Skip to main content
SpringerLink
Log in

HYBRID ORIENTATION SYSTEM FOR ORBITAL SPACECRAFT

  • Published:
Mechanics of Solids Aims and scope Submit manuscript

Abstract—

The spatial 3D gyrocompass, developed by the author to control the angular position of an orbiting spacecraft (SC), makes it possible to create an orientation system based on it, operating both from an Earth orientation device (EOD), and from an astro sensor (AS), or any another sensor without changing the basic structure of the algorithm. Such a system can be called a hybrid orientation system (HOS). The development of HOS is relevant in connection with the growth of the Customer’s requirements for the universalization of the development of SC control systems. The use of HOS makes it possible to reduce the load on the on-board computer, simplify ground testing of the SC control system, and improve the quality of SC control in flight due to a decrease in the branching of orientation algorithms. This article presents working algorithms, derivation of the main relations, and modeling results.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

REFERENCES

  1. I. N. Abezyaev, “Gyro-compass for orbital spacecraft,” RF Patent No. 2 597 018, Byull. Izobret., No. 24 (2016).

  2. K. A. Boyarchuk, V.V. Vilenskiy, V.Yu. Grishin, et al., “The system of orientation and stabilization of the "Condor-E” spacecraft,” in Proceedings of the Section 22 Named After Academician V.N. Chelomey of XXXVIII Scientific Conference on Cosmonautics (NPO Mashinostroyenia, Reutov, 2014), Vol. 22, pp. 408–424.

  3. I. N. Abezyaev, A. V. Andreyanenkova, P. E. Velichko, et al., “Method for restoring the heading orientation of a spacecraft using the orbital gyrocompass,” Inzh. Zh.: Nauka Innovats., No. 5(65), 1–8 (2017). https://doi.org/10.18698/2308-6033-2017-5-1621

  4. I. N. Abezyaev, P. E. Velichko, A. A. Karpunin, et al., “Development of the algorithm of the spacecraft programmed yaw turns with the use of orbital gyrocompass,” AIP Conf. Proc. 2171 (1), 060009 (2019).

    Article  Google Scholar 

  5. A. I. Tkachenko, “Attitude determination of a spacecraft using a vertical sensor,” Kosm. Nauka Tekhnol. 22 (2), 22–28 (2016). https://doi.org/10.15407/knit2016.02.022

    Article  Google Scholar 

  6. F. G. Major, “The mechanical gyrocompass,” in Quo Vadis: Evolution of Modern Navigation (Springer, New York, 2014), pp. 259–285.

    Book  Google Scholar 

  7. D. B. Reid, “Orbital gyrocompass evolution,” GON Intertial Sens. Syst. (ISS) 20, 149–170 (2016). https://doi.org/10.1109/InertialSensors.2016.7745672

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. JSC “Military and industrial corporation “NPO Mashinostroyenia”, 143966, Reutov, Moscow region, Russia

    I. N. Abezyaev

Authors
  1. I. N. Abezyaev
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to I. N. Abezyaev.

Additional information

Translated by M. Katuev

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Abezyaev, I.N. HYBRID ORIENTATION SYSTEM FOR ORBITAL SPACECRAFT. Mech. Solids 56, 471–477 (2021). https://doi.org/10.3103/S0025654421040026

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.3103/S0025654421040026

Keywords:

Search

Navigation