A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system

Shigeru Aso, Yasuhiro Tani, Tani Shohei Saiga, Ryohei Arakawa, Toru Shimada

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A new method with multi-section swirl injection method is proposed in order to improve fuel regression rate of hybrid rocket engine. The new method is to introduce swirling flow through injector ports, which are placed at several cross-sections along the fuel grain. In the present study, combustion tests for several grain types have been conducted to clarify influences of difference in the number and direction of swirl on the regression rate. Visualization of combustion chamber of hybrid rocket engines has been conducted and swirling turbulent flow has been observed. Also, throttling of hybrid rocket engine has been conducted successfully. To realize Multi-Section Swirl Injection Method for real flight, two-module type flight engine with swirl injection has been proposed and applied to flight experiment. Hybrid rocket engine with multi-section swirl injection method has been successfully tested under 2G acceleration environment.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - Jan 1 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: Jan 8 2018Jan 12 2018

Publication series

NameAIAA Aerospace Sciences Meeting, 2018
Number210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period1/8/181/12/18

Fingerprint

Rocket engines
Propulsion
Swirling flow
Combustion chambers
Turbulent flow
Visualization
Engines
Experiments

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Aso, S., Tani, Y., Saiga, T. S., Arakawa, R., & Shimada, T. (2018). A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system. In AIAA Aerospace Sciences Meeting (210059 ed.). (AIAA Aerospace Sciences Meeting, 2018; No. 210059). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-1415

A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system. / Aso, Shigeru; Tani, Yasuhiro; Saiga, Tani Shohei; Arakawa, Ryohei; Shimada, Toru.

AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018. (AIAA Aerospace Sciences Meeting, 2018; No. 210059).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Aso, S, Tani, Y, Saiga, TS, Arakawa, R & Shimada, T 2018, A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system. in AIAA Aerospace Sciences Meeting. 210059 edn, AIAA Aerospace Sciences Meeting, 2018, no. 210059, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Aerospace Sciences Meeting, 2018, Kissimmee, United States, 1/8/18. https://doi.org/10.2514/6.2018-1415
Aso S, Tani Y, Saiga TS, Arakawa R, Shimada T. A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system. In AIAA Aerospace Sciences Meeting. 210059 ed. American Institute of Aeronautics and Astronautics Inc, AIAA. 2018. (AIAA Aerospace Sciences Meeting, 2018; 210059). https://doi.org/10.2514/6.2018-1415
Aso, Shigeru ; Tani, Yasuhiro ; Saiga, Tani Shohei ; Arakawa, Ryohei ; Shimada, Toru. / A study on high performance hybrid rocket engine with multi-section swirl injection method for space propulsion system. AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018. (AIAA Aerospace Sciences Meeting, 2018; 210059).
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