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Development of an Algorithm and an Integrated Program for the Preliminary Sizing of Liquid propellant Rocket Engines

机译：液体火箭发动机初步定型算法和集成程序的开发

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摘要

In this paper, an algorithm is developed for the design of liquid propellant rocket en gines. Using this algorithm and several databases developed during the project, a pro gram was developed for the conceptual design and preliminary sizing of liquid propellant rocket engines for use in launch vehicles and spacecrafts. The current paper focuses on bi propellant engines with both cryogenic and storable propellant systems. Several different design methods were implemented for the design of each subsystem. Overall, the algorithm results are acceptable when compared to real engine data.
机译：本文提出了一种用于液体推进剂火箭发动机设计的算法。使用该算法和项目期间开发的几个数据库，开发了用于液体运载火箭发动机的概念设计和初步定型的程序，以用于运载火箭和航天器。当前的论文集中在具有低温和可储存推进剂系统的双推进剂发动机上。每个子系统的设计采用了几种不同的设计方法。总体而言，与实际发动机数据相比，算法结果是可以接受的。

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