火星进入减速器技术综述与展望
收稿日期: 2014-04-15
修回日期: 2014-10-08
网络出版日期: 2014-10-09
基金资助
国家自然科学基金(61273051,60804057);国家"863"计划(2011AA7034057E,2012AA121601)
Review and prospect of decelerator technologies for Mars entry
Received date: 2014-04-15
Revised date: 2014-10-08
Online published: 2014-10-09
Supported by
National Natural Science Foundation of China (61273051, 60804057); National High-tech Research and Development Program of China (2011AA7034057E, 2012AA121601)
李爽 , 江秀强 . 火星进入减速器技术综述与展望[J]. 航空学报, 2015 , 36(2) : 422 -440 . DOI: 10.7527/S1000-6893.2014.0279
With the continuous progress of the Mars exploration, future Mars missions, such as Mars sample return, manned Mars missions, and Mars base, require the lander with a larger size and heavier mass to land on the surface of the Mars, thus inevitably need more efficient deceleration technologies for Mars atmospheric entry. The history of aerodynamic deceleration for Mars entry is reviewed first based on the past successful Mars landing missions in the paper. Then, the characteristics and challenges of decelerator technologies encountered during Mars entry are analyzed in detail. And the system configuration and state-of-art of the inflatable decelerator, deployable decelerator and supersonic retro-propulsion decelerator are summarized. Finally, a more comprehensive analysis and outlook for these three Mars entry decelerators are conducted.
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