Concept of non-ablative thermal protection system for hypersonic vehicles
文献类型：期刊论文
| 作者 | Liu YF(刘云峰) ; Jiang ZL(姜宗林)
|
| 刊名 | AIAA Journal
 |
| 出版日期 | 2013-03 |
| 卷号 | 51期号:3页码:584-590 |
| 通讯作者邮箱 | yfliu.lhd@gmail.com; zljiang@imech.ac.cn |
| 关键词 | Flow fields Flow visualization Hypersonic aerodynamics Hypersonic vehicles Mach number Shock waves Thermal insulating materials Engineering applications Experimental datum Hypersonic wind tunnels Numerical results Stagnation points Thermal protection Thermal Protection System Working pressures |
| ISSN号 | 0001-1452 |
| 产权排序 | [Liu, Yunfeng; Jiang, Zonglin] Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China |
| 通讯作者 | Jiang, ZL (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China. |
| 中文摘要 | In order to reduce the shock-wave drag and aerodynamic heating of hypersonic vehicles effectively a new concept of non-ablative thermal protection system was proposed based on the idea of flowfield reconstruction. In this non-ablative thermal protection system a spike-blunt body structure and lateral jets are combined together to realize the flowfield modification. The spike transforms the bow shock into a conical shock, and the lateral jets increase the angle of conical shock wave and keep it away from the blunt body to avoid severe shock/shock interactions. Flow visualizations and pressure measurements were conducted in a hypersonic wind tunnel at Mach number 6 to demonstrate this concept. Numerical simulations were also carried out. Both experimental and numerical results demonstrate that the non-ablative thermal protection system works well for shock-wave drag reduction and thermal protection. The peak pressure at the reattachment region is reduced by 65% even under 4 deg attack angle by the lateral jet. Experimental data also show that the working pressure of lateral jets is much lower than that of forward-facing jets at the stagnation point. All the results show that the engineering application of non-ablative thermal protection system appears to be quite promising. |
| 学科主题 | 空气动力学 |
| 分类号 | 一类 |
| 类目[WOS] | Engineering, Aerospace |
| 研究领域[WOS] | Engineering |
| 关键词[WOS] | WAVE DRAG REDUCTION ; HEAT-TRANSFER ; ENERGY DEPOSITION ; SUPERSONIC-FLOW ; SHOCK-WAVE ; MITIGATION ; BODIES ; SPIKE ; JET |
| 收录类别 | SCI ; EI |
| 资助信息 | Y210061021 |
| 原文出处 | http://dx.doi.org/10.2514/1.J051875 |
| 语种 | 英语 |
| WOS记录号 | WOS:000315551200004 |
| 公开日期 | 2013-04-07 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/47144]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 推荐引用方式 GB/T 7714 | Liu YF,Jiang ZL. Concept of non-ablative thermal protection system for hypersonic vehicles[J]. AIAA Journal,2013,51(3):584-590. |
| APA | Liu YF,&Jiang ZL.(2013).Concept of non-ablative thermal protection system for hypersonic vehicles.AIAA Journal,51(3),584-590. |
| MLA | Liu YF,et al."Concept of non-ablative thermal protection system for hypersonic vehicles".AIAA Journal 51.3(2013):584-590. |
入库方式： OAI收割
来源：力学研究所
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