Design of control moment gyro electric drive with strict requirements on ensuring desired rotational velocities

Abstract


The paper discusses the issues of designing a control moment gyroscope electric drive with strict requirements in terms of the accuracy of ensuring a given rotation rate of the gyro motor suspension. A brief description of the control moment gyroscope electric drive applied currently is presented and the issues of improving the electric drive characteristics are discussed. As a solution, an electric drive is proposed which operates in the mode of feedback loop using angle sensors located on the axes of the gyroscope suspension and the engine rotor. The paper describes the arrangement of the control moment gyroscopes on advanced spacecraft for Earth remote sensing and presents the analytic expressions needed to calculate the control moments that affect the spacecraft. The moments are in the projection to the coordinate system brought into coincidence with the spacecraft. The paper compares spacecraft angular velocity stabilization errors for the cases of using the conventional scheme of control moment gyroscope electric drive and the newly developed one. The presented results can be used for developing control moment gyroscope electric drives to be mounted on spacecraft of different purpose with strict requirements on ensuring operation at specified rotational velocities.


About the authors

D. S. Polozhentcev

JSC “Control Devices Research Institute”; Saint Petersburg State University of Aerospace Instrumentation

Author for correspondence.
Email: pds6476564@yandex.ru

Russian Federation

Head of the Sector of Electric Drive Design; Assistant of the Department of Control in Engineering Systems

A. A. Davidov

Joint Stock Company Space Rocket Center “Progress”

Email: arrrtttem@mail.ru
ORCID iD: 0000-0001-9733-6165

Russian Federation

Leading Design Engineer of the Department of Spacecraft Attitude and Center of Mass Motion Control Systems

M. G. Shipov

Joint Stock Company Space Rocket Center “Progress”

Email: maxim.shipov@gmail.com
ORCID iD: 0000-0002-4265-3734

Russian Federation

Head of the Department of Spacecraft Attitude and Center of Mass Motion Control Systems

E. P. Kazakov

JSC “Control Devices Research Institute”; Saint Petersburg Electrotechnical University LETI

Email: e.kazakov.1@mail.ru

Russian Federation

Engineer of the Sector of Electric Drive Design; Postgraduate Student of the Department of Computer-Aided Design Systems

B. I. Malykh

JSC “Control Devices Research Institute”; D.F. Ustinov Baltic State Technical University VOENMEH

Email: malyhb@mail.ru

Russian Federation

First Category Technician of the Sector of Electric Drive Design; Master Student of the Department of Drive Systems, Mechatronics and Robotic Technology

References

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  3. Vasil'ev V.N. Sistemy orientatsii kosmicheskikh apparatov [Spacecraft attitude control systems]. Moscow: FGUP «NPP VNIIEM» Publ., 2009. 310 p.
  4. Polozhentcev D.S., Smirnov K.A. Control system of control moment gyroscope electric drive. Izvestia SPbETU «LETI». 2019. No. 8. P. 31-38. (In Russ.)
  5. Polozhentsev D.S., Dzhukich D.Y. Ispolnitel'nyy elektroprivod girodina. Sbornik nauchnykh trudov «Elektronnye i elektromekhanicheskie sistemy i ustroystva». Tomsk: Tomsk Polytechnic University Publ., 2016. P. 301-306. (In Russ.)
  6. Yakimovsky D.O., Polozhentcev D.S., Djukich D.Y. Increasing sensitivity of control moment gyroscope electric drive when operating at low rotational velocities. Proceedings of TUSUR University. 2018. V. 21, no. 3. P. 103-108. (In Russ.). doi: 10.21293/1818-0442-2018-21-3-103-108
  7. Kurenkov V.I., Gogolev M.Yu. Metody issledovaniya effektivnosti raketno-kosmicheskoy tekhniki: elektron. ucheb. posobie [Methods of investigating the efficiency of rocket and space equipment]. Samara: Samara State Aerospace University Publ., 2012. 285 p.

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