To validate the reusable technology for liquid rocket engine thrust chamber

the fluid-structural coupling method was adopted to simulate the effect of thrust chamber inner wall material

closeout thickness and regenerative cooling channel aspect ratio on the usable life of thrust chamber inner wall.Through computation

the stress and strain distribution of thrust chamber wall at different stage of each cycle under different inner wall materials

closeout thicknesses and cooling channel aspect ratios were obtained

and a post processing method was applied to predict the damage of the thrust chamber inner wall.The results show that the use of high yield strength inner wall material with reasonable ductility

low-stiffness closeout and high aspect ratio cooling channel can decrease the damage of thrust chamber inner wall and extend the usable life the thrust chamber.