| 火星探测降落伞模型高速风洞变迎角试验技术 |
| |
| 引用本文： | 杨贤文,郝东,易国庆,师建元,郭鹏.火星探测降落伞模型高速风洞变迎角试验技术[J].宇航学报,2019,40(12):1461-1467. |
| |
| 作者姓名： | 杨贤文 郝东 易国庆 师建元 郭鹏 |
| |
| 作者单位： | 中国空气动力研究与发展中心，绵阳 621000 |
| |
| 摘 要： | 为获得火星探测器物伞系统动力学仿真中需要使用的降落伞轴向力、法向力、俯仰力矩系数，开展了火星探测降落伞模型高速风洞变迎角试验技术研究，研制了火星探测降落伞模型高速风洞变迎角试验装置，进行了火星探测降落伞模型高速风洞变迎角试验，获得了火星探测降落伞模型在马赫数范围0.4～0.8、迎角范围0°～25°时的轴向力、法向力和俯仰力矩系数，并对支撑干扰及洞壁干扰影响进行了扣除修正。试验结果表明：火星探测降落伞模型的轴向力系数随迎角变化较小；常规透气伞的法向力系数随迎角增大而增大，在马赫数为0.4和0.6时，低透气伞的法向力系数在小迎角时随迎角增大而减小；在马赫数范围0.4～0.8时，常规透气伞静稳定，低透气伞的静稳定性较常规透气伞减小，在马赫数为0.4和0.6时，低透气伞在零迎角时静不稳定，出现了非零配平 迎角。
|
| 关 键 词： | 降落伞 高速风洞 测力 变迎角 火星探测 |
| 收稿时间： | 2019-01-23 |
Variable Angle of Attack Test Technique of Mars ExplorationParachute Model in High Speed Wind Tunnel |
| |
| YANG Xian wen,HAO Dong,YI Guo qing,SHI Jian yuan,GUO Peng.Variable Angle of Attack Test Technique of Mars ExplorationParachute Model in High Speed Wind Tunnel[J].Journal of Astronautics,2019,40(12):1461-1467. |
| |
| Authors: | YANG Xian wen HAO Dong YI Guo qing SHI Jian yuan GUO Peng |
| |
| Affiliation: | China Aerodynamics Research & Development Center, Mianyang 621000, China |
| |
| Abstract: | In order to obtain the parachute axial force, normal force and pitching moment coefficients for the dynamic simulation of a Mars probe parachute-payload system, the technical research on variable angle of attack test has been carried out in the high speed wind tunnel, a variable angle of attack test device has been developed, the axial force, normal force and pitching moment coefficients of the Mars exploration parachute model with Mach numbers from 0.4 to 0.8 at angles of attack from 0° to 25° are obtained by the variable angle of attack tests in the high speed wind tunnel, the influence of the support interference and wind tunnel wall interference on the test data is corrected. The test results show that the axial force coefficient of the Mars probe parachute model does not change much with the angle of attack; the normal force coefficient of the conventional fabric permeability parachute model increases with the increase of the angle of attack, the normal force coefficient of the lower fabric permeability parachute model decreases with the increase of the angle of attack at small angle of attack at Mach numbers of 0.4 and 0.6; the conventional fabric permeability parachute model is statically stable in the Mach number range from 0.4 to 0.8, the static stability of the conventional fabric permeability parachute model is greater than that of the lower fabric permeability parachute model, the lower fabric permeability parachute model is statically unstable at the angle of attack of zero and has a nonzero statically stable trim angle of attack at Mach numbers of 0.4 and 0.6. |
| |
| Keywords: | Parachute High speed wind tunnel Force measurement Variable angle of attack Mars exploration |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《宇航学报》浏览原始摘要信息 |
|
点击此处可从《宇航学报》下载全文 |
|
