JPRS ID: 9002 USSR REPORT ENGINEERING AND EQUIPMENT

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, i
26 MRRCH 1988 (FOUO 3r88) 1 OF 1
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JPRS L/9002
26 March 1980
_ USSR Report
ENGINEERING AND EQUIPMENT
(FOUO 3/80)
FBIS FOREIGN BROADCAST INFORMATION SERVICE
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'i
JP RS L/9002
26 March 1980
USSR REPORT
ENGINEERING AND EQUIPMENT
(FOUO 3/80)
This sErial publication contains articles, abstracts of articles and news
items from USSR scientific and technical journals on the specif ic subjecta
reflected in the table of contents.
Photoduplications of foreign-language sourcesmay be obtained from the
Photoduplication Service, Library of Congress, Washington, D. C. 20540.
Requests should provide adequate identification both as to the source and
- the individual article(s) desired.
CONTENTS PAGE
NAVI(;ATIO?`I A;V'f) GUIDANCE SYSTEMS 1
On the Choice of Signal Measurement Time in a Gyro-Optical Compass
(V. V. Seregin; IZVESTIYA VUZ MV I SSO SSSR
PRIBOROSTROYENIYE, Vol 22 No 6, 1978) 1
TURBINE AND ENGINE DESIGN 7
Engineering Design of 5olid-Propellant Guided Ballistic Missiles
(Y. M. Nikolayev and Y. S. Solomonov; INZHENERNOYE
PRCYEKTIROVANIYA UPRAVLYAYEMYKH BALLISTICHESKIKH
RAKET S RDTT, 1979) 7
ABSTRACTS
AERONAUTICAL & SPACE 10
Optimal Ratio Between Reaction Mass and Nuclear Electric Power , Source in an Ion Rocket 10
T"neory of Staged Acceleration 10
- a- [III - US5R - 21F 5&T FOUO]
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. CONTENTS (Continued)
Page
Optimization Algorithm for a Vehicle With a Limiteu-
Capacity Engine 11
Development of K. E. Tsiolkovskiy's Concept of a Staged Rocket..... 11
- Analysis of Multistage Systems With the Aid of a Functional
Depending on the Weight of Components 12
Certain Problems of the Design of Air-Space Shurtle Systems........ 12
FLUID MECHANICS 13
Dynamic Processes of Turbulence Development in
Longitudinal Currents 13
Shells in a Stream of Fluid and Gas. Problems of
Hydroelasticity 13
MECHANICS OF SOLIDS 15
Dependence of Spherical Motions of a Solid on Structural, ,
Kinematic, and Dynamic Parameters 15
Integrable Approximation of the Problem of Mot3.on of a Point
in the Gravitational Field of a Dynamically Asymmetric Body......
15
Observability of the Trajectory of Motion of a Spacecraft..........
16
Elastoplastic Flexure of a Variable-Rigidity Annular Plate
Under a Localized Load
16
A Complex Method for the Analysis of Plates With Special
Design Features
17
Analysis of a Pressurized Orthotropic Cylindrical Shell
With an Elastic Filler Under :ecalized Loading...................
17
Experimental Investigation of the Effect of Initial
Deviations of Shape on the Load Capacity of Cylindrical

18
Shells
Investigation of the Local Stability of Structurally
Anisotropic Shells
18
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= CONTENTS (Continued) Page
Contact Interaction of a Cylindrical Container With
Unilateral Elastic Brackets 19
Buckling of Cylindrical Shells Under Combined Loading in
the Presence of Creep 19
Adaptability of Thin Shells in the Junction Zone 20
= Plastic Buckling of Composite Shells 20
= Certdin Formulas of the Theory of Middle Bending of Flat
_ Shells Having a Complex Geometry 21
- On the Linear Theory of Two-Layer Shells With Layers of
_ Varying Thickness 21
- Strength and Reliability of Complex Systems 22
NAVIGATION AND GUIDANCE SYSTEMS 23
Generalized Equations of Controllable Spacecraft Spin 23
Uynamics of a Flywheel System for Controlling the Motion of a
Spacecraft Relative to its Center of Mass With Allowance
for Elastic Elements 23
Optimal Control of the Reorientation of a Gyrostatic Satellite..... 24
' Dual-Range Pressure Controller 24
Accelerometer 25
Cyclic Optimal Maneuverir,g Modes and Their Realizations............ 26
- c -
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NAVIGATION AND GUIDANCE SYSTEMS
UDC 531.383
ON THE CHOICE OF SIGNAL MEASUREMENT TIME IN A GYRO-OPTTCAL COMPASS
Leningrad IZVESTT_YA WZ MV I SSO SSSR�PRTBOROSTROYENIYE in Russian Vol 22
Na 6, Jun 79 pp 64-68 manuscript received 28 Feb 78
[Article by V.V. Seregin, Leningrad Institute of Precision Mechanics and
Optics]
[Text] Formulas are derived for the operation of a
gyro-optical compass on a stationary base and a selected
model for the errors of a laser gyroscope, where these
formulas relate the one-time signal measurement time
and the laser gyroscope errors, which are the determing
ones in the specified compass configuration. The input
signal level quantization errors are taken into account
in this case.
The utilization of a laser gyroscope to solve the problem of gyrocompass
design involves certain specific features of the measurement of its outtput
signal. This is due to the fact that the output parameter�of a laser
gyroscope is the beat frequency, which can be measured with high precision
only using digital methods [1]. For this, the output signal must be con-
verted to a pulse train, i.e., the signal must be quantized with respect
to the level. A consequence of this is the quantization error. Moreover,
it is necesssry to take into account the fact that during gprocompass
operation, it is necessary to measure the comparatively low angular
velocity which corresponds to the low beat frequency. In line with the
operational principle of digital frequency meters, a comparatively large
measurement time is required to measure these frequencies, where this
time also depends on the requisite precision.
