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This SpringerBrief discusses the determination and classification of the ambient temperature corrosion and stress corrosion properties of aerospace structural alloys, with emphasis on (1) aluminium alloys, modern (3rd generation) aluminium‒lithium alloys, stainless steels and titanium alloys and (2) some of the issues involved. Standard /reference data on environmental properties, including corrosion and stress corrosion, are mandatory for the qualification and certification of materials for aerospace vehicles, and also for the design of actual structures and components. Recommendations for further testing and evaluation are given at appropriate points in the text. The book concludes with a summary of the main topics.
Sustained load subcritical flaw growth characteristics of five alloys of interest to aircraft designers were investigated. The aluminum alloy (2024-T851) and steel alloy (18Ni-maraging) were studied in 3.5% sodium chloride solution and high humidity air environments while two of the titanium alloys, Ti-6Al-4V (recrystallized annealed) and Ti-6A1-6V-2Sn (solution-treated and overaged), were also investigated in these environments plus sump tank water. The Ti-6Al-4V (beta) alloy was tested in 3.5% sodium chloride solution. Wide differences between the alloys were noted not only in their cracking rates but also in their responses to similar loads and environments. Specimen thickness was found to have an important effect on stress corrosion susceptibility of the titanium alloys. Many coupons of specific titanium alloys had significant subsurface crack growth without visible surface growth. For these alloys, no precise threshold for stress corrosion cracking could be defined.
Stress corrosion cracking of certain 7079-T6 aluminum alloy aircraft structures involving sustained tensile stress acting in an unfavorable grain direction has occurred sometimes in surprisingly mild environments. The resistance of short-transverse specimens of 7079-T6 products has been evaluated at different levels of applied stress in several different seacoast and inland industrial atmospheres. It was found that the atmosphere was more critical than the generally accepted alternate-immersion test using 3.5 per cent sodium chloride. The results of the outdoor tests are correlated with eight accelerated exposures; and consideration is given to the most suitable laboratory stress corrosion test environment for this alloy. A detailed analysis of the constant deformation methods of stressing is included.
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
In accordance with the mission of AGARD the Structures and Materials Panel (SMP) has always kept an open eye for the possibilities to sponsor collaborative programmes of research. AGARD is unique in its ability to realise the cooperation of laboratories in up to sixteen nations. In this way AGARD distinguishes itself from other international scientific and technical organisations. In the 1970s the SMP decided to embark on collaborative research activities in the area of fatigue. One of the first activities was the Corrosion Fatigue Cooperative Testing Programme (CFCTP), the recursor to the Fatigue in Aircraft Corrosion Testing (FACT) programme. Both programmes are described in this report. Failure by fatigue and degradation by corrosion continue to be major considerations in aircraft design. Environmental effects influence both initiation and propagation of fatigue cracks, and dynamic loading may cause more rapid deterioration of corrosion protection systems. Therefore the conjuoint action of dynamic loading and environmental attack, i.e. corrosion fatigue, requires special attention. Many corrosion fatigue tests have been done on aluminum alloys. However, few included critical structural details like joints, under realistic cyclic load histories and in service-like environments. Even fewer used practical corrosion protection systems. These aspects are specifically addressed bye the CFCTP and FACT programmes. The results provide a significant contribution to the understanding of aircraft corrosion fatigue and should encourage further investigation in this difficult and challenging area of aerospace technology.
The problem of stress corrosion cracking (SCC), which causes sudden failure of metals and other materials subjected to stress in corrosive environment(s), has a significant impact on a number of sectors including the oil and gas industries and nuclear power production. Stress corrosion cracking reviews the fundamentals of the phenomenon as well as examining stress corrosion behaviour in specific materials and particular industries.The book is divided into four parts. Part one covers the mechanisms of SCC and hydrogen embrittlement, while the focus of part two is on methods of testing for SCC in metals. Chapters in part three each review the phenomenon with reference to a specific material, with a variety of metals, alloys and composites discussed, including steels, titanium alloys and polymer composites. In part four, the effect of SCC in various industries is examined, with chapters covering subjects such as aerospace engineering, nuclear reactors, utilities and pipelines.With its distinguished editors and international team of contributors, Stress corrosion cracking is an essential reference for engineers and designers working with metals, alloys and polymers, and will be an invaluable tool for any industries in which metallic components are exposed to tension, corrosive environments at ambient and high temperatures. - Examines the mechanisms of stress corrosion cracking (SCC) presenting recognising testing methods and materials resistant to SCC - Assesses the effect of SCC on particular metals featuring steel, stainless steel, nickel-based alloys, magnesium alloys, copper-based alloys and welds in steels - Reviews the monitoring and management of SCC and the affect of SCC in different industries such as petrochemical and aerospace