書誌事項
- タイトル別名
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- Increase in Performance of Laser Ignition Micro Solid Rocket by Control of Combustion Chamber Pressure
- レーザー チャッカ マイクロ コタイ ロケット ニ オケル ネンショウシツアツリョク セイギョ ニ ヨル セイノウ コウジョウ
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The authors have developed laser ignition micro solid rocket which is a propulsion system suitable for 10-kg-class microspacecrafts. Although the specific impulse is expected to increase by reducing the throat area, higher combustion chamber pressure with the smaller throat causes a couple of serious problems. One is throat erosion and the other is break of combustion chamber. In order to prevent these difficulties, we made three improvements in design of thruster. First, we reinforced the throat, and throat erosion did not occur. Secondly, we changed the ignition surface of the propellant. As a result, peak pressure reduced, but specific impulse also reduced. Thirdly, we made the propellant to encapsulate to constrain the combustion surface, and peak pressure reduced considerably. We designed thrusters which had smaller throat than conventional, and established the increase in specific impulse by 17%. We visualized the combustion chamber, and it was found that capsule could control the combustion surface of propellant.
収録刊行物
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- 日本航空宇宙学会論文集
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日本航空宇宙学会論文集 61 (1), 9-15, 2013
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
- 1390282679445732352
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- NII論文ID
- 10031168709
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 024277604
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可