NASA/SP-8082, NASA SPACE VEHICLE DESIGN CRITERIA (STRUCTURES): STRESS-CORROSION CRACKING IN METALS (AUG-1971)

NASA/SP-8082, NASA SPACE VEHICLE DESIGN CRITERIA (STRUCTURES): STRESS-CORROSION CRACKING IN METALS (AUG-1971)., This monograph presents criteria and recommends practices to prevent stress-corrosion cracking from impairing the structural integrity and flight-worthiness of space vehicles. Criteria and recommended practices for preventing stress-corrosion cracking from impairing the structural integrity and flightworthiness of space vehicles are presented. The important variables affecting stress-corrosion cracking are considered to be the environment, including time and temperature; metal composition, and structure; and sustained tensile stress. For designing spacecraft structures that are free of stress-corrosion cracking for the service life of the vehicle the following rules apply: (1) identification and control of the environments to which the structure will be exposed during construction, storage, transportation, and use; (2) selection of alloy compositions and tempers which are resistant to stress-corrosion cracking in the identified environment; (3) control of fabrication and other processes which may introduce residual tensile stresses or damage the material; (4) limitation of the combined residual and applied tensile stresses to below the threshold stress level for the onset of cracking throughout the service life of the vehicle; and (5) establishment of a thorough inspection program.