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- KOMURO Tomoyuki
- JAXA Kakuda Space Center
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- TOMIOKA Sadatake
- JAXA Kakuda Space Center
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- TAKAGI Shohei
- Department of Aerospace Engineering, Tohoku University
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- TAKAHASHI Masahiro
- JAXA Kakuda Space Center
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- UEDA Shuichi
- JAXA Kakuda Space Center
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- ITOH Katsuhiro
- JAXA Kakuda Space Center
抄録
Combination of a scramjet (supersonic combustion ramjet) flow-pass with embedded rocket engines (the combined system termed as Rocket Based Combined Cycle engine) are expected to be the most effective propulsion system for Booster stage of space launch vehicles. At hypersonic regime, it will be operated at rather high rocket engine output for final acceleration with some Isp gains due to air-breathing effects. In this regime, attaining thrust at this high-speed regime becomes very difficult, so that parallel injection of the fuel for scramjet combustion is favorable as the momentum of the injection can contribute to the thrust production. Thus, embedded rocket chamber was supposed to the operated as fuel rich gas generator at very high output. This configuration was tested at simulated flight Mach number of 11 at High Enthalpy Shock Tunnel (HIEST) with detonation tube as the source of the simulated rocket exhaust. However, combustion of the residual fuel in the rocket exhaust with airflow could not be attained in the past study, so that modification was carried out. Combustion was attained within the combustor, however, insufficient mixing was found to responsible for the rather low combustion efficiency, finding being from complementary mixing test at a blow-down type tunnel.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 (ists29), Pa_71-Pa_77, 2014
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001205319934336
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- NII論文ID
- 130004679628
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- ISSN
- 18840485
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- Crossref
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- 抄録ライセンスフラグ
- 使用不可