Abstract
A method of reducing the radiation power degradation of spacecraft solar array during combined geostationary orbit insertion using a booster and an electric propulsion system is considered in this paper. The essence of the method is to optimize the shape of the transfer trajectory and the perigee argument of the intermediate orbit. The maximum principle is applied to the problem of optimizing the SA electrical power at the end of 15 year spacecraft’s operational lifetime (EOL). For this, the equation for the current SA power and the constraint on this power at the EOL is added to the equations of spacecraft motion. The closed-form solution to the adjoint equation to SA power is obtained. Calculation of SA radiation degradation was carried out using the models of charged particle fluxes of Earth’s radiation belts, AE8 MAX and AP8 MAX. To increase the EOL SA power by 0.16–0.66% of the SA power at the beginning of the transfer depending on the parameters of intermediate orbits. The additional characteristic velocity increased relative to the minimum time trajectories by 13–1087 m/s depending on the parameters of intermediate orbits.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
REFERENCES
Ceccherini, S. and Topputo, F., System-trajectory optimization of hybrid transfers to the geostationary orbit, Space Flight Mechanics Meeting, AIAA SciTech Forum, 8–12 January 2018, Kissimmee, Florida, 2018.
Macdonald, M. and Owens, S.R., Combined high and low-thrust geostationary orbit insertion with radiation constraint, Acta Astronaut., 2018, vol. 142, pp. 1–9.
Messenger, S.R. Wong, F., et al., Low-thrust geostationary transfer orbit (LT2GEO) radiation environment and associated solar array degradation modeling and ground testing, IEEE Trans. Nucl. Sci., 2014, vol. 61, no. 6, pp. 3348–3355.
Mailhe, L.M. and Heister, S.D., Design of a hybrid chemical/electric propulsion orbital transfer vehicle, J. Spacecr. Rockets, 2002, vol. 39, no. 1, pp. 131–139.
Petukhov, V.G., Quasioptimal control with feedback for multiorbit low-thrust transfer between noncoplanar elliptic and circular orbits, Cosmic Res., 2011, vol. 49, no. 2, pp. 121–130.
Tada, H.Y., Carter, J.R., Anspaugh, B.E., and Downing, R.G., Solar Cell Radiation Handbook, Pasadena: California Institute of Technology, 1982, JPL-PUB-82-69.
Model’ kosmosa: nauchno-informatsionnoe izdanie (The Model of Cosmos: Scientific and Informational Edition), vol. 1: Fizicheskie usloviya v kosmicheskom prostranstve (Physical Conditions in Space), Panasyuk, M.I. and Novikov, L.S., Eds., Moscow: Biblion–Russkaya kniga, 2007.
Sinitsyn, A.A., Influence of the radiation degradation of solar cells on the efficiency of electrorocket engines, Polet, 2010, no. 1, pp. 22–29.
Starchenko, A.E., Optimization of trajectories of spacecraft ascent on a geostationary orbit aimed at reducing the radiation degradation of solar cells, Izv. Ross. Akad. Nauk: Energ., 2017, no. 3, pp. 128–145.
Imaizumi, M., Nakamura, T., Takamoto, T., Ohshima, T., et al., Radiation degradation characteristics of component subcells in inverted metamorphic triple-junction solar cells irradiated with electrons and protons, Prog. Photovoltaics: Res. Appl., 2017, vol. 25, no. 2, pp. 161–174.
Starchenko, A.E., Trajectory optimization of a low-thrust geostationary orbit insertion for total ionizing dose decrease, Cosmic Res., 2019, vol. 57, no. 4, pp. 289–300.
Kim, V., Stationary plasma thrusters in Russia: Problems and prospects, Tr. Mosk. Aviats. Inst., 2012, no. 60.
Sawyer, D.M. and Vette, J.I., AP-8 Trapped Proton Environment for Solar Maximum and Solar Minimum, NASA-TM-X-72605, NSSDC/WDC-A-R&S 76-06, 1976.
Vette, J.I., Trapped Radiation Environment Model Program (1964–1991), NSSDC/WDC-A-R&S 91-29, 1991.
Vette, J.I., The AE-8 Trapped Electron Model Environment, NSSDC/WDC-A-R&S 91-24, 1991.
Heynderickx, D., Comparison between methods to compensate for the secular motion of the South Atlantic anomaly, Radiat. Meas., 1996, vol. 26, no. 3, pp. 369–373.
Jensen, D.C. and Cain, J.C., An interim geomagnetic field, J. Geophys. Res., 1962, vol. 67, pp. 3568–3569.
Cain, J.C., Hendricks, S.J., Langel, R.A., and Hudson, W.V., A proposed model for the International Geomagnetic Reference Field-1965, J. Geomagn. Geoelectr., 1967, vol. 19, pp. 335–355.
Petukhov, V.G., Optimization of multi-orbit transfers between noncoplanar elliptic orbits, Cosmic Res., 2004, vol. 42, no. 3, pp. 250–268.
Petukhov, V.G., Method of continuation for optimization of interplanetary low-thrust trajectories, Cosmic Res., 2012, vol. 50, no. 3, pp. 249–261.
Shalashilin, V.A. and Kuznetsov, E.B., Metod prodolzheniya resheniya po parametru i nailuchshaya parametrizatsiya (The Method of Parametric Continuation and Optimal Parametrization), Moscow: Editorial URSS, 1999.
Hairer, F., Nørsett, S.P., and Wanner, G., Solving Ordinary Differential Equations I. Non-Stiff Problems, Berlin: Springer, 2008.
ACKNOWLEDGMENTS
The author thanks V.G. Petukhov for valuable comments during discussions of this article.
Funding
This work was supported by the Russian Science Foundation, agreement no. 16-19-10429.
Author information
Authors and Affiliations
Corresponding author
Additional information
Translated by N. Topchiev
Rights and permissions
About this article
Cite this article
Starchenko, A.E. Minimizing the Degradation of Triple Junction Solar Array of a Spacecraft during Geostationary Orbit Insertion. Cosmic Res 57, 364–377 (2019). https://doi.org/10.1134/S0010952519050083
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1134/S0010952519050083