An air-breathing electric propulsion system can collect the rarefied gas as propellant and extend the operating life of the satellite.One of the key technologies of this system is the design on the air-intake structure.In this paper, using the Direct Simulation Monte Carlo (DSMC) method, the effects of the aspect ratio, the cone angle of the air-intake, gird structure and its geometric parameters on the intake performance were examined numerically.The results show that increasing the aspect ratio of air-intake leads to the enhancement of the compression ratio and collection efficiency of air-intake.When the aspect ratio is 7,the maximum of compression ratio and collection efficiency are obtained and they are 200 and 0.65 respectively.With the increase of cone angle of air-intake at exit, both the compression ratio and collection efficiency of air-intake increase first and then decrease.The theoretical optimal value of the cone angle at exit is 70°.The grid structure improves the compression ratio and collection efficiency of the air-intake by effectively preventing the captured particles from escaping from the inlet of air-intake.Changing the thickness of grid plate has little effect on compression ratio and collection efficiency of air-intake.With the length of grid plate and the layer number of grid plate increasing, the compression ratio of air-intake increases, while the collection efficiency decreases.
XIE Xiaole
,
LI Jiyuan
,
WANG Xian
,
LU Haifeng
,
HAN Xianwei
. Influence of air-intake structure in air-breathing electric propulsion system on intake performance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022
, 43(3)
: 125272
-125272
.
DOI: 10.7527/S1000-6893.2021.25272
[1] ANDREUSSI T,FERRATO E,GIANNETTI V, et al.Development status and way forward of SITAEL's air-breathing electric propulsion engine[C]//AIAA Propulsion and Energy Forum, 2019.
[2] FEILI D, LOTZ B, MEYER B, et al.Testing and comprehensive modeling of a GIE utilizing atmospheric propellants[C]//33rd International Electric Propulsion Conference, 2013.
[3] 何慧东.日本"超低轨道技术试验卫星"任务及应用[J].国际太空,2018(9):50-53. HE H D.Japan's super low altitude test satellite mission and application[J].Space International, 2018(9):50-53(in Chinese).
[4] JENKINS L.Mission for planet earth:saving the planet[C]//AIAA SPACE Conference & Exposition, 2009.
[5] DEMETRIADES S T.A novel system for space flight using a propulsive fluid accumulator[J].Journal of the British Interplanetary Society, 1959, 17:114-119.
[6] BUSSARD R W.Galactic matter and interstellar flight[J].Astronautical Acta, 1960, 6(4):1-14.
[7] REICHEL R H, SMITH T L, HANFORD D R.Potentialities of air-scooping electrical space propulsion systems[C]//Electric Propulsion Development, 1962:711-743.
[8] REICHEL R H.The air-scooping nuclear-electric propulsion concept for advanced orbital space transportation missions[J].Journal of the British Interplanetary Society, 1978, 31:62-66.
[9] ZUKERMAN A, KRETSCHMER C B.A study of the feasibility of an atomic oxygen ramjet[J].Planetary & Space Science, 1961, 4:60-76.
[10] CANN G.A space electric ramjet[C]//11th Electric Propulsion Conference, 1975.
[11] NISHIYAMA K.Air breathing ion engine concept[C]//54th International Astronautical Congress of the International Astronautical Federation, 2003.
[12] FUJITA K.Air intake performance of air breathing ion engines[J].Journal of the Japan Society for Aeronautical & Space Sciences, 2004, 52(610):514-521.
[13] FUJITA K.Air-intake performance estimation of air-breathing ion engines[J].Transactions of the Japan Society of Mechanical Engineers Part B, 2004, 70(700):3038-3044.
[14] HISAMOTO Y, NISHIYAMA K, KUNINAKA H.Design of air intake for air breathing ion engine[C]//63th International Astronautical Congress, 2012.
[15] TAGAWA M, YOKOTA K, NISHIYAMA K, et al.Experimental study of air breathing ion engine using laser detonation beam source[J].Journal of Propulsion and Power, 2013, 29(3):501-506.
[16] DI CARA D, GONZALEZ DEL AMO J, SANTOVINCENZO A, et al.RAM electric propulsion for low earth orbit operation:an ESA study[C]//30th International Electric Propulsion Conference, 2007.
[17] HOHMAN K.Atmospheric breathing electric thruster for planetary exploration[R].2012.
[18] ROMANO F, BINDER T, HERDRICH G, et al.Air-intake design investigation for an air-breathing electric propulsion system[C]//34th International Electric Propulsion Conference, 2015.
[19] BARRAL S, CIFALI G, ALBERTONI R, et al.Conceptual design of an air-breathing electric propulsion system[C]//34th International Electric Propulsion Conference, 2015.
[20] BINDER T, BOLDINI P C, ROMANO F, et al.Transmission probabilities of rarefied flows in the application of atmosphere-breathing electric propulsion[C]//American Institute of Physics Conference Series, 2016.
[21] EROFEEV A I.Air intake in the transient regime of rarefied gas flow[J].TsAGI Science Journal, 2018, 49(2):137-148.
[22] LI Y W, CHEN X, LI D M, et al.Design and analysis of vacuum air-intake device used in air-breathing electric propulsion[J].Vacuum, 2015, 120:89-95.
[23] 张伟文,张天平.空间电推进的技术发展及应用[J].国际太空,2015(3):1-8. ZHANG W W, ZHANG T P.Technological development and application of electrically powered spacecraft propulsion[J].Space International, 2015(3):1-8(in Chinese).
[24] 张天平.兰州空间技术物理研究所电推进新进展[J].火箭推进,2015,41(2):7-13. ZHANG T P.New progress of electric propulsion technology in LIP[J].Journal of Rocket Propulsion, 2015, 41(2):7-13(in Chinese).
[25] BIRD G A.Molecular gas dynamics and the direct simulation of gas flows[M].Oxford:Clarendon Press, 1994:30-45.
[26] 庄洪春.宇航空间环境手册[M].北京:中国科学技术出版社,2000:41-46. ZHUANG H C.Space environment manual[M].Beijing:Science and Technology of China Press, 2000:41-46(in Chinese).
[27] 王娴,王秋旺,陶文铨,等.直接模拟蒙特卡罗方法在微通道流动模拟中的应用[J].工程热物理学报,2002,23(增刊):125-128. WANG X, WANG Q W, TAO W Q, et al.Application of direct simulation Monte Carlo method in microchannel flow simulation[J].Journal of Engineering Thermophysics, 2002, 23(supply):125-128(in Chinese).
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