简要回顾了人类火星探测并成功着陆火星的历史,对火星的基本情况及进入环境进行了介绍.对火星科学实验室项目情况、飞向火星的过程及进入气动热环境进行了描述.详细介绍了火星科学实验室进入舱防热材料的发展及相关气动热试验.
参考文献
[1] | Carol D;Marla A .Planetary mission entry vehicles quick reference guide.version 3.0.NASA-20070022789[R]. |
[2] | Spencer DA.;Braun RD. .MARS PATHFINDER ATMOSPHERIC ENTRY - TRAJECTORY DESIGN AND DISPERSION ANALYSIS[J].Journal of spacecraft and rockets,1996(5):670-676. |
[3] | Prince J L;Desai P N .Mars phoenix entry,descent,and landing simulation design and modeling analysis[R].American Institute of Aeronautics and Astronautics,2004. |
[4] | Grover M R;Cichy B D .Overview of the phoenix entry,descent and landing system architecture[R].American Institute of Aeronautics and Astronautics,2008. |
[5] | Desai P N;Prince J L .Entry,descent,and landing performance of the Mars phoenix lander[R].American Institute of Aeronautics and Astronautics,2008. |
[6] | William H. Willcockson .Mars Pathfinder Heatshield Design and Flight Experience[J].Journal of spacecraft and rockets,1999(3):374-379. |
[7] | Gupta RN.;Scott CD.;Lee KP. .AEROTHERMAL STUDY OF MARS PATHFINDER AEROSHELL[J].Journal of spacecraft and rockets,1996(1):61-69. |
[8] | Way D W .Mars science laboratory:entry,descent,and landing system performance.NASA-20090007730[R].,2009. |
[9] | 许春,王成良.火星探测技术综述[J].红外,2008(07):1-8. |
[10] | 史建魁;张仲谋 .火星环境探测结果分析[J].地球物理学进展,1997,12(04):98-108. |
[11] | Abilleira F .2011 Mars science laboratory mission design overview.NASA-20100031720[R]. |
[12] | Prakash R P .Mars science laboratory entry,descent,and landing System Overview.NASA-20110007176[R].,2011. |
[13] | Hollis B R;Liechty D S .Transition onset and turbulent heating measuroments for the Mars science laboratory entry vehicle[R].American Institute of Aeronautics and Astronautics,2005. |
[14] | Hollis B R .Blunt-body entry vehicle aerothermodynamics:transition and turbulence on the CEV and MSL configurations[R].American Institute of Aeronautics and Astronautics,2010. |
[15] | Schaefer J W .Experimental and analytical evaluation of the Apollo thermal protection system under simulated reentry conditions.NASA-CR-65817[R].,1965. |
[16] | Crouch R K .An investigation of ablation behavior of Avcoat 5026/39M over a wide range of thermal environments.NASA TM X-1778[R].,1969. |
[17] | Strauss E .Superlight ablative systems for Mars lander thermal protection[J].Journal of Spacecraft and Rockets,1967,4(10):1304-1307. |
[18] | Congdon W M .Ablation model validation and analytical sensitivity study for the Mars pathfinder heat shield[R].American Institute of Aeronautics and Astronautics,1995. |
[19] | Tran H K .Development of lightweight ceramic ablators and arc-jet test results.NASA TM-1087978[R].,1994. |
[20] | Tran H;Johnson C .Phenolic impregnated carbon ablators (PICA) for discovery class missions[R].American Institute of Aeronautics and Astronautics,1996. |
[21] | Tran H;Johnson C .Silicon impregnated resusable ceramic ablators for Mars follow-on missions[R].American Institute of Aeronautics and Astronautics,1996. |
[22] | M. A. Covington;J. M. Heinemann;H. E. Goldstein;Y.-K. Chen;I. Terrazas-Salinas;J. A. Balboni;J. Olejniczak;E. R. Martinez .Performance of a Low Density Ablative Heat Shield Material[J].Journal of spacecraft and rockets,2008(2):237-247. |
[23] | Agrawal P;Chavez-Garcia J F .Fracture in phenolic impregnated carbon ablator[R].American Institute of Aeronautics and Astronautics,2011. |
[24] | Gupta R N .Aerothermodynamic analysis of stardust sample return capsule with coupled radiationand ablation[R].American Institute of Aeronautics and Astronautics,1999. |
[25] | Olynick D;Chen Y K .Forebody TPS sizing with radiation and ablation for the stardust sample return capsule Entry,descent,and landing operations analysis for the stardust entry capsule[R].American Institute of Aeronautics and Astronautics,1997. |
