返回舱/空间探测器热防护结构发展现状与趋势

doi:10.7527/S1000-6893.2019.22792

Abstract

Abstract: In view of the demand of thermal protection system for China space transportation system and deep space exploration, domestic and international studies on development and status of thermal protection materials and structures for return capsules and space probes are reviewed, focusing on the design idea and the performance characteristics of representative materials and structures including honeycomb reinforced thermal protection materials, fiber reinforced thermal protection materials, combined thermal protection structures, and deployable thermal protection structures. On this basis, the development tendency and obstacles of the materials and structures are analyzed, showing that fiber reinforced thermal protection materials have predominance in structural weight and the seam design is the important obstacle to the corresponding structure development. Moreover, on the basis of existing materials, the combined thermal protection structure design is becoming an effective method for improving the efficiency of thermal protection structure. The deployable thermal protection structures are expected to significantly enhance the payload of spacecraft; however, the flexible thermal protection materials still need to be developed. Generally, more frequent space transportation and development of deep space exploration will play an important role in promoting the development of thermal protection structures.

Key words: space transportation system, deep space exploration, ablative materials, thermal protection structures, structural performance

CLC Number:

XIE Weihua, HAN Guokai, MENG Songhe, YANG Qiang, JIN Hua. Development status and trend of thermal protection structure for return capsules and space probes[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 22792-022792.

References 94

[40]	HONG C Q, HAN J C, ZHANG X H, et al. Novel phenolic impregnated 3-D fine-woven pierced carbon fabric composites:Microstructure and ablation behavior[J]. Composites Part B:Engineering, 2012, 43(5):2389-2394.
[41]	CHENG H M, XUE H F, HONG C Q, et al. Preparation, mechanical, thermal and ablative properties of lightweight needled carbon fibre felt/phenolic resin aerogel composite with a bird's nest structure[J]. Composites Science & Technology, 2017, 140:63-72.
[24]	LAUB B, CHEN Y K, JOHN A D. Development of a high-fidelity thermal/ablation response model for SLA-561V:AIAA-2009-4232[R]. Reston, VA:AIAA, 2009.
[1]	LAUB B, VENKATAPATHY E. Thermal protection system technology and facility needs for demanding future planetary missions[C]//Proceedings of International Workshop on Planetary Probe Atmospheric Entry and Descent Trajectory Analysis and Science. Paris:European Space Agency, 2003:1-9.
[42]	WANG C H, JIN X Y, CHENG H M, et al. Organic aerogel impregnated low-density carbon/carbon composites:Preparation, properties and response under simulated atmospheric re-entry conditions[J]. Materials & Design, 2017, 131:177-185.
[2]	梁馨, 罗丽娟,谭珏,等. 美国空间探测器热防护材料发展现状及趋势[J]. 材料导报, 2016, 30(S1):551-557. LIANG X, LUO L J,TAN J, et al. Current status and trend of thermal protection material for space exploration in America[J]. Materials Review, 2016, 30(S1):551-557(in Chinese).
[25]	VENKATAPATHY E, LAUB B, HARTMAN G J, et al. Thermal protection system development, testing, and qualification for atmospheric probes and sample return missions:Examples for Saturn, Titan and Stardust-type sample return[J]. Advances in Space Research, 2009, 44:138-150.
[3]	薛华飞, 姚秀荣,程海明,等. 热防护用轻质烧蚀材料现状与发展[J]. 哈尔滨理工大学学报, 2017, 22(1):123-128. XUE H F, YAO X R, CHENG H M, et al. Current situation development of lightweight ablation materials for thermal protection[J]. Journal of Harbin University of Science and Technology, 2017, 22(1):123-128(in Chinese).
[4]	赵梦熊. 载人飞船返回舱的烧蚀防热[J]. 气动实验与测量控制, 1996, 10(3):1-9. ZHAO M X. Ablative thermal protection of capsule type reentry vehicle[J]. Aerodynamic Experiment and Measurement & Control, 1996, 10(3):1-9(in Chinese).
[5]	易法军, 梁军,孟松鹤,等. 防热复合材料的烧蚀机理与模型研究[J]. 固体火箭技术, 2000, 23(3):49-57. YI F J, LIANG J, MENG S H, et al. Study on ablation mechanism and models of heatshield composites[J]. Journal of Solid Rocket Technology, 2000, 23(3):49-57(in Chinese).
[6]	张蕊. 美国载人航天商业运输的发展[J]. 航天器工程, 2011, 20(6):86-93. ZHANG R. Development of American human spaceflight commercial transportation[J]. Spacecraft Engineering, 2011, 20(6):86-93(in Chinese).
[43]	YIN R Y, CHENG H M, HONG C Q, et al. Synthesis and characterization of novel phenolic resin/silicone hybrid aerogel composites with enhanced thermal, mechanical and ablative properties[J]. Composites Part A:Applied Science and Manufacturing, 2017, 101:500-510.
[44]	贾献峰, 刘旭华,乔文明,等.酚醛浸渍碳烧蚀体(PICA)的制备、结构及性能[J]. 宇航材料工艺, 2016, 46(1):77-80,90. JIA X F, LIU X H, QIAO W M, et al. Preparation and properties of phenolic impregnated carbon ablator[J]. Aerospace Materials & Technology, 2016, 46(1):77-80,90(in Chinese).
[45]	贾献峰, 王际童,龙东辉,等. PICA-X的制备及其炭化前后性能研究[J]. 宇航材料工艺, 2016, 46(6):46-49. JIA X F,WANG J T, LONG D H, et al. Preparation and properties of PICA-X before and after carbonization[J]. Aerospace Materials & Technology, 2016, 46(6):46-49(in Chinese).
[46]	董金鑫, 朱召贤,姚鸿俊,等. 酚醛气凝胶/碳纤维复合材料的结构调控及性能研究[J]. 化工学报, 2018, 69(11):4896-4901. DONG J X, ZHU Z X, YAO H J, et al. Structural control and properties of phenolic aerogel/carbon fiber composites[J]. CIESC Journal, 2018, 69(11):4896-4901(in Chinese).
[26]	BECK R A S, DRIVER D M, WRIGHT M J, et al. Development of the Mars Science Laboratory heatshield thermal protection system:AIAA-2009-4229[R]. Reston, VA:AIAA, 2009.
[7]	NOWLIN S, THIMONS L. Surviving the heat:The application of phenolic impregnated carbon ablators[EB/OL]. (2013-02-01)[2018-07-21]. https://spacex.com.pl/files/2017-11/pica-x.pdf?870b177%20e37.
[47]	ELLERBY D, VENKATAPATHY E, STACKPOOLE M, et al. Woven thermal protection system based Heat-shield for Extreme Entry Environments Technology (HEEET)[C]//National Space and Missile Materials Symposium. Washington, D.C.:NASA, 2013:1-17.
[27]	TRAN H K. Development of lightweight ceramic ablators and arc-jet test results:NASA-TM-108798[R]. Washington, D.C.:NASA, 1994.