Since one of the characteristics of any gyrocompass circuit is its opera-
tional speed, the question of the choice of the signal measureritent time
of a laser gyroscope is an extremely important one in analyzing gyro-
optical compass operation. It is obviously expedient to consider the
operational speed in its interrelationship with the gyrocoznpass precision,
which is determined both by the gyro-opCical compass configuration and
the azimuth computation algorithm. In studying this question in the
1
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- following, we shall consider the additive errors introdueed by the laser
gyroscope itself and the errors in the measurement of its output signal,
assuming that the laser gyroscope is mounted on a stationary base with
respect to the earth, where this base has bsen horizontally leveled with
ideal precision.
Under these assumptions, we can represent the noise in the output signal
of the laser gyroscope in the following form:
Fa=Fo+a�t+F,(t) (1)
where FD is the displacement of the output characteristic zero, which
has a nonzero expectation value Fp (the mean square deviation of the zero
displacement, ao, characterizes the reproducibility of a measurement from
activation to activation); a is the rate of zero dtift, which we shall
consider to be a random quantity with a zero expectation value and a mean
square deviation aa (a characterizes the long term freqLency instability
[2]); Fc(t) is the fluctuation in the frequency, which can be cons3dered
as white noise with a dispersion QF in a certain range of frequencies
(Fc(t) defines the short term instability of the laser gproscope signal).
For the simplest configuration of a singlp component gyro-optical compass,
the time for the one-time measurement of the azimuth in [3] is determined
by the following formulas:
T ~ (2) T- 2k.A~�U�cosfp (3)
n
'1k � ~'AP
where n= wAP/Ap is the ratio of the zero drift, wAP, to the error in the
measurement of the laser gyroscope output signal, Ap, refernced to its
input; k is the laser gyroscope scale factor; U- coso is the horizontal
component of the angular rotational speed of the earth; dA is the azimuth
- computation error.
Thus, formula (2) establishes the relationship between the signal measure-
ment time and the laser gyroscope parameters, while formula (3) determines
the.measurement time as a function of the gyro-optical compass error.
In the case where the laser gyroscope operates as a pulse amplitude modu-
lated system [4], the following number of pulses are fed to the bidirec-
tional counter during the measurement time:
T
N=j Fn(t) �dt+k�T-U�cosip�casAtq, (4)
where q is the error in the measurement in the input signal, due to its
1eve1 quantization. The quantization error obeys an equiprobable distri-
bution law and has the following mean square deviation for the case of a
zero expectation value:
2
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I
Q~ - 2r3 (of a pulse)
(5)
Given the condition that the systematic error of a gyro-optical
compass, which is due to the expectation value of the zero shift of the
laser gyroscope characteristic, can.be calculated and compensated with
sufficient precision, the reproducibility of the measurement results
will exert the greatest influence on the operation of tAe simplest
compass configuration. This is manifest in the form of an additional
number of pulses, which is characterized by the mean square deviat3on
axo=ooT� ( 6 )
It is easy to find formulas from expression (4) for the error in the
calculation of the angle A due to the influence of the zero shift
and the quantization error. Taking (5) and (6) into account, there
formulas can be written in the form:
cosec A
a _Q cc,secA (7) �A2- 2j/3 �T�k�U~cosfp (8)
Al- ok.U�cosy
We choose the measurement time from the condition, under which the
quantization error (8) can be disregarded as compared to the error due
to the zero shift (7). The negligible error criterion of [5] can be
used as this condition:
�A2 < 3 �At�
(9)
By substituting formulas (7) and (8) in (9), we derive an expression
following transformation which defines the choice of the measurement time:
T ~ Y3
2ao - 2k,Q. ~ (10)
where aw is the mean square deviation of the zero shift, referenced to
the input of the laser gyroscope. It can be seen from (10) that with an
improvement in the laser gyroscope reproducibility (Qo decreases), the
measurement time increases. But in this case, the fact that the gyro-
compass error falls off, remaining at the level of (7), must be taken
into account. Tn this sense, formula (10) deterntines the optimal time for
a one-time measurement, which is expediently broken down into two equal
intervals, during which the signs of the frequency pedestal will be
opposite. This wi11 permifi a reduction in the influence of the long term
frequency instability, through the exclusion of the change in the size
of the frequency pedestal.
A similar problem, but with a different model for the errors of a laser
gyroscope, was treated in paper [6].
3
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If the procedure considered here for the determination of the measure-
ment time is applied with the same presupposition to the compass configur-
ation in which two laser gyroscopes are used with mutuallp perpendicular
input axes, then we obtain an expression which agrees with formula (lO).
Thus, a dual component configuration for a gyro-optical compass has no
advantages in terms of operational speed as compared to the single compo-
nent configuration. However, this can be confirmed only for the selPcted
model of the laser gyroscope errors and the given met&od of processing its
output signal.
We shall treat a single component gyro-optical compass configuration, in
which, just as in [7], two measurements are made at different positions
of the input axis of the laser gyroscope in the horizontal plane. If the
laser gyroscope is rotated without the vertical axis through 180�, then
the algorithm for the calculation of the azimuth i.s
' 1V1 - IVz (11)
A =BCCCOS 2T�k�U�tosvp
- where N1 and N2 are the numbers of pulses registered in the bidirectionai
counter for the corresponding positions of the laser gyroscope. Taking
(1) into account, these values can be represented in the form:
T.
Ni=J [Fo-i-a�t-1-Fc(t)]dt+*�T�U�cosfp�cosA�q, (12)
' zr
_ Na=f [Fo+a�t+Fc(t)]dt-k�T�U�cosg�cosA�q. (13)
r -
Each of these measurements contains a quantization error. Tts influence
on the error in the calculation of the azimuth A wi1 be determined by
- formula (8).
