Search Results for fuselage sheet

Alloy 2198 is an Al-Cu-Li alloy that is used in combination with 2196-T8 stringers for the fuselage skins of the Bombardier C-Series. This datasheet provides information on composition limits of the alloy 2198 and provides a performance comparison of 2198-T8 and 2024-T351 alloys.

Alloy 6156 is an Al-Si-Mg-Cu-Mn weldable alloy, developed for the lower portion of the fuselage, which required a T6 temper strength level and high damage tolerance properties. This datasheet provides information on key alloy metallurgy of this 6xxx series alloy. Fatigue crack growth and material toughness for various thicknesses of alloy 6156 clad T62 are illustrated.

This datasheet provides information on composition limits, processing effects on mechanical properties, and applications of alloy 2524. A comparison of strength minimums and typical damage tolerance properties for Alclad 2524-T3 with Alclad 2024-T3 plate is also provided.

The extrusion and sheet alloy 6056 was developed to provide weldable thin extrusions with an excellent balance between high strength and corrosion resistance. This datasheet provides information on composition limits, processing effects on mechanical properties, and applications of this 6xxx series alloy. It provides a material performance comparison of aluminum alloys 6056-T6511 with 2024-T3511 and 6056-T8511 with 2024-T3511.

This datasheet provides information on key alloy metallurgy and applications of Alclad 2029. It contains tables that present statistically determined mechanical property minimums for Alclad 2029-T8 sheet and plate. The plane stress fracture toughness and fatigue crack growth resistance of alloys 2029 and 2024 are illustrated.

Alloy 2055 is an Al-Cu-Li alloy developed as a replacement for high-strength 7xxx and 2xxx alloys in applications such as fuselage stringers and floor beams. This datasheet provides information on its key alloy metallurgy and illustrates the damage tolerance of 2055-T84 extrusions and 7xxx extrusions.

Alloy 6013 is a high-strength Al-Mg-Si-Cu alloy, developed for extruded automotive bumpers. This datasheet provides information on key alloy metallurgy, processing effects on physical, tensile, static and fracture properties, and fabrication characteristics of this 6xxx series alloy.

The aluminum alloy 7099 is a Kaiser aluminum high-strength Al-Mg-Zn-Cu alloy with zirconium that offers a less quench-sensitive alloy for properties in thicker sections for airframe structures such as wing ribs, spars, and skins, as well as fuselage frames and floor beams. This datasheet provides information on key alloy metallurgy and processing effects on mechanical properties of this 7xxx series alloy.

The primary motivation for the insertion of metal-matrix composites (MMCs) into aeronautical systems is the excellent balance of specific strength and stiffness offered by MMCs. This article provides information on the aerostructural, aeropropulsion, and aeronautical subsystem applications of MMCs. The applications include ventral fin, fuel access door covers, helicopter blade sleeve, fan exit guide vane, nozzle actuator piston rod, nozzle actuator links, T-1 racks, and hydraulic manifold.

The development of aluminum alloys has progressed along two tracks: heat treatable and non-heat treatable. The Aluminum Association alloy composition limits and product temper are defined for major alloying elements. This article summarizes the historical evolution of the different series of wrought aluminum alloys (1xxx to 8xxx) and discusses their applications based on the alloying system introduced by the Aluminum Association.

This datasheet provides information on composition limits for aluminum alloys 7150 and 7050, and processing effects on mechanical properties of alloy 7150-T7751 plate and 7150-T77511 extrusions.

This datasheet provides information on key alloy metallurgy, mill product specifications, processing effects on physical and mechanical properties, and applications of high-strength aerospace alloys 2024 and Alclad 2024. It contains tables that list values of tensile property limits for 2024 sheet, plate, and round product forms. Figures illustrate the effect of stretching and aging on toughness of the 2024 sheet and the effect of temperature on tensile properties of 1.0 mm thick Alclad 2024-T3 sheet.

Shot peen forming is a manufacturing process in which local compressive residual stresses form thin sheet metals and structural components in one or more dimensions. This article discusses the principle of the process with an emphasis on fundamental mechanisms. It presents the basic considerations in the simulation of shot peen forming and provides information on single impact and multiple-impact peening simulations. The article describes the equipment and tooling used in the process. It also analyzes the influence of process parameters on shot peen forming and illustrates possible shapes and contours, which are producible by shot peen forming. The article concludes with a table that presents typical peen forming applications in the aircraft and aerospace industries.

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 describes the commonly observed forms of airplane corrosion, namely: general corrosion, exfoliation corrosion, pitting corrosion, microbiologically induced corrosion, galvanic corrosion, filiform corrosion, crevice corrosion, stress-corrosion cracking, and fretting. It discusses the factors influencing airplane corrosion from the manufacturing perspective: design, manufacturing, and service-related factors. The article explains the collection of corrosion data and provides an overview of the implementation and evolution of airline corrosion prevention and control programs and directions being considered in the design for corrosion prevention of airplanes.

The extrusion alloy 7349 was developed by Pechiney and introduced in 1994 to provide higher strength properties than incumbent 7x75 and 7150 alloys. This datasheet provides information on composition limits and processing effects on mechanical properties of this aluminum alloy. Performance comparisons of alloys 7349-T6511 with 7175-T76511 and 7349-T7651 with 7175-T77511 are also illustrated.

Alloy 7097 is a quench insensitive Al-Mg-Zn-Cu-Zr alloy engineered for the most advantageous combination of strength, corrosion resistance, and fracture toughness in thick structural applications. This datasheet provides information on key alloy metallurgy of alloy 7097 and processing effects on mechanical properties of alloy 7097-T7651 plate.

This article discusses the fundamental variables involved in fatigue-life assessment, which describe the effects and interaction of material behavior, geometry, and stress history on the life of a component. It compares the safe-life approach with the damage-tolerance approach, which employs the stress-life method of fatigue life assessment. The article examines the behavior of three different metallic materials used in the design and manufacture of structural components: steel, aluminum, and titanium. It also reviews the effects of retardation and spectrum load on component life. The article concludes with case studies of fatigue life assessment from the aerospace industry.

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.