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本文致力于用固体火箭发动机计算机自动设计程序 PAPAO 进行阿里安5固体火箭友动机初步设计的研究。PAPAO 是在几年前首次研制的军用程序,并于最近得到扩展,使之适合于阿里安5固体火箭发动机壳体的要求和技术。本文中描述的扩展工作主要与壳体段和推进剂药柱的设计有关,并强调了为使计算时间和准确性之间保持合适的平衡在模型中采用的一些假设。这些模型使确定发动机的结构成为可能,它们满足所规定的推力-时间曲线的主要特性,当然也满足发动机的其他要求和约束条件。文中叙述了典型参数研究的结果,以证明 PAPAO 程序的功能。即在最优化过程中,它是一个主要工具,而且还能给设计者提供技术设计工作的原始依据。
This paper is devoted to the research on the preliminary design of Arion 5 solid rocket motive using the PAPAO (Solid State Rocket Engine Computer Automatic Design Program). PAPAO, the military program first developed several years ago, was recently expanded to suit the requirements and technology of the Allianz 5 solid rocket motor housing. The extensions described in this article are primarily concerned with the design of shell sections and propellant grains and emphasize some of the assumptions used in the model to maintain the proper balance between calculation time and accuracy. These models make it possible to determine the structure of the engine, which satisfies the main characteristics of the specified thrust-time curve and, of course, other requirements and constraints of the engine. The article describes the results of a typical parametric study to demonstrate the function of the PAPAO program. That is, in the optimization process, it is a major tool, but also to provide designers with the original basis for technical design work.