讨论了充气式再入飞行器对柔性热防护系统的具体要求,归纳了柔性热防护系统设计的一般准则.概述了柔性热防护系统在充气式再入飞行器中的应用现状,并指出在多层隔热毡(MLI)外表敷设耐高温涂层是柔性热防护系统的理想方案.介绍了柔性热防护系统的材料技术,指出轻质、柔性和耐高温是柔性热防护材料的主要特征,并建议在充气式再入飞行器的总体设计过程中采用Nextel 312作为主要候选材料来完成相应的热防护设计.
参考文献
| [1] | Marraffa L;Kaesing D;Baglioni P.Inflatable Re-entry technologies:flight demonstration and future prospects[J].ESA Bulletin,2000:78-85. |
| [2] | 夏刚,秦子增,张晓今.充气防热罩技术发展现状[J].导弹与航天运载技术,2002(01):19-24. |
| [3] | Kustas F M;Rawal S P;Willcockson W H et al.Inflatable decelerator ballute for planetary exploration spacecraft[R].AIAA 2000-1795,2000. |
| [4] | Kendall R T;Kendall R T .Development and use of inflatable payload recovery vehicles[R].AIAA 91-0888-CP,1991. |
| [5] | Kendall R T;Kendall R T .Advanced unmanned/manned space payload inflatable decelerator/delivery system[R].AIAA 95-3798,1995. |
| [6] | 夏刚,程文科,秦子增.充气式防热罩再入轨道设计[J].国防科技大学学报,2002(03):4-8. |
| [7] | Magazu HK.;Akin DL.;Lewis MJ. .Aerothermodynamics of a parashield re-entry vehicle[J].Journal of spacecraft and rockets,1998(4):434-441. |
| [8] | Rodimov V B R;Pichkhadze K et al.Inflatable ballutes to provide aerodynamic shape to the payload bus enabling its atmospheric entry[R].IAF-97-1503,1997. |
| [9] | Detlef Wilde;Stephan Walther.Inflatable reentry and descent technology (IRDT)-further developments[A].,2001 |
| [10] | Graflin M;Schottle U .Flight performance evaluation of the re-entry mission IRDT-1[R].IAF-01-V305,2001. |
| [11] | Zhao Mengxiong.Manned spacecraft aerodynamics[M].Nafional Defense Industry Press,2000:58-82. |
| [12] | Faurote G L;Burgess J L .Thermal and stress analysis of an attached inflatable decelerator (AID) deployed in the mars earth atmospheres[Z].NASA-CR- 111920,1971. |
| [13] | Han Hongshuo.Analysis on thermal protection systems,structures and materials for space transportation systems abroad[J].Aerospace Materials and Technology(in Chinese),1997(04):1-4. |
上一张
下一张
上一张
下一张
计量
- 下载量()
- 访问量()
文章评分
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%