Using the flywheel engines system in implementing the spacecraft solar orientation mode
Authors: Ignatov A.I., Ivanov G.A., Kolomiets E.S., Martynenkova E.V.
Published in issue: #10(130)/2022
DOI: 10.18698/2308-6033-2022-10-2219
Category: Aviation and Rocket-Space Engineering | Chapter: Aircraft Dynamics, Ballistics, Motion Control
The study is devoted to maintaining the solar orientation mode of the gyrostat spacecraft in the low earth orbit through a long period. The device shape is close to a cylinder with two fixed solar panels installed along the cylinder longitudinal axis symmetrically relative to it. In the solar orientation mode, the normal to the device solar arrays plane is invariably directed towards the Sun and the longitudinal axis oscillates relative to the orbit plane. To implement the specified spacecraft motion mode, a system of four flywheel engines is used, which rotation axes are directed in parallel to the side edges of the quadrangular pyramid. Position of the pyramid side edges relative to the coordinate system rigidly connected to the device is determined by two angles, which are the parameters of the flywheel engine system. The law of the gyrostatic moment control is considered ensuring attenuation of the perturbed spacecraft motion in the vicinity of its solar orientation and limiting accumulation of its intrinsic kinetic moment of the flywheel engines by controlling the device rotation angle around the normal to the light-sensitive side of the solar arrays. It is demonstrated that selection of certain parameters of the flywheel engines coordinate system would assist in implementing the solar orientation mode without unloading the gyrostatic moment during the entire flight time. Results of numerical simulation of the complete system of the spacecraft motion equations in its solar orientation mode are presented taking into account the influence of gravitational and aerodynamic moments, which confirms correctness of the selected parameter values.
References
[1] Ignatov A.I., Sazonov V.V. Otsenka nizkochastotnykh mikrouskoreniy na bortu ISZ v rezhime odnoosnoy solnechnoy orientatsii [Evaluation of low-frequency microaccelerations on board a satellite in the monoaxial solar orientation mode]. Kosmicheskiye issledovaniya — Cosmic Research, 2013, vol. 51, no. 5, pp. 342–349.
[2] Ignatov A.I. Stabilizatsiya rezhima solnechnoy orientatsii sputnika Zemli bez nakopleniya kineticheskogo momenta girosistemy [Stabilization of the satellite solar orientation mode without accumulation of the gyro system kinetic moment]. Izvestiya RAN. TiSU — Bulletin of the RAS. Journal of Computer and Systems Sciences International, 2020, no. 3, pp. 164–176.
[3] Ignatov A.I. Otsenka nizkochasotnykh mikrouskoreniy na bortu ISZ v rezhime solnechnoy orientatsii [Evaluation of low-frequency microaccelerations on board a satellite in the solar orientation mode]. Kosmicheskiye issledovaniya — Cosmic Research, 2022, vol. 60, no. 1, pp. 1–14.
[4] Bazhinov I.K., Gavrilov V.P., Yastrebov V.D., et al. Navigatsionnoye obespechenie poleta orbitalnogo kompleksa “Salyut-6” — “Soyuz” — “Progress” [Navigation support in the flight of the “Salyut-6” – “Soyuz” – “Progress” orbital system]. Moscow, Nauka Publ., 1985.
[5] Beletsky V.V. Dvizhenie iskusstvennogo KA otnositelno tsentra mass [Artificial spacecraft motion relative to the center of mass]. Moscow, Nauka Publ., 1965.
[6] Meeus J. Astronomical Formulae for Calculators. Enlarged 2nd edition. Willmann-Bell Publ., 1982 [In Russ.: Meeus J. Astronomicheskie formuly dlya kalkulyatorov. Moscow, Mir Publ., 1988].
[7] Ignatov A.I. Vybor geometricheskikh parametrov raspolozheniya sistemy dvigateley-makhovikov pri upravlenii vraschatelnym dvizheniem kosmicheskogo apparata [Selection of geometric parameters of the flywheel engine system position in controlling the spacecraft angular motion]. Izvestiya RAN, TiSU — Bulletin of the RAS, Journal of Computer and Systems Sciences International, 2022, vol. 61, no. 1, pp. 83–103.
[8] Gantmacher Felix. R. Teoriya matrits [Matrix Theory]. Moscow, Nauka Publ., Chief editorial board of physical and mathematical literature, 1988.
[9] Markley F.L., Reynolds R.G., Liu F.X. Maximum torque and momentum envelopes for reaction-wheel arrays. Journal of Guidance, Control, and Dynamics, 2010, vol. 33, no. 5, pp. 1606–1614.
[10] Yoon H., Seo H.H., Choi H.-T. Optimal uses of reaction wheels in the pyramid configuration using a new minimum infinity-norm solution. Aerospace Science and Technology, 2014, vol. 39, pp. 109–119.
[11] Yoon H., Seo H.H., Park Y.-W., Choi H.-T. A new minimum infinity-norm solution: with application to capacity analysis of spacecraft reaction wheels. American Control Conference (ACC), 2015, pp. 1241–1245.
[12] Strang G. Lineynaya algebra i eye primeneniya [Linear algebra and its application]. Moscow, Mir Publ., 1980.