Structural design and material usage of airframe and dynamic components are investigated with regard to reducing vulnerability from small arms fire and improving crash-worthiness; design flight operating conditions and relationship to critical structural loadings are investigated; it is found possible to reduce flight loadings to 50% static level for airframe, 85% fatigue level for main rotor, and to 50% fatigue level for control system; use of material having high fracture toughness can appreciably improve damaged strength so that order of 70% residual strength is attained for critical areas; schematic structural diagram of these areas and design features that can reduce vulnerability and improve crashworthiness. (08697)
Vulnerability and crashworthiness in design of rotary wing vehicle structures
SAE Paper
SAE Meeting ; 1968 Military
1968
20 pages
Conference paper
English
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Vulnerability and Crashworthiness in the Design of Rotary Wing Vehicle Structures
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