Analysis of a Reusable Lunar Transfer Vehicle Using Nuclear Electric Propulsion

Аuthors

Loeb H. W.^1*, Mogulkin A. .^2**, Obukhov V. A.^3**, Petukhov V. G.^3***

1. Justis-Liebig-Universitat, Physikalisches Institut, Giessen, Germany
2. ,
3. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: Horst.w.loeb@expl.physik.uni-giessen.de
**e-mail: riame@sokol.ru
***e-mail: vgpetukhov@gmail.com

Abstract

A reusable electrically propelled cargo spacecraft with nuclear power plant, which should perform five round–trips between a low Earth orbit (800 km) and a low Lunar orbit (100 km) and transport components of a future permanently manned Lunar station, is considered. The spacecraft will weigh 61.8 tons, payload of 25 tons including, at the launch from the low Earth orbit. The nuclear–electric propulsion system will consist of a 1 MW nuclear power plant (of 20 tons in mass) and 4 clusters of 10 radio–frequency ion thrusters each. 28 of them will produce total thrust of 18.2 N and consume 840 kW of power. 10.8 tons of Xenon will be consumed per a round trip. The designed radio–frequency ion thruster “RFIT–45” with the ionizer diameter of 45 cm shall have the following performance: power consumption of 35 kW, specific impulse of 7000 s, and lifetime of 50 000 hrs.
According to the mission analysis, the reusable lunar transport spacecraft can deliver up to 128.5 tons of payload to the low Lunar orbit or 57.4 tons of payload to the lunar surface by 5 trips during about 7 years, delivery of payload of 205.2 tons to the low Earth orbit being necessary for securing mentioned operations, that being 2 – 3.5 times less than without the use of electric propulsions.

Keywords:

radio frequency ion thruster, reusable lunar transfer vehicle, low earth orbit, low lunar orbit, nuclear electric propulsion unit

References

1. Afanas’ev I. Novosti kosmonavtiki, Moscow, 2010, no. 2, pp.44-47.
2. Loeb H.W., Feili D., Popov G.A., Obukhov V.A., Balashov V.V., Mogulkin A.I., Murashkov V.M. , Nesterenko A.N., Khartov S. Design of High—Power High—Specific Impulse RF—Ion Thruster, Proceedings of the 32 International Electric Propulsion Conference, Kurhaus, Wiesbaden, Germany, 2011, IEPC—2011—290.
3. Loeb H.W., Freisinger J., Grah K.H., Scharmann A. State of the Art of the RIT. Ion Thrusters and Their Spin—offs, 39 International Astronautical Congress, 1988, Bangalore, India, IAF—88—258.
4. Sackett L.L., Malchow H.L., Edelbaum T.N. Solar Electric Geocentric Transfer with Attitude Constraints, Cambridge,1975, NASA CR—134927.
5. Petukhov V.G. One Numerical Method to Calculate Optimal Power—Limited Trajectories, Proceedings Electric Propulsion International Conference , Moscow, 1995, IEPC—95—221.
6. Petukhov V.G. Kosmicheskie issledovanija, 2004, vol. 42, no.3, pp. 260–279.
7. Konstantinov M.S., Petukhov V.G. Materialy 17 International Symposium «Space Flight Dynamics Spacecraft Insertion into High Working Orbits Using Light—Class Launcher and Electric Propulsion», Moscow, 2003, pp. 1-14.
8. Konstantinov M.S., Petukhov V.G. Materialy 57 International Astronautical Congress «Easy Engineering Technique of Optimal Electric Propulsion Trajectory Estimation», Valencia, Spain, IAC—06—C4, 2006, 11 p.
9. Petukhov V.G., Svotina V.V. Materialy 3 European Conference for Aero—Space Science «Robust Suboptimal Feedback Control for Low—Thrust Transfers Between Noncoplanar Elliptical and Circular Orbits», Versailles, France, EUCASS—2009, 8 p.
10. Petukhov V.G. Proektno—ballisticheskij analiz lunnogo transportnogo kosmicheskogo apparata s jelektroraketnoj dvigatel’noj ustanovkoj (Design and ballistic analysis of the lunar transport spacecraft with electro-propulsion system), XXXIII Akademicheskie chtenija po kosmonavtike, posvjashhennye pamjati akademika S.P. Koroleva i drugih vydajushhihsja otechestvennyh uchenyh — pionerov osvoenija kosmicheskogo prostranstva, Moscow, 2009, pp. 65-66.
11. Ivashkin V.V., Petukhov V.G. Opredelenie traektorii pereleta KA ot Zemli k Lune s maloj tjagoj pri ispol’zovanii orbity zahvata Lunoj (Determination of the trajectory of the flight spacecraft from the Earth to the moon with low thrust when using capture orbit the Moon), XXXIII Akademicheskie chtenija po kosmonavtike, posvjashhennye pamjati akademika S.P. Koroleva i drugih vydajushhihsja otechestvennyh uchenyh — pionerov osvoenija kosmicheskogo prostranstva, Moscow, 2009, pp. 127-128.
12. Petukhov V.G. Kosmicheskie issledovanija, 2011, vol. 49, no. 2, pp. 121–130.

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