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| 火箭发动机尾罩热分离流场的数值模拟 | |
| 引用本文： | 袁先旭,杨明智,陈坚强.火箭发动机尾罩热分离流场的数值模拟[J].空气动力学学报,2007,25(1):60-64. |
| 作者姓名： | 袁先旭 杨明智 陈坚强 |
| 作者单位： | 1. 中国空气动力研究与发展中心,四川,绵阳,621000;中南大学轨道交通安全教育部重点实验室,湖南,长沙,410075 2. 中南大学轨道交通安全教育部重点实验室,湖南,长沙,410075 3. 中国空气动力研究与发展中心,四川,绵阳,621000 |
| 基金项目： | 国家自然科学基金(10572145,10502055)资助项目 |
| 摘 要： | 潜射导弹的发动机一般用尾罩加以保护以防止海水侵蚀,发动机点火后尾罩存在热分离过程,本文应用非定常数值模拟方法和动网格技术数值模拟了发动机尾喷管超声速流场的建立过程,分析了高温燃气与尾罩碰撞后反射流动对发动机防护罩的非定常载荷,计算结果表明本文计算方法可以用来数值研究广泛存在的气流瞬态冲击效应。 |
| 关 键 词： | 动态分离 非定常载荷 动网格 |
| 文章编号： | 0258-1825（2007）01-0060-04 |
| 修稿时间： | 2005-01-292005-03-29 |
Numerical simulation for rocket engine cabin unsteady flow with back shield separation |
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| YUAN Xian-xu,YANG Ming-zhi,CHEN Jian-qiang.Numerical simulation for rocket engine cabin unsteady flow with back shield separation[J].Acta Aerodynamica Sinica,2007,25(1):60-64. | |
| Authors: | YUAN Xian-xu YANG Ming-zhi CHEN Jian-qiang |
| Institution: | 1. China Aerodynamic Research and Development Center, Sicuan Miangyan 621000, China; 2. Key Laboratory for Track Traffic Safety of Ministry Education CSU , Changsha 410075, China |
| Abstract: | In order to defend corrading by seawater,the engine of missile launching under water is protected by back shield.After engine ignition,the back shield will be separating because of impacting by combustion gas.In this paper,the establishing process of supersonic flow in rocket engine is simulated by an unsteady CFD method and dynamic grid technique.The unsteady aerodynamic loads induced by inverse high temperature combustion gas from back shield are presented.The results show possibility of engineering application on gas instantaneous impact effect by present methods. |
| Keywords: | dynamic separation unsteady aerodynamic loads dynamic grid |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ | |