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- WADA Yutaka
- Department of Space and Astronautical Science, Grad.Univ.Advanced Studies
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- TSUTSUMI Akimasa
- Department of Aeronautics and Astronautics, Tokai University
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- SEIKE Yoshio
- NOF Corporation
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- NISHIOKA Makihito
- University of Tsukuba
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- SHIMADA Toru
- ISAS/JAXA
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- HASEGAWA Katsuya
- ISAS/JAXA
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- KOBAYASHI Kiyokazu
- ISAS/JAXA
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- HORI Keiichi
- ISAS/JAXA
Description
Tetra-ol glycidyl azide polymer (GAP) is one of the best candidates for the solid fuel of gas hybrid rocket system because of self-combustibility and high heat of formation. Combustion model of GAP was developed by Beckstead et al. and they applied it to tri-ol GAP successfully. We have applied this model to tetra-ol GAP as an initial attempt, and numerical simulation showed that maximum temperatures in the gas phase exceeded those of experimental results significantly, and calculated burning rates were much higher than strand burner data, thus, modification of the model taking account of combustion incompleteness was found to be necessary. Modifications of combustion model were made taking the residue analysis results into account as Blow Off Mechanism. Simulated final temperature in the gas phase and burning rate are lowered effectively and coincide well with experimental data adjusting kinetic parameters.
Journal
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7 (ists26), Pa_1-Pa_5, 2009
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Keywords
Details 詳細情報について
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- CRID
- 1390001205212630144
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- NII Article ID
- 130000151802
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- ISSN
- 13473840
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- Text Lang
- en
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- Data Source
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- JaLC
- Crossref
- CiNii Articles
- OpenAIRE
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- Abstract License Flag
- Disallowed