Performing the integration in (12) and (13), and substituting the result
in (11), it is not difficult to confirm that the displacement of the laser
gyroscope zero in this compass configuration does not yield an error in
the azimuth calculation. For this reason, when finding the condition for
the determination of the signal measurement time, it is necessary in this
- case to take into account the error due to the zero drift, the mean square
- deviation of which is
_cQ�T�cosecA
aA3-'2-k-U-c0S_?, (14)
Summing the errors of (8) and (14), we obtain a function which has a
clearly pronounced minimum at a certain value of the measnrement time.
This time is determined by the function:
= Ta = Y3
3QQ (15)
4
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and is optimal in terms of the criterion of a minimum in the mean square
error. The gyrocompass time will be composed of the time for the execu-
tion of two measurements:
y1. , ~16)
Tr =2V ~ _
3ao ~o
In this case, the error in gyrocompass operation due to the zero drift
and the signal quantization will amount to:
+2_ 0,537 cosec A V-
2
QA- ~A2 QA8- k�U�.COStp ~a' . (17)
and will define the maximum achievable error given ideal filtering of
the fluctuations in the output signal of the laser gyroscope.
~ If the gyrocompass operates with two signal measurements, then the
- application of the negligibility criterion to the quantization error
yielcls an overstated measurement time and value of the azimutfi calcula-
tion error, and consequer.tly, does not allow for the determination of
the optimum measurement time.
As an example, we shall use the derived formulas to calculate the para-
meters of the laser gyroscope cited in [8]: the reproducibility is
+ 9.74 � 10'7 sec-1; the long term instability over one hour is
+ 4.87 � 10-7 sec-1; the scale factor is 1.15 � 105 Hz � sec. We shall
assume ~ = 60� and cosec A= 1. Using formulas (10), (7) and (8), we
obtain xespectively:
T= t/3 = 23,2 : aA I _ 1/3-0'2 , _ ~'G;
2�(1,5G�1/3�0,2 ~ 15�cos60
1
,
',t2 = 2 j~3 � 23,2 � 0,56 � 15 � cos GO� - 10 .2.
Using formulas (16) and (17), we compute that :(Q _ 0,1 �0,56 Hz � s~
~ a - a.aeoo =5,185�10-6 rit �~-1
'.r _ 1,52 = 6GG,7c. ~ a 0�537 � j~5, I 85 � 10'e = 1' .
Y5,185� 10'tl S A 0,56� IS�cos6U"
The studies performed here allow for the conclusion that the problem of
optimizing gyro-optical compass speed, where the compass operates on a
stationary base, should be solved taking into account the model for the
laser gyroscope errors and the algorithm for processing its output signal
in the specific compass configuration.
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BIBLTOGRAPHY
- 1. Fedorov, B.F., et al, "Opticheskiy kvanfiovy giroskop" ["An Optical Laser
Gyroscope"], Moscow, Mashinostroyeniye Publishers, 1973.
2. Bychkov, S.I., et a1., "Lazernyy girascop" ["A Laser Gproscope"], Moscow, ~
Sovetskoye Radio Publishers, 1975.
3. Seregin, V.V., "0 bystrodeystvii giroopticheskogo kampasa" ["On the
Operational Speed of a Gyro-Optical Compass"], TZV. WZpV SSSR,
PRIBOROSTROYENIXE [PROCEEDINGS OF THE USSR HTGHER EDUCATTONAL
INSTITUTES, TNSTRUMENT CONSTRUCTTON], 1975, Vol 18, No 12.
- 4. Seregin V.V., Smirnov, V.Ya., "K voprosu ob obrabotke informatsii v
KOKG" ["On the Question of Data Processing in KOKG [not further de-
fined]"], Abstract No 5.32.615, RZH METROLOGTYA I TZMERITEL'NAYA
TEKHNIKA [JOURNAL OF ABSTRACTS IN METROLOGX AND TNSTRUMENTATION
ENGINEERTNG], 1976, No 5.
5. Malikov, M.F., "Osnovy metrologii" [F'Fundamentals of Metrology"],
'Mascow, 1949.
6. Kuznetsov, G.M., et al., "Ob opredelenii azimuta lazernym giroskopom"
["On the Determination of Azimuth with a Laser Gyroscope"], IZV. WZOV
SSSR - PRIBOROSTROYENIYE, 1976, Vol 19, No 6.
7. Ivanov, V.A., Yalynychev, N.A., "K teorii pretsizionnogo indikatora
meridiana" ["On the Theory of a Precision Meridian Tndicator"], IZV.
VUZOV SSSR - PRTBOROSTROYENTYE, 1968, Vol 21, No 6. -
8. Langford, R., "Datchiki inertsial'npkh sistem na novykR fizicheskikh
prints.ipakh" ["Inertial System Transducers using New Physical Princi-
ples"], VOPROSY RAKETNOY TEKHNIKI, 1966, No 9, 10.
COPYRIGHT: Izvestiya vuzov SSSR "Priborostroyeniye", 1979.
[8144/681-8225]
8225
CSO: 8144/681
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TURBINE AND ENGINE DESIGN
UDC 623.451.8(024)
ENGINEERING DESIGN OF SOLID-PROPELLANT GUIDED BALLISTIC MISSILES
Moscow INZHENERNOYE PROYEKTIROVANIYA UPRAVLYAYEMYKH BALLISTICHES;CIKH RAKFT S RDTT (Engineering Design of Guided Ballistic Missiles with Solid-Propel-
lant Rocket Engines) in Russian 1979 signed to press 7 Mar 79 pp 1-4 _
[Annotation, table of contents and foreword from book by Yuriy Mikhaylo- `
vich Nikolayev and Yuriy Semenovich Solomonov, Voyenizdat, 5,500 copies, -
240 pages]
[Text] The book sets forth the methods for designing guided ballistic
missiles with solid-propellant based rocket engines that are used mainly
during the initial stages of designing a missile system. It shows the
importance of these methods to establishing the solutions that are incor-
porated in the deYelopment of a missile and to refining the possible val-
ues oi' its flight-engineering characteristics.
