综述了热防护材料的发展历史,重点介绍了深空探测用烧蚀防热材料体系,并通过Pioneer Venus、Galileo、Stardust等探测任务的热防护系统(TPS)选材方案分析,对未来深空探测TPS材料进行技术需求分析.
参考文献
| [1] | Laud B;Venkatapathy E.Thermal protection system technology and facility needs for determining future planetary missions[A].Lisbon,Protugal,2003 |
| [2] | Sylvia M J.Thermal protection materials[A].Boston,MA,2011 |
| [3] | Cozmuta I.Defining ablative thermal protection system margins for planetary entry vehicles[A].Honolulu,HI,2011 |
| [4] | Mathieu R D.Mechanical spallation of charring ablators in hyperthermal environments[J].AIAA Journal,1964(09):1621-1627. |
| [5] | Sullivan J M;Kobayashi W S.Spallation modeling in the charring material thermal response and ablation (CMA) computer program[A].Honolulu,HI,1987 |
| [6] | Land B;Wright M J;Verkatapatty E.Thermal protection system(TPS) design and the relationship to atmospheric entry evironments[A].Atlanta,GA,2008 |
| [7] | Crouch R K;Walberg G D .An investigation of ablation behavior of Avcoat 5026 39M over a wide range of thermal environments.NASA-TM-X-1778 69N22933[R].,1969-4. |
| [8] | Nestler D E .The effects of liquid layers on ablation performance[Memo No.022,TFM-8151-022][R].General Electric Co,RSD,Thermodynamics Fund,1963-12. |
| [9] | Bethe H A;Adams M C .A theory for the ablation of glassy materials[J].Journal of Aerospace Sciences,1959,26(06):321-328. |
| [10] | Laub B;Chen Y K;Dec J A.Development of a high fidelity thermal/ablation response model for SLA-561V[A].San Antonio,TX,2009 |
| [11] | Beck R;Driver D;Wright M.Development of the mars science laboratory heatshield thermal protection system[A].San Antonio,TX,2009 |
| [12] | Donald M C .Thermal protection systems manned spacecraft flight experience.93N12449[R].,1992-10. |
| [13] | Bartlett E P;Abbett M J;Nicolet W E et al.Improved heat-shield design procedures for manned entry systems,part ii-application to Apollo[Report No.75-15][R].Aerotherm,1970-6. |
| [14] | Gray C R;Varacalle D J .Viking project phase Ⅲ ablation performance test report.TN-3770119[R].,1971-7. |
| [15] | Laub B .Ablator modeling:why not much has changed over the past 45 plus years.ARC-E-DAA-TN3105[R].,2011-3. |
| [16] | Korb L;Clancy H.The shuttle orbiter thermal protection system:a material and structural overview[A].,1980:232-249. |
| [17] | Wakefield R M;Pitts W C .Analysis of the heat-shield experiment on the Pioneer-Venus entry probes.AIAA 80-1494[R].,1980-7. |
| [18] | Milos FS. .GALILEO PROBE HEAT SHIELD ABLATION EXPERIMENT[J].Journal of spacecraft and rockets,1997(6):705-713. |
| [19] | Tran H;Johnson C;Rasky D et al.Phenolic impregnated carbon ablator (PICA) as thermal protection systems for discovery missions[NASA TM-110440][R].,1997. |
| [20] | Cheatwood F M;Merski N R;Riley C J.Aerothermodynamic evironment definition for the Genesis sample return capsule[A].Anaheim,California,2001 |
| [21] | Fimmel R O;Colin L;Burgess E .Pioneer Venus[NASA SP-461][R].,1983. |
| [22] | Esper J;Lengowski M .Resin-Impregnated carbon ablator:a new ablative material for Hyperbolic entry speeds[R].,2012-9. |
| [23] | Thompson J M;Daniel J D .Analysis of cured carbonphenolic decomposition products to investigate the thermal decomposition of nozzle materials.NASA N91-28082[R].,1989-1. |
| [24] | Graves R A;Witte W G .Flight-test analysis of Apollo heat-shield material using the pacemaker vehicle system.NASA-TN-D-4713[R].,1968-8. |
| [25] | Crouch R K;Walberg G D .An investigation of ablation behavior of Avcoat 5026 39M over a wide range of thermal environments.NASA-TM-X-1778 69N22933[R].,1969-4. |
| [26] | NASA .gov,NASA selects material for orion spacecraft heat shield[Z].,2009. |
| [27] | William H. Willcockson .Mars Pathfinder Heatshield Design and Flight Experience[J].Journal of spacecraft and rockets,1999(3):374-379. |
| [28] | Brian R. Hollis;Derek S. Liechty .Transition Due to Heat-Shield Cavities on a Mars Entry Vehicle[J].Journal of spacecraft and rockets,2006(2):354-366. |
| [29] | Laub B;Chen Y K.Development of a high-fidelity thermal/ablation response model for SLA-561V[A].San Antonio,TX,2009 |
