# Low energy trajectories for the Moon-to-Earth space flight

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## Abstract

The Moon-to-Earth low energy trajectories of ‘detour’ type are found and studied within the frame of the Moon-Earth-Sun-particle system. These trajectories use a passive flight to the Earth from an initial elliptic selenocentric orbit with a high aposelenium. The Earth perturbation increases the particle selenocentric energy from a negative value first to zero and then to a positive one and therefore leads to a passive escape of the particle motion from the Moon attraction near the translunar libration point*L* _{2}. This results in the particle flight to a distance of about 1.5 million km from the Earth where the Sun gravitation decreases the particle orbit perigee distance to a small value that leads to the particle approaching the Earth vicinity in about 100 days of the flight. A set of the Moon-to-Earth ‘detour’ trajectories is defined numerically. Characteristics of these trajectories are presented. The ‘detour’ trajectories give essential economy of energy (about 150 m/s in Delta V) relative to the usual ones.

## Keywords

‘Detour’ lunar trajectories Moon-Earth flight escape gravitational perturbations## Preview

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## References

- Belbruno E A and Miller J K 1993 Sun-Perturbed Earth- to-Moon Transfer with Ballistic Capture;
*J. Guidance, Control and Dynamics***16**(**4**) 770–775.CrossRefGoogle Scholar - Belló Mora M, Graziani F
*et al*2000*A Systematic Analy- sis On Week Stability Boundary Transfers To The Moon*; Presented at the 51st International Astronautical Congress, held in Rio de Janeiro, Brazil, October 2000. Paper IAF-00-A.6.03, p. 12Google Scholar - Egorov V A and Gusev L I 1980
*Dynamics of the Earth-to- Moon Space flights*(Moscow, USSR: Nauka Publishers) 543 pp.Google Scholar - Gatland K 1982
*The Illustrated Encyclopedia of Space Tech- nology*(London: Salamander Book Ltd.) 296 pp.Google Scholar - Hiroshi Yamakawa, Jun’ichiro Kawaguchi, Nobuaki Ishii, Hiroki Matsuo 1993
*On Earth-Moon Transfer Trajectory with Gravitational Capture*; Presented at AAS/AIAA Astrodynamics Specialist Conference, Victoria, USA. Paper AAS 93-633, p. 20.Google Scholar - Ivashkin V V 2002 On Trajectories of the Earth-Moon Flight of a Particle with its Temporary Capture by the Moon;
*Doklady Physics, Mechanics***47**(**11**) 825–827.CrossRefGoogle Scholar - Ivashkin V V 2003
*On the Earth-to-Moon Trajectories with Temporary Capture of a Particle by the Moon*; Presented at the 54th International Astronautical Congress, held in Bremen, Germany, September 29–October 3, 2003. Paper IAC-03-A.P.01, pp. 1–9.Google Scholar - Ivashkin V V 2004a
*On Trajectories for the Earth-to-Moon Flight with Capture by the Moon*; Proceedings of the International Lunar Conference 2003 (eds) Steve M Durst*et al*, American Astronautical Society AAS. Vol. 108, Science and Technology Series, Paper AAS 03-723, pp. 157–166.Google Scholar - Ivashkin V V 2004b On Particle’s Trajectories of Moon-to- Earth Space Flights with the Gravitational Escape from the Lunar Attraction;
*Doklady Physics, Mechanics***49**(**9**) 539–542.CrossRefGoogle Scholar - Ivashkin V V 2004c
*On the Moon-to-Earth Trajectories with Gravitational Escape from the Moon Attraction*: Presented at the 18th International Symposium of Space Flight Dynamics, held in Munich, Germany, 11–16 October, 2004. Paper P0111, http://www.issfd.dlr.de/papers/P0111. pdf.Google Scholar - Koon W S, Lo M W, Marsden J E
*et al*2001 Low Energy Transfer to the Moon;*Celestial Mechanics and Dynami- cal Astronomy*(Netherlands: Kluwer Academic Publish- ers)**81**63–73.Google Scholar - Lidov M L 1961 Evolution of the Planets Artificial Satellites Orbits under Effect of the Outer Bodies Gravity Pertur- bations;
*Artificial Satellites of the Earth*(Moscow, USSR: Nauka Publishers)**8**5–45.Google Scholar - Lidov M L 1962 The Evolution of Orbits of Artificial Satellites of Planets under the Action of Gravitational Perturbations of External Bodies;
*Planet. Space Sci.***9**719–759.CrossRefGoogle Scholar - Stepan’yants V A and L’vov D V 2000 Effective Algorithm for the Motion Differential Equations System Solving;
*Mathematical Modeling*(Moscow, Russia),**12**(**6**) 9–14.Google Scholar - Sternfeld A 1934 Sur les trajectories permettant d’un corps attractit central á partir d’une orbite keplérienne donnée;
*Comptes rendus de l’Acad. des Sciences*(Paris, France)**198**711–713.Google Scholar - Sternfeld A 1937
*Introduction to Cosmonautics*(Moscow, USSR: ONTI NKTP Publishers), 318 pp; 1974 2nd edn (Moscow, USSR: Nauka Publishers), 240 pp.Google Scholar - Sternfeld A 1956
*Artificial Satellites of the Earth*(Moscow, USSR: GITTL Publishers), 180 pp; 1958 2nd edn,*Arti-ficial Satellites*(Moscow, USSR: GosTekhIzdat Publish- ers), 296 pp.Google Scholar