Browse Topic: Coatings, colorants, and finishes

Items (5,458)
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
This specification covers an aircraft-quality, low-alloy steel in the form of round, non-welded tubing free from OD surface seams.
AMS E Carbon and Low Alloy Steels Committee
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, flash welded rings, and stock for forging or flash welded rings.
AMS E Carbon and Low Alloy Steels Committee
This specification covers an aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
This specification covers a corrosion-resistant steel in the form of cold-worked bars and wire up to 1.750 inch (44.45 mm) inclusive, in nominal diameter or least distance between parallel sides (see 8.4).
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a high-strength, corrosion-resistant alloy in the form of bar up to 1.75 inches (44.4 mm) in diameter (see 8.2 and 8.7).
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a high-strength, corrosion-resistant alloy in the form of bars up to 1.75 inches (44.4 mm) in diameter (see 8.2 and 8.7).
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a corrosion and heat-resistant iron alloy in the form of welding wire.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a corrosion and heat-resistant steel in the form of welding wire.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a corrosion and heat-resistant steel in the form of bars, forgings, and forging stock. These products have been used typically for parts requiring oxidation resistance and high strength up to 800 °F (427 °C) and where such parts may require welding during fabrication, but usage is not limited to such applications.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a free-machining, corrosion-resistant steel in the form of cold-worked bars and wire up to 1.750 inches (44.45 mm) inclusive, in nominal diameter or least distance between parallel sides (see 8.5).
AMS F Corrosion Heat Resistant Alloys Committee
AMS4325A prohibits unauthorized exceptions (3.7), revises condition (3.2), properties (3.4.5), quality (3.5.1), reports (4.4.1), and identification (5.1.1), and results from a Five-Year Review and update of this specification.
AMS D Nonferrous Alloys Committee
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing up to 32 square inches (206 cm2) in area (see 8.5).
AMS D Nonferrous Alloys Committee
This specification establishes the requirements for brush plating of cadmium by electrodeposition.
AMS B Finishes Processes and Fluids Committee
Hybrid additive manufacturing (AM) and subtractive manufacturing (SM) processes utilize the combination of AM (e.g., LPBF and DED) and SM (e.g., milling and turning operations) to produce the final part. Due to the poor surface roughness resulting from the uneven melting of powders in AM, the subtractive process is a necessary finishing operation to improve the surface roughness of the AM part. The hybrid AM/SM technology combines the benefits of AM and SM processes to create complex geometry while introducing good surface finish and compressive stress to prevent crack initiation. However, the relationship between large process parameter space and the residual stress/distortion in the part is not well understood, which impedes the adoption of hybrid AM/SM to minimize the residual stress in the final product. To expedite the process optimization, we establish a pipeline for the sequential modeling of additive manufacturing (AM) and subtractive manufacturing (SM) processes. Key accomplishments achieved under this study include (1) development of thermal abstraction technique for the AM process to speed up the macroscale level heat transfer analysis based on the manufacturing factors including scanning vector, laser power, dwelling time, etc.; (2) development of the sequentially coupled thermal-mechanical model to predict the residual stress and distortion after AM process by passing the temperature history obtained from heat transfer analysis to the mechanical analysis at each time point; (3) validation of the thermal-mechanical model for AM using thin-wall structure from literature and cantilever beam structure from UNT’s experiments data; (4) conduction of the parametric study on the chamber temperature and part design in the AM process to demonstrate how the temperature gradient and supporting structure affect the residual stress and distortion; (5) exploration of macro and micro scale models to predict the bulk and surface residual stress after cutting; (6) applying the developed modeling framework to tailoring the hybrid AM/SM process. To support model verification and demonstration, we print cantilever beam structure with different supporting structure designs and cutting strategies to study how these factors affect the final part residual stress and distortion. The data collected in the printing and cutting process is used to examine the applicability of the developed simulation tool.
