航天飞机热防护系统
火星探测计划
航空航天工程
火星大气层
船员
隔热板
航空学
火星探测
天体生物学
环境科学
工程类
热的
气象学
火星人
物理
作者
Robin Beck,David M. Driver,Michael Wright,Helen Hwang,Karl T. Edquist,Steven Sepka
出处
期刊:Journal of Spacecraft and Rockets
[American Institute of Aeronautics and Astronautics]
日期:2014-04-28
卷期号:51 (4): 1139-1150
被引量:69
摘要
Early in the development of the Mars Science Laboratory thermal protection system on the heatshield, project management planned to use Lockheed Martin’s Super Light Ablator in honeycomb as the ablative material based on successful use on previous Mars entry heatshields and on stagnation arcjet tests at heating rates beyond the design levels. Because this heatshield would be the first to experience combined turbulent flow and high shear environments as it entered the Mars atmosphere, tests were performed in various arcjet facilities on flat-plate, wedge, and swept-cylinder specimen configurations in order to ascertain the effects of shear on the material. During the course of these tests, a set of conditions within the flight envelope was identified that resulted in catastrophic failure in the SLA-561V. Consequently, project management decided to replace the SLA-561V with the phenolic-impregnated carbon ablator, the material that had flown successfully on the Stardust mission and was undergoing intense testing and characterization for the Crew Exploration Vehicle Thermal Protection System Advanced Development Program. With only two years remaining before the expected launch date, and less than 18 months before the heatshield delivery date, the Mars Science Laboratory team developed and built NASA’s first tiled ablator flight heatshield that contributed to the outstanding success of the spacecraft’s entry, descent, and landing on 5 August 2012.
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