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介绍了一种战术火箭固体发动机药柱温度测量技术,测量系统主要由一个温度传感器和一个与嵌入式计算机相连的特殊的测量单元组成。该系统随某型号发动机进行了温度循环试验和温度冲击试验,同时用ANSYS软件对试验过程进行了模拟计算,试验测量结果与计算结果符合很好。还提出了药柱等效温度概念和计算方法,并给出了通过发动机外壁温度和药柱内壁温度计算等效温度的拟合公式。发动机最后进行了地面试验,获得圆满成功,证明该测量系统是可靠的,具有实用价值。
A kind of tactical rocket solid cylinder temperature measurement technology is introduced. The measuring system mainly consists of a temperature sensor and a special measuring unit connected with the embedded computer. The system with a certain type of engine temperature cycling test and temperature impact test, at the same time using ANSYS software to simulate the test process, test results and calculated results in good agreement. The concept and calculation method of the equivalent temperature of the grain are also proposed and the fitting formula for calculating the equivalent temperature by the temperature of the outer wall of the engine and the inner wall temperature of the grain is given. Finally, the engine ground test, a complete success, that the measurement system is reliable and has practical value.