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针对火箭设计过程中的气动特性计算,对计算流体力学软件FASTRAN进行二次开发。在C++语言环境下编写火箭气动设计平台中FASTRAN自动化批处理模块。用户使用此模块输入作业的关键参数,自动批量生成脚本文件,并从后台加载计算进程,使用脚本功能自动控制参数设置和计算过程,完成后导出气动力与气动载荷数据,以内置格式自动生成结果报告。这一过程代替人工操作,减少了工作量,提高了设计效率。以两种火箭构型为例,计算并分析得出不同状态下的升、阻力系数和压心位置随马赫数的变化规律。计算结果与实验数据吻合良好,误差在可接受范围内,可以为火箭的初步设计提供参考和依据。
Aiming at the aerodynamic characteristics calculation in rocket design process, the second development of FASTRAN is carried out. In the C + + language environment to write rocket pneumatic design platform FASTRAN automated batch processing module. Users can use this module to enter the key parameters of the job, automatically generate script files in batches, load the calculation process from the background, use the script function to automatically control the parameter setting and calculation process, and then export the aerodynamic and pneumatic load data to generate the result in built-in format automatically report. This process instead of manual operation, reducing the workload and improve the design efficiency. Taking two kinds of rockets configuration as an example, the law of rising and dragging resistance and the location of pressure center with Mach number are calculated and analyzed. The calculated results are in good agreement with the experimental data and the error is within the acceptable range, which can provide reference and basis for the preliminary design of the rocket.