Thc book is inte:ided for specialists who work in the rocket-engineering
fiel.d and also for audiences and students of senior courses at higher edu-
cational institutions who are familiar with the basics of designing
missiles.
The information cited in the book is based upon data published in the open
domestic and foreign press.
Contents
Page
~ Foreword 4
Chapter 1. General Information about Guided Missiles.
1. The basic requirements made an UBR's [guided ballistic
missiles] 5
5
2. Brief information about the working principles of UBR's in
flight 9
3. Stages in the creation of a UBR and the tasks solved during
design 23
7
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4. The concep-t of missile-systems effectiveness and of criteria
for evaluai;ing it 27
Chaptcc, 2. 13ases of' the Theory of Flighl; of U131t's
_ i. Flight of the UBR during the inactive leg 38
2. Flight of the UBR during the active leg 46
3. I;nergy capability and maximum flight range of the UBR......... 56
9. The precision of GCh [nose cone] impact on the target......... 66
5. Basic concepts about UBR dynamic characteristics 76
Chapter 3. Characteristics of the Component Elements of a UBR with
RDTT [solid-propellant rocket engine]
1. The nose cone, the system for overcoming the PRO [antimissile
defense], and the UBR guidance system 83
2. Solid propellants and their main characteristics 91
3. Solid-propellant engines 101
4. Control devices for missiles with RDTT's 130
5. The characteristics of materials used in missile manufacture.. 137
Chapter 4. The Preparation of Baseline Data for Design
1. The tasks and subject matter of designing ballistic missiles.. 146
2. tihaping thc payload 149
3. Evaluation of the range of values of the UBR's basic
characteristics 156
4. Certain peculiarities of the choice of various conceptual and
design-development solutions 164
5. Peculiarities of choice of the solid propellant 174
Chapter 5. Determination of the UBR's Design Parameters
1. Design parameters and methods for determining them............ 184
2. Analysis of the geometric and weight characteristics of
missiles with RDTT's 191
3. An approximate ballistic-missile analysis of a UBR............ 220
4. The effect of change of various parameters on the UBR's
flight-engineering characteristics 227
Bibliography 240
Foreword
- The designing of guided ballistic missiles is a complicated and important
stage of developing them, in the process of which the mutually related
problems of the missile as a whole and of its individual systems and com-
ponents must be solved. This process presupposes a systematization and
generalization of the experience gained in missile manufacture and the de-
velopment of new methods for integrated analysis of a missile that consid-
er more fully the mutual influence of various engineering solutions.
8
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An attempt has been made in this book to set forth the subject matter ot'
methodsfor designing guided ballistic missiles with RDTT's that are used
' in engineering practice at the initial stage of design.
Chapter 1 gives basic information about guided ballistic missiles, the
stages and tasks of design, and the concept of missile-systems effective-
ness.
Chapter 2 sets forth the bases of the theory of flight of ballistic mis-
~ siles and the guidance of them, to the extent necessary for a rational
choice of a missile's basic design parameters during ballistic design.
Chapter 3 contains basic information about the arrangement and operating
principles of the main components and assemblies of a missile with RDTTs,
including the nose cone, the control system, the system of defense against ~
PRO and the systems that support its functioning, solid-propellant char-
ges, and guidance and stabilization devices. '
Later chapters analyze in detail the stage of preparation and establish-
ment of the main baseline data for ballistic designing,and the tasks and
subject matter of this important stage of the process of designing a mis -
sile as a whole are disclosed.
Design methods for weight-and-energy, geometric,and ballistic analyses
that will enable the connection between the missile's basic design parame-
ters and its flight-engineering characteristics to be established as
applicable to the characteristics of certain standard conceptual and ~
design-development schemes for rockets and their components.
The numerical and factual data cited in the book are based upon informa-
tion in the open domestic and foreign press.
Copyright: Voyenizdat 1979
11409
CSO: 8144/0692
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Aeronautical & Space
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USSR
UDC 629.78.076.6
UP7'IMAI, itA`I'IO 13l?'CWF(:N RrACTTON MASS AND NUCI.EAR E-LECTRIC POWI?R SOl1kCI~~ TN
AN ION ROCKLT
Moscow IDEI K. E. TSIOLKOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's Ideas
in Present-Day Light] in Russian, 1979 pp 34-40
MERKULOV, I. A.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract
- No 7.41.84]
[Text] Problems of the theory of the optimization of the electrical
rocket engine, whose utilization in rockets had in principle been proposed
by Tsiolkovsky, are considered. Dimensionless criteria typifying ion-
, thruster rockets are derived. The optimal ratio between the reaction mass
and the nuclear electric power source is demonstrated.
[456-1386)
USSR
THEORY OF STAGED ACCELERATION
UDC 629.78.076.6
Moscow IDEI K. EL. '1SIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day LighC] in Russian, 1979 pp 46-50
KAZNEVSKIY, V. P.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract
No 7.41.85]
[Text] The theory of the effectiveness of staged acceleration in discussed
with respect to multistaged vehicles successively fueled during their
acceleration from several mass carrier accumulators. A general formula-
tion of Tsiolkovsky's classical equation applicable to the staged accelera-
tion of multistaged vehicles is derived.