[8]	VENKATAPATHY E, BECK R, ELLERBY D, et al. Development challenges of game-changing entry system technologies from concept to mission infusion[C]//37th IEEE Aerospace Sciences. Piscataway, NJ:IEEE Press, 2016:1-13.
[9]	SUZUKI T, AOKI T, OGASAWARA T, et al. Nonablative lightweight thermal protection system for mars aeroflyby sample collection mission[J]. Acta Astronautica, 2017, 136:407-420.
[48]	FELDMAN J D, ELLERBY D, STACKPOOLE M, et al. Development of 3D woven ablative thermal protection systems (TPS) for NASA spacecraft[C]//South Texas Society for the Advancement of Materials and Process Engineering (SAMPE) Chapter Meeting. Washington, D.C.:NASA, 2015:1-68.
[28]	TRAN H K, JOHNSON C E, RASKY D J, et al. Phenolic Impregnated Carbon Ablators (PICA) for Discovery missions:AIAA-1996-1911[R]. Reston, VA:AIAA, 1996.
[29]	AGRAWAL P, CHAVEZGARCIA J F, PHAM J. Fracture in phenolic impregnated carbon ablator[J]. Journal of Spacecraft and Rockets, 2013, 50(4):735-741.
[10]	BARCENA J, FLOREZ S, PEREZ B, et al. FP7/space project "HYDRA" hybrid ablative development for re-entry in planetary atmospheric thermal protection[C]//7th European Workshop on TPS & Hot Structures. Paris:European Space Agency, 2013.
[49]	VENKATAPATHY E, ELLERBY D, GAGE P, et al. Heat-shield for extreme entry environment technology (HEEET) development status[C]//13th International Planetary Probe Workshop, 2016.
[30]	WILLCOCKSON W H. Stardust sample return capsule design experience[J]. Journal of Spacecraft and Rockets, 1999, 36(3):470-474.
[11]	BARCENA J, FLOREZ S, PEREZ B, et al. Novel hybrid ablative/ceramic heatshield for earth atmospheric re-entry[C]//13th European Conference on Spacecraft Structures, Materials & Environmental Testing. Paris:European Space Agency, 2014.
[50]	MILOS F S, CHEN Y K, MAHZARI M. Arcjet tests and thermal response analysis for dual-layer woven carbon phenolic:AIAA-2017-3353[R]. Reston, VA:AIAA, 2017.
[31]	TRAN H K, JOHNSON C E, HSU M T, et al. Qualification of the forebody heatshield of the Stardust's sample return capsule:AIAA-1997-2482[R]. Reston, VA:AIAA, 1997.
[12]	BARCENA J, LAGOS M, AGOTE I, et al. SMARTEES FP7 space project-Towards a new TPS reusable concept for atmospheric reentry from low earth orbit[C]//7th European Workshop on TPS & Hot Structures. Paris:European Space Agency, 2013.
[51]	ELLERBY D, BOGHOZIAN T, DRIVER D, et al. Heatshield for Extreme Entry Environment Technology (HEEET) development and maturation status[C]//Outer Planet Advisory Group (OPAG) Spring Meeting. Washington, D.C.:NASA, 2018.
[13]	李志杰, 果琳丽,张柏楠,等. 国外可重复使用载人飞船发展现状与关键技术研究[J]. 航天器工程, 2016, 25(2):106-112. LI Z J, GUO L L, ZHANG B N, et al. Study on development status and key technologies of reusable manned spacecraft[J]. Spacecraft Engineering, 2016, 25(2):106-112(in Chinese).
[14]	杨雷, 张柏楠,郭斌,等. 新一代多用途载人飞船概念研究[J]. 航空学报, 2015, 36(3):703-713. YANG L, ZHANG B N, GUO B, et al. Concept definition of new-generation multi-purpose manned spacecraft[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3):703-713(in Chinese).
[15]	董彦芝, 刘峰,杨昌昊,等. 探月工程三期月地高速再入返回飞行器防热系统设计与验证[J]. 中国科学:技术科学, 2015, 45(2):151-159. DONG Y Z, LIU F, YANG C H, et al. Design and verification of the TPS of the circumlunar free return and reentry flight vehicle for the 3rd phase of Chinese Lunar exploration program[J]. Scientia Sinica Technologica, 2015, 45(2):151-159(in Chinese).
[32]	VENKATAPATHY E, REUTHER J. NASA crew exploration vehicle, thermal protection system, lessons learned[C]//6th International Planetary Probe Workshop, 2008.
[16]	BARTLETT E P, ANDERSON L W, CURRY D M. An evaluation of ablation mechanisms for the Apollo heat shield material[J]. Journal of Spacecraft and Rockets, 1971, 8(5):463-469.
[52]	VENKATAPATHY E, ELLERBY D, STACKPOOLE M, et al. Heatshield for Extreme Entry Environment Technology (HEEET)[C]//11th Venus Exploration Analysis Group (VEXAG) Meeting, 2013.
[33]	MILOS F S, GASCH M J, PRABHU D K. Conformal Phenolic Impregnated Carbon Ablator (C-PICA) arcjet testing, ablation and thermal response:AIAA-2015-1448[R]. Reston, VA:AIAA, 2015.
[17]	REUTHER J. Orion thermal protection system, advanced development project[C]//7th International Planetary Probe Workshop, 2010.
[53]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. Preliminary development of a multifunctional hot structure heat shield:AIAA-2014-0350[R]. Reston, VA:AIAA, 2014.
[34]	GASCH M, BECK R, AGRAWAL P. Arcjet testing of advanced conformal ablative TPS[C]//38th Annual Conference on Composites, Materials and Structures. Washington D.C.:NASA, 2014:1-27.
[18]	STROUHAL G, CURRY D M. Thermal protection system performance of the Apollo command module:AIAA-1966-1718[R]. Reston, VA:AIAA, 1966.
[54]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. A multifunctional hot structure heat shield concept for planetary entry:AIAA-2015-3530[R]. Reston, VA:AIAA, 2015.
[19]	ERB R B, GREENSHIELDS D H, CHAUVIN L T, et al. Apollo thermal protection system development[J]. Journal of Spacecraft and Rockets, 1970, 7(6):727-734.
[35]	STACKPOOLE M M, GHANDEHARI E M, THORNTON J J, et al. Flexible ablators:US 9592923 B1[P]. 2017-03-14.
[55]	LANGSTON S L, LANG C G, SAMAREH J A. Parametric study of an ablative TPS and hot structure heatshield for a Mars entry capsule vehicle:AIAA-2017-5290[R]. Reston, VA:AIAA, 2017.
[20]	CICHAN T, NORRIS S D, MARSHALL P F. Orion:EFT-1 flight test results and EM-1/2 status:AIAA-2015-4414[R]. Reston, VA:AIAA, 2015.
[21]	党嘉立, 顾兆栴. 中国"神州号"载人飞船返回舱防热材料现状及展望[C]//第十二届全国复合材料学术会议论文集. 北京:中国复合材料学会, 2002:15-19. DANG J L, GU Z Z. Status & prospect of thermal protective materials on China's Shenzhou spacecraft[C]//12th National Conference on Composite Materials. Beijing:Chinese Society for Composite Materials, 2002:15-19(in Chinese).
