The case study includes the alignment analysis between crankshaft and input shaft for clutch systems. The impact of component tolerances on axial alignment measurements in regard to these applications is discussed. The study shows that when combined with effective tolerance combinations, Variation Simulation Analysis (VSA) facilitates operational visibility; thus improve quality, reduce manufacturing cost, and enable reduction of production release time. The case study presents the impact of component tolerances at two levels: 1. Pre-Design, 2. Optimized Design.
Guleryuz, Burcu, Raper, Martin, Kocabas, Cagkan
Creating an Efficient Geometrical Measurement Planning Process2015-01-26169/15/2015
The scope and purpose of this paper is to give input and propose solutions to the creation of an efficient and productive geometrical measurement planning process. The case study outline what is important and how to identify and determine the preconditions and input data which is required to start the preparation and planning activities of geometrical measurements. That is why the following three main research and development questions should be answered: Firstly; What is the need and why does an efficient and productive geometrical measurement planning process contribute to decrease cost upstream as well as downstream in terms of reduced lead times in measurement planning process work? Secondly; Why are reduced uncertainties related to geometrical; functionality, specification and verification, important? And how are they linked to each other and how can they be theoretically modeled and defined in terms of uncertainties? The last question is; How is the current geometrical measurement planning process constructed and what does it contain and how is it functioning? By applying a more systematic and holistic approach in product realization and measurement planning activities, the accomplished study indicates improvements and high potential for cost savings, from 3 up to 12 times. Hence the improvement potential is strongly dependent of the actual geometrical complexity level of the airframe assembly being studied. Results from this study will further improve and develop current applied geometrical measurement planning process and will contribute to a more effective and productive working methodology and process.
Lindqvist, Richard, Jansson, Tobias
Proposed Metrological Method for Identifying Automotive Brake Discs2015-01-06914/14/2015
The main aim of this work is to develop an identification method to demonstrate the crucial surfaces of automotive braking system. Two brand new brake discs manufactured by two different manufacturers are tested. A typical disc to the one of them was put under working condition in actual braking system. Dimensional and geometrical deviations are investigated using advanced engineering metrological technique. Mechanical properties, tribological characteristics and chemical analyses are investigated. A coordinate measuring machine, universal hardness tester, mass comparator and XRF spectrometer are used in these diagnoses. Measurements of dimensional and geometrical deviations such as disc thickness variations, thickness deviations, straightness, parallelism, runout of disc surfaces are conducted. A comparison between form deviations in disc surfaces have been carried out and analyzed. The effect of material properties of the influencing surfaces on the wear rate and hardening of surfaces has been discussed. Wear rate under severe sliding conditions is thus strongly influenced by the geometrical and hardness characteristics. The wear rate of used brake disc rotor induced fatigue phenomena is accurately identified. Correlations between design specifications and real surface characteristics are evaluated. The results showed that implementation of the engineering metrology techniques to understand and predict the dynamic behaviors for auto brake discs are necessary successful. Moreover, repeatability of the measurement results is conducted to confirm their precision.
Ali, Salah H. R., Zahwi, Sarwat Z. A., Dadoura, Hassan H.
SEAL, BONDED, 302 CORROSION RESISTANT STEEL, AMS5516, MOLD IN GROOVE, SILICONE RUBBER, AMS7268AS27197B (Historical)7/7/2014
A-6C2 Seals Committee
SEAL, BONDED, 302 CORROSION RESISTANT STEEL, AMS5516, MOLD IN GROOVE, FLUOROSILICONE RUBBER, MIL-DTL-25988AS27198B (Historical)6/13/2014
A-6C2 Seals Committee
SEAL, BONDED, 302 CORROSION RESISTANT STEEL, AMS5516, MOLD IN GROOVE, FLUOROCARBON RUBBER, AMS7276AS27196B (Historical)6/13/2014
A-6C2 Seals Committee
SEAL, BONDED, ALUMINUM ALLOY 6061-T6, AMS4027, MOLD IN GROOVE, NBR RUBBER, AMS-R-7362AS27195A (Historical)4/29/2014
A-6C2 Seals Committee
SEAL, BONDED, ALUMINUM ALLOY 6061-T6, AMS4027, MOLD IN GROOVE, NBR RUBBER, AMS-P-5315AS27194B (Historical)4/8/2014
A-6C2 Seals Committee
SEAL, BONDED, ALUMINUM ALLOY 6061-T6, AMS4027, MOLD IN GROOVE, NBR RUBBER, AMS-P-5315AS27194A (Historical)1/9/2014
A-6C2 Seals Committee
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