Document Type : Research Paper

Authors

1 Member of the faculty of the Space Science Research Group Aerospace Research Institute, Ministry of Science, Research and Technology.Tehran.IRAN

2 Department of Aerospace Engineering, KN. Toosi University of Technology.Tehran,IRAN

3 Department of Aerospace Engineering, KN. Toosi University of Technology.Terhan, IRAN

4 Department of Aerospace Engineering, KN. Toosi University of Technology.Tehran, IRAN

Abstract

The main goal of this paper is to introduce the Moon exploration mission design based on existing technology.The Moon exploration mission design entailsoptimal maneuvering orbit, payload and launch vehicle design. Optimal maneuvering orbit is designed with respect to Circular Restricted Three Body Problem (CRTBP) to model the motion of a spacecraft in the Earth/Moon system. To this end, optimal maneuvering orbitadopted CRTBP as dynamical model and obtained three-dimensional Earth to Moon transfers with low cost. This method is more preferable and flexible than Hohmann transfer because of its lower cost and its access to various inclinations in departure and arrival.The optimal Launch Vehicle Conceptual Design (LVCD) algorithm is based on optimization of major design parameters. LVCD algorithm is coded in a software to let the design engineer explore the design space and to reduce the cost and time of the conceptual design phase that is developed by the authors.The optimization process is performed subject to the restrictions and the performance index is optimized in a mutual iteration mechanism. Consequently, the designed launch vehicle ability to satisfy the mission objectives and its requirements is evaluated.