[26] | Johnson C E;Tran H K .Stardust backshell and back interface plate design verification tests in the NASA Ames arc jet facilities[R].American Institute of Aeronautics and Astronautics,1997. |
[27] | Desai P N .Entry,descent,and landing operations analysis for the stardust entry capsule[R].American Institute of Aeronautics and Astronautics,2006. |
[28] | Finekenor M .Optical property measurements on the stardust sample return capsule.NASA-20070031961[R].,2007. |
[29] | Edquist KT .Mars science laboratory entry capsule aerothermodynamics and thermal protection system.NASA-20070016625[R].,2007. |
[30] | Tauber M .Ames research center shear tests of SLA-561V heat shield material for Mars-pathfinder.NASA-TM-1996-110402[R].,1996. |
[31] | Sepka S A .Testing of SLA-561V in NASA-Ames'turbulent flow duct With augmented radiative heating[R].American Institute of Aeronautics and Astronautics,2011. |
[32] | Driver D M .Arc jet testing in a shear environment for Mars science laboratory thermal protection system[R].American Institute of Aeronautics and Astronautics,2009. |
[33] | Goken T .Computational analysis of arc-jet wedge tests including ablation and shape change[R].American Institute of Aeronautics and Astronautics,2010. |
[34] | Agrawal P .Multidimensional testing of thermal protection materials in the arcjet test facility[R].American Institute of Aeronautics and Astronautics,2011. |
[35] | Beck R A .Development of the Mars science laboratory heatshield thermal protection system[R].American Institute of Aeronautics and Astronautics,2009. |
[36] | Wright M J;Beck R A .Sizing and margins assessment of the Mars science laboratory aeroshell thermal protection system[R].American Institute of Aeronautics and Astronautics,2009. |
[37] | MacLean M .Investigation of blunt bodies with CO2test gas including catalytic effects[R].American Institute of Aeronautics and Astronautics,2005. |
[38] | MacLean M .Numerical assessment of data in catalytic and transitional flows for Martian entry[R].American Institute of Aeronautics and Astronautics,2006. |
[39] | Wright M J .A review of aerothermal modeling for Mars entry missions.NASA-20100021401[R]. |
[40] | Gazarik M J .Overview of the MEDLI project.NASA-20080013510[R]. |
[41] | Beerman A F .Development of a tool to recreate the Mars science laboratory aerothermal environment.NASA-20100036469[R]. |
[42] | Santos J A .Isotherm sensor calibration program for Mars science laboratory heat shield flight data analysis.NASA-20110014965[R]. |
[43] | Calomino A .Evaluation of the NASA arc jet capabilities to support mission requirements.NASA-SP-2010-577[R]. |
[44] | Del Papa S V .The development of a CO2 test capability in the NASA JSC arcjet for Mars reentry simulation.NASA-20110011509[R]. |
[45] | Laub B .Rotating arc jet test model:time-accurate trajectory heat flux replication in a ground test environment.NASA-20110013229[R]. |
[46] | Herdrich G .Mars entry simulation using the inductively heated plasma generator IPG4[R].American Institute of Aeronautics and Astronautics,2001. |
[47] | Endlich P .Mars entry simulation with dust using an inductively heated generator[R].American Institute of Aeronautics and Astronautics,2002. |
[48] | Zang T A;Dwyer-Cianciolo A M .Overview of the NASA entry,descent and landing systems analysis study.NASA-20100033145[R].,2010. |
[49] | Dwyer-Cianciolo A M .Entry,descent and landing systems analysis study:phase 1 report.NASA-TM-2010-216720[R].,2010. |
[50] | Cassell A M .Development of thermal protection materials for future Mars entry,descent and landing systems[R].American Institute of Aeronautics and Astronautics,2010. |
[51] | Del Corso J A .Advanced high-temperature flexible TPS for inflatable aerodynamic decelerators[R].American Institute of Aeronautics and Astronautics,2011. |
[52] | Beck R A .An overview of NASA' s current materials development efforts for Mars EDL.NASA-20110012048[R]. |
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%