The application discloses a
combustion chamber structure for limiting the shrinkage and deformation of a
head surface of a
propellant, which comprises a
propellant column, a shell with an insulating layer, and a lining layer, and further comprises an insulating ring, which is arranged at the head of the
combustion chamber and is bonded to the shell with the insulating layer by means of an
adhesive, and the
propellant column is bonded to the shell with the insulating layer and the insulating ring through the lining layer. By arranging the insulating ring with a limiting function at the
head surface of the
combustion chamber, the radial shrinkage and deformation of the
head surface are effectively prevented, so that the
assembly interference problem between the inner surface of the propellant column and an ignition device due to the solidification deformation of the inner surface of the propellant column is avoided, the danger caused by the artificial shaping of the head surface is avoided, meanwhile, the gap formed between the insulating ring and the ignition device can effectively prevent the ignition device from being ablated and falling off, and then the thrust and pressure
oscillation phenomenon caused by the
ablation and falling off of the ignition device is avoided, which is favorable for improving the working efficiency of the
solid rocket engine, and the process is simple, the universality is high, the production and maintenance costs are reduced, and the cost reduction and benefit increase are realized.