Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane

Kengo Ohe; Masato Mizuchi; Shigeru Aso; Yasuhiro Tani; Sho Ohyama; Kentaro Araki; Hiroshi Tada; Toru Shimada

doi:10.2514/6.2014-3954

Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane

Kengo Ohe, Masato Mizuchi, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Hiroshi Tada, Toru Shimada

Space Systems Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

5 Citations (Scopus)

Abstract

Hybrid rocket engine with multi-section swirl injection method was designed and tested for the flight experiments of subscale space plane. Combustion experiments were carried out with high density polyethylene (HDPE) and paraffin fuel and gaseous oxygen with several combustion conditions. Fundamental data for flyable hybrid rocket including usefulness of high pressure CFRP oxygen tank have been revealed. Flight simulation using the measured thrust data clarified the reachable altitude and required thrust to future flight experiments.

Original language	English
Title of host publication	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)	9781624103032
DOIs	https://doi.org/10.2514/6.2014-3954
Publication status	Published - 2014
Event	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States Duration: Jul 28 2014 → Jul 30 2014

Publication series

Name	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

Other

Other	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Country/Territory	United States
City	Cleveland
Period	7/28/14 → 7/30/14

All Science Journal Classification (ASJC) codes

Energy Engineering and Power Technology
Aerospace Engineering
Control and Systems Engineering
Electrical and Electronic Engineering
Mechanical Engineering

Access to Document

10.2514/6.2014-3954

Cite this

Ohe, K., Mizuchi, M., Aso, S., Tani, Y., Ohyama, S., Araki, K., Tada, H., & Shimada, T. (2014). Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-3954

Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane. / Ohe, Kengo; Mizuchi, Masato; Aso, Shigeru et al.
50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Ohe, K, Mizuchi, M, Aso, S, Tani, Y, Ohyama, S, Araki, K, Tada, H & Shimada, T 2014, Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane. in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, American Institute of Aeronautics and Astronautics Inc., 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014, Cleveland, United States, 7/28/14. https://doi.org/10.2514/6.2014-3954

Ohe K, Mizuchi M, Aso S, Tani Y, Ohyama S, Araki K et al. Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc. 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). doi: 10.2514/6.2014-3954

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abstract = "Hybrid rocket engine with multi-section swirl injection method was designed and tested for the flight experiments of subscale space plane. Combustion experiments were carried out with high density polyethylene (HDPE) and paraffin fuel and gaseous oxygen with several combustion conditions. Fundamental data for flyable hybrid rocket including usefulness of high pressure CFRP oxygen tank have been revealed. Flight simulation using the measured thrust data clarified the reachable altitude and required thrust to future flight experiments.",

author = "Kengo Ohe and Masato Mizuchi and Shigeru Aso and Yasuhiro Tani and Sho Ohyama and Kentaro Araki and Hiroshi Tada and Toru Shimada",

note = "Funding Information: This research is supported by the Hybrid Rocket Research Working Group (HRrWG) of Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. The authors would like to express gratitudes for their financial support and valuable discussions. Publisher Copyright: {\textcopyright} 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.; 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 ; Conference date: 28-07-2014 Through 30-07-2014",

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doi = "10.2514/6.2014-3954",

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AU - Ohyama, Sho

AU - Araki, Kentaro

AU - Tada, Hiroshi

AU - Shimada, Toru

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AB - Hybrid rocket engine with multi-section swirl injection method was designed and tested for the flight experiments of subscale space plane. Combustion experiments were carried out with high density polyethylene (HDPE) and paraffin fuel and gaseous oxygen with several combustion conditions. Fundamental data for flyable hybrid rocket including usefulness of high pressure CFRP oxygen tank have been revealed. Flight simulation using the measured thrust data clarified the reachable altitude and required thrust to future flight experiments.

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Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane

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