Accuracy of the indicator gyrostabilizer is determined primarily by the feedback channel gain (stiffness) coefficient of the gyrostabilizer. When efforts to increase accuracy, there appear problems of ensuring stability and quality of regulation, which in modern gyrostabilizers are connected, first of all, to the presence of the structure finite stiffness in the drive torque transmission circuit located on the housing. Stiffness in the drive circuit could be significantly increased by installing an additional inertial support element on the platform in order to ensure that the stabilization moment is created by interaction of the platform with this body, but not with the housing. Flywheel or a two- degree-of-freedom gyro could be used as a support element. In the latter case, a power gyrostabilizer is obtained. In the flywheel indicator gyrostabilizer, it is convenient to use a housing torque motor as a stabilization drive, if its rotor is fixed on the platform, and the stator is used as a flywheel. It should be mentioned that it is advisable to use the proposed scheme of obtaining information about angular velocity of the flywheel rotation from measurements of current and voltage of the specified torque motor in order to generate an unloading channel in accordance with the flywheel rotational velocity, which is obviously required in a gyrostabilizer with a support inertial element. The work uses analytical and graphic forms to present physical and mathematical models of a gyro stabilization automatic flywheel system based on the indicator flywheel double-circuit gyrostabilizer with a housing torque motor. Results of studies aimed at establishing stability and accuracy of such a stabilization system are presented; requirements to its parameters and elements are indicated.

1.
Kokush
,
A. A.
,
Fateev
,
V. V.
,
Evstratov
,
L. N.
, &
Kozlov
,
V. V.
(
1999
). U.S. Patent No. 5,868,031.
Washington, DC
:
U.S. Patent and Trademark Office
.
2.
Kozlov
,
V. V.
,
Yevstratov
,
L. N.
, &
Chapman
,
L. T.
(
2012
). U.S. Patent No. 8,125,564.
Washington, DC
:
U.S. Patent and Trademark Office
.
3.
Meshchanov
,
A. S.
, &
Gataullina
,
L. A.
(
2018
).
Robust Control of a Gyroscopic Stabilizer at Sliding Modes
.
Russian Aeronautics
,
61
(
4
),
671
676
.
4.
Belyanin
,
L. N.
,
Doan
,
K. V.
,
Pozharskiy
,
T.
, &
Nguyen
,
T. Y.
(
2016
).
Design and analysis of power supply and information transfer to three-axis gyroscope stabilizer platform
.
In MATEC Web of Conferences. Vol. 48: Space Engineering.—Les Ulis
,
2016
. (Vol.
48
, p.
1001
). [sn].
5.
Malyutin
D.M.
,
Raspopov
V.Y.
,
Ivanov
Y. V.
(
2003
).
Experience in developing of the bore sight stabilization and control systems
.
16th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2009 - Proceedings
.
93
94
.
6.
Serebrennyi
,
V.
,
Boshliakov
,
A.
, &
Ovsiankin
,
G.
(
2018
).
Active stabilization in robotic vision systems
.
In MATEC Web of Conferences
(Vol.
161
, p.
03019
).
EDP Sciences
.
7.
Vavilova
N.B.
,
Golovan
A.A.
,
Panyov
A.A.
,
Konon
A.V.
,
Laptiev
A.A.
(
2009
).
Experience in developing of the boresight stabilization and control systems
.
17th Saint Petersburg International Conference on Integrated Navigation Systems
,
ICINS
2010
- Proceedings.
145
147
.
8.
Egorov
,
Y. G.
, &
Smirnov
,
S. V.
(
2010
).
The synthesis of parameter setting algorithms in the adaptive correction system of the radio telescope inertial orientation system
.
In 17th Saint Petersburg International Conference on Integrated Navigation Systems
,
ICINS 2010-Proceedings
(pp.
128
129
).
9.
Somov
,
Y.
, &
Siguerdidjane
,
H.
(
2011
, August).
Nonius Guidance and Robust Image Motion Stabilization of a Large Space Astronomical Telescope
.
