PSI - Issue 40

N.A. Makhutov et al. / Procedia Structural Integrity 40 (2022) 264–274 Nikolay A.Makhutov at al. / Structural Integrity Procedia 00 (2022) 000 – 000

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3

operating torsion time amplitudes of stresses maximum stress

τ

σ а

σ max

nominal stress fracture stress

σ n σ c

yield stress at at temperature t yield stress at room temperature t 0 ultimate strength at at temperature t ultimate strength at room temperature t 0

t y 

0 y 

t u 

0 u 

flows of liquids, (oxygen, hydrogen) and gas combustion products

Ф

t 

increase in material temperature relative narrowing at fracture

ψ с

the ductility of steels in an atmosphere of gaseous hydrogen

ψ cH

Fig. 1. The framework for solving the main problems of the life cycle in the development and operation of a rocket engine.

In terms of the uniqueness of the design, complexity, and importance of the step-by-step solution of the problems of strength, service life, and safety at all stages of the life cycle of rocket and space systems (Fig. 1), a special place was and is still occupied by the problems of design and operation of liquid-propellant rocket engines (LRE) of various types that are distinguished by their power capacity, purpose, and types of fuel and oxidizer employed (Makhutov, 2011; Makhutov, 2013; Makhutov, 2019; Wei Wang, 2019).