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http://dx.doi.org/10.6112/kscfe.2016.21.2.112

MULTI-PHYSICAL SIMULATION FOR THE DESIGN OF AN ELECTRIC RESISTOJET GAS THRUSTER IN THE NEXTSAT-1  

Chang, S.M. (School of Mechanical, Automotive, Naval Architecture, and Ocean Engineering, Kunsan National University)
Choi, J.C. (Research Institute, Space Solution, Inc.)
Han, C.Y. (Satellite R&D Head Office, Korea Aerospace Research Institute)
Shin, G.H. (SaTReC, Korea Advanced Institute of Science and Technology)
Publication Information
Journal of computational fluids engineering / v.21, no.2, 2016 , pp. 112-119 More about this Journal
Abstract
NEXTSat-1 is the next-generation small-size artificial satellite system planed by the Satellite Technology Research Center(SatTReC) in Korea Advanced Institute of Science and Technology(KAIST). For the control of attitude and transition of the orbit, the system has adopted a RHM(Resisto-jet Head Module), which has a very simple geometry with a reasonable efficiency. An axisymmetric model is devised with two coil-resistance heaters using xenon(Xe) gas, and the minimum required specific impulse is 60 seconds under the thrust more than 30 milli-Newton. To design the module, seven basic parameters should be decided: the nozzle shape, the power distribution of heater, the pressure drop of filter, the diameter of nozzle throat, the slant length and the angle of nozzle, and the size of reservoir, etc. After quasi one-dimensional analysis, a theoretical value of specific impulse is calculated, and the optima of parameters are found out from the baseline with a series of multi-physical numerical simulations based on the compressible Navier-Stokes equations for gas and the heat conduction energy equation for solid. A commercial code, COMSOL Multiphysics is used for the computation with a FEM (finite element method) based numerical scheme. The final values of design parameters indicate 5.8% better performance than those of baseline design after the verification with all the tuned parameters. The present method should be effective to reduce the time cost of trial and error in the development of RHM, the thruster of NEXTSat-1.
Keywords
NEXTSat-1; Gas Thruster; Multi-physical Design; Shape Design;
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Times Cited By KSCI : 3  (Citation Analysis)
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1 2014, Lee, S.H., Shin, G.H., Tahk, G.M., Chae, J.S., Jang, T.S., Seo, J.G. and Cha, W.H., "Preliminary Configuration Design for NEXTSat-1," Proceedings of the 2014 Spring Conference, The Korean Society for Aeronautical and Space Sciences, Jeju, Korea, 2014, pp.924-927.
2 Surrey Satellite Technology US LLC., Surrey Micro Gas Propulsion System: accessible in web, http://www.sst-us.com/ downloads/datasheets/gas-propulsion-system.
3 2014, Mission Design Division Staff, Small Spacecraft Technology State of Art, NASA/TP-2014-216648, Rev.1, Ames Research Center, Moffett Field, California.
4 2014, Kwon, K., Walker, M.L.R. and Mavris, D.N., "Study on Anomalous Electron Diffusion in the Hall Effect Thruster," International Journal of Aeronautical and Space Sciences, Vol.15, No.3, pp.320-334.   DOI
5 2005, Hanhwa Aerospace Research Institute, Manufacture of Resistojet Engine for Small Satellite, Aerospace Research Institute, Hanhwa Corp., M1-0417-00-0013, Ministry of Science and Technology, Korea.
6 2010, Kim, S.S. and Chang, S.M., "Compressibility Effect in the Axisymmetric Internal Flow Past a Microgap," Transactions of the Korean Society of Mechanical Engineers (B), Vol.34, No.12, pp.1061-1069.   DOI
7 2003, Kim, J.S., Lee, K.H., Han, C.Y., Jang, K.W. and Choi, J.C., "Design and Integrtion of STM Propulsion System for LEO Observation Satellite Development," Journal of the Korean Society for Aeronautical and Space Sciences, Vol.31, No.8, pp.115-124.   DOI
8 2006, Sandberg, R.D. and Fasel, H.F., "Numerical Investigation of Transitional Supersonic Axisymmetric Wakes," Journal of Fluid Mechanics, Vol.563, No.1, pp.1-41.   DOI
9 1985, Champion, K.S.W., Cole, A.E. and Kantor, A.J., "Standard and Reference Atmospheres," in Handbook of Geophysics and the Space Environment, edited by A.S. Jursa, Air Force Geophysics Laboratory, Bedford, Massachusetts, pp.14-(1-43).
10 2013, He, B., Zhang J. and Cai G., "Research on Vacuum Plume and its Effect," Chinese Journal of Aeronautics, Vol.26, No.1, pp.27-36.   DOI
11 2004, Schenk, O. and Gartner, K, "Solving Unsymmetric Sparse Systems of Linear Equations with PARDISO," Journal of Future Generation Computer Systems, Vol.20, No.3, pp.475-487.   DOI
12 2001, Hazewinkel, M., "Newton method," Encyclopedia of Mathematics, Springer, ISBN 978-1-55608-010-4: accessible in web, http://www.encyclopediaofmath.org/index.php/Newton_method.
13 1990, Bich, E., Millat, J. and Vogel, E., "The Viscosity and the thermal conductivity of Pure Monoatomic Gases from Their Normal Boiling Point up to 5000K in the Limit of Zero Density and at 0.101325 MPa," Journal of Physical Chemistry Reference Data, Vol.19, No.6, pp.1289-1305.   DOI
14 2007, AK Steel, "Product Data Sheet: 316/316L Stainless Steel," AK Steel Corp., West Chester, Ohio, 2007: accessible in web, http://www.aksteel.com/pdf/markets_products/stainless/austenitic/316_316l_data_sheet.pdf.
15 2010, Osterman, V. and Antes Jr., H., Critical Melting Points and Reference Data for Vacuum Heat Treating, Rev. 4, Solar Atmospheres, Fontana, California.
16 1999, Strachan, A., Cagin, T. and Goddard III, W.A., "Phase Diagram of MgO from Density-functional Theory and Molecular-dynamics Simulations," Physical Review B, Vol.60, No.22, pp.15084-15092.   DOI