[22]	王春明, 梁馨,孙宝岗,等. 低密度烧蚀材料在神舟飞船上的应用[J]. 宇航材料工艺, 2011, 41(2):5-8. WANG C M, LIANG X, SUN B G, et al. Application of low density ablative material on Shenzhou spacecraft[J]. Aerospace Materials & Technology, 2011, 41(2):5-8(in Chinese).
[23]	叶培建, 杨孟飞,彭兢,等. 中国深空探测进入/再入返回技术的发展现状和展望[J]. 中国科学:技术科学, 2015, 45(3):229-238. YE P J, YANG M F, PENG J, et al. Review and prospect of atmospheric entry and earth reentry technology of China deep space exploration[J]. Scientia Sinica Technologica, 2015, 45(3):229-238(in Chinese).
[36]	STACKPOLE M, THORNTON J, FAN W, et al. Development of low density flexible carbon phenolic ablators[C]//2011 National Space and Missile Materials Symposium. Washington, D.C.:NASA, 2011:1-22.
[56]	BARCENA J, FLOREZ S, PEREZ B, et al. Novel hybrid ablative/ceramic development for re-entry in planetary atmospheric thermal protection:interfacial adhesive selection and test verification plan:AIAA-2014-2373[R]. Reston, VA:AIAA, 2014.
[24]	LAUB B, CHEN Y K, JOHN A D. Development of a high-fidelity thermal/ablation response model for SLA-561V:AIAA-2009-4232[R]. Reston, VA:AIAA, 2009.
[37]	ZELL P, VENKATAPATHY E, ARNOLD J. The block-ablator-in-a-honeycomb heat shield architecture overview[EB/OL]. (2014-05-19)[2018-07-22]. https://www.researchgate.net/publication/228543129.
[57]	TRIANTOU K, MERGIA K, MARINOU A, et al. Novel hybrid ablative/ceramic layered composite for earth re-entry thermal protection:Microstructural and mechanical performance[J]. Journal of Materials Engineering and Performance, 2015, 24(4):1452-1461.
[25]	VENKATAPATHY E, LAUB B, HARTMAN G J, et al. Thermal protection system development, testing, and qualification for atmospheric probes and sample return missions:Examples for Saturn, Titan and Stardust-type sample return[J]. Advances in Space Research, 2009, 44:138-150.
[58]	TRIANTOU K, MERGIA K, FLOREZ S, et al. Thermo-mechanical performance of an ablative/ceramic composite hybrid thermal protection structure for re-entry applications[J]. Composites Part B:Engineering, 2015, 82:159-165.
[38]	MCGUIRE M K. Dual heat pulse, dual layer thermal protection system sizing analysis and trade studies for human Mars entry descent and landing:AIAA-2011-0343[R]. Reston, VA:AIAA, 2011.
[59]	TRIANTOU K, PEREZ B, MARINOU A, et al. Performance of cork and ceramic matrix composite joints for re-entry thermal protection structures[J]. Composites Part B:Engineering, 2017, 108:270-278.
[26]	BECK R A S, DRIVER D M, WRIGHT M J, et al. Development of the Mars Science Laboratory heatshield thermal protection system:AIAA-2009-4229[R]. Reston, VA:AIAA, 2009.
[60]	TRIANTOU K, MERGIA K, PEREZ B, et al. Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications[J]. Composites Part B:Engineering, 2017, 111:270-278.
[39]	BOUILLY J M, PLAINDOUX C. ASTERM:Maturation of a new low density ablative material[C]//7th European Workshop on TPS & Hot Structures. Paris:European Space Agency, 2013.
[61]	BARCENA J, GARMENDIA I, TRIANTOU K, et al. Infrared and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems[J]. Acta Astronautica, 2017, 134:85-97.
[62]	李俊宁, 胡子君,孙陈诚,等. 高超声速飞行器隔热材料技术研究进展[J]. 宇航材料工艺, 2011,41(6):10-13, 31. LI J N, HU Z J, SUN C C, et al. Thermal insulation materials for hypersonic vehicles[J]. Aerospace Materials & Technology, 2011,41(6):10-13, 31(in Chinese).
[27]	TRAN H K. Development of lightweight ceramic ablators and arc-jet test results:NASA-TM-108798[R]. Washington, D.C.:NASA, 1994.
[40]	HONG C Q, HAN J C, ZHANG X H, et al. Novel phenolic impregnated 3-D fine-woven pierced carbon fabric composites:Microstructure and ablation behavior[J]. Composites Part B:Engineering, 2012, 43(5):2389-2394.
[63]	SUN J J, HU Z J, LI J N, et al. Thermal and mechanical properties of fibrous zirconia ceramics with ultra-high porosity[J]. Ceramics International, 2014, 40:11787-11793.
[41]	CHENG H M, XUE H F, HONG C Q, et al. Preparation, mechanical, thermal and ablative properties of lightweight needled carbon fibre felt/phenolic resin aerogel composite with a bird's nest structure[J]. Composites Science & Technology, 2017, 140:63-72.
[64]	LI J N, HU Z J, WANG X T, et al. Preparation of nanoporous alumina superinsulator with ultra-low thermal conductivity and improved heat resistance up to 1200℃[J]. Ceramics International, 2017, 43:8343-8347.
[65]	张泽, 王晓栋,吴宇,等. 气凝胶材料及其应用[J]. 硅酸盐学报, 2018, 46(10):1426-1446. ZHANG Z, WANG X D, WU Y, et al. Aerogels and their applications-A short review[J]. Journal of the Chinese Ceramic Society, 2018, 46(10):1426-1446(in Chinese).
[66]	高庆福, 张长瑞,冯坚,等. 氧化硅气凝胶隔热复合材料研究进展[J]. 材料科学与工程学报, 2009, 27(2):302-306. GAO Q F, ZHANG C R, FENG J, et al. Progress of silica aerogel insulation composites[J]. Journal of Materials Science and Engineering, 2009, 27(2):302-306(in Chinese).
[28]	TRAN H K, JOHNSON C E, RASKY D J, et al. Phenolic Impregnated Carbon Ablators (PICA) for Discovery missions:AIAA-1996-1911[R]. Reston, VA:AIAA, 1996.
[42]	WANG C H, JIN X Y, CHENG H M, et al. Organic aerogel impregnated low-density carbon/carbon composites:Preparation, properties and response under simulated atmospheric re-entry conditions[J]. Materials & Design, 2017, 131:177-185.
[67]	PARALE V G, JUNG H N R, HAN W, et al. Improvement in the high temperature thermal insulation performance of Y2O3 opacified silica aerogels[J]. Journal of Alloys and Compounds, 2017, 727:871-878.
[29]	AGRAWAL P, CHAVEZGARCIA J F, PHAM J. Fracture in phenolic impregnated carbon ablator[J]. Journal of Spacecraft and Rockets, 2013, 50(4):735-741.
[43]	YIN R Y, CHENG H M, HONG C Q, et al. Synthesis and characterization of novel phenolic resin/silicone hybrid aerogel composites with enhanced thermal, mechanical and ablative properties[J]. Composites Part A:Applied Science and Manufacturing, 2017, 101:500-510.
