ANALYSIS OF STANDARDS FOR THE DESIGN OF SPHERICAL STATIONARY AVIATION OXYGEN CYLINDERS
DOI:
https://doi.org/10.18372/0370-2197.3(112).21619Keywords:
composite materials, strength, liner, cylinder classification, aviation systems, design, mechanical propertiesAbstract
This article presents a comparative analysis of the requirements of industry standard OST 1 03749-74 for stationary spherical aviation cylinders with a capacity of 2–25 liters, designed for an operating pressure of 21 MPa (210 kgf/cm²), intended for storing medical and technical oxygen on board an aircraft, and the international standard ISO 11119-1, which regulates the design, manufacture, and testing of Type 2 refillable composite cylinders with annular fiber wrapping around a metal liner. The objective of this work is to identify the differences between the design schemes of Types 1 and 2 and to justify directions for improving the spherical steel oxygen cylinder. The comparison was conducted using a normative and technical analysis based on criteria such as design scheme, materials, strength calculations, testing, cyclic durability, reliability, service life, and external factors. It was established that OST 1 03749-74 provides for the load to be borne by a solid steel wall and for its strength to be specified based on absolute mechanical characteristics, whereas ISO 11119-1 is based on load distribution between a metal liner and a composite shell, with evaluation based on the criterion of stress in the fiber. The requirements for oxygen equipment are analyzed in detail separately, specifically regarding the degreasing of the internal cavity, protective coatings, and the compatibility of materials with an oxidizing environment. It is shown that linerless composite structures of types 4–5 are not intended for oxidizing gases, whereas type 2 retains a metal barrier between the oxygen and the composite material. Based on a comparison of regulatory requirements and the results of research on metal-composite cylinders, the feasibility of forming a composite shell on a steel liner without changing the operating pressure has been demonstrated. This allows for the redistribution of hoop stresses onto the composite shell and reduces the overall weight of the structure by 15–30% while maintaining strength, safety, and oxygen compatibility.
References
1. OST 1 03749-74. 1974. 7 p.
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