Search Results for aircrafts

This article provides information on the applications of fiber-reinforced composites in commercial and military aircrafts. It tabulates the composite components in various types of aircraft. The applications of the composites in the components of Boeing 727, 737, 757, 767, 777, and 777-200 are schematically illustrated.

This article describes the protective coatings technology used in naval aircrafts. It reviews the future needs and trends of the protective coatings technology based on advancing technology, environmental concerns, and operational requirements. The article discusses the standard finishing systems for aircrafts: the surface pretreatment system, primer, topcoat, advanced-performance topcoat, self-priming topcoat, and specialty coatings. It presents safe compliant solutions to environmental problems associated with the protective coatings technology. These solutions include the use of environmental regulations and hazardous materials, nonchromated pretreatments, waterborne technology, high-solids technology, and touch-up paints. The article also deals with the use of electrodeposition coatings, powder coatings, adhesive films, paint application equipment, and non-chromated sealants in the protective coatings technology.

This article describes the influences of the operational environments of U.S. Navy aircraft during corrosion-control process. The most widely used materials in airframe structures and components, such as aluminum, steel, titanium, and magnesium alloy systems, are reviewed. The article provides information on the inspections steps, corrosion-control issues, and corrosion-prevention strategies for naval aircraft. It contains a table that lists typical locations of corrosion on the aircraft. The article also provides examples of aircraft corrosion damage.

Corrosion, fatigue, and their synergistic interactions are among the principal causes of damage to aircraft structures. This article describes aircraft corrosion fatigue assessment in the context of different approaches used to manage aircraft structural integrity, schedule aircraft inspection intervals, and perform repair and maintenance of aircraft in service. It illustrates the types of corrosive attack observed in aircraft structures, including uniform, galvanic, pitting, filiform, fretting, intergranular, exfoliation corrosion, and stress-corrosion cracking. The article discusses geometric parameters such as pit dimensions, surface roughness, loss of metal thickness, and volume increase due to pillowing to quantitatively characterize the types of corrosion. It also explains the two most common fatigue life assessment methods used in the military aerospace industry: fatigue crack initiation and crack growth analysis.

This article describes two analysis methods that are used to determine the life of aircrafts: fatigue life and fracture mechanics methods. The life limiting factors that control the durability of the aircraft are also discussed. The article provides an overview of the various approaches to corrosion identification and prevention. These include safe-life, fail-safe, and damage tolerance approaches. The article discusses their application to the process of extending the life of aircraft structural components.

Damage tolerance is a philosophy used for maintaining the structural safety of commercial transport aircrafts. This article describes the structural evaluations necessary to comply with the regulations contained in the Federal Air worthiness Requirements 25.571 whose guidance is given in Advisory Circular 25.571-1A from the Federal Aviation Administration. It provides an overview of the historical evolution of damage tolerance philosophy and presents a discussion of the design philosophies and a summary of the evaluation tasks for damage tolerance certification.

This article focuses on friction and wear of automotive and aircraft brakes. It provides a comparison of friction and wear behaviors, frictional characteristics, and frictional performance of the friction materials. The article describes the components of brake friction materials and the classifications of brake lining materials. It discusses the effect of formulation compositions and manufacturing processes and the effect of braking operation conditions. The article provides information on aircraft brake linings, which operate under a wide range of kinetic energy conditions. The morphology effect of graphite on automotive brake drum and disk is explained. The article also describes the characteristics of specific wear rates for both normal and local cast iron in automotive brake drums and disk rotors. It provides information on noises, vibrations, and harshness caused by brake pads. The article concludes with information on physical and chemical testing of brakes and toxicity of brake formulation and regulations.

This article presents the damage tolerance criteria for military composite aircraft structures to safely operate the structures with initial defects or in-service damage. It describes the effects of defects, such as wrinkles in aircraft structures, and the reduction in compressive strength and tensile strength. The article reviews low velocity impacts in aircraft structures in terms of resin toughness, laminate thickness, specimen size and impactor mass, and post-impact fatigue. It explains the tension strength analysis, such as linear elastic fracture mechanics and R-curve methods, to predict the residual strength of the structures.

This article focuses on failure analyses of aircraft components from a metallurgical and materials engineering standpoint, which considers the interdependence of processing, structure, properties, and performance of materials. It discusses methodologies for conducting aircraft investigations and inspections and emphasizes cases where metallurgical or materials contributions were causal to an accident event. The article highlights how the failure of a component or system can affect the associated systems and the overall aircraft. The case studies in this article provide examples of aircraft component and system-level failures that resulted from various factors, including operational stresses, environmental effects, improper maintenance/inspection/repair, construction and installation issues, manufacturing issues, and inadequate design.

