Investigation of the Throttling Characteristics of Axial-injection End-burning Hybrid Rockets

2017 ◽  
Vol 65 (4) ◽  
pp. 157-167 ◽  
Author(s):  
Yuji SAITO ◽  
Toshiki YOKOI ◽  
Ayumu TSUJI ◽  
Kazunobu OMURA ◽  
Hiroyuki YASUKOCHI ◽  
...  
Keyword(s):  
Axial Injection ◽  
Hybrid Rockets

Response Mechanisms in Axial-Injection End-Burning Hybrid Rockets

2019 ◽  
Author(s):  
Yuji Saito ◽  
Ayumu Tsuji ◽  
Ai Yamada ◽  
Harunori Nagata
Keyword(s):  
Axial Injection ◽  
Hybrid Rockets

Study on Hysteresis Characteristics of Axial-injection End-burning Hybrid Rockets under Throttling Operation

2019 ◽  
Vol 67 (4) ◽  
pp. 119-125
Author(s):  
Masaya Kimino ◽  
Yuji Saito ◽  
Yushi Okutani ◽  
Ayumu Tsuji ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
Axial Injection ◽  
Hybrid Rockets ◽  
Hysteresis Characteristics

Investigation of Regression Rate under High-Pressure in Axial-Injection End-Burning Hybrid Rockets

2018 ◽  
Author(s):  
Yushi Okutani ◽  
Yuji Saito ◽  
Masaya Kimino ◽  
Ayumu Tuji ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
High Pressure ◽  
Axial Injection ◽  
Regression Rate ◽  
Hybrid Rockets

scholarly journals High Pressure Fuel Regression Characteristics of Axial-Injection End-Burning Hybrid Rockets

2019 ◽  
Vol 35 (2) ◽  
pp. 328-341 ◽  
Author(s):  
Yuji Saito ◽  
Masaya Kimino ◽  
Ayumu Tsuji ◽  
Yushi Okutani ◽  
Kentaro Soeda ◽  
...  
Keyword(s):  
High Pressure ◽  
Axial Injection ◽  
Hybrid Rockets

scholarly journals Investigation of Throttling Response Characteristics of Axial-Injection End-Burning Hybrid Rockets

2018 ◽  
Vol 16 (1) ◽  
pp. 9-18 ◽  
Author(s):  
Yuji SAITO ◽  
Masaya KIMINO ◽  
Ayumu TSUJI ◽  
Kazunobu OMURA ◽  
Hiroyuki YASUKOCHI ◽  
...  
Keyword(s):  
Axial Injection ◽  
Response Characteristics ◽  
Hybrid Rockets

Examining Port Geometry/Solid Loading for Additively Manufactured Fuels in Hybrid Rockets

2020 ◽  
pp. 1-9
Author(s):  
Gregory Young ◽  
Terrence L. Connell ◽  
Kyle Fennell ◽  
Steve Possehl ◽  
Michael Baier
Keyword(s):  
Solid Loading ◽  
Hybrid Rockets

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

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