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目前,国内外许多学者对侵蚀燃烧现象已作了许多研究,主要可分为实验法和理论法。实验法又可分为试件法和药柱法。试件法虽然可获得较好的精度,但与真实发动机工作条件相比真实性较差;药柱法又有串联发动机法、中止燃烧法和压力-时间曲线分析法,但这些方法的精度较低,只能获得平均燃速。目前还不能用理论法直接求出燃速表达式。为了克服上述方法的不足之处,本文发展了一种固体火箭发动机侵蚀燃速辨识方法。该方法采用控制论中的辨识技术,根据一发试车压力-时间曲线来确定药柱的侵蚀燃速表达式。这种方法的特点是真实性好,能迅速、准确、可靠地获得侵蚀燃速表达式。本文通过对某固体火箭发动机药柱侵蚀燃速关系式的确定,研究和分析了在燃速辨识过程中所遇到的一些问题、获得了在三种装药初温下,以修正的格林公式表示的侵蚀燃迷公式。证实了这种方法在工程应用上的可行性和可靠性。
At present, many scholars at home and abroad have made many researches on the phenomena of erosion and combustion, which can be mainly divided into experimental and theoretical methods. Experimental method can be divided into specimen method and medicine column method. Although the test piece method can obtain better accuracy, it has less authenticity compared with the real working condition of the engine. The columnar method has a series engine method, which stops the combustion method and the pressure-time curve analysis method, but the accuracy of these methods is lower Low, can only get the average burning rate. At present, we can not directly find the combustion rate expression by theoretical method. In order to overcome the shortcomings of the above methods, this paper developed a solid rocket motor erosive combustion rate identification method. In this method, the identification technique in cybernetics is used to determine the erosive combustion rate expression of a pellet according to the pressure-time curve of a test run. This method is characterized by good realism, can quickly, accurately and reliably obtain the erosive combustion rate expression. In this paper, the determination of the burning rate of a solid rocket motor grain erosion, to study and analyze some of the problems encountered in the identification of burning rate, obtained under the initial charge of three kinds of loading, with a modified Green formula Said the erosion of burning fans formula. This method has proved the feasibility and reliability of engineering application.