KARACHUN V.V.
National
Technical University of Ukraine “KPI”
THE DUAL-CHANNEL SCHEME OF AUTOCOMPENSATION
OF THE OBSTACLES IMPACT
Two differently
rotating angle rate sensors of ÄÓÑÓ2-6AÑ series with the same orientation of the gimbal relatively to the set basis are installed in a
reverberation chamber
[1-4].
The forced rotation of the gyroscope gimbal around the axis, which is
parallel to the angular momentum vector. The gyroscope was set up on a platform of universal turntable table of ÓÏÃ-56 series in order to ensure collinearity of the kinetic momentum vector of gyroscope 
and angle rate vector
of forced rotation of the gimbal.
The tests showed that the ÄÓÑÓ errors at the influence of
the acoustic
level
(~ 163-165 dB) change the sign at the change of
direction of the gyromotor rotation and has the
character of instrumental error of the gyroscope. Thus, the dual-channel scheme can only average
the size of this
error, and the second scheme – reduce to zero, but in the average for the period of
rotation.
The experiments prove that the effective means of
compensation of intense sound fields is a modulation of constant perturbance moments of a periodic function of
time. A
known
technical realization of this
method lies
in autocompensation of acoustic error by a forced rotation of the gyroscope gimbal axis, parallel to the vector of the
gyroscope kinetic momentum.
Let’s expand the task of the analysis and study the gyrostabilizer
operation in
aircraft operating
conditions, in other words, at the simultaneous impact of intense acoustic perturbation, and the carrier vibration caused by the engine operation.
In this case I is
suggested an advanced scheme of power (Fig. 1).
A biaxial power gyrostabilizer contains the basis 1 on which the dampers are fixed 18, 19, 20 and 21 with
fixed bearings of the gyroscope precession axes of swo-stage gyroscopes 22, 23 with the same kinematics of the gimbal, parallel to each other
vectors of
the angular momentum 
and mutually perpendicular precession
axes 
and 
. The basis on 1 forcedly rotates with angle rate 
by a special engine 6 around its axis, perpendicular to the
plane of the stabilized platform 5 on which it is installed.
Fig.
1. The kinematic scheme of the power gyrostabilizer
The output signal of the
gyroscope angle sensors 24 and 25 reaches the converter of coordinates 9, which is mechanically
connected with the base 1. The output signal of the converter of coordinates 9 reaches the coordinated device 14 and the input
amplifiers 10 and 11 which are controlled by the stabilizing engines 12 and 13 . To coordinate the directions of the kinetic momentum vectors 
and 
of gyroscopes with the vector of angle rate 
from 1 base, it is carried out the correction of their position relatively to the basis 5 by giving signals from the angle sensors
24 and 25 to amplifiers 26 and 27, the output signal of which reaches the sensors of moments 28 and 29 which are on the precession axis of gyroscopes. The bearings of the outer frame 15 are set on shock absorbers of the
gyrostabilizer 16 and 17, which are rigidly attached to the body of the carrier.
The
indicated
stabilizer with forced rotation of a gyroscope gimbal contains basis 1 on which the shock absorbers 2 and 3 is set a tree-stage
automatic non-corrected 4 gyroscope in the gimbal.
Initially, the vector 
of the kinetic momentum is perpendicular to the plane of the gyrostabilized platform 5. The basis1 forcedly rotates with angle rate 
by aspecial engine 6 around the axis, perpendicular to the
plane of the stabilized platform 5 on which it is set. On the axes of the gyroscope gimbal there are angle sensors 7 and
8, which receive signals from the converter of coordinates 9 and then reinforce by amplifiers 10 and 11 on the controlled windings of stabilizing engines 12 and 13. The coordinated unit 14 is electrically
connected with
the converter
of coordinates 9 . The bearings of the external frame 15 are set on shock absorbers of the
gyrostabilizer 16 and 17, which are rigidly attached to the body of the carrier.
References
1. Mel'nik, V.N.
Stress-strain state of a gyroscope suspension under acoustic loading [Òåêñò]/ V.N. Mel'nik// Strength of Materials. ISSN:
00392316. Volume: 39. Issue: 1. Pages: 24-36. Year: 2007-01-01. EID:
2-s2.0-34147198666. Scopus ID: 34147198666.
DOI:
10.1007/s11223-007-0004-6.
2.
Mel'nik, V.N. Determining gyroscopic integrator errors due to
diffraction of sound waves [Òåêñò]/ V.N. Mel'nik,
V.V. Karachun // ²nternational
Applied Mechanics. ISSN: 10637095.
Volume: 40. Issue: 3. Pages: 328-336. Year: 2004-03-01. EID: 2-s2.0-3042853113.
Scopus ID: 3042853113. DOI:
10.1023/B:INAM.0000031917.13754.2a.
3.
Karachun, V.V. Stress-strain state of the surface of a circular
cylindrical shell under the action of acoustic waves [Òåêñò]/ V.V. Karachun, V.G. Lozovik // Strength of
Materials. ISSN: 00392316. Volume: 29. Issue: 3. Pages: 313-317. Year: 1997-05-01. EID:
2-s2.0-84881176024. Scopus ID: 84881176024. DOI: 10.1007/BF02767450.
4. Karachun, V.V. Special
features of the state of stress and strain of plates with finite dimensions
under acoustic load [Òåêñò]/ V.V. Karachun //
Strength of Materials. ISSN: 00392316. Volume: 22. Issue: 10. Pages: 1512-1516.
Year:
1990-10-01. EID: 2-s2.0-0026170749. Scopus ID: 0026170749. DOI: 10.1007/BF00767241.