基于三维模型空间离散的固体发动机装药燃面计算方法  

A Three-dimensional Model Spacial Discretization based Propellant Grain Burning Surface Approach

作　　者：费阳 解红雨 张治宇 冯翔 Fei Yang;Xie Hong-yu;Zhang Zhi-yu;Feng Xiang(People’s Liberation Army No.96901,Beijing,100094)

机构地区：[1]中国人民解放军96901部队,北京100094

出　　处：《导弹与航天运载技术》2022年第3期32-36,共5页Missiles and Space Vehicles

摘　　要：装药燃面计算是固体发动机优化设计过程中的重要环节,通用、高效、准确的燃面计算方法有利于提高固体发动机设计效率和设计精度。针对传统Level-set燃面计算方法药型定义复杂、精度不高等缺点,结合SolidWorks三维实体建模和多线程并行计算技术,通过最小符号距离方法对三维装药进行精确离散化表达,实现快速、准确实现复杂三维装药燃面推移计算。计算结果与CAD实体造型法结果一致。与传统方法相比,该方法无需通过代码定义药柱构型和迭代计算,可直接用于不同固体发动机药柱设计。The propellant grain burning surface design occupies an essential role in the solid rocket motor design process and it is believed that a general,efficient and accurate burning surface computing method is vital in promoting the design efficiency and accuracy.The level set burning surface calculation method has been recognized as a general and robust approach,however,a lack of flexibility in mathematically describing the propellant geometry undermines its efficiency and accuracy.In order to eliminate the technical obstacles,depending on the Solid Modeling,Minimum Distance Function(MDF)and parallel computing technologies,a new method is provided which is able to conveniently and accurately provide discrete description to the propellant grain geometry and therefore fast and accurate burning surface calculation can be achieved.

关 键 词：固体发动机 燃面计算 空间离散 最小符号距离 多线程并行计算 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]