Low Enriched Uranium based Nuclear Rocket Propulsion Technology: Mars Exploration Mission

  • Gaurab Neupane Department of Mechanical Engineering, SRM Institute of Science and Technology, Kattankulathur, Chennai, India

Abstract

Many space agencies like NASA, SPACE-X have promised to send humans into the red planet in future. So, considering their project of mars colonization, nuclear rocket propulsion would be the better option. Replacing chemical rockets by nuclear rockets may reduce the mission duration and also can reduce the mass of the propellant used. In chemical rockets, propellant releases energy through combustion but in case of nuclear rockets, propellant i.e. hydrogen is heated up in controlled fission reaction in nuclear reactor inside the rocket engine. Specific impulse of the nuclear rocket is greater than chemical rocket. This helps in providing gigantic thrust as a result mission duration is decreased. The challenging parameter of increasing specific impulse is solved by maximizing specific impulse which is done by increasing the exhaust core temperature. The fuel is selected in such a way so that the exhaust temperature would be obtained. The (U, Zr) C –graphite fuel is selected because it has high uranium density and melting point is equivalent to exhaust core temperature which is sufficient enough to enhance the reactivity of the fissile material and thus to increase the rocket performance. A mathematical analysis shows that the percentage of mass of propellant used in mars mission will be lesser than the chemical rockets because the specific impulse is expected to be more in nuclear propulsion. The specific impulse obtained from the CFD Analysis of rocket nozzle is 979 sec with exit velocity of 9604m/s.

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References

[1] Ryan McLaren and Magdi Ragheb, “Nuclear Propulsion Choices For Space Exploration,” University of Illinois at Urbana-Champaign, 1st International Nuclear and Renewable Energy Conference (INREC10), Amman, Jordan, March 21-24, 2010.
[2] Stanley K. Borowski, David R McCurdy, ThomasW packard, “Nuclear Thermal Propulsion (NTP): A Proven Growth Technology for Human NEO / Mars Exploration Missions”, National Aeronautics and Space Administration.
[3] A.Yayli, A.A. Aksi, “Nuclear Fuels In Space Rockets”, Cekmece Nuclear Research and Training Center, Nuclear Fuel Technology Deparhnent P. 0. Box. I Atattlrk Airport 34149 Istanbul I Turkey.
[4] Paolo f. venneri , yonghee kim "A feasibility study on low enriched uranium fuel for nuclear thermal rockets - II" , Korea advanced institute of science & technology, Elsevier, Progress in nuclear energy 2015.
[5] Stanley Gunn, "Nuclear propulsion - a historical perspective", Elsevier, Space Policy 17 (2001).
[6] Paolo f. venneri , yonghee kim, "Advancements in the Development of Low Enriched Uranium Nuclear Thermal Rockets” Elsevier, Energy procedia 131(2017).
[7] A. Lou Qualls, Jim Werner "Steps in the Development of Nuclear Thermal Propulsion Fuels”, NASA’s Science Technology Mission Directorate (STMD).
[8] Christopher L Moore, "Technology development for human exploration of mars", Elsevier, Acta Astronautica 67(2010).
[9] B.V.V. Naga Sudhakar, B Purna Chandra Shekhar, P Narendra Mohan, Md Touseef Ahmad, "Modeling and simulation of Convergent-Divergent Nozzle Using Computational Fluid Dynamics”, International Research Journal of Engineering and Technology (IRJET), Volume: 03 Issue: 08 Aug-2016.
[10] K.P.S.Surya Narayana1, K.Sadhashiva Reddy "Simulation of Convergent Divergent Rocket Nozzle using CFD Analysis” , IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE), Volume 13, Issue 4 Ver. I (Jul. - Aug. 2016).
[11] Seung Hyun Nam, Paolo Venneri, Yong Hee Kim, Soon Heung Chang, "Preliminary conceptual design of a new moderator reactor utilizing an LEU fuel for space nuclear thermal propulsion”, Elsevier , Progree in Nuclear Energy 91(2016).
[12] National Aeronautics and Space Administration, NASA, http://www.nasa.gov
[13] National Aeronautics and Space Administration Glenn Research Center, http://www.grc.nasa.gov
Published
2019-01-04
How to Cite
NEUPANE, Gaurab. Low Enriched Uranium based Nuclear Rocket Propulsion Technology: Mars Exploration Mission. International Journal of Research and Engineering, [S.l.], v. 6, n. 1, p. 569-574, jan. 2019. ISSN 2348-7860. Available at: <https://digital.ijre.org/index.php/int_j_res_eng/article/view/369>. Date accessed: 20 may 2019. doi: https://doi.org/10.21276/ijre.2019.6.1.4.