Optimal Maintenance of Spacecraft with Low-Thrust Engines on Sun-Synchronous Orbit

Authors: Wang Lijie, Baranov A.A. Published: 15.04.2015
Published in issue: #2(101)/2015  

DOI: 10.18698/0236-3941-2015-2-68-83

Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control  
Keywords: sun-synchronous orbit, low-thrust engine, linear programming method, optimal maintenance, interior-point algorithm

The problem of sun-synchronous orbit maintenance for the spacecrafts using low-thrust engines is investigated. The required orbital characteristics and evolutions of the orbital parameters associated with drag and solar attraction are analyzed. Discrete mathematical model of the spacecraft motion is developed taking into account the action of limited control. A linear programming method with restriction of thrust based on the application of the interior-point algorithm is used. The combined maintenance strategy is proposed in order to obtain maximum free flight time for spacecraft. This strategy consists of the expectation strategy for longitude control, as well as precautionary strategy for the inclination correction. Effectiveness of the proposed algorithm is proved by numerical simulations. Distribution of control impulses over each correction circuit is analyzed, the annual summary characteristic velocity value with respect to solar activity is also estimated.


[1] Chernov A.A., Chernyavskiy G.M. Orbity sputnikov distancionnogo zondirovaniya Zemli. Lektsii i uprazhneniya [Orbit of remote sensing satellites. Lectures and exercises]. Moscow, Radio i svyaz’ Publ., 2004. 200 p.

[2] Kolosov G.E., Van Lijie. Correction of flight parameters with low thrusters. Polet. Obshcherossiyskiy nauchno-tekhnich. Zhurnal [Scientific and technical journal "Polyot" ("Flight")], 2012, no. 11, pp. 27-36 (in Russ.).

[3] Bakhshiyan B.Ts., Nazirov R.R., El’yasberg P.E. Opredelenie i korrektsiya dvizheniya: garantiruyushchiy podkhod [Determination and correction of motion: guaranteed approach]. Moscow, Nauka Publ., 1980. 360 p.

[4] Nazirov R.R., Timohova T.A. Optimal linear correction of the elliptical orbits. Avtomatika i telemehanika [Automation and Remote Control], 1993, no. 3, pp. 93101 (in Russ.).

[5] Ulybyshev Yu.P. Optimization of multi-mode rendezvous trajectories with constraints. Kosmicheskie issledovaniya [Cosmic Research], 2008, vol. 46, no. 2, pp. 135-147 (in Russ.).

[6] Baranov A.A., De Prado A.F.B., Razumny V.Yu., Baranov An.A. Optimal low-thrust transfers between close near-circular coplanar orbits.Kosmicheskie issledovaniya [Cosmic Research], 2011, vol. 49, no. 3, pp. 278-288 (in Russ.).

[7] Garulli A., Giannitrapani A., Leomanni M., Scortecci F. Autonomous low-earth-orbit station-keeping with electric propulsion. J. of guidance control and dynamics, 2011, vol. 34, no. 6, pp. 1683-1693.

[8] Dubrovinskiy Ya.V., Zhuravlev K.V., Shershneva N.I. Ballistic modeling and calculation of operating orbits of advanced hydrometeorological spacecraft. Voprosy elektromekhaniki.[Electromechanical problems], 2005, vol. 102, pp. 220-234(in Russ.).

[9] Kazakovtsev V.P., Koryanov V.V., Betanov V.V., Usachev V.A., Golov N.A. Disturbed motion of low-orbiting small mass satellite. Polet. Obshcherossiyskiy nauchno-tekhnich. Zhurnal [Scientific and technical journal "Polyot" ("Flight")], 2014, no. 6, pp. 14-20 (in Russ.).

[10] Vallado D.A. Fundamentals of astrodynamics and applications. Microcosm Press, Hawthorne and Springer, New York. 2007. 1055 p.

[11] Chobotov V.A. Orbital Mechanics.AIAA education series, 3rd edition, 2002. 455 p.

[12] Ulybyshev Y. Continuous thrust orbit transfer optimization using large-scale linear programming. J. of guidance, control, and dynamics, 2007, vol. 30, no. 2, pp. 427436. doi:10.2514/1.22642

[13] Wright S.J. Primal-dual interior-point methods. Society for Industrial and Applied Mathematics. Philadelphia. 1997. 289 p.

[14] Picone J.M., Hedin A.E., Drob D.P., Aikin A.C. NRLMSISE-00 empirical model of the atmosphere: statistical comparisons and scientific issues. J. Geophysical research, 2002, vol. 107, no. 12A, pp. 1468-1483.

[15] Standish E.M. JPL planetary and lunar ephemerides, DE405/LE405. JPL interoffice memorandum IOM 312. F-98-048. 1998.