[456-1386]
10
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USSR
UDC 629.78.076.6
OPTIMIZATION ALGORITHM FOR A VEHICLE WITH A LIMITED~CAPACiTY ENGINE
Moscow IDEI K. E. TSIOL'KOVSI:OGO I SOVREMENNOST' [K.\E. Tsiolkovsk.y's
Ideas in Present-Day Light] in Ruseian, 1979 pp 76-83\
F-1
KONSTANTINOV, M. S. ;
~
;
[From REFERATIVNYY ZHURNAL 41. RAKETOSTRQYENIYE No 7, 1979 Abstract No
1
7.41.87]
~
[Text] The work of optimization of a spacecraft with an 1eingine of limited
capacity is analyzed with respect to the problem of a rouridtrip flight
- between the orbits of an artificial satellite of Earth and'an artificial
satellite of Mars, on the assumption of coplanarity of the orbits of Earth
and Mars, disregarding their eccentricity. The space of selectable para-
meters of the vehicle and the effectiveness o� the algorithm, particularly
with respect to the satisfaction of inequality-type conditions, are investi-
gated. Figures 2;-references 3.
[456-1386] USSK UDC 629.764.7.001
' AEVELOPMENT OF K. E. TSIOLKOVSKIY'S CONCEPT OF A STAGED ROCKET
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 23-34 VORBO'YEV, L. M.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.151]
[Text] The results of the development of Tsiolkovsky's concept of rocket
stages are considered:' A theory of the optimization of the basic design
parameters of multistage rockets is presented. The domains of rational
application of one-, two-, and three-stage rockets are described.
[456-1386]
11
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USSR UDC 629.764.7.001
ANALYSIS OF MULTISTAGE SYSTEMS WITH THE AID OF A FUNCTIONAL DEPENDINC ON
THF WI:TGHT OF COMPONFNTS
Moscow IDEI I. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 41-45
BALASHOV, V. V.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.152]
[Text] The procedure for constructing a functional for the optimization
of the basic parameters of multistage rockets with vertical launching and
horizontal landing of the carrier and the orbital stage is examined. The
introduction of generalized parameters into mass ratios was"used in
optimizing the rocket stage systems. References 2.
[456-1386J,
USSR
UDC 629.782.001
CERTAIN PROBLEMS OF THE DESIGN OF AIR-SPACE SHUTTLE SYSTEMS
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 113-122
BALASHOV, V. V.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.153]
[Text] Possible methods of spaceship launching as o riginally proposed by
Tsiolkovskiy are examined. The.present-day state of the art as regards
the development of the space shuttle is analyzed. The basic problems of
reusable vehicle design are discussed. Figures 2; references 2.
[456-1386]
12
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Mechanics
FOR OFFICIAL USE ONLY
USSR
UDC 629.78:533.1
z
DYNAMIC PROCESSES OF TURBULENCE DEVELOPMENT IN LONGITUDINAL CURRENTS
K()SMICItI:SKIYI: ISSLL;DOVANIYA [Space Research] in Russian Vol 17 No 1, 1979
pp 60-68
GUDKOVA, V. A., VOLOSEVICH, A. V,, LIPEROVSKIY, V. A. and SKURIDIN, G. A.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.117]
[Text] The dynamics of the processes of flow of magnetospheric longitudinal
currents with developed anomalous drag is considered. It is shown that in
a sufficiently narrow tube of force, processes of turbulent heating should
result in disrupting the quasi-steady turbulent state. On the other hand,
in a sufficiently broad tube of force the onset of a quasi-steady state is
possible. In connection with the theoretical analysis, possible experi-
mental techniques for investigating anomalous drag in a magnetospheric
tube of force are considered. References 26.
[456-1386] USSR UDC 629.78.015.4
SHELLS IN A STREAM OF FLUID AND GAS. PROBLEMS OF HYDROELASTICITY
Moscow OBOLOCHKI V POTOKE ZHIDKOSTI I GAZA. ZADACHI GIDROUPRUGOSTI in
Russian, Nauka, 1979 320 pp.
VOL'MIR, A. S.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.179 K]
[Text] Tra.nsient processes in shell-fluid systems and echo signals
generated in the fluid by shells under deformation are investigated. A
special section deals with problems of hydrodynamics of blood circulation,
which pertain to biophysics. The behavior of shells in non-detached flow
(divergence, flutter in sub- and supersonic gas flow) and in stalled flow
(buffeting, ash-caused oscillations, galloping) is investigated. The
effect of atmospheric turbulence on civil-engineering structures is con-
sidered. Numerical and experimental methods in aero- and hydroelasticity
. 13
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are reviewed. Converse problems of aeroelasticity associated with the
identification of system parameters and external effects are investigated.
The book is designed for scientists specializing in various domains of
continuum mechanics, graduate students, advanced-course students in
universities and higher educational institutions, and aircraft, ship-
building, machine-building, and structural engineers. Figures 172;
references 335.
[456-1386]
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Mechanics of Solids
FOR OFFICIAL USE ONLY
USSR
UDC 629.78.076.6
DEPENDENCE OF SPHERICAL MOTIONS OF A SOLID ON STRUCTURAL, KINEMATIC, AND
DYNAMIC PARAMETERS
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 61-72
DOBRONRAVOV, V. V.
' [From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.861
[Text] The dependence of the spherical motions of a solid on structural,
kinematic, and dynamic parameters is examined with respect to the motion
of a spacecraft relative to its center of mass. It is shown that the
solution of a number of known problems formulated in this study has a
direct bearing on techniques for controlling automatic and manned space-
craft, whose principles had been formulated by K. E. Tsiolkovsky.
References 5.
[456-1386J
USSR
UDC 629.78.076.6
INTEGRABLE APPROXIMATION OF THE PROBLEM OF MOTION OF A POINT IN THE
GRAVITATIONAL FIELD OF A DYNAMICALLY ASYM TRIC BODY
KOSMICHESKIYE ISSLEDOVANIYA [Space Research] in Russian Vol 17 No 1,
1979 pp 161-164
OREKHOV, V. N.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.89] .
