航天推进技术研究院主办
[1]王宏亮,史 超,赵 曙,等.火星大气来流模拟装置CFD仿真与试验[J].火箭推进,2020,46(01):89-95.
WANG Hongliang,SHI Chao,ZHAO Shu,et al.CFD and experimental studied on the Mars atmosphere incoming flow equipment[J].Journal of Rocket Propulsion,2020,46(01):89-95.
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WANG Hongliang,SHI Chao,ZHAO Shu,et al.CFD and experimental studied on the Mars atmosphere incoming flow equipment[J].Journal of Rocket Propulsion,2020,46(01):89-95.
火星大气来流模拟装置CFD仿真与试验
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
46
期数:
2020年01期
页码:
89-95
栏目:
研究与设计
出版日期:
2020-02-29
- Title:
- CFD and experimental studied on the Mars atmosphere incoming flow equipment
- Keywords:
- Mars detector; rarefied atmosphere incoming flow; CFD simulation; experimental test; vcacuum chamber
- 分类号:
- V430文献标识码:A 文章编号:1672-9374(2020)01-0089-07
- 摘要:
- 根据我国火星着陆巡视器工作过程,其着陆发动机需要在相对火星大气高速迎风运动中可靠点火。由于巡视器着陆时发动机喷管出口气流与火星稀薄气流方向相反,目前无法通过理论计算准确获得着陆过程的动态流场对发动机起动过程的影响量值。为验证火星着陆环境下发动机点火的适应性,需要建立发动机的火星大气来流试验环境模拟条件。为模拟发动机在火星大气条件下的相对运动,在真空舱内发动机保持固定,前端设置环形来流形成装置,该装置在发动机喷管周围形成一定速度的逆向来流包络。采用数值模拟技术结合试验验证方法,在火星着陆器巡视器主发动机性能考核试验中,针对来流的形成装置开展了设计研究工作。来流模拟试验测试数据表明:在确保贮箱供应压力稳定的条件下,来流模拟系统能够形成100～200 m/s速度的稳定来流,发动机在来流下能稳定启动工作,真空舱压力满足试验要求。
- Abstract:
- According to the orbit and land detector working process,the landing rocket engine needs to be ignited steadily when the detector is landing toward the surface of the Mars.Due to the shortage of theoretical method which can be used to evaluate the accuracy effect of dynamic reverse flow flied to the rocket engine when it started, the experimental test and evaluation platform were needed to be built to test the starting adaptation of the rocket engine of the detector for the atmosphere of Mars.In order to simulate the relative velocity between the rocket engine and Mars atmosphere, one atmosphere incoming flow equipment were set towards to the outlet of the nozzle of the engine which fixed in the vacuum chamber.The equipment can generate a certain speed of atmosphere incoming flow to the nozzle.Based on the CFD and experimental test method, the CFD and experimental analysis for atmosphere incoming flow equipment were studied in the testing process for the rocket engine of Mars detector.The testing data show that the stable atmosphere incoming flow of 100～200 m/s can be generated through the equipment, the rocket engine can start stably under the incoming flow condition and the pressure of the vacuum chamber was retained under the requirement of the test.
参考文献/References:
[1] GUYNN M D, CROOM M A,SMITH S C,et al. Evolution of a Mars airplane concept for the ARES Mars scout mission[R].AIAA 2003-657.
[2] RONALD G.Wind tunnel simulations of aeolian process[R].NASA-eb-176382.
[3] CHRISTOPHER V S. Wind tunnel tests to determine drag coefficients for the Mars tumbleweed[R].AIAA 2005-248.
[4] BRAUN R D, WRIGHT H S, CROOM M A, et al.Design of the ARES Mars airplane and mission architecture[J].Journal of Spacecraft and Rockets, 2006, 43(5):1026-1034.
[5] NORNBERG P.The new danish/esa Mars simulation wind tunnel at arhus university[C]//41st Lunar and Planetary Science Conference,2010.
[6] TANAKA Y, OKABE Y, SUZUKI H, et al.Conceptual design of Mars airplane for geographical exploration[C]// Proceedings of the 36th JSASS Annual Meeting. Tokyo:JSASS,2005.
[7] OYAMA A, FUJII K.A study on airfoil design for future Mars airplane[C]//44th AIAA Aerospace Sciences Meeting and Exhibit.Reno, Nevada.Reston, Virigina:AIAA, 2006.
[8] ANYOJI M.et al.Development of low density wind tunnel to simulate atmospheric flight on Mars[R].AIAA 2009-1517.
[9] 战培国.国外火星风洞及火星环境风工程研究[J].环境科学与技术, 2014, 37(S2):206-209.
[10] 史建魁, 张仲谋, 刘振兴, 等.火星环境探测结果分析[J].地球物理学进展, 1997, 12(4):98-108.
[11] 欧阳自远, 肖福根.火星及其环境[J].航天器环境工程, 2012, 29(6):591-601.
[12] 王宏亮, 李广会, 曹明明, 等.推力室逆置点火瞬时真空舱流场数值与试验研究[J].火箭推进, 2014, 40(2):77-81.WANG H L, LI G H, CAO M M, et al.Numerical and experimental study of flow field in vacuum chamber during ignition transient of reversely-fixed thrust chamber[J].Journal of Rocket Propulsion, 2014, 40(2):77-81.
[13] 唐家鹏.FLUENT 14.0超级学习手册[M].北京:人民邮电出版社, 2013.
[14] 王福军.计算流体动力学分析:CFD软件原理与应用[M].北京:清华大学出版社, 2004.
[15] 黄飞, 赵波, 程晓丽, 等.返回器高空稀薄气动特性的真实气体效应研究[J].宇航学报, 2014, 35(3):283-290.
[16] ANYIJI M.Development of low density wind tunnel to simulate atmospheric flight on Mars[R].AIAA 2009-1517.
[17] WHITE B R.A low-density boundary-layer wind tunnel facility[R].AIAA 1987-0291.
[18] CHRISTOPHER V S.Wind tunnel tests to determine drag coefficients for the Mars tumbleweed[R].AIAA 2005-248.
[19] MERRISON J P.Latest results from the European mars simulation wind tunnel facility[Z].2011.
[20] RONALD G.Wind tunnel simulations of aeolian processes[R].NASA-cb-176382.
备注/Memo
收稿日期:2019-04-27; 修回日期:2019-06-29基金项目:国家技术基础科研项目(JSJL2015203B029)作者简介:王宏亮(1979—),男,博士,研究领域为液体火箭发动机试验技术
更新日期/Last Update:
2020-02-25