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 | |
| Publication status | Published - Jan 1 2014 |
| Event | 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States Duration: Jul 28 2014 → Jul 30 2014 |
Other
| Other | 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 |
|---|---|
| Country | United States |
| City | Cleveland |
| Period | 7/28/14 → 7/30/14 |
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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
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 proceeding › Conference contribution
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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 -