[Text] The generalized problem of two fixed centers in which separation
of variables yields a detailed qualitative analysis of motion may be
regarded as an integrable approximation of the problem of motion of a
material point in the gravitational field of a spheroidal body. The
potential.approximation proposed in this paper makes possible the
separation of variables in the approximation problem for the case in
~ which the attracting body has a triaxial central ellipsoid of inertia.
References 6.
[456-1386J
15
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USSR
UDC 629.78.076.6
OBSERVABILITY OF THE TRAJECTORY OF MOTION OF A SPACECRAFT
iZVESTTYA LENINGRADSKOGO ELEKTROTEKHNZCHESKOGO INSTITUTA [Bulletin of
I,eningrad Electrical Engineering institute] in Russian No 241, 1978
pp 31-37
SIDOROV, A. S. _
, [From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.93]
[Text] The application of general methods of the theory of observability _
of nonlinear dynamic objects to a particular problem of determining
motion on the basis of ineasurement data is co-asidered. The conditions
under which an unequivocal reconstruction of the unperturbed Keplerian
orbit of a spacecraft with an incomplete set of sensors is possible are
determined. An orbit reconstruction algorithm is proposed. Figures 3,
references 7.
[456-1386J
USSR
UDC 629.78.015.4
EI,ASTOPLASTIC FLEXURE OF A VARIABLE-RIGIDITY ANNULAR PLATE UNDER A
LOCALIZED LOAD
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 3-10
BINKEVICH, YE. V. and ULANOVA, N. P.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No.
7.41.176]
[Text] An algorithm for a numerical'solution of the problem of the elasto-
plastic buckling of asymmetrically loaded plates with a rigidity having a
square-law variation is constructed. On the basis of Budyanskiy's criterion
the possibility of applying the theory of small elastoplastic deformations _
to the solution of this problem is substantiated. Figures 3, references 7.
[456-1386]
16
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USSR
UDC 629.78.015.4
A COMPLEX METHOD FOR THE ANALYSIS OF PLATES WITH SPECIAL DESIGN FEATURES
.
Moscow TEMATICHESKIY SBORNIK NAUCHNYKH TRUDOV. MOSKOVSKIY AVIATSIONNYY
INSTITUT [Thematic Collection of Scientific Papers. Moscow Aviation _
Institute] in Russian No 467, 1978 pp 51-54
MATYUSHEV, YU. S., BRODSKIY, S. I., and MOVCHAN, A. A.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.4.177 by T. A. Ye.]
[Text] When allowance is made for every possible design feature
(stiffening fins, contour elements, notches and their reinforcements),
such effective approximation methods as the finite-difference method and
the finite-element method are inconvenient to apply in their classical
matrix form, i.e. require an extensive computer memory. Direct methods
occupy a small computer memory but then the time of the solution of
problems is extraordinarily long. The article proposes an algorithm
based on the application of a modified conjugate-gradient method. The
method as fast as matrix versions, and at the same time it occupies a
much smaller volume of computer memory. Figures 2, references 2.
[456-1386]
USSR
UDC 629.78.015.4
ANALYSIS OF A PRESSURIZED ORTHOTROPIC CYLINDRICAL SHELL WITH AN ELASTIC
FILLER UNDER LOCALIZED LOADING
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 14-19
VLASENKO, I. N.
~ [From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.180]
[Text] On the basis of the engineering moment theory of anisotropic
shells an equilibrium equation of a pressurized orthotropic cylindrical
shell with an elastic filler is derived. Formulas for the analysis of
stresses and strains also are derived. Sample calculations are presented.
Figures 2, ref erences 3.
[456-1386]
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USSR
UDC 629.78.015.4
EXPERIMENTAL INVESTIGATION OF THE EFFECT OF INITIAL DEVIATIONS OF SHAPE
ON THE LOAD CAPACITY OF CYLINDRICAL SHELLS
Kiev PRUCHNOS`1'' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability �
of Complex Systems] in Russian, 1979 pp 19-26
CAYDUC1iENK0, A. P., GUDRAMOVICH, V. S. and DEMENKOV, A. F.
(From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.181]
[Text] A method for producing cylindrical shells with specified initial
deviations of shape is described. The behavior of cylindrical shells
with artificially induced initial deviations of shape under the action of
a combination of axial stress and external pressure is experimentally
investigated. Experimental and theoretical findings on the load capacity
of shells are presented. Figures 7, references 4.
[456-1386)
USSR UDC 629.78.015.4
INVESTIGATION OF THE LOCAL STABILITY OF STRUCTURALLY ANISOTROPIC SHELLS
Kiev YROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 53-58
YERSHOV, N. P.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.182]
[Text] Experimental findings on plates with zero positive Gaussian
curvature under the combined load of normal pressure and compressive
stress are analyzed. Conditions for integrity of the shells are derived
with respect to specified safety margins, and the necessary geometrical
= parameters are found for the area between stiffening ribs to ensure
reliable performance of reinforced shells under local loading, are -
derived. Figures 3.
[456-1386]
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USSR
UDC 629.78.015.4
- CONTACT TNTERACTION OF A CYLINDRICAL CONTAINER WITH UNILATERAL ELASTIC
iiRACKt:'1'S ~
- Kiev PROCHNOST' I NADEZHNOST' SLOZANYKH SISTEM [Strength and Reliability
of Compiex Systems] in Russian, 1979 pp 64-73
KATAN, L. I. and MAKEYEV, YE. M.
