Basic MATLAB Simulation of Ion Propulsion Rocket by Chlorine as Propellant via Negative Ion Pair Thrusting

Dr. A. Kanni Raj

Abstract


Ion propulsion rocketry is increasingly becoming popular by ion-ion pair thrusting concept, because they need low propellant, and design thrust around 1.5N with low electric power and high efficiency. Basic MATLAB simulation of negative ion-negative ion pair propulsion is explained in this article. Negative ion plasma is obtained from electronegative gas, example, chlorine, by attachment of electron. Formation of large stable negative ion is achievable due to high electron affinity of chlorine. Electron affinity is a measure of energy exchange due to the addition of electron to a neutral atom to form a negative ion. When the neutral chlorine picks up electrons and forms chloride (Cl-) ion,the energy released due to exothermic reaction is-349kJ/mol (ie,-3.6eV/atom). Mechanism of attachment of electron to chlorine involves the formation of intermediates. Due to that, the high repulsive force is created between the same negative ions. Average distance between any neighboringions is important for rocket thrust calculation, and is determined by propellant exhaust velocity. Mass flow rate of propellant is assessed from the ratio of total mass of propellant needed for operation to time periods. This accelerates negative ions to a high velocity in the thrust vector direction with a significantly intense magnetic field and the exhaust of negative ions through nozzle. On comparing with theoretical value and earlier method (xenon ion-electron), this method is capable of achieving required thrust with low electric power (1kW).

Full Text:

PDF

References


References

Sathiyavel, C., and Kanniraj, A., “Simulation Based on Ion-Ion Plasma Techniques of Electric Propulsion in Mars Mission Using Chlorine Gas,” International Journal of Scientific and Engineering Research, Vol.5, pp.114-120, 2014.

Martinez, R.A., “Electric Field Breakdown Properties of Ion Thruster Optics,” MS Thesis, Colorado State University, Fort Collins, Colorado, USA, 2007.

Berend, N., R. Epenoy, R., Cliquet, E., Laurent-Varin, J.L., and Avril, S., “Technological Requirements of Nuclear Electric Propulsion Systems for Fast Earth Mars Transfers,” Progress in Propulsion Physics, Vol. 4, pp.313-336, 2013.

Levchenko, I., Bazaka, K., Ding,Y., Raitses, Y., Mazouffre,S., Henning, T., Klar, P.J., Shinohara, S., Schein, J., Garrigues, L., Kim, M., Lev, D., Taccogna, F., Boswell, R.W., Charles,C., Koizumi, H., Shen, Y., Scharlemann, C., Keidar, M., and Xu, S., “Space Micropropulsion Systems for Cubesats and Small Satellites: From Proximate Targets to Furthermost Frontiers,” Applied Physics Reviews, Vol.5, ID:011104, https://doi.org/10.1063/1.5007734, 2018.

Longmier, B.W., Bering, E.A., Carter, M.D., Cassady, L.D., Chancery, W.J., Chang Diaz, F.R., Glover, T.W., Hershkowitz, N., Ilin, A.V., McCaskill, G.E., Olsen, C.S., and Squire, J.P., “Ambipolar Ion Acceleration in anExpanding Magnetic Nozzle,” Plasma Sources Science and Technology, Vol.20, pp.1-9, ID:015007, doi:10.1088/0963-0252/20/1/015007, 2011.

Aanesland, A., Meige, A., and Chabert, P., “Electric Propulsion Using Ion-Ion Plasmas,” Journal of Physics : Conference Series, Vol.162, ID:012009, pp.1-14, doi:10.1088/1742-6596/162/1/012009, 2009

Goebel, D.M., and Katz, I., “Fundamentals of Electric Propulsion: Ion and Hall Thruster,” Jet Propulsion Lab : Space Science and Technology Series, USA, 2000.

Einat, M., E. Jerby, E., and Rosenman, G., “Free-electron Maser Driven by a Two-stage Ferroelectric Electron-gun,” Journal of Applied Physics, vol.93, pp.2304-2306, 2003.

Bacal, M., McAdams, R., and Lepetit, B., “The Negative Ion Mean Free Path and its Possible Implications,” AIP Publishing : Conference Proceedings, Vol.1390, pp.13-21, doi.org/10.1063/1.3637370, 2011.

Lovtsov, A.S., and Kravchenko, D.A., “Kinetic Simulation of Plasma in Ion Thruster Discharge Chamber, Comparison with Experimental Data,” Procedia Engineering, Vol.185, pp.326 – 331, 2017.

Ilin, A.V., Chang Diaz, F.R., Glover, T.W., Carter, M.D., Cassady, L.D., and White, H., “Nuclear Electric Propulsion Mission Scenarios Using VASIMR Technology,” Nuclear and Emerging Technologies for Space, USA, 2012.

Lingwei, Z., Yu, L., Juan, L. Zuo, G., Haocheng, J. Wang Haixing, W., and Haibin, T., “Numerical Simulation of Characteristics of CEX Ions in Ion Thruster Optical System,” Chinese Journal of Aeronautics, Vol.23, pp.15-21, 2010.

Si, R., and Fischer, C. F., “Electron affinities of Ar and its Homologous Elements Cl, Br, and I,” Physical Reviews A, Vol.98, ID: 052504, pp.1-7, doi/10.1103/ PhysRevA.98.052504, 2018.

Sangregorio, M., Xie, K., Wang, N., Guo, N., and Zhang, Z., “Ion Engine Grids : Function, Main Parameters, Issues, Configurations, Geometries, Materials and Fabrication Methods,” Chinese Journal of Aeronautics, Vol.31, pp.1635–1649, 2018.

V.G. Petukhov, V.G., and Wook, W.S., “Joint Optimization of the Trajectory and the Main Parameters of an Electric Propulsion System,” Procedia Engineering, Vol.185, pp.312 – 318, 2017.

Chen, M., Sun, A., Chen, C., and Xia, G., “Particle Simulation of Grid System for Krypton Ion Thrusters,” Chinese Journal of Aeronautics, Vol.31, pp. 719–726, 2018.


Refbacks

  • There are currently no refbacks.