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Realization of modes of satellite attitude motion with a small level of microaccelerations using electromechanical executive devices

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Abstract

Quasi-static microaccelerations are estimated for a satellite specially designed to perform space experiments in the field of microgravity. Three modes of attitude motion of the spacecraft are considered: passive gravitational orientation, orbital orientation, and semi-passive gravitational orientation. In these modes the lengthwise axis of the satellite is directed along the local vertical, while solar arrays lie in the orbit plane. The second and third modes are maintained using electromechanical executive devices: flywheel engines or gyrodynes. Estimations of residual microaccelerations are performed with the help of mathematical modeling of satellite’s attitude motion under the action of gravitational and aerodynamic moments, as well as the moment produced by the gyro system. It is demonstrated that all modes ensure rather low level of quasi-static microaccelerations on the satellite and provide for a fairly narrow region of variation for the vector of residual microacceleration. The semi-passive gravitational orientation ensures also a limited proper angular momentum of the gyro system.

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References

  1. Sazonov, V.V., Komarov, M.M., Polezhaev, V.I., et al., Microaccelerations onboard the Mir Orbital Station and Prompt Analysis of Gravitational Sensitivity of Convective Processes of Heat and Mass Transfer, Kosm. Issled., 1999, vol. 37, no. 1, pp. 86–101. [Cosmic Research, pp. 80–94].

    Google Scholar 

  2. Zemskov, V.S., Raukhman, M.R., and Shalimov, V.P., Gravitational Sensitivity of Solutions-Melts at the Crystallization of Two-Phase InSb-InBi Alloys under Space Conditions, Kosm. Issled., 2001, vol. 39, no. 4, pp. 384–389. [Cosmic Research, pp. 359–364].

    Google Scholar 

  3. Zemskov, V.S., Raukhman, M.R., Shalimov, V.P., et al., The Influence of Arrangement of Growth Setups onboard a Spacecraft on Microgravity Conditions of Experiments: An Example of Floating Zone Melting of InSb:Te onboard the Foton-3 Satellite, Kosm. Issled., 2004, vol. 42, no. 2, pp. 144–154. [Cosmic Research, pp. 137–147].

    Google Scholar 

  4. Sazonov, V.V., Chebukov, S.Yu., Abrashkin, V.I., et al., Analysis of Low-Frequency Microaccelerations onboard the Foton-11 Satellite, Kosm. Issled., 2001, vol. 39, no. 4, pp. 419–435. [Cosmic Research, pp. 391–407].

    Google Scholar 

  5. Beuselinck, T., van Bavinchove, C., Sazonov, V.V., and Chebukov, S.Yu., An Analysis of Low-Frequency Component in Microacceleration Measurements Made onboard the Foton M-2 Satellite, Kosm. Issled., 2008, vol. 46, no. 5, pp. 463–483. [Cosmic Research, pp. 436–455].

    Google Scholar 

  6. Beuselinck, T., van Bavinchove, C., Abrashkin, V.I., et al., Determination of Attitude Motion of the Foton M-3 Satellite according to the Data of Onboard Measurements of the Earth’s Magnetic Field, Kosm. Issled., 2010, vol. 48, no. 3, pp. 252–265. [Cosmic Research, pp. 246–259].

    Google Scholar 

  7. Sarychev, V.A., Belyaev, M.Yu., Sazonov, V.V., and Tyan, T.N., Determination of Microaccelerations on Orbital Complexes Salyut-6 and Salyut-7, Kosm. Issled., 1986, vol. 24, pp. 337–344. [Cosmic Research, p. 267].

    ADS  Google Scholar 

  8. Bryukhanov, N.A., Tsvetkov, V.V., Belyaev, M.Yu., et al., Experimental Investigation of the Modes of Operation of Uncontrolled Attitude Motion of the Progress Spacecraft, Kosm. Issled., 2006, vol. 44, no. 1, pp. 52–61. [Cosmic Research, pp. 48–57].

    Google Scholar 

  9. Beletskii, V.V., Dvizhenie iskusstvennogo sputnika otnositel’no tsentra mass (Artificial Satellite Motion Relative to Its Center of Mass), Moscow: Nauka, 1965.

    Google Scholar 

  10. Sarychev, V.A., Issues of Attitude Control of Satellites, in Itogi Nauki Tekh., Ser.: Issled. Kosm. Prostr., vol. 11, Moscow: VINITI, 1978.

    Google Scholar 

  11. Sazonov, V.V., Gravitational Orientation of Satellites with Gyrodynes, Kosm. Issled., 1988, vol. 26, no. 2, pp. 315–317. [Cosmic Research, p. 266].

    Google Scholar 

  12. Markley, F.L., Attitude Determination Using Vector Observation and Singular Value Decomposition, The Journal of the Astronautical Sciences, 1988, vol. 36, no. 3, pp. 245–258.

    Google Scholar 

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Authors and Affiliations

  1. Federal State Unitary Enterprise Khrunichev Research and Production Space Center, Novozavodskaya ul. 18., 121087, Moscow, Russia

    A. I. Ignatov

  2. Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Miusskaya pl. 4, 125047, Moscow, Russia

    V. V. Sazonov

Authors
  1. A. I. Ignatov
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  2. V. V. Sazonov
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Original Russian Text © A.I. Ignatov, V.V. Sazonov, 2012, published in Kosmicheskie Issledovaniya, 2012, Vol. 50, No. 5, pp. 380–393.

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Ignatov, A.I., Sazonov, V.V. Realization of modes of satellite attitude motion with a small level of microaccelerations using electromechanical executive devices. Cosmic Res 50, 353–366 (2012). https://doi.org/10.1134/S0010952512050024

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  • DOI: https://doi.org/10.1134/S0010952512050024

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