Hybrid Propulsion Technology Development in Japan for Economic Space Launch
Hybrid Propulsion Technology Development in Japan for Economic Space Launch
复制标题
日本用于经济航天发射的混合推进技术开发
DOI：
10.1007/978-3-319-27748-6_22
复制
发表时间：
2017
影响因子：
1.9
通讯作者：
T. Usuki
中科院分区：
文献类型：
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作者：
T. Shimada;S. Yuasa;H. Nagata;S. Aso;I. Nakagawa;K. Sawada;K. Hori;Masahiro Kanazaki;Kazuhisa Chiba;T. Sakurai;T. Morita;K. Kitagawa;Y. Wada;D. Nakata;M. Motoe;Y. Funami;K. Ozawa;T. Usuki
对于大量轻型（所谓的纳卫星/微卫星）的经济型专用太空发射器的需求目前正在迅速增长。在此进行的评估表明，使用混合推进方式进行经济型太空发射具有很强的合理性。本文描述了一种开发这种经济型三级发射器的典型概念，并给出了开发方案，该发射器采用了成组单元混合火箭发动机。由于混合火箭推进的优势，通过在原材料、生产、运输、储存和操作等所有开发方面采取合理数量的质量保证和质量控制措施，可以开发出可靠、安全的轻型卫星专用经济型发射器。通过对这种发射系统应用多目标优化技术，针对轻型卫星发射的典型任务场景获得了可能的发射系统示例。此外，还描述了一些对混合推进经济型太空发射有重要贡献的关键技术，包括燃料退移速率特性、旋流氧化剂流型混合火箭、液氧汽化、多段旋流喷射、低温熔点热塑性燃料、通过变强度旋流氧化剂流型（A - SOFT）混合实现推力和氧燃比同时控制、内弹道数值模拟等等。
The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizer-flow-type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.
DOI：
10.2514/6.2001-3537
发表时间：
2001-07
期刊：
--
影响因子：
--
作者：
S. Yuasa;Kengo Yamamoto;Hitoshi Hachiya;K. Kitagawa;Youichi Oowada
通讯作者：
S. Yuasa;Kengo Yamamoto;Hitoshi Hachiya;K. Kitagawa;Youichi Oowada
DOI：
--
发表时间：
2004
期刊：
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference AIAA-2004-3479
影响因子：
--
作者：
Yuasa;Saburo
通讯作者：
Saburo