IFAC Proceedings Volumes
,
44
(
1
),
5142
5147
.
10.
Egorov
,
Y. G.
, &
Smirnov
,
S. V.
(
2012
).
Simulation of adaptive correction algorithms of radio telescope inertial orientation system
.
In 19th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2012-Proceedings
(pp.
102
104
).
11.
Bykovsky
,
A. V.
,
Polynkov
,
A. V.
, &
Arsenyev
,
V. D.
(
2013
).
Gravimetric systems. Development experience
.
Aerospace Instrumentation
, (
12
),
11
19
.
12.
Sokolov
,
A. V.
,
Krasnov
,
A. A.
,
Starosel’tsev
,
L. P.
, &
Dzyuba
,
A. N.
(
2015
).
A gyro stabilization system with fiber-optic gyroscopes for an air-sea gravimeter
.
Gyroscopy and Navigation
,
6
(
4
),
338
343
.
13.
Gus’kov
,
A. A.
, &
Norinskaya
,
I. V.
(
2017
).
Effect of the gyroplatform control error on the accuracy of the initial azimuth alignment of the gyro inclinometer
.
Gyroscopy and Navigation
,
8
(
4
),
270
278
.
14.
Krasnov
,
A. A.
,
Nesenyuk
,
L. P.
,
Peshekhonov
,
V. G.
,
Sokolov
,
A. V.
, &
Elinson
,
L. S.
(
2011
).
Integrated marine gravimetric system
.
Development and operation results. Gyroscopy and Navigation
,
2
(
2
),
75
81
.
15.
Besekerskiĭ
,
V. A.
, &
Fabrikant
,
E. A.
(
1968
).
Dinamicheskiĭ sintez sistem giroskopicheskoĭ stabilizats︡ ii (Dynamic Synthesis of Gyrostabilization Systems). Sudostroenie
,.
16.
Single axis power gyrostabilizer: method. instructions to perform lab. work on the discipline
Theory of gyroscopes and gyrostabilizers
” /
Kuleshov
A. V.
,
Fateyev
V. V.
;
Bauman MGTU - M.: Publishing House of the Bauman MSTU
,
2015
. -
30
p.: il. - Bibliography.: p. 25. - ISBN 978-5-7038-4324-6.
17.
Pelpor
,
D.S.
(
1986
). Gyroscopic systems.
P1. M.: High School
.
18.
Mikrin
,
E. A.
,
Bogachev
,
A. V.
,
Platonov
,
V. N.
,
Sumarokov
,
A. V.
, &
Shiryaev
,
V. P.
(
2010
).
Effects of reaction wheel rotor unbalances on micro accelerations onboard an advanced SC
.
In 17th Saint Petersburg International Conference on Integrated Navigation Systems, ICINS 2010-Proceedings
(pp.
327
329
).
19.
Somov
,
S.
(
2011
).
Dynamics of Spacecraft Guidance and Spin-up of the Gyrodine’s Rotors at Pulse-width Control
.
20.
Banshchikov
,
A. V.
, &
Bourlakova
,
L. A.
(
2004
).
On Stability of a Satellite with Gyrodines
.
In Proc. Seventh Workshop on Computer Algebra in Scientific Computing
(pp.
61
69
).
21.
Fateyev
V. V.
Gyroscopic stabilizers with flywheel drive
//
Proceedings of HEI, Instrumentation. –
No.
11
. -
1985
.
22.
Bogachev
,
A. V.
,
Vorob’eva
,
E. A.
,
Zubov
,
N. E.
,
Mikrin
,
E. A.
,
Misrikhanov
,
M. S.
,
Ryabchenko
,
V. N.
, &
Timakov
,
S. N.
(
2011
).
Unloading angular momentum for inertial actuators of a spacecraft in the pitch channel
.
Journal of Computer and Systems Sciences International
,
50
(
3
),
483
490
.
This content is only available via PDF.
You do not currently have access to this content.