Corrosion and Stress Corrosion Testing of Aerospace Vehicle Structural Alloys
Corrosion and Stress Corrosion Testing of Aerospace Vehicle Structural Alloys

Author: Russell Wanhill

Publisher: Springer

Published: 2018-05-24

Total Pages: 73

ISBN-13: 3319895303

DOWNLOAD EBOOK

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.

Comparison of Stress Corrosion Cracking Properties of Several Aircraft Structural Alloys
Comparison of Stress Corrosion Cracking Properties of Several Aircraft Structural Alloys

Author: JT. Ryder

Publisher:

Published: 1978

Total Pages: 9

ISBN-13:

DOWNLOAD EBOOK

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 Testing of 7079-T6 Aluminum Alloy in Various Environments
Stress Corrosion Testing of 7079-T6 Aluminum Alloy in Various Environments

Author: B. W. Lifka

Publisher:

Published: 1967

Total Pages: 21

ISBN-13:

DOWNLOAD EBOOK

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.

The Fatigue in Aircraft Corrosion Testing (FACT) Programme
The Fatigue in Aircraft Corrosion Testing (FACT) Programme

Author: R. J. H. Wanhill

Publisher:

Published: 1989

Total Pages: 330

ISBN-13:

DOWNLOAD EBOOK

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.