Error Inherent in Simulating Planetary Thermal Effect on the Spacecraft Surface by using Isotropic Planetary Radiation Intensity Field Model Instead of Anisotropic

In order to mathematically simulate the thermal effect that radiation emitted by planets has on spacecraft, two intensity field models describing planetary radiation may be used depending on the emitter specifics: isotropic and anisotropic. The isotropic model is based on the assumption that the local surface density of outgoing radiation flux is the same for all surface regions visible from orbit. In the case of the anisotropic model this value is assumed to be proportional to the zenith angle cosine for each surface element on the side of the planet that is illuminated by the Sun. Published results of studies concerning developing planetary radiation field simulators indicate that thermal vacuum installations where the working volume is comparable to the total installation volume can only reproduce the sotropic planetary radiation intensity field model. It is a pressing issue to determine whether and when it is possible to replace the anisotropic model with an isotropic one when physically simulating the effect that the solar radiation reflected from a planet and intrinsic radiation flows generated by planets with no atmosphere have on spacecraft. The investigation that we conducted regarding this issue was based on comparing the results of computing the irradiance of spacecraft elements using the models under consideration. These computation results allowed us to conclude that it is possible to physically simulate the effect of solar radiation flows reflected from planets combined with intrinsic (infrared) radiation flows generated by planets with no atmosphere by means of using simulators reproducing isotropic radiation fields in their working volumes

The study was conducted as part of a government assignment by the Ministry of Education and Science of the Russian Federation (code FSFF-2020-0016)

Литература

[1] Zaletaev V.M., Kapinos Yu.V., Surguchev O.V. Raschet teploobmena kosmicheskogo apparata [Heat exchange calculation for spacecraft]. Moscow, Mashinostroenie Publ., 1979.

[2] Petrov G.I., red. Modelirovanie teplovykh rezhimov kosmicheskogo apparata i okruzhayushchey ego sredy [Modeling of spacecraft thermal regimes and its environment]. Moscow, Mashinostroenie Publ., 1971.

[3] Kolesnikov A.V., Serbin V.I. Modelirovanie usloviy vneshnego teploobmena kosmicheskikh apparatov [Modelling external heat exchange conditions of spacecraft]. Moscow, Informatsiya--XXI vek Publ., 1997.

[4] Finchenko V.S., Kotlyarov E.Yu., Ivankov A.A. Sistemy obespecheniya teplovykh rezhimov avtomaticheskikh mezhplanetnykh stantsiy [Systems for providing thermal regimes of automatic interplanetary stations]. Khimki, NPO Lavochkina Publ., 2018.

[5] Astakhov N.N., Kargu D.L., Gorbulin V.I., et al. Mathematical modeling of solar panel temperature dynamics in various conditions of orbital space missions. Vestn. Mosk. Gos. Tekh. Univ. im. N.E. Baumana, Mashinostr. [Herald of the Bauman Moscow State Tech. Univ., Mechan. Eng.], 2016, no. 6, pp. 4--21 (in Russ.). DOI: http://dx.doi.org/10.18698/0236-3941-2016-6-4-21

[6] Gritsevich I.V., Nenarokomov A.V. Determination of external thermal effect on the surface of orbital spacecraft. Teplovye protsessy v tekhnike, 2013, vol. 5, no. 10, pp. 445--456 (in Russ.).

[7] Garzon A., Villanueva Y.A. Thermal analysis of satellite Libertad 2: a guide to cubesat temperature prediction. J. Aerosp. Technol. Manag., 2018, no. 10. DOI: http://dx.doi.org/10.5028/jatm.v10.1011

[8] Labibian A., Pourtakdoust S., Alikhani A., et al. Development of a radiation based heat model for satellite attitude determination. Aerosp. Sc. Technol., 2018, vol. 82-83, pp. 479--486. DOI: https://doi.org/10.1016/j.ast.2018.09.031

[9] Sudomoin P.D., Shabanov V.A., Platonov K.A., et al. Research on thermal conditions of a small space vehicle. Vestn. Mosk. Gos. Tekh. Univ. im. N.E. Baumana, Mashinostr. [Herald of the Bauman Moscow State Tech. Univ., Mechan. Eng.], 2016, no. 2, pp. 28--44 (in Russ.). DOI: https://doi.org/10.18698/0236-3941-2016-2-28-44

[10] Zaletaev V.M. Intrinsic Earth emission on partially screened spacecraft elements. Kosmicheskie issledovaniya, 1970, vol. 8, no. 4, pp. 636--639 (in Russ.).

[11] Kolesnikov A.V., Paleshkin A.V., Syzdykov Sh.O. Modeling external heat loads on the spacecraft in a thermal vacuum chamber. J. Eng. Phys. Thermophy., 2019, vol. 92, no. 4, pp. 965--970. DOI: https://doi.org/10.1007/s10891-019-02010-9

[12] Wang J., Liu Sh., Pei Yi. Infrared lamp array simulation technology used during satellite thermal testing. IJAME, 2010, vol. 4, no. 9, pp. 707--709.

[13] Kolesnikov A.V., Paleshkin A.V., Shemetova E.V. Thermal loading simulators with diffuse emitter modules operating over a strictly bounded solid angle. Vestn. Mosk. Gos. Tekh. Univ. im. N.E. Baumana, Mashinostr. [Herald of the Bauman Moscow State Tech. Univ., Mechan. Eng.], 2018, no. 4, pp. 47--54 (in Russ.). DOI: http://dx.doi.org/10.18698/0236-3941-2018-4-47-54

[14] Eliseev V.N., Tovstonog V.A. Teploobmen i teplovye ispytaniya materialov i konstruktsiy aerokosmicheskoy tekhniki [Heat transfer and thermal testing of aerospace materials and structures]. Moscow, Bauman MSTU Publ., 2014.

[15] Ul’yanov V.A., Solov’yev M.V. Thermal vacuum tests optimization of space complexes at VC 600/300 facility. Polet, 2009, spec. iss., pp. 82--93 (in Russ.).

[16] Cao Zh., Pei Yi., Liu Sh., et al. Infrared lamp array design and radiation heat flux analysis. Proc. 7th IASME/WSEAS Int. Conf. Heat Transf. Therm. Eng. Env., pp. 96--100.

[17] Turner T.L., Ash R.L. Numerical and experimental analyses of the radiant heat flux produced by quartz heating systems. NASA Tech. Pap. 3387, NASA, 1994.

[18] Kobranov G.P., Tsvetkov A.P., Belov A.I., et al. Vneshniy teploobmen kosmicheskikh apparatov [External heat exchange of spacecraft]. Moscow, Mashinostroenie Publ., 1977.