Based on the process flow of solid propellant integrated coating technology, the influence of solidification of wound shell with propellant on structural integrity of propellant column is studied. Six propellant structures are proposed, and mathematical and geometric models are built by using finite element software ANSYS. The stress and strain fields of each propellant structure are calculated under 40 C constant temperature curing. The thermal stress states of the TCM column and the differences of curing stress fields of each propellant are analyzed. The curing calculation at 20 ~ 60 °C and the prototype experiment at 20 °C are carried out for one of the drugs. The calculation results show that the main stress is generated in the composite winding layer and the main strain is generated in the heat insulation layer during the curing process. There is a large stress concentration at the hard contact between the charge column and the head, and the maximum stress reaches 15 MPa. The extension of the head and a certain void can effectively control the stress, and the maximum stress can be reduced to 4. 8 MPa. The size of the flower core and the length of the charge column have little effect on the curing stress. The size can be adjusted according to the requirements of the finished product in the actual process.