[44]	贾献峰, 刘旭华,乔文明,等.酚醛浸渍碳烧蚀体(PICA)的制备、结构及性能[J]. 宇航材料工艺, 2016, 46(1):77-80,90. JIA X F, LIU X H, QIAO W M, et al. Preparation and properties of phenolic impregnated carbon ablator[J]. Aerospace Materials & Technology, 2016, 46(1):77-80,90(in Chinese).
[45]	贾献峰, 王际童,龙东辉,等. PICA-X的制备及其炭化前后性能研究[J]. 宇航材料工艺, 2016, 46(6):46-49. JIA X F,WANG J T, LONG D H, et al. Preparation and properties of PICA-X before and after carbonization[J]. Aerospace Materials & Technology, 2016, 46(6):46-49(in Chinese).
[46]	董金鑫, 朱召贤,姚鸿俊,等. 酚醛气凝胶/碳纤维复合材料的结构调控及性能研究[J]. 化工学报, 2018, 69(11):4896-4901. DONG J X, ZHU Z X, YAO H J, et al. Structural control and properties of phenolic aerogel/carbon fiber composites[J]. CIESC Journal, 2018, 69(11):4896-4901(in Chinese).
[68]	XU L, JIANG Y G, FENG J Z, et al. Infrared-opacified Al2O3-SiO2 aerogel composites reinforced by SiC-coated mullite fibers for thermal insulations[J]. Ceramics International, 2015, 41:437-442.
[30]	WILLCOCKSON W H. Stardust sample return capsule design experience[J]. Journal of Spacecraft and Rockets, 1999, 36(3):470-474.
[69]	LIU R L, DONG X, XIE S T, et al. Ultralight, thermal insulating, and high-temperature-resistant mullite-based nanofibrous aerogels[J]. Chemical Engineering Journal, 2019, 360:464-472.
[47]	ELLERBY D, VENKATAPATHY E, STACKPOOLE M, et al. Woven thermal protection system based Heat-shield for Extreme Entry Environments Technology (HEEET)[C]//National Space and Missile Materials Symposium. Washington, D.C.:NASA, 2013:1-17.
[70]	MA J, YE F, YANG C P, et al. Heat-resistant, strong alumina-modified silica aerogel fabricated by impregnating silicon oxycarbide aerogel with boehmite sol[J]. Materials & Design, 2017, 131:226-231.
[31]	TRAN H K, JOHNSON C E, HSU M T, et al. Qualification of the forebody heatshield of the Stardust's sample return capsule:AIAA-1997-2482[R]. Reston, VA:AIAA, 1997.
[71]	ZU G Q, SHEN J, ZOU L P, et al. Highly thermally stable zirconia/silica composite aerogels prepared by supercritical deposition[J]. Microporous and Mesoporous Materials, 2017, 238:90-96.
[48]	FELDMAN J D, ELLERBY D, STACKPOOLE M, et al. Development of 3D woven ablative thermal protection systems (TPS) for NASA spacecraft[C]//South Texas Society for the Advancement of Materials and Process Engineering (SAMPE) Chapter Meeting. Washington, D.C.:NASA, 2015:1-68.
[72]	ZU G Q, SHEN J, WANG W Q, et al. Heat-resistant, strong titania aerogels achieved by supercritical deposition[J]. The Journal of Supercritical Fluids, 2015, 106:145-151.
[32]	VENKATAPATHY E, REUTHER J. NASA crew exploration vehicle, thermal protection system, lessons learned[C]//6th International Planetary Probe Workshop, 2008.
[73]	吴晓栋, 崔升,王岭,等. 耐高温气凝胶隔热材料的研究进展[J]. 材料导报, 2015, 29(5):102-108. WU X D, CUI S, WANG L, et al. Advance in research of high temperature resistant aerogel used as insulation material[J]. Materials Review,2015, 29(5):102-108(in Chinese).
[74]	FENG J Z, FENG J, JIANG Y G, et al. Ultralow density carbon aerogels with low thermal conductivity up to 2000℃[J]. Materials Letters, 2011, 65:3454-3456.
[49]	VENKATAPATHY E, ELLERBY D, GAGE P, et al. Heat-shield for extreme entry environment technology (HEEET) development status[C]//13th International Planetary Probe Workshop, 2016.
[33]	MILOS F S, GASCH M J, PRABHU D K. Conformal Phenolic Impregnated Carbon Ablator (C-PICA) arcjet testing, ablation and thermal response:AIAA-2015-1448[R]. Reston, VA:AIAA, 2015.
[75]	SUN W, DU A, GAO G H, et al. Graphene-templated carbon aerogels combining with ultra-high electrical conductivity and ultra-low thermal conductivity[J]. Microporous and Mesoporous Materials, 2017, 253:71-79.
[76]	XU X, ZHANG Q Q, HAO M L, et al. Double-negative-index ceramic aerogels for thermal superinsulation[J]. Science, 2019, 363:723-727.
[50]	MILOS F S, CHEN Y K, MAHZARI M. Arcjet tests and thermal response analysis for dual-layer woven carbon phenolic:AIAA-2017-3353[R]. Reston, VA:AIAA, 2017.
[34]	GASCH M, BECK R, AGRAWAL P. Arcjet testing of advanced conformal ablative TPS[C]//38th Annual Conference on Composites, Materials and Structures. Washington D.C.:NASA, 2014:1-27.
[77]	BECK R A S, ARNOLD J O, WHITE S, et al. Overview of initial development of flexible ablators for hypersonic inflatable aerodynamic decelerators:AIAA-2011-2511[R]. Reston, VA:AIAA, 2011.
[51]	ELLERBY D, BOGHOZIAN T, DRIVER D, et al. Heatshield for Extreme Entry Environment Technology (HEEET) development and maturation status[C]//Outer Planet Advisory Group (OPAG) Spring Meeting. Washington, D.C.:NASA, 2018.
[35]	STACKPOOLE M M, GHANDEHARI E M, THORNTON J J, et al. Flexible ablators:US 9592923 B1[P]. 2017-03-14.
[78]	HUGHES S J, DILLMAN R A, STARR B R, et al. Inflatable Re-entry Vehicle Experiment (IRVE) design overview:AIAA-2005-1636[R]. Reston, VA:AIAA, 2005.
[52]	VENKATAPATHY E, ELLERBY D, STACKPOOLE M, et al. Heatshield for Extreme Entry Environment Technology (HEEET)[C]//11th Venus Exploration Analysis Group (VEXAG) Meeting, 2013.
[36]	STACKPOLE M, THORNTON J, FAN W, et al. Development of low density flexible carbon phenolic ablators[C]//2011 National Space and Missile Materials Symposium. Washington, D.C.:NASA, 2011:1-22.
[79]	DILLMAN R. Inflatable Reentry Vehicle Experiment-3(IRVE-3) project overview & instrumentation[C]//Entry Descent and Landing Workshop. Washington, D.C.:NASA, 2015.
