嵌金属丝端面燃烧发动机非平行层燃面退移与参数辨识

Parameter Identification of Nonuniform Burning Effect of End-Burning Solid Rocket Motors with Embedded Wires

针对嵌金属丝端面燃烧发动机试验曲线中,难以使用平行层退移理论来解释和预测的一类异常压强峰进行了研究。定性地确定了嵌金属丝端面燃烧发动机中可能引起非平行层退移的因素,运用准一维稳态流场模型、快速近似传热分析和Level set方法,对这些因素造成的影响进行定量的参数辨识,从而来解释和预测发动机试验曲线中所出现的异常压强峰。结果表明:根据参数辨识结果进行的仿真所输出的曲线与试验曲线高度吻合,成功复现了平行层燃烧理论所无法预测的压强峰值。该方法具有通用性,可直接应用于类似发动机的内弹道预示。

A kind of abnormal pressure peak which cannot explain or predict such pressure peaks reasonably by the commonly-used parallel combustion law in experimental pressure curves of end-burning solid rocket motors with embedded wires is studied.The factors that may cause the grain to burn nonuniformly are determined qualitatively.Then,a burning model,combining with the quasi-one-dimensional steady flow model,a fast heat transfer approximation model,and the level set method,is established.Parameter identification is invoked to find optimal parameters for the model,under the criterion of fitting the simulation result to the experimental ones.The results show that the final outputs are highly consistent with the experimental curves,and the abnormal pressure peak,which cannot be explained via the parallel combustion law,is successfully reproduced.The method proposed by this article is universal enough to be applied to the performance predicting of similar solid rocket motors.