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

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

3 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 languageEnglish
Title of host publication50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624103032
DOIs
Publication statusPublished - Jan 1 2014
Event50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States
Duration: Jul 28 2014Jul 30 2014

Other

Other50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
CountryUnited States
CityCleveland
Period7/28/147/30/14

Fingerprint

Rockets
Oxygen
Experiments
Carbon fiber reinforced plastics
Rocket engines
High density polyethylenes
Paraffins

All Science Journal Classification (ASJC) codes

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

Cite this

Ohe, K., Mizuchi, M., Aso, S., Tani, Y., Ohyama, S., Araki, K., ... 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 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; Tani, Yasuhiro; Ohyama, Sho; Araki, Kentaro; Tada, Hiroshi; Shimada, Toru.

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.

Research output: Chapter in Book/Report/Conference proceedingConference 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. 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 https://doi.org/10.2514/6.2014-3954
Ohe, Kengo ; Mizuchi, Masato ; Aso, Shigeru ; Tani, Yasuhiro ; Ohyama, Sho ; Araki, Kentaro ; Tada, Hiroshi ; Shimada, Toru. / Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.
@inproceedings{5ec62fa00ce74d39a201cbbc212d8ccf,
title = "Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane",
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",
year = "2014",
month = "1",
day = "1",
doi = "10.2514/6.2014-3954",
language = "English",
booktitle = "50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014",
publisher = "American Institute of Aeronautics and Astronautics Inc.",

}

TY - GEN

T1 - Study on hybrid rocket with multi-section swirl injection method toward flight experiments of subscale space plane

AU - Ohe, Kengo

AU - Mizuchi, Masato

AU - Aso, Shigeru

AU - Tani, Yasuhiro

AU - Ohyama, Sho

AU - Araki, Kentaro

AU - Tada, Hiroshi

AU - Shimada, Toru

PY - 2014/1/1

Y1 - 2014/1/1

N2 - 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.

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.

UR - http://www.scopus.com/inward/record.url?scp=84913550560&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84913550560&partnerID=8YFLogxK

U2 - 10.2514/6.2014-3954

DO - 10.2514/6.2014-3954

M3 - Conference contribution

AN - SCOPUS:84913550560

BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

PB - American Institute of Aeronautics and Astronautics Inc.

ER -