北极救生艇用气动喷射推进器:效率论证

M. Sergeev, V. Tarovik, N. Valdman, A. Labuzov
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摘要

研究对象和目的。本文综述了北极救生艇气动喷射推进效率论证研究的成果。这些结果得出的结论是,这种非传统类型的推进可能是一种在紧急情况下快速逃离危险区的有前途的解决方案。材料和方法。本文给出的结果是基于固体力学、变质量力学和传热学的研究和验证方法。通过对有关该主题的出版物和专利的总结分析,以及KSRC研究人员的经验,证实了在结冰条件下从海洋设施疏散人员的任务的相关性。主要结果。这项研究得出了救生艇运动学的数据,以及各种类型推进剂的数学参数曲线。还分析了气动喷气推进器在设计条件下在热扰动和惯性扰动作用下的运行稳定性。封闭式救生艇紧急脱离危险区的试验结果表明,这种救生艇推进方式具有一定的实用潜力。结论就快速逃离危险区而言,气动喷气推进可能会显著提高疏散过程的效率。简单的设计和操作原理减少了准备紧急逃生所需的时间。此外,这种类型的推进装置在设计条件方面对长期热扰动具有鲁棒性。可以通过改变推进剂的热力学性质来确保预先定义的安全半径。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Pneumatic-jet propulsor for Arctic lifeboat: efficiency justification
Object and purpose of research. This paper reviews the findings of efficiency justification study for pneumatic-jet propulsion of Arctic lifeboat. These results lead to the conclusion that this non-conventional type of propulsion could be a promising solution for fast escape beyond the hazard zone in case of emergency. Materials and methods. The results presented in this paper are based on well-studied and proven methods of solid mechanics, variable-mass mechanics and heat transfer. The relevance of the task of personnel evacuation from marine facilities in ice conditions is confirmed by the summary analysis of publications and patents about this topic, as well as by the experience of KSRC researchers. Main results. The study yielded the data on the lifeboat’s kinematics, as well as the curves of kimematic parameters for various types of the propellant. It also analysed the stability of pneumatic-jet propulsor operation in design conditions under effect of thermal and inertial disturbances. The results obtained for the closed lifeboat’s emergency escape from the hazard zone have shown that this type of lifeboat propulsion surely has practical potential. Conclusion. Pneumatic-jet propulsion might considerably increase the evacuation process efficiency in terms of the fast escape from the hazard zone. Simple design and operation principle reduce the time needed to prepare for the emergency escape. Also, this type of propulsion features robustness against long-term thermal disturbances with respect to its design condi-tions. Pre-defined safety radius may be ensured through variation of the propellant’s thermodynamic properties.
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