关键词: 喷管烧蚀计算;固体火箭发动机;复合材料;反应动力化学;参数估计

Abstract: A method combining theoretical model with test results to determine kineticparameters (activation energy and pre-exponential factor) of ablative reactions forcarbon-base materials has been developed.The theoretical model is based on ananalysis of a turbulent boundary layer over a carbon surface with thermo-chemical ablation.The boundary layer equations coupled with surface ablation equations and heat conduction equations are solved simultaneously and numerically and the ablative type needn’t be pre-assumed in the calculation process.Ablation of material with oxido-gas has been tested in an arc-plasma jet which simulates the flow conditions at rocket nozzle throat.Compared computional results from the proposed model with experimental data,the chemical kinetic properties of the ablative reaction are obtained. The chemical kinetic properties of graphite reacting with CO2,as a practical example,was determined in the paper.

Key words: Ablation;Nozzle throat;Solid rocket engine;Composite;Reaction kinetic chemistry;Parameter estimation