<p>Aerospace applications involve numerous thin-walled revolving parts with complex structures on their inner walls. In pursuit of higher strength and lower weight, these parts are usually made of titanium alloy, nickel-based alloy and aluminum alloy, and the sidewall thickness is very thin. Because of the large diameter, thin wall thickness and easy deformation of these parts, it is a challenge to process them by conventional machining methods. In this study, inwall co-rotating electrochemical machining (ICRECM) is proposed for processing revolving parts such as rocket cabin parts, and the process of machining the complex structure on the inner wall of a rocket cabin part is systematically studied. A mathematical model for predicting the forming contour of the anode is established. The three-dimensional modeling method of the cathode tool for machining the inner wall structure of revolving parts is proposed, and the cathode tool for machining the rocket cabin part is designed. The electrochemical dissolution behavior of 5A06 aluminum alloy is analyzed, and the curve of material removal efficiency is accurately measured by the constant voltage method. A design method of special jet nozzles is presented, and the flow field during the machining process of rocket cabin parts is analyzed. The simulation results show that the flow velocity in most locations of the processing area exceeds 20&#xa0;m/s by using designed jet nozzles. The rocket cabin part meeting the design accuracy was successfully manufactured via ICRECM. The wall thickness of the processed rocket cabin part is 1&#xa0;mm, and the height of the complex structure on the inwall is 8&#xa0;mm. This indicates that the ICRECM process can efficiently and accurately manufacture the complex structure on the inwall of rocket cabin parts.</p>