|Table of Contents|

CFD and experimental studied on the Mars atmosphere incoming flow equipment(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2020年01期
Page:
89-95
Research Field:
研究与设计
Publishing date:

Info

Title:
CFD and experimental studied on the Mars atmosphere incoming flow equipment
Author(s):
WANG Hongliang;  SHI Chao;  ZHAO Shu;  WANG Pengjun
(Xi’an Aerospace Propulsion Test Technology Institute,Xi’an 710100, China)
Keywords:
Mars detector;  rarefied atmosphere incoming flow;  CFD simulation;  experimental test;  vcacuum chamber
PACS:
V430文献标识码:A 文章编号:1672-9374(2020)01-0089-07
DOI:
-
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.

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.

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Last Update: 2020-02-25