固体火箭发动机自动化参数设计软件模型与实现

SOFTWARE MODEL AND THE REALIZATION OF AUTOMATIC PARAMETER DESIGN OF A SOLID PROPELLANT ROCKET MOTOR

分析了固体火箭发动机自动化设计的数学模型和设计过程 ,以及设计参数与图形生成模块的数据传递 ,并以某续航发动机设计为例 ,完成了发动机自动化参数设计的软件编制。通过使用该软件对续航发动机的设计和一些方案的论证 ,可知其使用方便 ,把设计者从繁复的计算中解放出来 ,大大提高了设计效率。

Mathematical model and the design process in the automatic parameter design of a solid propellant rocket motor, as well as the data transmission between parameter design and drawing generating modules are analyzed. The automatic design software involves in it some important modules such as mass prediction, choice of propellants, prediction of mass ratio, grain design, external ballistic fitting, internal ballistics, etc. Each module works with each other to complete all tasks in rocket motor design and correction from iteration calculations. Based on the sustainer motors, the parameter design software is programmed. Through the design of the sustainer motor and scheme argument using the software, it is seen that the software frees the designers from complicated work of calculation and enhances the design efficiency.