Research on Ablation Device Suitable for Thermal Protection System of Solid Rocket Ramjet

In solid rocket propulsion systems, overload effects induced by aircraft maneuvers can lead to gas accumulation in the afterburning chamber, resulting in severe localized ablation of thermal insulation layers and significantly compromising overall operational stability. Traditional ablation experimental methods (e.g., oxyacetylene and plasma ablation) exhibit poor correlation with the actual thermal environments in solid rocket ramjets, thereby posing substantial challenges for simulating real operational conditions. To address this issue, an oxygen-kerosene engine-based ablation device was developed. Methodologically, the CEA-optimized oxygen-to-fuel ratio (3.5) enabled authentic combustion simulation, while 3D compressible flow modeling (Ansys Fluent 2020 R2) quantified critical parameters such as chamber pressure and achieved precise control of surface temperature. Ablation experiments were conducted on diverse ablative materials using this device, yielding a maximum error in mass ablation rate of only 5.67%. This demonstrates the high accuracy of the device, which meets the requirements for ablation experiments. This reliable simulator (with an error <6%) provides a validated platform for high-fidelity evaluation of ablation performance in maneuverable solid rocket ramjets.