Abstract: To deal with the problem of propellant burning surface regression coupled with flow field in a sin.gle-pulse solid attitude control motor，a theoretical basis of the coupling method was given to establish a bidirec.tional coupled simulation model based on dynamic mesh. Face-offsetting method was utilized for modeling thepropellant burning surface regression. The mesh was optimized by mesh smoothing and rebuilding techniques forsolving the deformation of fluid meshes. The coupling process was calculated by using loosely coupled method. Anumerical coupled simulation between internal flow field and burning surface regression for the single-pulse solidattitude control motor used in the PAC-3 extended range interceptor missile was carried out by the coupling meth.od. The internal trajectory and other various parameters were obtained. The results are consistent with related ex.perimental results. The maximum relative error of chamber pressure is 3.96%. Face-offsetting method can effec.tively track the regression of the propellant burning surface. The coupled method can accurately and stably simu.late the coupling process between the internal flow field and the propellant surface regression，which can be used for providing an effective solution to the multi-physics coupling of single-pulse solid attitude control motor.

Key words: Single-pulse； Solid attitude control motor； Burning surface regression； Face-offsetting method；Coupled simulation

摘要： 为解决单脉冲固体姿态控制发动机内流场与推进剂燃面退移耦合的问题，给出了耦合方法的理论基础，建立了基于动网格的双向耦合模型。采用面偏移法处理燃面退移过程，利用网格平顺与网格重建技术优化网格，解决网格变形问题；通过松耦合方式进行耦合计算。针对 PAC-3增程拦截弹使用的单脉冲固体姿态控制发动机，进行了内流场与推进剂燃面退移耦合数值模拟，得到了该发动机内弹道特性曲线及其它性能参数。结果表明， PAC-3单脉冲固体姿态控制发动机仿真结果与相关实验结果吻合较好，计算得到燃烧室压强最大相对误差为 3.96%。面偏移法能够有效追踪推进剂燃面，建立的耦合方法能够对内流场与推进剂燃面退移耦合过程进行准确稳定的模拟，为单脉冲固体姿态控制发动机多物理模型耦合模拟提供了有效的解决方案。

关键词: 单脉冲；固体姿态控制发动机；燃面退移；面偏移法；耦合数值模拟