复杂星孔球形药柱燃面近似解析计算方法

Approximate solution to combustion area of the spherical grain with complex star pore

球形星孔药柱是固体火箭发动机广泛采用的一种药型,多呈现复杂的三维特性。为进行设计参数的快速选择与优化,以一种具有复杂星孔的球形药柱为基础,给出了药柱燃面变化规律的近似解析计算方法,依据该方法能够在设计初期快速计算药柱燃面的变化规律,并能依此进行发动机工作性能预估,进而对设计参数进行调整和初步优化;近似解析方法与三维CAD方法所得到的燃面变化规律基本吻合,燃烧面积最大偏差小于4%。

Spherical star pore grain is widely used in solid propellant rocket motor, and it presents complex three-dimension feature. Based on a complex spherical star pore grain, approximate analytic solution was proposed for rapid optimization and selection of design parameters. The solution can be used for rapidly calculating change law of grain combustion area at the beginning of design, then predicting work performance of motor, finally adjusting and optimizing design parameters. Change law of combustion area obtained with approximate solution agrees well with that with 3D CAD method, and the maximum error is less than 4%