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Selective Catalytic Reduction (SCR) processes have been one of the most widely used denitration methods at present and the property of low tempreture catalyst becomes a hot research. The Mn-Ce/TiO2 catalyst was prepared by incipient impregnation method. The influence of load capacity, reaction temperature, O2 content, etc. on denitration were studied by a fixed bed catalyst reactor with ammonia gas. Results showed that catalyst with load capacity 18% performed high NO removal rate of 90% at conditions of reaction temperature 160°C, low space velocity, NH3/NO molar ratio 1: 1, O2 concentration 6%.

The ablative performance of the C/SiC ceramic matrix composite material is studied experimentally using a experimental system based on solid rocket motor and liquid rocket engine in this paper. It is mainly studied how the ablative performance is influenced by ablation time, particle and temperature. It is indicated that the ablative performance decays with longer ablation time. The ablation becomes acute when the temperature is higher than 2973K, and the higher temperature, the more significant ablation. In addition, a large amount of vapor increases the thermochemical ablation of the material.

To provide the test method for thermal shock resistance of throat insert material in rocket motor design, an experimental method with a SRM of scale down was developed to simulate the thermal load of full-size rocket motor’s throat insert. The test guaranteed the consistency of propellant、chamber pressure 、rate of ignition pressurization and the contour of the surface of throat insert with full-size rocket motor, and make a compromise of condition of throat insert at the same time. This method had well reappearance of the fracture failure of throat insert of a full-size rocket motor, which proved the feasibility of the test method to a certain extent. A comparison test for thermal shock resistance of two different composite materials was carried out. The experimental results indicate that two reserve C/C composite materials had good thermal shock resistance than three directions woven C/C composite material which used in the motor of failure, and the performance of carbon fabric pierced C/C composite material was better than no woven fabric pierced C/C composite material in some sort.