Some Aerospace Applications of 7075 (B95) Aluminium Alloy

This chapter starts with a brief overview of the historical development of aerospace aluminium alloys. This is followed by a listing of a range of current alloys with a description of the alloy classification system and the wide range of tempers in which Al alloys are used. A description is given of the alloying and precipitation hardening behaviour, which is the principal strengthening mechanism for Al alloys. A survey of the mechanical properties, fatigue behaviour and corrosion resistance of Al alloys is followed by a listing of some of the typical aerospace applications of Al alloys. The Indian scenario with respect to production of primary aluminium and some aerospace alloys, and the Type Certification process of Al alloys for aerospace applications are described. Finally there is a critical review of some of the gaps in existing aerospace Al alloy technologies.

Materials Science and Engineering A-structural Materials Properties Microstructure and Processing, 2000

Driven by the increasing requirements from aircraft producers, Hoogovens Aluminium Rolled Products GmbH, together with Hoogovens Research & Development, has enhanced the property combinations of their aircraft materials. For these types of material, optimised processing routes as well as new alloy chemistries have been investigated. Whilst retaining the strength levels required by the aerospace industry, new processing routes offer major improvements in ductility, toughness, fatigue performance and in reduction of residual stress in large dimension plate and sheet products. A further goal of investigating new alloy chemistries is the trend towards new joining techniques such as welding and brazing for aircraft structures. These new joining techniques require different property combinations compared to the conventional aerospace alloys. In parallel to these improved processing routes and new alloy developments, new ultrasonic inspection techniques have been developed, which are able to predict fatigue performance and residual stress in thick plate products.

Progress in Aerospace Sciences, 1996

Aluminum alloys have been the primary material of choice for structural components of aircraft since about 193C. Although polymer matrix composites are being used extensively in high-performance military aircraft and are being specified for some applications in modern commercial aircraft, aluminum alloys are the overwhehning choice for the fuselage, wing, and supporting structure of commercial airliners and military cargo and transport. Well known performance characteristics, known fabrication costs, design experience, and established manufacturing methods and facilities, are just a few of the reasons for the continued confidence in aluminum alloys that will ensure their use in significant quantities for the rest of this century and likely well into the next one. But most significantly, there have been major advances in aluminum aircrat~ alloys that continue to keep them in a competitive position. In the early years aluminum alloys were developed by trial and error, but over the past thirty years there have been significant advances in our understanding of the relationships among composition, processing, microstructural characteristics and properties. This knowledge base has led to improvements in properties that are important to aircraft applications. Thi~; review covers the performance and property requirements for airframe components in current aircraft aad describes aluminum alloys and product forms which meet these requirements. It also discusses the structure/property relationships of aluminum aircraft alloys and describes the background and drivers for the development of modern aluminum alloys to improve performance. Finally, technologies under development for future aircraft are discussed. CONTENTS 7.1. Market driven materials development 7.2. Recent advances and applications of 2XXX and 7XXX alloys 7.3. Recent advances and applications of aluminum-lithium alloys 132 REFERENCES 168 170 170 Application of modem aluminum alloys to aircraft

2019

Conventionally processed aluminium alloys (i.e., those in the 2xxx/6xxx/7xxx series) are currently used in the aerospace sector due to their capabilities of withstanding extreme conditions. Additive manufacturing produces complex net-shape and light-weight parts, with high versatility on design and improved functionalities, which is extremely attractive to the aerospace industry. Thermal characteristics in the selective laser melting (SLM) process are critical for high-strength aluminium alloys because they are susceptible to hot tearing and hot cracking, also during conventional processing. On the contrary, the currently SLM-processable aluminium alloys (i.e., AlSi10Mg) do not meet the mechanical requirements for aeronautical applications. In this work, the development of different high strength Al alloys processable for SLM is described. Two approaches have been taken: (1) to improve the mechanical properties of currently processable aluminium alloys; (2) to avoid hot cracking of ...

Volume 02 Issue 02, 2021

Researchers have turned to search for new materials that will meet all the aerospace industry requirements. When it is almost impossible to achieve this with a single material, composite materials have been studied, and there have been great developments in this field. Many elements are used in aircraft construction, but aluminum is the most preferred due to its low density, good castability, high strength, corrosion resistance, and good fatigue strength. However, its strength and stiffness limit its usability. To solve this problem, aluminum is combined with various elements. Aluminum metal matrix composites are an example of this. Aluminum metal matrix composites are preferred in aircraft applications due to their high specific modulus and good mechanical and thermal properties. This review provides information on the use of aluminum metal matrix composite materials in the aerospace industry.

Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications, 2013

The mechanical behaviour of the commercial aluminium alloys EN AW-5182, EN AW-6016 and EN AW-7021 is investigated at temperatures ranging from 298 to 77 K and strain rates from 1.7 Â 10 À3 to 6.6 Â 10 À2 s À1 . A device that allows testing at cryogenic temperatures is developed and demonstrated, where the specimens are subject to uniaxial tensile loads. The influence of a solution heat treatment for precipitation hardenable alloys is shown. The strain-hardening coefficient is determined and mapped in terms of the experimentally investigated uniform elongation. The experimental data of tested aluminium alloys are compared with EN AW-1050A-H14, which is used as a reference. The effect of the Portevin-LeChatelier effect on ductility and strength is discussed. The Ludwik relationship is adapted to describe materials showing a Portevin-LeChatelier effect.

Combustion Engines, 2024

Possibilities to modify the properties of the AW7075 aluminum alloy for the automotive industry ARTICLE INFO The paper investigated the AW7075 aluminum alloy that is used in the automotive industry. The alloy is widely used, among others, in the production of heads and engine blocks. The possibility of obtaining various properties of the alloy (material states) by appropriate heat treatment (saturation and aging) was demonstrated. The results of strength, hardness, abrasion, and fracture toughness tests of the alloy in the T73, RRA, and HTPP aging treatments, in comparison with the T651 reference state, are presented. The need to select the appropriate parameters of heat treatment in relation to the load conditions of the structural element, especially in elements with notches, was indicated. Depending on the state of the AW7075 alloy, the results prove the wide and diverse possibilities of its use and should be used consciously in the design and production processes of modern automotive drivetrain components.

Industrial laboratory. Diagnostics of materials, 2019

The results of experimental studies of the static strength, fatigue and crack resistance of modern improved aluminum alloys 1163ATV, 1163RDTV, 1441RT1, 1163T, 1163T7, 1161T, V95ochT2, B96-3pchT12., 1973T2 developed at the All-Russian Scientific Research Institute for Aviation Materials (VIAM, Russia); and 2524-T3, 6013-T6 HDT, 2324-T39, C433-T351, 7055-T7751 developed at ALCOA (USA) are presented. Those materials are used in the construction of modern operated and designed aircraft. The experimental data were obtained in testing standard specimens on electro-hydraulic machines MTS (USA), Instron (Great Britain) and Schenk (FRG). The tested specimens were cut from semi-products manufactured according to serial technologies. The mechanical properties of materials under tension (σb, σ0.2, δ), fatigue characteristics, fatigue crack growth rate, stress crack propagation curves under static loading (R-curves), conditionally critical stress intensity factors are determined according to dom...

General Characteristics. The unique combinations of properties provided by aluminum and its alloys make aluminum one of the most versatile, economical, and attractive metallic materials for a broad range of uses-from soft, highly ductile wrapping foil to the most demanding engineering applications. Aluminum alloys are second only to steels in use as structural metals.