| [30] | Edquist K T;Hollis B R;Dyakonov A A et al.Mars science laboratory entry capsule aerothermodynamics and thermal protection system.NASA IEEAC Paper 1423[R].,2007-3. |
| [31] | Tran H K.Qualification of the forebody heatshield of the Stardust's Sample Return Capsule[A].Atlanta,GA,1997 |
| [32] | Kowal T J.Thermal protection system (heat shield) development-advanced development project[A].,2010 |
| [33] | Beck R;Driver D;Wright M.Development of the mars science laboratory heatshield thermal protection system[A].San Antonio,Texas,2009 |
| [34] | Space X manufactured heat shield material[Z].,2009. |
| [35] | Milos F S;Chen Y K.Ablation and thermal response property model validation for phenolic impregnated carbon ablator[A].Orlando,Florida,2009 |
| [36] | Tang C Y;Wright M J.Analysis of the forebody aeroheating environment during Genesis Sample return capsule reentry[A].Reno,Nevada,2007 |
| [37] | 王春明,梁馨,孙宝岗,谭朝元,孙红卫.低密度烧蚀材料在神舟飞船上的应用[J].宇航材料工艺,2011(02):5-8. |
| [38] | Congdon W M .Development testing of families of advanced ablative heat shields for human exploration/development of space.NASA Contract T-956W,Final report[R].,2000-5-31. |
| [39] | Congdon W M;Curry D M;Collins T J.Response modeling of lightweight charring ablators and thermal radiation testing results[A].Huntsville,AL,2003 |
| [40] | Sylvia M J;Matthew J G;Dan L.Development of new TPS at NASA ames research center[A].Dayton,Ohio,2008 |
| [41] | Johnson S M.Recent developments at ARC in low-to mid-density ablators[A].Daytona Florida,2008 |
| [42] | Kratsch K M;Loomis W C;Randles P W .Jupiter probe heat shield design[AIAA-77-427][R].,1977. |
| [43] | Nelson H F .Analysisof Jupiter Probe Heat Shield Recession Uncertainties[AIAA-78-919][R].,1978. |
| [44] | F. S. Milos;Y. -K. Chen;T. H. Squire;R. A. Brewer .Analysis of Galileo Probe Heatshield Ablation and Temperature Data[J].Journal of spacecraft and rockets,1999(3):298-306. |
| [45] | Kontinos D A;Stackpoole M.Post-Flight analysis of the stardust sample return capsule earth entry[A].,2008 |
| [46] | Del Papa S V .The development of a CO2 test capability in the NASA JSC arcjet for Mars reentry simulation[NASA-20110011509][R]. |
| [47] | Laub B .Rotating arc jet test model:time-accurate trajectory heat flux replication in a ground test environment[NASA-20110013229][R]. |
| [48] | Herdrich G.Mars entry simulation using the inductively heated plasma generator IPG4[A].Anaheim,California,2001 |
| [49] | Endlich P.Mars entry simulation with dust using an inductively heated generator[A].St.Louis,Missouri,2002 |
| [50] | Y. -K. Chen;Frank S. Milos .Ablation and Thermal Response Program for Spacecraft Heatshield Analysis[J].Journal of spacecraft and rockets,1999(3):475-483. |
| [51] | Raiche G A;Driver D M.Shock layer optical attenuation and emission spectroscopy measurements during arc jet testing with ablating models[A].Reno,Nevada,2004 |
| [52] | Kenneth S .Heating analysis for the Pioneer Venus Multiprobe Mission[ADA280165][R].,1974. |
| [53] | Venkatapatty E;Land B;Hartman J.Selection and certification of TPS:constraints and considerations for Venus mission[A].Adanta,GA,2008 |
| [54] | Tauber M E;Wercinski P F;Papadopoulos P et al.Estimates of Heatshielding Requirements for Saturn Probe Missions[R].Space Projects Division,1994-7-29. |
| [55] | Venkatapathy E;Arnold J O;Bowles J V.Multi-Layer,multifunctional,thermal protection in a honeycomb system for aerocapture and direct atmospheric entry[A].,2008 |
| [56] | National Academy Press.Mars sample return,issues and recommendations[M].Space Studies Board,National Research Council,Washington D.C,1997 |
| [57] | Lockwood M K.Titan aerocapture systems analysis[A].Huntsville,AL,2003 |
| [58] | Takashima N;Hollis B R;Zoby E V.Preliminary aerothermodynamics of Titan Aerocapture Aeroshell[A].Huntsville,AL,2003 |
| [59] | Laub B.Thermal protection concepts and issues for Aerocapture at Titan[A].Huntsville,AL,2003 |
| [60] | Lockwood M K.Neptune aerocapture mission systems analysis[A].Providence,RI,2004 |
| [61] | Laub B;Chen Y K.TPS challenges for Neptune aerocapture[A].Providence,RI,2004 |
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%