以烧蚀型防热复合材料、非(微)烧蚀型防热复合材料,高温高效隔热复合材料以及高温透波复合材料为重点,简要总结了国内外防热复合材料发展现状,介绍了我国重点领域的突破与进展,并展望了未来防热复合材料的发展趋势.
参考文献
| [1] | Tran H,Johnson C,Rasky D,et al.Phenolic impregnated carbon ablator(PICA)as thermal protection systems for discovery missions[R].NASA Technical Memorandum110440,1997. |
| [2] | Fitzer E,Manocha L M.Carbon reinforcements and carbon/carbon composites[M].Berlin Heidelberg:Springer-Verlag,1998. |
| [3] | Harris J N.Proceedings of the symposium on electromagnetic windows[R].ADA303062,1978. |
| [4] | 郭正.宇航复合材料[M].北京:中国宇航出版社,1999. |
| [5] | Cline P B,Schultz F E.Investigation of the effect of material properties on composite ablative material behavior[R].N67-37114,1967. |
| [6] | Warga J J.Low-cost fabrication techniques for solid rocket nozzles[R].ADA305540,1970. |
| [7] | Gras E G.Performance analysis of reinforced plastics tested in material evaluation rocket motor[R].AGCMF-521,1963. |
| [8] | Laud B,Venkatapathy E.Thermal protection system technology and facility needs for determining future planetary missions[C]∥International Workshop on Planetary Probe Atmospheric Entry and Descent Trajectory Analysis and Sciences.Lisbon,2003. |
| [9] | Dimitrienko L.Verification of model for heat-mechanical process in ablating composites,final report[R].ADA353825,1998. |
| [10] | Verkatapatty E,Reather J.NASA crew exporation vehicle,thermal protection system,lessons learned[C]∥6th International Planetary Probe Workshop.Atlanta,2008. |
| [11] | Katzman H A,Mallon J J,Barry W T.Polyarylacetylenematrix composites for solid rocket motor components[R].ADA30205,1995. |
| [12] | Rossi R C,Wong W C.Availability of aerospace rayon for SRM nozzle insulator[R].ADA318772,1996. |
| [13] | 赵稼祥.航天先进复合材料的现况与展望[J].飞航导弹,2000(1):58-63.Zhao Jiaxiang.The development and prospect of aerospace advanced composite materials[J].Winged Missiles Journal,2000(1):58-63. |
| [14] | Donald L S.Carbon-carbon composites(CCC)-A historical perspective[R].WL-TR-96-4107,1996. |
| [15] | 周瑞发,韩雅芳,李树索.高温结构材料[M].北京:国防工业出版社,2006. |
| [16] | David E G.Ceramic matrix composite thermal protection systems and hot structures for hypersonic vehicles,AIAA2008-2682[R].15th AIAA Space Planes and Hypersonic Systems and Technologies Conference,2008. |
| [17] | Rivers H K,David E G.Advances in hot structures development[C]∥5th European Workshop on Thermal Protection Systems and Hot Structures.Noordwijk,The Netherlands:2006. |
| [18] | Edward J A P,Chris H,Greg S,et al.High temperature and ultra-high-temperature ceramic fibre development and applications[R].ADA508757,2009. |
| [19] | John C,francesco I.Thermal protection system of the space shuttle[R].ADA308170,1989. |
| [20] | David J.x一37 flight demonstrator:Orbital vehicle technology development approach[R].Marshall Space Flight Center,2004. |
| [21] | Erik R B,Joseph C M,David R P.Thermal conductivity and compressive strain of aerogel insulation blankets under applied hydrostatic pressure[J].Transactions of the ASME,2007,129:232-235. |
| [22] | Frances I H,Godfrey C M.High temperature aerogels for thermal protection systems[C]∥32nd Annual Conference on Composite Materials and Structures.Daytona Beach,FL:2008. |
| [23] | Gilreath M C,Castellow S L.High temperature dielectric properties of candidate space-shuttle thermal protection system and antenna-window materials,D-7523[S].NASA Technical Note,1974. |
| [24] | Facciano A.High-temperature composite applications for supersonic missile airframes[J].SAMPE Journal,2001 (1):9. |
| [25] | Abhiraman A S.Formation,structure and properties of boron nitride fibers from polymer precursors[R].ADA247679,1992. |
| [26] | Place T M.Low loss radar window for reentry vehicle:United States,4786548[P].1988. |
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%