Solid Rocket Motor Throat -Hafnium Carbide

Because carbon/carbon (C/C) composites have superior high-temperature thermal physical and mechanical properties compared with other materials, they are currently the first choice for solid rocket motor nozzle throats. When the engine is working, the C/C composite rocket throat will be destroyed by the erosion and ablation of the heat flow of high temperature, high pressure, high speed and containing corrosive particles in the harsh thermal environment, which is manifested by the expansion of the throat diameter, the rough and uneven surface, the irregular profile, etc., which will affect the working pressure of the engine and decrease the efficiency of the nozzle.
Example: When a certain type of weapon system nozzle throat lining carbon matrix is ​​added with 8%-10% of the HfC material produced by our company, the ablation resistance of the HfC-C/C composite material can be greatly improved. HfC contributes to the ablation resistance of HfC-C/C composite throat lining mainly in two aspects: First, because HfC preferentially reacts with oxygen during the high temperature ablation process to form HfO2 at the ablation temperature of 3500 ℃, it effectively prevents oxidation of the carbon matrix and carbon fiber in the composite material by the aerobic atmosphere; Second, because HfC has high strength and hardness, it effectively improves the overall resistance to mechanical abrasion and scouring of the material.The mechanical erosion caused by the gas to the throat lining of the inner surface is effectively suppressed. Obviously, the ablation resistance of the Hf CC/C composite material increases with the increase of the Hf C content. The experimental results show that when the HfC content reaches 8%-10%, the line ablation rate of the HfC-C/C composite throat lining will appear approximately constant and stable ablation stage. Under the test conditions of the solid rocket engine, the HfC-C/C composite throat lining has good ablation resistance.