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PERSPECTIVE OF LAUNCH VEHICLE SIZE AND WEIGHT BASED ON PROPULSION SYSTEM CONCEPT

机译：基于推进系统概念的发射车尺寸和重量的透视

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摘要

Three primary elements determine launcher size and weight. These are the configuration concept, the propulsion concept and the industrial material/fabrication capability. These three can be represented as a sizing index [P. Czysz, C. Bruno, K. Kato, Interactions between propulsion systems and the configuration concepts defines the design space, AIAA-2001-1924, 10th International Space planes and Hypersonic Systems and Technologies Conference, Kyoto, Japan, April 2001]. For a given industrial materials/fabrication capability, the configuration and propulsion concepts interact directly. One method identifying the solution space for each combination of parameters is discussed in the 10th International Space Planes and Hypersonic Systems and Technologies Conference in Kyoto, Japan in April 2001. A significant number of propulsion system concepts have been studied and reported. This paper focuses on those that are applicable to launch vehicles. Each propulsion system concept is briefly described and accompanied by a sketch. The intent is to show weight ratio and the onboard oxygen carried by the vehicle drive this direct interaction. The lesser the weight ratio and the smaller the oxygen-to-fuel ratio, the smaller is the size and gross weight of the vehicle.
机译：三个主要因素决定了发射器的尺寸和重量。这些是配置概念，推进概念和工业材料/制造能力。这三个可以表示为上浆指数[P。 Czysz，C. Bruno，K. Kato，推进系统与配置概念之间的相互作用定义了设计空间，AIAA-2001-1924，第十届国际空间飞机和高超音速系统与技术会议，日本京都，2001年4月。对于给定的工业材料/制造能力，配置和推进概念直接相互作用。在2001年4月于日本京都举行的第10届国际空间飞机和高超音速系统技术大会上，讨论了一种确定每种参数组合的解空间的方法。已经研究并报告了许多推进系统概念。本文重点介绍适用于运载火箭的车辆。简要介绍了每个推进系统的概念，并附有草图。目的是显示重量比，车辆携带的车载氧气驱动这种直接相互作用。重量比越小，氧燃料比越小，车辆的尺寸和总重越小。

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