[From REFERATIVNYY 7.HURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.183]
[Text] The contact interaction between a cylindxical shell and arbitrarily
positioned unilateral elastic brackets of varying extent is investigated. The resolving system of nonlinear algebraic equations derived by the
trigonometric series method is linearized by an iterative process. Sample
calculations are presented. Figures 3, references 5.
[456-1386]
USSR UDC 629.78.015.4 c
BUCKLING OF CYLINDRICAL SHELLS UNDER COMBZNED LOADING IN THE PRESENCE OF
CREEP
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 89-95
POSHIVALOV, V. P.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.184] -
[Text] The buckling of cylindrical shells under the combined load of an
axial compressive stress and internal pressure in the presence of creep
, is examined. A hardening theory is applied. The fundamental equations
are linearized by a method of sequential loading. Sample calculations
of the buckling of a cylindrical shell in the presence of creep are ~
examined. Figures 7, references 6.
[456-1386]
19
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USSR UDC 629.78.015.4
AI)Al''i'A131 I.l'I'Y 01? 'I'fl I N SIII:LI,S IN T1iI: JUNCTION 7.QNi:
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 95-102 -
SEL'SKIY, YU. S.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.1951
[Text] A relationship between the stress concentration in the elastic
stage and the critical load adaptability is established on the basis of
an approximate method for taking adaptability into account. The limiting
internal pressure in the zone of contact between a cylindrical branch
pipe and a spherical vessel, and in the region of the attachment of a
conical bottom to a cylindrical shell, is determined. Figures 3,
references 3.
[456-1386]
USSR UDC 629.78.015.4 `
PLASTIC BUCKLING OF COMPOSITE SHELLS
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 34-41
GUDRAMOVICH, V. S. and KONOVALENKOV, V. S.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No -
7.41.186]
[Text] The authors consider purely plastic bulging of a thinwalled system
consisting of a cylindrical shell abutting to two conical shells. One
edge of this system is clamped, and the other edge is free. The small-
parameter method is applied and formulas of the deformation theory and
of the flow theory for a diagram with linear hardening are utilized.
Figures 1, references 4.
{456-1386]
20
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r
FOR OFFICIAL USE ONLY
USSR
UDC E29.78.915.4
CERTAIN FORM[JLAS OF THE THEORY OF MIDDLE BENDING OF FLAT SHELLS HAVING
A COMPLEX GEOMETRY
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems] in Russian, 1979 pp 26-33
GALIMOV, K. Z., KORNISHIN, M. S. and PAYMUSHIN, V. N.
[From REFERATIVNYY LHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.187]
[Text] A variational equation of the theory of the mean flexure of flat
shells, analogous to the formula of N. A. Alumyae, is derived on the basis
of certain transformations of the Lagrange variational equation for the
case in which shells on the tangential stress contour represent specified
quantities. Resolving equations and boundary conditions relative to the
bending of the shells are derived in general coordinates, and the functions
of tangential forces are found on the basis of this equation for shells of
complex geometry with a boundary on the middle surface that coincides with
coordinate lines. References 6.
[456-1386]
USSR UDC 629.78.015.4
ON THE LINEAR THEORY OF TWO-LAYER SHELLS WITH LAYERS OF VARYING THICKNESS
Kuybyshev VOPROSY PROCHNOSTI I DOLGOVECHNOSTI ELEMENTOV AVIATSIONNYKH
KONSTRUKTSIY
[Problems of the Strength and Durability of Structural Aircraft Components]
in Russian No 4, 1978 pp 19-251
PAYMUSHCHIN, V. N. and ODINOKOV, A. YU.
(From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.1881
[Text] A linear theory of two-layer shells with layers of variable smoothly
changing thickness is constructed. The thickness of these layers is assumed
to be substantial, and hence the Timoshenko straight-line hypothesis is
appli.ed to the layers and allowance is made for the difference in the
21
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metrics of their median surfaces, which are assumed to be mutually flat.
Basic formulas of the deformation theory are derived with respect to the
curvature lines of one of the layers. A system of seven differential_
equations of shell equilibrium is derived by a variational method; the
common order of these equations is 14. This system, along with the static
boundary conditions of the problem, is derived for the case in which the
contour lines of the median surfaces of the layer coincide with coordinate
lines and the boundary shear planes are formed by the motion of the normals
along these lines. Figures 1, references 7.
[456-1386]
USSR UDC 629.78.017.1
STRENGTH AND RELIABILITY OF COMPLEX SYSTEMS
Kiev PROCHNOST' I NADEZHNOST' SLOZHNYKH SISTEM [Strength and Reliability
of Complex Systems], Collected Scientific Papers, Dnepropetrovsk Depart-
ment of the Academy of Sciences USSR in Russian, Nauk. Dumka, 1979
204 pn
Dnepropetrovsk Affiliate of the USSR Academy of Sciences
_ [From REFERATIVNYY ZAURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.190 K]
[Text] Current problems of the theory of the strength and reliability of
complex systems are discussed. Theoretical and experimental findings on
bearing capacity and stabil3ty as well as on the stress-strain state of
shell structures under non-uniform loads and in the presence of contact
interactions (with, in this case, allowance for the physical nonlinearity
of the material) are presented. Probabilistic failure models are discussed
in relation to the solution of durability problems. Certain problems of
the rz.~,:dom process overshoot theory are considered, as are approximation
formulas for multivariate norrnal distribution functions and the problems
of conducting speeded-up durability tests. The book is designed for
- researchers and engineers dealing with strength and reliability, as well
as for graduate and advanced-course students majoring in the corresponding
fields. Figures.
