中国空间科学技术Issue(4)：69-75,7.DOI:10.3780/j.issn.1000-758X.2015.04.010
火星盘缝带伞跨声速风洞试验研究
Research on Transonic Wind Tunnel Tests of Mars Disk-Gap-Band Parachutes
高树义 1戈嗣诚 2梁艳3
作者信息
- 1. 西北工业大学航天飞行动力学技术重点实验室，西安 710072
- 2. 北京空间机电研究所，北京 100094
- 3. 北京空间机电研究所，北京 100094
- 折叠
摘要
Abstract
In the Mars entry decelerate landing program , the parachute is a key instrument of the aerodynamic decelerator system . Because of the particularity of the Mars atmosphere , the parachute used for the Mars misson deploys under the supersonic , low density , low dynamic pressure conditions . So the construction and sizing of the Mars parachute is much important . The Mars parachute technology was investigated and analyzed by four types of parachute ,considering the disk‐band area ratio and porosity of the canopy material . To determine the drag and static stability of the various types of disk‐gap‐band parachute model , the Mars parachute transonic characteristics test in China was firstly conducted . The front truss and wind tunnel balance was used to measure the axis force on the parachute model ,and the photography was used to observe the angle of attack of the parachute . The test results show that , the transonic drag coefficient of the disk‐gap‐band parachute accords with the theoretical one and can satisfy the Mars mission requirements . It is also observed that the reduction of stability of the disk‐gap‐band parachute is accompanied by the increasing of the drag performance .关键词
进入减速/盘缝带伞/跨声速/风洞试验/火星着陆器Key words
Entry decelerate/Disk-gap-band parachute/T ransonic/Wind tunnel tests/M ars lander引用本文复制引用
高树义,戈嗣诚,梁艳..火星盘缝带伞跨声速风洞试验研究[J].中国空间科学技术,2015,(4):69-75,7.