[53]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. Preliminary development of a multifunctional hot structure heat shield:AIAA-2014-0350[R]. Reston, VA:AIAA, 2014.
[37]	ZELL P, VENKATAPATHY E, ARNOLD J. The block-ablator-in-a-honeycomb heat shield architecture overview[EB/OL]. (2014-05-19)[2018-07-22]. https://www.researchgate.net/publication/228543129.
[80]	LICHODZIEJEWSKI L, KELLEY C, TUTT B, et al. Design and testing of the inflatable aeroshell for the IRVE-3 flight experiment:AIAA-2012-1515[R]. Reston, VA:AIAA, 2012.
[54]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. A multifunctional hot structure heat shield concept for planetary entry:AIAA-2015-3530[R]. Reston, VA:AIAA, 2015.
[38]	MCGUIRE M K. Dual heat pulse, dual layer thermal protection system sizing analysis and trade studies for human Mars entry descent and landing:AIAA-2011-0343[R]. Reston, VA:AIAA, 2011.
[81]	DELCORSO J A, CHEATWOOD F M, BRUCE W E, et al. Advanced high-temperature flexible TPS for inflatable aerodynamic decelerators:AIAA-2011-2510[R]. Reston, VA:AIAA, 2011.
[55]	LANGSTON S L, LANG C G, SAMAREH J A. Parametric study of an ablative TPS and hot structure heatshield for a Mars entry capsule vehicle:AIAA-2017-5290[R]. Reston, VA:AIAA, 2017.
[39]	BOUILLY J M, PLAINDOUX C. ASTERM:Maturation of a new low density ablative material[C]//7th European Workshop on TPS & Hot Structures. Paris:European Space Agency, 2013.
[40]	HONG C Q, HAN J C, ZHANG X H, et al. Novel phenolic impregnated 3-D fine-woven pierced carbon fabric composites:Microstructure and ablation behavior[J]. Composites Part B:Engineering, 2012, 43(5):2389-2394.
[82]	BRUCE W E, MESICK N J, FERLEMANN P G, et al. Aerothermal ground testing of flexible thermal protection systems for hypersonic inflatable aerodynamic decelerators[C]//9th International Planetary Probe Workshop, 2012.
[56]	BARCENA J, FLOREZ S, PEREZ B, et al. Novel hybrid ablative/ceramic development for re-entry in planetary atmospheric thermal protection:interfacial adhesive selection and test verification plan:AIAA-2014-2373[R]. Reston, VA:AIAA, 2014.
[41]	CHENG H M, XUE H F, HONG C Q, et al. Preparation, mechanical, thermal and ablative properties of lightweight needled carbon fibre felt/phenolic resin aerogel composite with a bird's nest structure[J]. Composites Science & Technology, 2017, 140:63-72.
[57]	TRIANTOU K, MERGIA K, MARINOU A, et al. Novel hybrid ablative/ceramic layered composite for earth re-entry thermal protection:Microstructural and mechanical performance[J]. Journal of Materials Engineering and Performance, 2015, 24(4):1452-1461.
[42]	WANG C H, JIN X Y, CHENG H M, et al. Organic aerogel impregnated low-density carbon/carbon composites:Preparation, properties and response under simulated atmospheric re-entry conditions[J]. Materials & Design, 2017, 131:177-185.
[83]	HUGHES S J, CHEATWOOD F M, CALOMINO A M, et al. Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology development overview[C]//10th International Planetary Probe Workshop, 2013.
[58]	TRIANTOU K, MERGIA K, FLOREZ S, et al. Thermo-mechanical performance of an ablative/ceramic composite hybrid thermal protection structure for re-entry applications[J]. Composites Part B:Engineering, 2015, 82:159-165.
[43]	YIN R Y, CHENG H M, HONG C Q, et al. Synthesis and characterization of novel phenolic resin/silicone hybrid aerogel composites with enhanced thermal, mechanical and ablative properties[J]. Composites Part A:Applied Science and Manufacturing, 2017, 101:500-510.
[44]	贾献峰, 刘旭华,乔文明,等.酚醛浸渍碳烧蚀体(PICA)的制备、结构及性能[J]. 宇航材料工艺, 2016, 46(1):77-80,90. JIA X F, LIU X H, QIAO W M, et al. Preparation and properties of phenolic impregnated carbon ablator[J]. Aerospace Materials & Technology, 2016, 46(1):77-80,90(in Chinese).
[45]	贾献峰, 王际童,龙东辉,等. PICA-X的制备及其炭化前后性能研究[J]. 宇航材料工艺, 2016, 46(6):46-49. JIA X F,WANG J T, LONG D H, et al. Preparation and properties of PICA-X before and after carbonization[J]. Aerospace Materials & Technology, 2016, 46(6):46-49(in Chinese).
[46]	董金鑫, 朱召贤,姚鸿俊,等. 酚醛气凝胶/碳纤维复合材料的结构调控及性能研究[J]. 化工学报, 2018, 69(11):4896-4901. DONG J X, ZHU Z X, YAO H J, et al. Structural control and properties of phenolic aerogel/carbon fiber composites[J]. CIESC Journal, 2018, 69(11):4896-4901(in Chinese).
[59]	TRIANTOU K, PEREZ B, MARINOU A, et al. Performance of cork and ceramic matrix composite joints for re-entry thermal protection structures[J]. Composites Part B:Engineering, 2017, 108:270-278.
[84]	SWANSON G, SMITH B, AKAMINE R, et al. The HIAD orbital flight demonstration instrumentation suite[C]//15th International Planetary Probe Workshop, 2018.
[85]	曹旭, 黄明星,丁弘,等. 充气式再入与减速系统柔性热防护材料的热冲击试验[J]. 载人航天, 2018, 24(1):26-33. CAO X, HUANG M X, DING H, et al. Thermal shock test of flexible thermal protection system for inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(1):26-33(in Chinese).
[86]	曹旭, 廖航,许望晶,等. 充气式减速技术试验器的设计和飞行试验[J]. 载人航天, 2018, 24(6):802-808. CAO X, LIAO H, XU W J, et al.Design and flight test of demonstration aircraft with inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(6):802-808(in Chinese).
[87]	贺卫亮, 才晶晶,汪龙芳,等. 一次发射多次返回的充气式再入飞行器技术[J]. 载人航天, 2011(4):37-42. HE W L, CAI J J, WANG L F, et al.Inflatable reentry technologies research for Single Launching and MultiReentry (SLMR) space transporting system[J]. Manned Spaceflight, 2011(4):37-42(in Chinese).
[60]	TRIANTOU K, MERGIA K, PEREZ B, et al. Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications[J]. Composites Part B:Engineering, 2017, 111:270-278.
[47]	ELLERBY D, VENKATAPATHY E, STACKPOOLE M, et al. Woven thermal protection system based Heat-shield for Extreme Entry Environments Technology (HEEET)[C]//National Space and Missile Materials Symposium. Washington, D.C.:NASA, 2013:1-17.
[61]	BARCENA J, GARMENDIA I, TRIANTOU K, et al. Infrared and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems[J]. Acta Astronautica, 2017, 134:85-97.
