Surrey Research Update on N2O Catalytic Decomposition for Space Applications
Surrey Research Update on N2O Catalytic Decomposition for Space Applications
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萨里 N2O 催化分解空间应用研究最新进展
DOI：
10.2514/6.2001-3922
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发表时间：
2001
影响因子：
5.6
通讯作者：
T. Lawrence
中科院分区：
文献类型：
--
作者：
V. Zakirov;G. Richardson;M. Sweeting;T. Lawrence
一氧化二氮被建议用作先进小型卫星的推进剂。由于其独特的性质，一氧化二氮可用于冷气、单组元、双组元和阻力喷射推进器，从而涵盖所有小型卫星推进功能。这种推进剂不需要排出系统。因此，氧化亚氮的应用，被认为是有益的多模式小卫星推进系统。为了证明一氧化二氮作为火箭推进剂的潜力，催化分解建议用于可再启动单组元推力器概念。为此，萨里大学研究了一氧化二氮的催化分解。本文介绍了最新的研究成果。名称Ea活化能，kJ/mol AH ° r反应焓，kJ/mol m质量流量，gm/s p压力，bar Qin输入能量，J Qh加热器输入能量，J Qdec一氧化二氮分解释放的输入能量，J T废气温度，° C t时间，s引言先进的小卫星需要先进的推进系统。这种系统将支持小型航天器成功完成其使命所需的推进功能。将一氧化二氮用作小型航天器的推进剂，可使推进系统的性能优于现有系统。这是可能的，因为这种物质的独特性质。一氧化二氮可以以液体的形式储存在航天器上，储存密度相对较高，可以长期储存。它的高蒸汽压力消除了对机载驱逐系统的需要。其无毒性和与普通建筑材料的良好相容性建议廉价的系统设计和开发。在气相中，它可以用于冷气和蒸汽推进。这种化学品的化学分解能力导致其用于可重新启动的单组元和双组元推进剂，版权所有© 2001，由美国航空航天研究所有限公司所有。All rights reserved. 1 American Institute of Aeronautics and Astronautics（c）2001年美国航空航天学会或经作者和/或作者赞助组织许可出版。推进器因此，一氧化二氮可用于冷气、单组元、双组元和阻力喷射推进器。由于一种自增压推进剂可以实现全部推进功能，因此可以设想采用多模式推进系统来满足各种各样的使命要求。这种系统将使用不同类型的推进器，由一个简单设计的储存罐提供一氧化二氮。由于其有效的推进剂管理，这种多模式推进系统是非常灵活的小卫星使命的情况变化。在早期的出版物中详细讨论了一氧化二氮在航天器上应用的优点。'
Nitrous oxide is suggested as a propellant for advanced small satellites. Due to its unique properties, nitrous oxide can be employed in cold-gas, monopropellant, bipropellant, and resistojet thrusters, thus covering all small satellite propulsion functions. This propellant does not require an expulsion system. The application of nitrous oxide is, therefore, considered beneficial for multi-mode small satellite propulsion system. To demonstrate nitrous oxide potential as a rocket propellant, catalytic decomposition is suggested for restartable monopropellant thruster concept. For this purpose nitrous oxide catalytic decomposition has been studied at the University of Surrey. The latest research results are presented in this paper. NOMENCLATURE Ea activation energy, kJ/mol AH°r reaction enthalpy, kJ/mol m mass flow rate, gm/s p pressure, bar Qin input energy, J Qh input energy by heater, J Qdec input energy released by nitrous oxide decomposition, J Texhaust gas temperature, °C t time, s INTRODUCTION Advanced small satellites require advanced propulsion systems. Such a system will support propulsion functions required for small spacecraft to successfully fulfil its mission. Application of nitrous oxide as a propellant for a small spacecraft can result in a propulsion system with performance advantageous over existing systems. This is possible due to unique properties of this substance. Nitrous oxide can be stored as a liquid with relatively high storage density onboard a spacecraft for long periods. Its high vapour pressure eliminates the need for an onboard expulsion system. Its non-toxicity and excellent compatibility with common construction materials suggest inexpensive system design and exploitation. In a gas phase it can be used for coldgas and electrothermal propulsion. The ability of this chemical to exothermically decompose leads towards its use for restartable monoand bipropellant Copyright © 2001 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. 1 American Institute of Aeronautics and Astronautics (c)2001 American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization. thrusters. Thus, nitrous oxide can be used in coldgas, monopropellant, bipropellant, and resistojet thrusters. Since the whole range of propulsion functions can be covered by one self-pressurising propellant, multimode propulsion systems can be envisioned to satisfy a wide variety mission requirements. Such systems would employ different types of thrusters fed by nitrous oxide from a single, simply designed storage tank. Due to its efficient propellant management this multi-mode propulsion system is very flexible to small satellite mission scenario change. The advantages of nitrous oxide application on spacecrafts are discussed in details in the earlier publications.'