翼柱形药柱燃面退移过程的变量化设计方法

Burning surface regression analysis of finocyl grain configuration by variational design method

固体火箭发动机翼柱形药柱燃面拓扑结构复杂,现有燃面退移仿真算法存在耗费时间长、燃面面积计算不准确及算法通用性差等问题。针对以上问题,采用变量化约束草图驱动的设计方法,通过执行图形比例变换,缩小药柱尺寸规模,还研究了一种新的颜色标识燃面算法,避免燃面统计疏漏与重复,并提出了适合单组翼、大小翼、前后翼等多种翼柱形药柱燃面退移仿真的通用解决方案。经实例验证,执行比例变换,使得仿真时间缩短了31.8%,仿真结果与试验结果最大误差为3.1%。该方法能快捷准确处理各种翼柱形药柱,并已获得了应用。

As having complex burning surfaces topology finocyl grain regression analysis has such issues as long simulation time,the calculation of burning surfaces area not accurate and no universal algorithms.In order to solve the issues above,variational design method is adopted.Scaling transformation is performed to decrease the geometric size of grain to save computation time.A new color-marked burning surface area algorithm is proposed to avoid the omission and repetitioeness in the process of calculating burning area.The universal solution of regression analysis for single group fins,front-rear fins and size distribution fins finocyl grain is also summarized.The simulation results show that： 31.8% of simulation time is reduced through the graphic scaling transformation and the maximum error between the results of proposed method and experiment results is only 3.1%.This method can process a variety of finocyl grains accurately and rapidly,and has got some application in home solid rocket motor design.