| Project/Area Number |
22560100
|
|---|
| Research Category |
Grant-in-Aid for Scientific Research (C)
|
| Allocation Type | Single-year Grants |
|---|
| Section | 一般 |
|---|
| Research Field |
Materials/Mechanics of materials
|
|---|
| Research Institution | Japan Aerospace Exploration Agency |
|---|
Principal Investigator |
YAMANISHI Nobuhiro 独立行政法人宇宙航空研究開発機構, 情報・計算工学センター, 研究員 (70450715)
|
|---|
| Co-Investigator(Kenkyū-buntansha) |
NISHIMOTO Miki 独立行政法人宇宙航空研究開発機構, 情報・計算工学センター, 研究員 (40450704)
YOSHIMURA Shinobu 東京大学, 工学(系)研究科(研究院), 教授 (90201053)
KASAHARA Naoto 東京大学, 工学(系)研究科(研究院), 教授 (30421580)
|
|---|
| Co-Investigator(Renkei-kenkyūsha) |
AKIBA Hiroshi 株式会社アライドエンジニアリング, 代表取締役社長
|
|---|
| Project Period (FY) |
2010 – 2012
|
| Project Status |
Completed (Fiscal Year 2012)
|
| Budget Amount *help |
¥4,550,000 (Direct Cost: ¥3,500,000、Indirect Cost: ¥1,050,000)
Fiscal Year 2012: ¥910,000 (Direct Cost: ¥700,000、Indirect Cost: ¥210,000)
Fiscal Year 2011: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000)
Fiscal Year 2010: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
|
|---|
| Keywords | 環境強度 / ロケット / 構造工学 / 破壊 / マルチフィジクス / 極限環境 / 破損 |
|---|
| Research Abstract |
In developing liquid rocket engine, life time of combustion chamber is an important design issue. However, it is very difficult to quantitatively predict the life time because complicated multi-physics phenomena occur under severe conditions in the combustion chamber. The LE-X engine is under study in JAXA as the next booster engine. In its research and development, shorter development time, lower cost and higher reliability are sought by using front-loading design approaches. Therefore, it is indispensable to evaluate the life time of the combustion chamber precisely in the early phase of development. In order to improve accuracy in the life prediction, we focus on the interaction between thermo-fluid behaviors and structural responses, and have developed a new analysis procedure, that is, high-fidelity multi-physics coupled simulation. By applying this procedure, we have investigated the mechanisms and the dominant factors of residual deformation occurred in the throat, which was experienced under development of the upper stage engine. It has been revealed that the throat’s residual deformation strongly depends on cooling capability in the shutdown process, which is affected by the transient flows of both combustion gas and coolant.
|