[62]	李俊宁, 胡子君,孙陈诚,等. 高超声速飞行器隔热材料技术研究进展[J]. 宇航材料工艺, 2011,41(6):10-13, 31. LI J N, HU Z J, SUN C C, et al. Thermal insulation materials for hypersonic vehicles[J]. Aerospace Materials & Technology, 2011,41(6):10-13, 31(in Chinese).
[88]	DILLMAN R. Inflatable reentry vehicles and instrumentation needs[C]//2015 IEEE International Conference on Wireless for Space and Extreme Environments (WiSEE). Piscataway, NJ:IEEE Press, 2015.
[63]	SUN J J, HU Z J, LI J N, et al. Thermal and mechanical properties of fibrous zirconia ceramics with ultra-high porosity[J]. Ceramics International, 2014, 40:11787-11793.
[48]	FELDMAN J D, ELLERBY D, STACKPOOLE M, et al. Development of 3D woven ablative thermal protection systems (TPS) for NASA spacecraft[C]//South Texas Society for the Advancement of Materials and Process Engineering (SAMPE) Chapter Meeting. Washington, D.C.:NASA, 2015:1-68.
[64]	LI J N, HU Z J, WANG X T, et al. Preparation of nanoporous alumina superinsulator with ultra-low thermal conductivity and improved heat resistance up to 1200℃[J]. Ceramics International, 2017, 43:8343-8347.
[65]	张泽, 王晓栋,吴宇,等. 气凝胶材料及其应用[J]. 硅酸盐学报, 2018, 46(10):1426-1446. ZHANG Z, WANG X D, WU Y, et al. Aerogels and their applications-A short review[J]. Journal of the Chinese Ceramic Society, 2018, 46(10):1426-1446(in Chinese).
[66]	高庆福, 张长瑞,冯坚,等. 氧化硅气凝胶隔热复合材料研究进展[J]. 材料科学与工程学报, 2009, 27(2):302-306. GAO Q F, ZHANG C R, FENG J, et al. Progress of silica aerogel insulation composites[J]. Journal of Materials Science and Engineering, 2009, 27(2):302-306(in Chinese).
[89]	SWANSON G, CHEATWOOD N, JOHNSON K, et al. Manufacturing challenges and benefits when scaling the HIAD stacked-torus aeroshell to a 15m-class system[C]//13th International Planetary Probe Workshop, 2016.
[67]	PARALE V G, JUNG H N R, HAN W, et al. Improvement in the high temperature thermal insulation performance of Y2O3 opacified silica aerogels[J]. Journal of Alloys and Compounds, 2017, 727:871-878.
[49]	VENKATAPATHY E, ELLERBY D, GAGE P, et al. Heat-shield for extreme entry environment technology (HEEET) development status[C]//13th International Planetary Probe Workshop, 2016.
[68]	XU L, JIANG Y G, FENG J Z, et al. Infrared-opacified Al2O3-SiO2 aerogel composites reinforced by SiC-coated mullite fibers for thermal insulations[J]. Ceramics International, 2015, 41:437-442.
[90]	VENKATAPATHY E, ARNOLD J, FERNANDEZ I, et al. Adaptive Deployable Entry and Placement Technology (ADEPT):A feasibility study for human missions to mars:AIAA-2011-2608[R]. Reston, VA:AIAA, 2011.
[69]	LIU R L, DONG X, XIE S T, et al. Ultralight, thermal insulating, and high-temperature-resistant mullite-based nanofibrous aerogels[J]. Chemical Engineering Journal, 2019, 360:464-472.
[50]	MILOS F S, CHEN Y K, MAHZARI M. Arcjet tests and thermal response analysis for dual-layer woven carbon phenolic:AIAA-2017-3353[R]. Reston, VA:AIAA, 2017.
[70]	MA J, YE F, YANG C P, et al. Heat-resistant, strong alumina-modified silica aerogel fabricated by impregnating silicon oxycarbide aerogel with boehmite sol[J]. Materials & Design, 2017, 131:226-231.
[91]	ARNOLD J O, PETERSON K H, YOUNT B C, et al. Thermal and structural performance of woven carbon cloth for adaptive deployable entry and placement technology:AIAA-2013-1370[R]. Reston, VA:AIAA, 2013.
[71]	ZU G Q, SHEN J, ZOU L P, et al. Highly thermally stable zirconia/silica composite aerogels prepared by supercritical deposition[J]. Microporous and Mesoporous Materials, 2017, 238:90-96.
[51]	ELLERBY D, BOGHOZIAN T, DRIVER D, et al. Heatshield for Extreme Entry Environment Technology (HEEET) development and maturation status[C]//Outer Planet Advisory Group (OPAG) Spring Meeting. Washington, D.C.:NASA, 2018.
[72]	ZU G Q, SHEN J, WANG W Q, et al. Heat-resistant, strong titania aerogels achieved by supercritical deposition[J]. The Journal of Supercritical Fluids, 2015, 106:145-151.
[73]	吴晓栋, 崔升,王岭,等. 耐高温气凝胶隔热材料的研究进展[J]. 材料导报, 2015, 29(5):102-108. WU X D, CUI S, WANG L, et al. Advance in research of high temperature resistant aerogel used as insulation material[J]. Materials Review,2015, 29(5):102-108(in Chinese).
[92]	CASSELL A, GORBUNOV S, YOUNT B, et al. System level aerothermal testing for the Adaptive Deployable Entry and Placement Technology (ADEPT)[C]//13th International Planetary Probe Workshop, 2016.
[74]	FENG J Z, FENG J, JIANG Y G, et al. Ultralow density carbon aerogels with low thermal conductivity up to 2000℃[J]. Materials Letters, 2011, 65:3454-3456.
[52]	VENKATAPATHY E, ELLERBY D, STACKPOOLE M, et al. Heatshield for Extreme Entry Environment Technology (HEEET)[C]//11th Venus Exploration Analysis Group (VEXAG) Meeting, 2013.
[75]	SUN W, DU A, GAO G H, et al. Graphene-templated carbon aerogels combining with ultra-high electrical conductivity and ultra-low thermal conductivity[J]. Microporous and Mesoporous Materials, 2017, 253:71-79.
[93]	WERCINSKI P. The Adaptable, Deployable Entry and Placement Technology (ADEPT)[C]//14th International Planetary Probe Workshop, 2017.
[76]	XU X, ZHANG Q Q, HAO M L, et al. Double-negative-index ceramic aerogels for thermal superinsulation[J]. Science, 2019, 363:723-727.
[53]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. Preliminary development of a multifunctional hot structure heat shield:AIAA-2014-0350[R]. Reston, VA:AIAA, 2014.
[94]	SMITH B, WILLIAMS J, WERCINSKI P, et al. ADEPT SR-1 development and testing[C]//15th International Planetary Probe Workshop, 2018.
[77]	BECK R A S, ARNOLD J O, WHITE S, et al. Overview of initial development of flexible ablators for hypersonic inflatable aerodynamic decelerators:AIAA-2011-2511[R]. Reston, VA:AIAA, 2011.