[456-1386]
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Navigation ana uuiaance 5ystems
FOR OFFICIAL USE ONLY
. USSR ' UDC 629.78.076.6
GENERALIZED EQUATIONS OF CONTROLLABLE SPACECRAFT SPIN
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 98-104
GARTUNG, YU. A. and LOYENKO, YU. M.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.88]
[Text] A system of differential equations of controlled spherical motion
of a solid, programmed with the aid of differential constaints of a general
kind, is constructed. General formulas for computing the corresponding
control actions are derived. Cases of natural realization of the con-
straints in question are considered. References 4.
[456-1386]
USSR
UDC 629.78.017.2
DYNAMICS OF A FLYWHEEL SYSTEM FOR CONTROLLING THE MOTION OF A SPACECRAFT
RELATiVE TO ITS CENTER OF MASS WITH ALLOWANCE FOR ELASTIC ELEMENTS
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovskiy's
Ideas in Present-Day Light] in Russian, 1979 pp 83-90
POPOV, V. I. and SEVEROVA, L. V.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.110]
[Text] The dynamics of a flywheel system for controlling the motion of a
- spacecraft relative to the center of mass is considered with allowance for
elastic elements. A system of equations convenient for numerical realiza-
tion in a computer is derived, and illustrative examples are presented
along with an algorithm. Figures 4, references 5.
[456-1386]
23
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USSR
UDC 629.78.017.2
OPTIMAL CONTROL OF THE REORIENTATION OF A GYROSTATIC SATELLITE
KOSMTCIII:SKTYi? T.SSL1;DOVANIYA [Space Research] in Rues3an Vo1 1.7 No 1, 1979
pp 18-23
7.LOCHEVSKIY, S. I.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.113]
[Text] The problem of reorienting a gyrostatic satellite in a circular
orbit within a Newtonian gravitational field is considered.. The optimal
pattern of control of the kinetic moments of three flywheels installed
along the major axes of inertia of the satellite is synthesized. The
integral r.m.s. functional of the components of the kinetic moment of
the flywheel is minimized. References 10.
[456-1386]
USSR
DUAL-RANGE PRESSURE CONTROLLER
UDC 629.78.064.2(088.83)
USSR Author's Certificate Cl. G 05 D 16.06, No 594488, filed 9 Jan 73,
No 1868828, published 24 Mar 78
BAVAROVSKIY, L. S., DOBKIN, R. I., LASTOCHKIN, A. D., RATMANSKIY, 0. I.,
Kievpromarmatura Scientific Production Association
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.194 P]
[Text] This invention concerns a direct-action gas controller and may
be used in flight-vehicle pneumatic systems. The traditional 2-range
pressure governor contains a casing with inlet and outlet branch pipes,
a main spring-loaded sensor, a lid, and an adjuster. A shortcoming of
the traditional 2-range governor, whose adjuster is air-driven, is the
need to install an additional 3-way electropneumatic valve, a main pipe,
a piston, and two drain lines for the idle passage of the working medium.
To reduce energy losses and simplify the governor, the adjuster is designed
in the form of an electromagnet mounted in the lid. The armature of the
electromagnet is connected via a bracket to one end of an extra spring
contacting the sensor; the other end of the spring is connected via an
adjustment screw to the lid. Figures 1.
[456-1386]
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USSR
ACCELEROMETER
UDC 629.78:531.768(088.83)
USSR Author's Certificate G 01 P 15/02, No 605179, filed 6 Jan 75,
No 2093093, published 21 Apr 78
CALKIN, YU. S., KRUTSKIKH, Z. A., GRIGOR'YEV, G. A., KORYAGIN, A. V.,
KAGAN, M. G. and PISAREV, G. N.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.234 P] '
[Text] The invention pertains to an accelerometer and may be used in
homing systems as well as in systems for measurement of small linear ,
, accelerations of missiles and spacecraft. The traditional accelerometers
contain an inertial mass in the shape of-a bushing mounted on a shaft
whose rotation generates a gas-dynamic bearing; a flexible nylon thread with a negligibly small cross-rigidity, whose one end is attached to the
- inertial mass and the other, to a fixed casing serving as a converter of
gas-dynamic friction to an axial stress impeding the movement of the
inertial mass under the action of angular acceleration; and a recording
device. A shortcoming of such conventional accelerometers is stable'sub-
harmonic oscillations of the inertial ma:;s relative to the axis of the
suspension, which oscillations alter the o;xtput characteristic of the
devtce. These oscillations are due to the following factors: 1) the
presence of a small curvature of the restoring system, cor.responding to
a thread tension of the order of 0.05 gf; 2) the presence of per.turbations
induced in the inertial mass by the rotating shaft, as reflected in the
wobble of the shaft surface relative to the rotational axis of the shaft;
and 3) the presence of nonlinearity of the force characteristic of the
thread when under low tension, owi�g io thc aarodynamic moment of friction.
The aim of the invention is to dampen the radial oscillations of the sen-
sory element and to enhance the stability of the accelerometer's output
characteristic. To accomplish this aim, the accelerometer thread is
profiled in a plane in the form of segments of ares. Figures 3.
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USSR
CYCLIC OPTIMAL MANEUVERING MODES AND THEIR REALIZATIONS
UDC 629.78.017.2
Moscow IDEI K. E. TSIOL'KOVSKOGO I SOVREMENNOST' [K. E. Tsiolkovsky's
Ideas in Present-Day Light] in Russian, 1979 pp 91-98
GURMAN, V. I. and NIKULIN, A. M.
[From REFERATIVNYY ZHURNAL 41. RAKETOSTROYENIYE No 7, 1979 Abstract No
7.41.111]
[Text] A new type of maximally economical control modes for movements
of the spacecraft center of mass and about that center by means of
limited-thrust engines is derived with the aid of V. F. Krotov's _ optimality theory and the multiple-maximum method. The features of such
control modes, termed cylic optimal modes, and the possibilities of
implementing them are investigated. Figures 3, references 5.
[456-1386]
CSO: 1861 - END -
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