STP821: Application of Laboratory Test Data to Engineering Design

    Simenz, RF
    Department Manager, Design Specialist, and Research Scientist, Materials and Processes, Lockheed-California Company, Burbank, Calif.

    Pengra, JJ
    Department Manager, Design Specialist, and Research Scientist, Materials and Processes, Lockheed-California Company, Burbank, Calif.

    Langenbeck, SL
    Department Manager, Design Specialist, and Research Scientist, Materials and Processes, Lockheed-California Company, Burbank, Calif.

    Pages: 20    Published: Jan 1984


    Abstract

    The use of currently available stress corrosion threshold data in design is discussed. Examples of service failures are detailed for parts which laboratory data have assisted in determining the cause of failure and resolution of the problem.

    Stress corrosion test results of over 300 high-strength steel specimens are summarized. Specimens were tested by bend and axial tension loading and exposed to high humidity and alternate immersion in salt water. A comparison of 4340 and 300M alloys and the effect of product form, grain direction, part size, and stress concentration on the stress corrosion characteristics of these high-strength alloys are made. Methods for the use of these data and other published data are outlined. This use includes original design as well as analysis efforts to extend the service life of existing aircraft. Engineers' future needs for stress corrosion data point to the new-technology aluminum alloys and extended crack growth data under meaningful environments and loading conditions.

    Keywords:

    atmospheric stress corrosion tests, stress corrosion threshold, stress corrosion cracking, high-strength steels, aluminum alloys, stress concentration, forging, bar, cadmium plating, chromium plating, crack propagation, airframe landing gears, failures, inclusions, grinding, residual stresses


    Paper ID: STP34426S

    Committee/Subcommittee: G01.05

    DOI: 10.1520/STP34426S


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