High-velocity oxyfuel (HVOF)-applied thermal spray coatings are viable candidates for replacement of hard chrome in numerous applications. HVOF thermal spraying can be used to deposit both metal alloy and cermet coatings that are dense and highly adherent to all the commonly used base metals in airframe structures. This article summarizes the results of materials and component testing. It also presents a cost/benefit analysis of HVOF WC/17Co and WC/10Co4Cr coatings on aircraft landing gear components.

The inclusion of damage tolerance design and a systematic review of design procedures allow the U.S. Air Force to design, manufacture, and maintain systems that are structurally safe and economically prudent. After a brief introduction of fracture mechanics, this article describes the particular aspects that relate to damage tolerance in aircraft design. It discusses the use of fracture mechanics as a method of predicting failure, understanding failure mechanisms, and suggesting inspection methods to protect against failure in pressure vessels. Various programs of U.S. Air Force to design aircraft structure, namely, airframe structural integrity programs, engine structural integrity program, and mechanical subsystems structural integrity program are also discussed.

Mechanical properties are described as the relationship between forces (or stresses) acting on a material and the resistance of the material to deformation (i.e., strains) and fracture. This article briefly introduces the typical relationships between metallurgical features and the mechanical behavior of metals. It explains the deformation and fracture mechanisms of these metals. Typical properties measured during mechanical testing related to these deformation mechanisms and the microstructures of metals are discussed. The article reviews the various factors that affect the deformation response of the metal: strain rate, temperature, nature of loading, stress-corrosion cracking, and presence of notches.

The quality of brazed stainless steel joints depends on the selection of the brazing process, process temperature, filler metal, and the type of protective atmosphere or flux. This article provides a detailed discussion on the applicability and brazeability of stainless steel and lays an emphasis on the selection of suitable filler metal, brazing processes, and its corresponding furnace atmosphere for brazing different grades of stainless steel. The types of brazing processes include torch brazing, furnace brazing in different atmospheres (dissociated ammonia, dry hydrogen, and vacuum atmosphere), dip brazing in salt bath, and high-energy-beam brazing. A complete list of the typical compositions and properties of standard brazing filler metals for brazing stainless steel is also provided.

This article presents an introduction to brazing, including information on its mechanics, advantages, and limitations. It reviews soldering with emphasis on chronology, solder metals, and flux technology. The article also provides useful information on mass, wave, and drag soldering. It presents a table which contains information on the comparison of soldering, brazing, and welding.

This article describes the physical principles of brazing with illustrations and details elements of the brazing process. The elements of brazing process include filler-metal flow, base-metal characteristics, filler-metal characteristics, surface preparation, joint design and clearance, temperature and time, rate and source of heating, and protection by an atmosphere or flux. The article explains the different types of brazing processes: manual torch brazing, furnace brazing, induction brazing, dip brazing, resistance brazing, infrared (quartz) brazing, exothermic brazing, electron-beam and laser brazing, microwave brazing, and braze welding.

Soldering is defined as a joining process by which two substrates are bonded together using a filler metal with a liquidus temperature. This article provides an overview of fundamentals of soldering and presents guidelines for flux selection. Types of fluxes, including rosin-base fluxes, organic fluxes, inorganic fluxes, and synthetically activated fluxes, are reviewed. The article describes the joint design and precleaning and surface preparation for soldering. It addresses some general considerations in the soldering of electronic devices. Soldering process parameters, affecting wetting and spreading phenomena, such as temperature, time, vapor pressure, metallurgical and chemical nature of the surfaces, and surface geometry, are discussed. The article also describes the applications of furnace soldering, resistance soldering, infrared soldering, and ultrasonic soldering. It contains a table that lists tests commonly used to evaluate the solderability properties of selected soldered components.

Affordability is the key issue facing design engineers and manufacturers of composite components for current and next-generation aircraft, spacecraft, propulsion systems, and other advanced applications. This article describes the software tools available for modeling and analyzing costs associated with design and manufacturing options for advanced composites programs. It presents an example of a composite exhaust nozzle shroud where the design and manufacture options were analyzed and adjusted, based on the use of cost analysis tools. The article also lists some of the attributes found in various cost modeling software and the potential cost benefits.