低熔点热塑性推进剂的低成本火箭

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN Pub Date : 1900-01-01 DOI:10.2322/tastj.17.350

Hikaru Isochi, Hikaru Otabe, T. Uematsu, Nobuji Kato, K. Hori, Y. Morita, R. Akiba

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摘要

固体火箭推进剂的性能改进和成本降低一直是固体火箭领域关注的焦点。使用低熔点热塑性塑料作为燃料粘合剂是解决方案之一。本文介绍了一种低温热塑性推进剂的成型方法及在新型混合装置上的试验结果。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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The Low-Cost Rocket with Low Melting Temperature Thermoplastic Propellant

The performance improvement and cost reduction of solid rocket propellants has been a major concern of the solid rocket community. The use of low melting temperature thermoplastic as a fuel binder is one of the solutions. This paper presents a molding method of LTPs (Low Melting Temperature Thermoplastic Propellant) and the result of tests with a new mixing device.

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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

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