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为研究典型固体推进剂装药的排气羽流特性,采用能量计算星程序和ANSYS-Fluent软件对双基(DB)推进剂、复合改性双基(CMDB)推进剂及硝酸酯增塑聚醚(NEPE)推进剂燃烧及排气羽流场进行了模型构建和求解,获得了羽流温度和羽流流速等特性参数,采用红外热像仪和TDLAS流速测试系统对其进行了实验验证,并将模拟结果与实验结果进行对比.结果表明,流场计算获得3种推进剂的羽流流速分别为1 002.38、1 279.01、1 243.16 m/s.实验中应考虑推进剂羽流流场的非均匀性及实际测试状态与数值模型的一致性;流场计算获得的羽流温度与红外热像仪测试结果定性一致,应改进实验方案获得羽流的真实辐射率,并考虑数值模型的理想化假设带来的偏差.“,”To study the exhaust plume characteristics of three typical solid propellant charge,the construction and solving of model for the combustion and exhaust plume field of three kinds of solid propellants,double-base(DB) propellant,composite modified double-base(CMDB) propellant and NEPE propellant,were performed by the Energy Calculation Star(ECS)program and ANSYS-Fluent software.The plume characteristic parameters,such as plume temperature and plume velocity were obtained.Thermal Infrared Imager and Tunable Diode Laser Absorption Spectroscopy (TDLAS) velocity measurement system were employed to validate the simulation results and the simulation results were compared with the experimental ones.Results show that the plume velocity of the three propllants calculated by low field are 1 002.38,1 279.01,1 243.16 m/s,respectively.In the experiment,the nonuniformity of propellant flow field and the consistency of actual test condition and numerical model should be considered.The plume temperature calculated by the flow field is qualitatively consistent with the test results obtained by Thermal Infrared Imager.The experimental scheme should be improved to obtain the real radiation coefficient and the deviations from the idealized assumptions of the numerical model should be taken into account.