含氮单组分火箭推进剂的应用前景

O. Ponomarov, O.O. Dobrodomov, O. Kulyk
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引用次数: 0

摘要

这项工作的目标是分析利用现有的基于高能含氮物质水溶液的单一推进剂组合物作为低推力发动机的主要推进剂的可能性,例如用于气象火箭、上层发动机和航天器控制发动机系统。本文提出了一种考虑基于可再生能源的成分选择和论证的方法,主要从推进剂成分的可用性及其安全性和能源效率的角度进行分析。建议使用单一还原剂-氧化剂化学推进剂(能量饱和组合物)的能量作为替代来源。开发非碳氢化合物含氮替代能源,使其转化和积累到行星氮、氧和水循环中,是一个迫切需要解决的问题。本文详细介绍了含氮物质作为氧化剂的推进剂混合物,并考虑了一些还原剂,如醇、酰胺等与高能添加剂(铝、镁)组成。计算结果符合目标,表明所考虑的成分可以作为低推力发动机的主推进剂。新推进剂技术的优点是:可用性、低成本、可生产性、环境友好性、相对低毒性,主要是推进系统和发射设备的设计更简单。拟议的推进剂成分正在测试中,计划用于超轻型亚轨道火箭的持续发动机,并有可能进一步发展为轨道火箭系统。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Prospects for the use of nitrogen-containing single-component rocket propellants
The goal of this work is to analyze the possibility of using existing monopropellant compositions based on aqueous solutions of high-energy nitrogen-containing substances as the main propellant for low-thrust engines, for example, for meteorological rockets, for upper-stage engines, and in spacecraft control engine systems. This paper presents an approach that considers the selection and justification of ingredients based on renewable energy sources, the analysis being carried out primarily from standpoint of the availability of propellant components and their safety and energy efficiency. It is proposed that the energy of unitary reducing agent – oxidizer chemical propellants (energy-saturated compositions) be used as an alternative source. The development of nonhydrocarbon nitrogen-containing alternative energy sources with the possibility of their conversion and accumulation into the planetary nitrogen, oxygen, and water cycles is an urgent problem. The paper presents detailed information on propellant mixtures of nitrogen-containing substances as oxidizers and considers a number of reducing agents, such as alcohols, amides, etc. in composition with high-energy additives (aluminum, magnesium). The calculated results obtained meet the objectives and demonstrate that the compositions considered can be used as the main propellant for low-thrust engines. The advantages of the new propellant technology: availability, a low cost, produceability, environmental friendliness, a relatively low toxicity, and, primarily, a simpler design of the propulsion system and launch equipment. The proposed propellant composition, which is under test, is planned for use in the sustainer engines of ultralight suborbital rockets with the possibility of further development to an orbital rocket system.
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