[54]	WALKER S P, DARYABEIGI K, SAMAREH J A, et al. A multifunctional hot structure heat shield concept for planetary entry:AIAA-2015-3530[R]. Reston, VA:AIAA, 2015.
[78]	HUGHES S J, DILLMAN R A, STARR B R, et al. Inflatable Re-entry Vehicle Experiment (IRVE) design overview:AIAA-2005-1636[R]. Reston, VA:AIAA, 2005.
[55]	LANGSTON S L, LANG C G, SAMAREH J A. Parametric study of an ablative TPS and hot structure heatshield for a Mars entry capsule vehicle:AIAA-2017-5290[R]. Reston, VA:AIAA, 2017.
[79]	DILLMAN R. Inflatable Reentry Vehicle Experiment-3(IRVE-3) project overview & instrumentation[C]//Entry Descent and Landing Workshop. Washington, D.C.:NASA, 2015.
[56]	BARCENA J, FLOREZ S, PEREZ B, et al. Novel hybrid ablative/ceramic development for re-entry in planetary atmospheric thermal protection:interfacial adhesive selection and test verification plan:AIAA-2014-2373[R]. Reston, VA:AIAA, 2014.
[57]	TRIANTOU K, MERGIA K, MARINOU A, et al. Novel hybrid ablative/ceramic layered composite for earth re-entry thermal protection:Microstructural and mechanical performance[J]. Journal of Materials Engineering and Performance, 2015, 24(4):1452-1461.
[80]	LICHODZIEJEWSKI L, KELLEY C, TUTT B, et al. Design and testing of the inflatable aeroshell for the IRVE-3 flight experiment:AIAA-2012-1515[R]. Reston, VA:AIAA, 2012.
[58]	TRIANTOU K, MERGIA K, FLOREZ S, et al. Thermo-mechanical performance of an ablative/ceramic composite hybrid thermal protection structure for re-entry applications[J]. Composites Part B:Engineering, 2015, 82:159-165.
[59]	TRIANTOU K, PEREZ B, MARINOU A, et al. Performance of cork and ceramic matrix composite joints for re-entry thermal protection structures[J]. Composites Part B:Engineering, 2017, 108:270-278.
[81]	DELCORSO J A, CHEATWOOD F M, BRUCE W E, et al. Advanced high-temperature flexible TPS for inflatable aerodynamic decelerators:AIAA-2011-2510[R]. Reston, VA:AIAA, 2011.
[60]	TRIANTOU K, MERGIA K, PEREZ B, et al. Thermal shock performance of carbon-bonded carbon fiber composite and ceramic matrix composite joints for thermal protection re-entry applications[J]. Composites Part B:Engineering, 2017, 111:270-278.
[61]	BARCENA J, GARMENDIA I, TRIANTOU K, et al. Infrared and vibration tests of hybrid ablative/ceramic matrix technological breadboards for earth re-entry thermal protection systems[J]. Acta Astronautica, 2017, 134:85-97.
[62]	李俊宁, 胡子君,孙陈诚,等. 高超声速飞行器隔热材料技术研究进展[J]. 宇航材料工艺, 2011,41(6):10-13, 31. LI J N, HU Z J, SUN C C, et al. Thermal insulation materials for hypersonic vehicles[J]. Aerospace Materials & Technology, 2011,41(6):10-13, 31(in Chinese).
[82]	BRUCE W E, MESICK N J, FERLEMANN P G, et al. Aerothermal ground testing of flexible thermal protection systems for hypersonic inflatable aerodynamic decelerators[C]//9th International Planetary Probe Workshop, 2012.
[63]	SUN J J, HU Z J, LI J N, et al. Thermal and mechanical properties of fibrous zirconia ceramics with ultra-high porosity[J]. Ceramics International, 2014, 40:11787-11793.
[64]	LI J N, HU Z J, WANG X T, et al. Preparation of nanoporous alumina superinsulator with ultra-low thermal conductivity and improved heat resistance up to 1200℃[J]. Ceramics International, 2017, 43:8343-8347.
[65]	张泽, 王晓栋,吴宇,等. 气凝胶材料及其应用[J]. 硅酸盐学报, 2018, 46(10):1426-1446. ZHANG Z, WANG X D, WU Y, et al. Aerogels and their applications-A short review[J]. Journal of the Chinese Ceramic Society, 2018, 46(10):1426-1446(in Chinese).
[66]	高庆福, 张长瑞,冯坚,等. 氧化硅气凝胶隔热复合材料研究进展[J]. 材料科学与工程学报, 2009, 27(2):302-306. GAO Q F, ZHANG C R, FENG J, et al. Progress of silica aerogel insulation composites[J]. Journal of Materials Science and Engineering, 2009, 27(2):302-306(in Chinese).
[83]	HUGHES S J, CHEATWOOD F M, CALOMINO A M, et al. Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology development overview[C]//10th International Planetary Probe Workshop, 2013.
[67]	PARALE V G, JUNG H N R, HAN W, et al. Improvement in the high temperature thermal insulation performance of Y2O3 opacified silica aerogels[J]. Journal of Alloys and Compounds, 2017, 727:871-878.
[68]	XU L, JIANG Y G, FENG J Z, et al. Infrared-opacified Al2O3-SiO2 aerogel composites reinforced by SiC-coated mullite fibers for thermal insulations[J]. Ceramics International, 2015, 41:437-442.
[84]	SWANSON G, SMITH B, AKAMINE R, et al. The HIAD orbital flight demonstration instrumentation suite[C]//15th International Planetary Probe Workshop, 2018.
[85]	曹旭, 黄明星,丁弘,等. 充气式再入与减速系统柔性热防护材料的热冲击试验[J]. 载人航天, 2018, 24(1):26-33. CAO X, HUANG M X, DING H, et al. Thermal shock test of flexible thermal protection system for inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(1):26-33(in Chinese).
[86]	曹旭, 廖航,许望晶,等. 充气式减速技术试验器的设计和飞行试验[J]. 载人航天, 2018, 24(6):802-808. CAO X, LIAO H, XU W J, et al.Design and flight test of demonstration aircraft with inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(6):802-808(in Chinese).
[87]	贺卫亮, 才晶晶,汪龙芳,等. 一次发射多次返回的充气式再入飞行器技术[J]. 载人航天, 2011(4):37-42. HE W L, CAI J J, WANG L F, et al.Inflatable reentry technologies research for Single Launching and MultiReentry (SLMR) space transporting system[J]. Manned Spaceflight, 2011(4):37-42(in Chinese).
[69]	LIU R L, DONG X, XIE S T, et al. Ultralight, thermal insulating, and high-temperature-resistant mullite-based nanofibrous aerogels[J]. Chemical Engineering Journal, 2019, 360:464-472.
[70]	MA J, YE F, YANG C P, et al. Heat-resistant, strong alumina-modified silica aerogel fabricated by impregnating silicon oxycarbide aerogel with boehmite sol[J]. Materials & Design, 2017, 131:226-231.
[88]	DILLMAN R. Inflatable reentry vehicles and instrumentation needs[C]//2015 IEEE International Conference on Wireless for Space and Extreme Environments (WiSEE). Piscataway, NJ:IEEE Press, 2015.