Keywords

[1]      Available, [on line]: http://www.jaxa.jp/projects/ sat/selene
[2]      Available, [on line]: http://nssdc.gsfc.nasa.gov
[3]      Available, [on line]: http://sci.esa.int/science-e
[4]      Available, [on line]: http://www.isro.gov.in/ Chandrayaan
[5]      Frank A. Slazer, James C. Harvey, Robert J. Sirko, Jonathan D. Barr, David K. Bonnar, Scott C. Ward, Delta IV Launch Vehicle Growth Options to Support NASA’S Space Exploration Vision, 55th International Astronautical Congress, Vancouver, Canada, 2004.
[6]      Charania, A.C., Andrew, M., Crocker, E. Bradford, J. andR. Olds, J.,“A Method for Strategic Technology Investment Prioritization for Advanced Space Transportation Systems,”52nd International Astronautical Congress, Toulouse, France, 1-5 Oct 2001.
[7]      Hofeller, J.Bjelde, B. andVozoff, M., “Responsiveness of the Falcon 1 Launch Vehicle, Associated Challenges, and Projected Improvements,” 6th Responsive Space Conference, Los Angeles, CA, April 28–May 1, 2008.
[8]      Conley, C., “Low Energy Transit Orbits in the Restricted Three-Body Problem,” SIAM Journal of Applied Mathematics, Vol. 16, 1968, pp. 732-746.
[9]      Belbruno, E. and Miller, J., A Ballistic Lunar Capture Trajectory for the Japanese Spacecraft Hiten, JPL IOM 312/90.4-1731-EAB, June 15, 1990.
[10]   Koon, W.S., Lo, M.W., Marsden, J.E., & Ross, S.D., “Shoot the Moon, Spaceflight Mechanics 2000,”AAS, Vol. 105, Part II, 2000, pp. 1017-1030.
[11]   Parker, J. S. and Lo, M.W., “Shoot the Moon 3D,”Advances in the Astronautical Sciences, AAS 05-383, 2006.
[12]   Koon,W.S.,Lo, M.W.,Marsden, J.E. andRoss, S.D.,“Dynamical Systems, the Three-Body Problem and Space Mission Design,” word scientific, Equdiff 99,  2000, pp. 1167-1181.
[13]   Howard D. Curtis, Orbital Mechanics for Engineering Students, Embry Riddle Aeronautical University Dayton Beach, Florida, 2005, pp. 570-574.
[14]   Martin J. L. Turner, Rocket and Spacecraft Propulsion, Principles, Practice and New Developments (Second Edition), 2005, pp. 25-30.
[15]   John R. Beisel, Martin Baltimore, “A Weight Engineer's Viewof The Space Age Vehicle,”The Seventeenth Conference of S.A.W.E,The Belmont plaza,New York, 1958.
[16]   R. Pence, D.,“Preliminary Weight Estimation of Liquid Propellant Stages,”26th Annual Conference at Boston, Massachusetts, May 1-4, 1967.
[17]   R. Reitz, G., Denver Colorado, “A Methodof Weight Estimation for Advanced Missile Design,”23rd National Conference, SAWE Dalastexas, May 18-21, 1964.
[18]   Mirshams, M.,Karimi, H. andNaseh, H.,“Algorithm for Optimization of Mass Distribution in Multi-stage Liquid Propellant Launch Vehicle,”6thIranian Society of Aerospace Conference, K.N. Toosi University of Technology, 2007 (in Persian).
[19]   Malyshev, V.V.,Krasilshikov, M.N.,Bobronikov, V.T. andDishel, V.D.,Aerospace Vehicle Control, Modern Theory and Applications, Institute aeronautics and Space, Brazil, IAE, 1996.
[20]   E. Kirk, D.,Optimal Control Theory An Introduction, Monterey, California, 1970.
[21]   Mirshams,M.,Karimi, H. andNaseh,H.,“Suggestion Algorithm for Determination of Pitch program in Multi-stage Launch Vehicle in Conceptual Design Phase,”6th Iranian Society of Aerospace Conference, K.N. Toosi University of Technology, 2007 (in Persian).
[22]   Lewis, J. andM.Rice,Th.,“Design of University Launch Vehicle System,”Journal of AIAA, Department of Aerospace Engineering, University of Maryland at College Park, 1992.
[23]   Chakroborty, Sh. R. Wertz, J. andConger,R., "The Scorpius Expendable Launch Vehicle Family and Status of the Sprite Small Launch Vehicle," 1stResponsive Space Conference, April 1-3, 2003.
[24]   Tsohas,J. andJ. Droppers, L.,“Sounding Rocket Technology Demonstration for Small Satellite Launch Vehicle Project,”AIAA, 24-27 April 2006.
[25]   Mirshams, M.,Karimi, H. andNaseh, H.,“Multi-stage liquid propellant launch vehicle conceptual design based on combinatorial optimization of major design parameters,”Journal of Space Science & Technology (JSST), Vol. 1, No. 1, 2008, pp. 21-36 (in Persian).
[26]   Mirshams, M.,Karimi, H. andNaseh,H.,“Launch Vehicle Conceptual Design (LVCD) Software,”7th International Conference Society of Aerospace, Sharif University of Technology, 2009(in Persian).
[27]   Mahyari, M.N.,Karimi, H.,Naseh, H. andMirshams, M.,“Numerical and Experimental investigation of vortex breaker effectiveness on the improvement in launch vehicle ballistic parameters,”Journal of Mechanical, Science and Technology, Vol. 24, No. 10, 2010, pp. 1997-2006.
[28]   Akhlaghi, A.M., Naseh, H., Mirshams, M., Irani, S.,“A Bayesian Networks Approach to Reliability Analysis of a Launch Vehicle Liquid Propellant Engine,”Journal of Aerospace, Science and Technology (JAST), 2012.
[29]   Rothschild,W.,Boyd, D. andHenderson,E., “Shuttle Derived Launch VehicleConcepts,”AIAA Conference, Long Beach, California, 30 August -1 September 2005.
[30]   Berglund, M.,Marin, D. andWilkins, M., “The Next-Generation Heavy-Lift Vehicle - The Inaugural Flight of the EELV Delta IV Heavy,”AIAA Conference, Long Beach, California, 30 August -1 September 2005.
[31]   Ishimoto, Sh.,FujiiI,K..andShimura, K.,“A Design Study of a Next Generation Launch System,” ISTS 2008-g-9, 26th ISTS, Hamamatsu, Japan,June 2008.
[32]   Joveini, H., “Safireomid,” Azarioon Book Company (published in persian), 2009.
[33]   Kakoi, M., Design of Transfers from Earth –Moon L1/L2Libration Point, Orbits toa Destination Object, [Thesis PhD],Purdue University, 2015.
[34]   Soo No, T.,Lee, J.,Eon Jeon, G. andLee, D.,“A Study on Earth-Moon Transfer Orbit Design,”Int’l J. of Aeronautical & Space Sci.Vol. 13, No. 1, 2012, pp. 106–116.
[35]   I.Abouelmagd, E.,Asiri, H.M. andSharaf, M.A.,“The effect of oblateness in the perturbed restricted three-body problem,”MeccanicaVol. 48, No. 10, 2013, pp 2479–2490.
[36]   L. Bradley, D.,M. Sharp, A. and Kumar, R.,“Student-Designed Liquid Rocket Engine From Concept to Completion,”Joint Propulsion Conference, AIAA Propulsion and Energy Forum, 4865, 2018.