Lua, JimLi, RuiRajanna, ManojHaridas, Ravi SankarMishra, Rajiv
A study into the effects of a low ice adhesion strength coating and combined low power thermal heater system was conducted. Preliminary tests determined the mass of ice necessary to shed from the low ice adhesion strength coating at a specific ambient temperature (-4°C, -8°C, -12°C, and-16°C). The heater tests were conducted at an ambient temperature of -20°C, where the same mass of ice was accreted for each specific case temperature. With the accreted mass, the heaters were turned on until a shed event occurred. The surface temperature at the shed event was recorded. For colder temperatures such as -12°C and-16°C, the surface needed to reach a temperature within 1°C of -12°C and-16°C, respectively, to initiate a shed event. For the warmer cases the replication of ice at -20°C was not feasible, as the type of ice influences adhesion strength. Ice accreted at -20°C has different physical properties than ice formed at warm temperatures, therefore the surface temperature required for shedding did not match between the two tests. Results from the heater tests led to a discovery of a value that describes the adhesion strength normalized with respect to shed surface temperature. The value was found to be -1.09 psi/°C, averaged over six cases with varying conditions. This value is dependent upon a wide range of adhesion strength values for the system but opens possibilities of a full understanding of the hybrid thermal/passive coating system. With the experimental characterization of the adhesion strength to shed surface temperature value, future coating development could rely on heating the surface and recording the surface temperature needed for shedding. With such value, the ice adhesion strength of the coating could be characterized without the need for ice adhesion strength measurements.
Tyndall, JackPalacios, Jose
ABSTRACT
Gaugelhofer, LukasJohn, JonasHajek, ManfredYavrucuk, Ilkay
ABSTRACT
DaSilva, Mary
This specification covers a low-alloy steel in the form of bars, forgings, mechanical tubing, and forging or tubing stock.
AMS E Carbon and Low Alloy Steels Committee
This SAE Aerospace Standard (AS) provides standardized gland (groove) design criteria and dimensions for O-ring seal glands for static and dynamic applications, and other seals.
A-6C2 Seals Committee
This specification covers an aluminum-lithium alloy in the form of extruded profiles with a maximum cross-sectional area of 19 in2 (123 cm2) and a maximum circle size of 11 inches (279 mm) from 0.040 to 0.499 inch (1.00 to 12.50 mm) in thickness (see 8.7).
AMS D Nonferrous Alloys Committee
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
This specification covers an aircraft-quality, low-alloy, heat-resistant steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
This standard establishes the minimum requirements for training, examination, and certification of aerospace coatings application personnel applying liquid organic coatings to interior structural or exterior substrates. It establishes criteria for the certification of personnel requiring appropriate knowledge of the technical principles underlying aircraft surface preparation and coatings application for both protective and decorative purposes. Persons who successfully complete the requirements of this certification standard are considered to be able to successfully and consistently perform a broad spectrum of aerospace coatings application tasks to achieve the desired engineering purposes. This certification is not intended to determine or replace any aerospace coating operation’s proprietary engineering for the depainting, preparation, or subsequent application of organic coatings materials to aircraft surfaces.
AMS G8 Aerospace Organic Coatings Committee
AMS B Finishes Processes and Fluids Committee
This specification covers a free-machining, corrosion-resistant steel in the form of bars, wire, forgings, and forging stock.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles (shapes), and tubing 0.040 to 4.000 inches (1.00 to 100.00 mm) in nominal diameter, least dimension, or wall thickness (see 8.7).
AMS D Nonferrous Alloys Committee
AMS G8 Aerospace Organic Coatings Committee
This specification covers a corrosion and heat-resistant steel in the form of sheet, strip, and plate 0.0010 inch (0.025 mm) and above in nominal thickness (see 8.6).
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a corrosion and heat-resistant cobalt alloy in the form of bars, forgings, flash welded rings, and stock for forging or flash welded rings.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a corrosion and heat-resistant steel in the form of bars, wire, forgings, mechanical tubing, flash welded rings, and stock for forging, flash welded rings, or heading.
AMS F Corrosion Heat Resistant Alloys Committee
This specification covers a premium aircraft quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
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