[71]	ZU G Q, SHEN J, ZOU L P, et al. Highly thermally stable zirconia/silica composite aerogels prepared by supercritical deposition[J]. Microporous and Mesoporous Materials, 2017, 238:90-96.
[72]	ZU G Q, SHEN J, WANG W Q, et al. Heat-resistant, strong titania aerogels achieved by supercritical deposition[J]. The Journal of Supercritical Fluids, 2015, 106:145-151.
[73]	吴晓栋, 崔升,王岭,等. 耐高温气凝胶隔热材料的研究进展[J]. 材料导报, 2015, 29(5):102-108. WU X D, CUI S, WANG L, et al. Advance in research of high temperature resistant aerogel used as insulation material[J]. Materials Review,2015, 29(5):102-108(in Chinese).
[89]	SWANSON G, CHEATWOOD N, JOHNSON K, et al. Manufacturing challenges and benefits when scaling the HIAD stacked-torus aeroshell to a 15m-class system[C]//13th International Planetary Probe Workshop, 2016.
[74]	FENG J Z, FENG J, JIANG Y G, et al. Ultralow density carbon aerogels with low thermal conductivity up to 2000℃[J]. Materials Letters, 2011, 65:3454-3456.
[75]	SUN W, DU A, GAO G H, et al. Graphene-templated carbon aerogels combining with ultra-high electrical conductivity and ultra-low thermal conductivity[J]. Microporous and Mesoporous Materials, 2017, 253:71-79.
[90]	VENKATAPATHY E, ARNOLD J, FERNANDEZ I, et al. Adaptive Deployable Entry and Placement Technology (ADEPT):A feasibility study for human missions to mars:AIAA-2011-2608[R]. Reston, VA:AIAA, 2011.
[76]	XU X, ZHANG Q Q, HAO M L, et al. Double-negative-index ceramic aerogels for thermal superinsulation[J]. Science, 2019, 363:723-727.
[91]	ARNOLD J O, PETERSON K H, YOUNT B C, et al. Thermal and structural performance of woven carbon cloth for adaptive deployable entry and placement technology:AIAA-2013-1370[R]. Reston, VA:AIAA, 2013.
[77]	BECK R A S, ARNOLD J O, WHITE S, et al. Overview of initial development of flexible ablators for hypersonic inflatable aerodynamic decelerators:AIAA-2011-2511[R]. Reston, VA:AIAA, 2011.
[92]	CASSELL A, GORBUNOV S, YOUNT B, et al. System level aerothermal testing for the Adaptive Deployable Entry and Placement Technology (ADEPT)[C]//13th International Planetary Probe Workshop, 2016.
[78]	HUGHES S J, DILLMAN R A, STARR B R, et al. Inflatable Re-entry Vehicle Experiment (IRVE) design overview:AIAA-2005-1636[R]. Reston, VA:AIAA, 2005.
[93]	WERCINSKI P. The Adaptable, Deployable Entry and Placement Technology (ADEPT)[C]//14th International Planetary Probe Workshop, 2017.
[79]	DILLMAN R. Inflatable Reentry Vehicle Experiment-3(IRVE-3) project overview & instrumentation[C]//Entry Descent and Landing Workshop. Washington, D.C.:NASA, 2015.
[94]	SMITH B, WILLIAMS J, WERCINSKI P, et al. ADEPT SR-1 development and testing[C]//15th International Planetary Probe Workshop, 2018.
[80]	LICHODZIEJEWSKI L, KELLEY C, TUTT B, et al. Design and testing of the inflatable aeroshell for the IRVE-3 flight experiment:AIAA-2012-1515[R]. Reston, VA:AIAA, 2012.
[81]	DELCORSO J A, CHEATWOOD F M, BRUCE W E, et al. Advanced high-temperature flexible TPS for inflatable aerodynamic decelerators:AIAA-2011-2510[R]. Reston, VA:AIAA, 2011.
[82]	BRUCE W E, MESICK N J, FERLEMANN P G, et al. Aerothermal ground testing of flexible thermal protection systems for hypersonic inflatable aerodynamic decelerators[C]//9th International Planetary Probe Workshop, 2012.
[83]	HUGHES S J, CHEATWOOD F M, CALOMINO A M, et al. Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology development overview[C]//10th International Planetary Probe Workshop, 2013.
[84]	SWANSON G, SMITH B, AKAMINE R, et al. The HIAD orbital flight demonstration instrumentation suite[C]//15th International Planetary Probe Workshop, 2018.
[85]	曹旭, 黄明星,丁弘,等. 充气式再入与减速系统柔性热防护材料的热冲击试验[J]. 载人航天, 2018, 24(1):26-33. CAO X, HUANG M X, DING H, et al. Thermal shock test of flexible thermal protection system for inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(1):26-33(in Chinese).
[86]	曹旭, 廖航,许望晶,等. 充气式减速技术试验器的设计和飞行试验[J]. 载人航天, 2018, 24(6):802-808. CAO X, LIAO H, XU W J, et al.Design and flight test of demonstration aircraft with inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(6):802-808(in Chinese).
[87]	贺卫亮, 才晶晶,汪龙芳,等. 一次发射多次返回的充气式再入飞行器技术[J]. 载人航天, 2011(4):37-42. HE W L, CAI J J, WANG L F, et al.Inflatable reentry technologies research for Single Launching and MultiReentry (SLMR) space transporting system[J]. Manned Spaceflight, 2011(4):37-42(in Chinese).
[88]	DILLMAN R. Inflatable reentry vehicles and instrumentation needs[C]//2015 IEEE International Conference on Wireless for Space and Extreme Environments (WiSEE). Piscataway, NJ:IEEE Press, 2015.
[89]	SWANSON G, CHEATWOOD N, JOHNSON K, et al. Manufacturing challenges and benefits when scaling the HIAD stacked-torus aeroshell to a 15m-class system[C]//13th International Planetary Probe Workshop, 2016.
[90]	VENKATAPATHY E, ARNOLD J, FERNANDEZ I, et al. Adaptive Deployable Entry and Placement Technology (ADEPT):A feasibility study for human missions to mars:AIAA-2011-2608[R]. Reston, VA:AIAA, 2011.
[91]	ARNOLD J O, PETERSON K H, YOUNT B C, et al. Thermal and structural performance of woven carbon cloth for adaptive deployable entry and placement technology:AIAA-2013-1370[R]. Reston, VA:AIAA, 2013.
[92]	CASSELL A, GORBUNOV S, YOUNT B, et al. System level aerothermal testing for the Adaptive Deployable Entry and Placement Technology (ADEPT)[C]//13th International Planetary Probe Workshop, 2016.
[93]	WERCINSKI P. The Adaptable, Deployable Entry and Placement Technology (ADEPT)[C]//14th International Planetary Probe Workshop, 2017.
[94]	SMITH B, WILLIAMS J, WERCINSKI P, et al. ADEPT SR-1 development and testing[C]//15th International Planetary Probe Workshop, 2018.

Development status and trend of thermal protection structure for return capsules and space probes

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