Evaluation of the possibility to use composite material in the structure of the rocket stage cryogenic conical tank

Abstract

Reducing mass of the launch vehicle components structure to increase the payload mass launched into orbit is one of the main areas in developing the space services market. Modern designs of the launch vehicles require extremely high fuel mass fraction, which necessitates introduction of the low-density materials. Fuel tanks could count for 70...80% of the total product volume, which results in the development of tanks for the cryogenic fuel obtaining decisive importance in design and development of the new type of launch vehicles. Introduction of the composite materials in designing a cryogenic fuel tank makes it possible to lower its mass by 30% compared to a reference aluminum tank, which, accordingly, allows increasing the inserted payload mass. Review of the methods used in manufacturing the cryogenic composite fuel tanks is presented. Liner manufacturing technology and its material are proposed, taking into account the temperature difference during shaping and its interaction with the cryogenic fuel. Composite material and method for manufacturing the composite tank are selected. Design calculation of the composite cryogenic tank was carried out.