TY - CHAP
T1 - Hybrid Propulsion Technology Development in Japan for Economic Space Launch
AU - Shimada, Toru
AU - Yuasa, Saburo
AU - Nagata, Harunori
AU - Aso, Shigeru
AU - Nakagawa, Ichiro
AU - Sawada, Keisuke
AU - Hori, Keiichi
AU - Kanazaki, Masahiro
AU - Chiba, Kazuhisa
AU - Sakurai, Takashi
AU - Morita, Takakazu
AU - Kitagawa, Koki
AU - Wada, Yutaka
AU - Nakata, Daisuke
AU - Motoe, Mikiro
AU - Funami, Yuki
AU - Ozawa, Kohei
AU - Usuki, Tomoaki
N1 - Funding Information:
This research is supported by the Hybrid Rocket Research Working Group (HRrWG) of ISAS, JAXA.
Publisher Copyright:
© 2017, Springer International Publishing Switzerland.
PY - 2017
Y1 - 2017
N2 - 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.
AB - 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.
KW - A-SOFT hybrid rocket
KW - Dedicated launcher for lightweight satellites
KW - Economic space launch
KW - Hybrid rocket launch system
KW - Multi-objective optimization
KW - Swirling-oxidizer-flow-type hybrid rocket
KW - Throttling with O/F control
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UR - http://www.scopus.com/inward/citedby.url?scp=85101921864&partnerID=8YFLogxK
U2 - 10.1007/978-3-319-27748-6_22
DO - 10.1007/978-3-319-27748-6_22
M3 - Chapter
AN - SCOPUS:85101921864
T3 - Springer Aerospace Technology
SP - 545
EP - 575
BT - Springer Aerospace Technology
PB - Springer Nature
ER -