Search Results

Pressure on costs and budgets makes automating processes within the aerospace and space industries necessary. Misunderstandings about reductions to these complex systems can result in the improper application of these systems, often leading to poor outcomes and project failure. This course introduces the components of automation critical to the practice of acquiring, installing, and maintaining automation. The instructor presents the types, components, operation, application, cost benefits, laws, strengths, and limitations of automation.

This course is verified by Probitas as meeting the AS9104/3A requirements for Continuing Professional Development. Production and continual improvement of safe and reliable products is key in the aviation, space, and defense industries. Customer and regulatory requirements must not only be met, but they are typically expected to exceeded requirements. Due to globalization, the supply chain of this industry has been expanded to countries which were not part of it in the past and has complicated the achievement of requirements compliance and customer satisfaction.

AMS-STD-595A Color Chips Precise Color Matching, Individual Color Chips: A 3 x 5 inch color chip supplied in a 3 x 5 inch protective envelope for each AMS-STD-595 color, suitable for matching quality control inspection purposes. SAE Product Code: EA-10032 AMS-STD-595 – Colors Used in Government Procurement. This standard presents the colors used by Government Activities in a format suitable for color selection matching and for quality control inspection for paints and coatings. Standard is used with DoD and other Federal Agencies as a primary source of color reference.

Parts, such as bolts, turbine wheels, discs, buckets, and blades, for high strength and oxidation resistance up to 1500 F when suitably heat treated.

This specification covers a corrosion and heat resistant nickel alloy in the form of sheet, strip, and plate procured in SI (metric) units.

The System Architecture Virtual Integration (SAVI) program is a collaboration of industry, government, and academic organizations within the Aerospace Vehicle System Institute (AVSI) with the goal of structuring a new integration process that relies on a single-truth architectural framework. The SAVI approach of Integrate, then Build provides a modern distributed development environment which arrests the propagation of requirements errors through the development life cycle. It does so by capturing design assumptions and shared properties of the system design in an authoritative, annotated architectural model. This reference model provides a common, analyzable framework for confirming that system requirements remain complete, consistent, and correct at all levels of system decomposition. Core concepts of SAVI include extensive use of model-based system engineering tools and use of a single-truth reference architectural model.

Silicones have been utilized in multiple industries in the last 50 years and their applications are still expanding as technology grows. Ice phobic coatings, as an example, have been utilized on lock walls, navigation channels, wind turbines, hydropower intakes, and aircraft. Without protection these applications have a high risk of failure in the functions they perform. For example, ice build up on an aircraft?s aerodynamic surfaces increases drag which reduces lift during flight operations. Utilizing a silicone ice phobic coating significantly reduces the adhesion of ice to aerodynamic surfaces. Compared to other polymeric materials, silicones are known for their broad operating temperature range and lend themselves to excellent performance in a variety of harsh environments. Especially in low temperatures where ice adhesion is a concern, silicones retain their elastomeric physical properties and low modulus.

In any new aircraft development program there are many important design decisions that determine profitability potential. The key to making new aircraft profitable is to design features that will command more money than the cost to provide them within the market's ability to absorb them. The business model in this paper shows how to predict or find: 1) the costs to provide various aircraft features; 2) the values that aircraft buyers place on these features; 3) the amount of money that buyers have to commit to them, 4) the open spaces in the market in which to place new designs and 5) the predicted profits from new designs. In this process, this paper extends previous work on the law of value and demand, which states that attributes determine value; value determines price; and that price determines demand. This four-dimensional, non-negative system hosts a business model that describes the features needed to enable aircraft designs to go from concepts to profitable assembly lines.

High Speed Machining of CFRP Parts Investigation of the influence of new geometries, cutting datas and coolant capabilities on the surface finish of CFRP parts. State of the art: Different CFRP grades and machining conditions make geometry adjustments to the tool necessary. Mechanical failures through machining operations can be avoided in most of the cases. New unidirectional CFRP grades and dry machining processes again lead to machining problems. This study investigates new geometries to avoid heat damage with dry maching and air coolant in case of unidirectional CFRP. With help of a thermo camera and the surface investigation with a scanning electron microscope, heat damage can be analysed and therefore new geometries can be developed and tested. Target is to develop a new multi purpose CFRP geometry to meet the requirements of the future. The reduction of different geometries used leads to major cost savings. Presenter Ingo von Puttkamer, Guhring oHG

The presentation provides an overview about the activities of Eurocae Working Group 72 (WG-72) starting with a brief synopsis of the context which suggested why such a committee should be established in 2006. It then goes into further detail about the drivers for the work of the committee, which call for the products to be delivered. It addresses some of the challenges with respect to its users. It points out that one of the lessons the committee learned was importance of the focus on the users, such that the products provide their maximum utility. Hence, the users should better be among the participants to achieve this objective. Other industries have dealt with the subject of Information System (or Cyber-Physical) Security long before this industry was forced to consider it. Consequently there are many industry standards and national or international norms, which may help to develop what is deemed needed for Civil Aviation.

Many manufacturing companies want to apply AFP technology to complex high-curvature part shapes. As new AFP machine technologies are developed to specifically apply material over complex shapes, new and innovative NC programming approaches are needed to successfully, reliably, and accurately apply material with good consolidation, while meeting the fiber direction and coverage requirements. A big issue with AFP is the production rate vs. part complexity. Most complex shapes can be created with a single .125? wide strip (tow) of material. But the production time would be impractically long. So machine builders create 6, 8, 16, even 32 tow AFP heads, and use the widest tow possible for the highest laydown rates. But then wide compaction rollers on these systems have difficulty consolidating material over curved surfaces, and the minimum steering radius of wider tows challenge the software?s ability to meet the layup requirements.

In a variety of industries there is a growing need to manufacture high quality carbon fibre epoxy matrix composite structures at greater production rates and lower costs than has historically been the case. This has developed into a desire for the automation of the manufacture of components, and in particular the lay-up phase, with Automated Tape Laying (ATL) and Fibre Placement (AFP) the most popular choices. When used for large primary structures there are such potential gains to be had that both techniques have seen rapid implementation into manufacturing environments. But significant concerns remain and these have limited their wider adoption into secondary structure manufacturing, where manual forming of woven broadgoods is dominant. As a result the manufacture of secondary structures is generally explored for costs reduction through drape simulation and lower cost materials.

A combination of laboratory reactor measurements and vehicle FTP testing has been combined to demonstrate a method for diagnosing the formation of NO2 from a diesel oxidation catalyst (DOC). Using small cores from a production DOC and simulated diesel exhaust, the laboratory reactor experiments are used to support a model for DOC chemical reaction kinetics. The model we propose shows that the ability to produce NO2 is chemically linked to the ability of the catalyst to oxidize hydrocarbon (HC). For thermally damaged DOCs, loss of the HC oxidation function is simultaneous with loss of the NO2 production function. Since HC oxidation is the source of heat generated in the DOC under regeneration conditions, we conclude that a diagnostic of the DOC exotherm is able to detect the failure of the DOC to produce NO2. Vehicle emissions data from a 6.6 L Duramax HD pick-up with DOC of various levels of thermal degradation is provided to support the diagnostic concept.