SCIENTIFIC ABSTRACT PANICHEVA, A. S. - PANIKAR, V. I.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001239020010-3
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: January 3, 2017
• Document Release Date: August 1, 2000
• Sequence Number: 10
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT


PAVICHE-VA, A. S.: 14aster Tech Sci (aiss) -- "Invest"i&,aVion of the pronerties
of austenitic steel on a chrow-manginese baf3o". Moscow, 1T58- 15 PP (Min
Higher Educ USSR, Moscow Oraer of I-enin and Oriler of IAborRea Banner Higher
Tech School im Bauman), 150 copies (KL, No 4, 1959, 127)

PANICHETA, G.P., ISHROMOV, A,S.
Stamped plywood barrels. Standartisateiia 24 no.7:37-38
ii 16o. (MIRA 13!7)
(Barre le-Standards)

PANICHEVA.-G,S*
Development of the state stan&-,rd 5958-59 for stamped pl7wood
barrels for various products. Trudy 11IL Tary no-4:39-44
(Bar3L-ele-Standards) (MIRA 34:12)
(Plywood)

I.ACCESSION NR: AP4043677 S/0109164/009/008/1433/1439
AUTHOR: Morgulis, N. D.; Levitskiy, S. M.; Panichevskiv, V. A.
ITITLE: Determination of parameters of gas-discharge cesium plasma by the
superhigh-frequency method
SOURCE: Radiotekhnika'i elektronika, v. 9. no. 8, 1964, 1433-1439
ITOPIC TAGS: plasma, plasma gas collision,, plasma measurement, cesium
1,.plasma, gas discharge plasma
ABSTRACT: An experimental investigation of the electrons. collision frequency
and rate of decay of a weak ionized cesium plasma by the SHF-resonator method
at. 3-cm wavelength is reported. Charge concentrations within 10 11- 1012 crn-5
and cesium vapor pressures within 0.91-0.2 torr were used. Byrneasuringthe
I I ~ 7
IQ-factor of a cesium-plasma-filled resonator at various pressures, the collision
frequency at I tori was found to be 3x 109 per aec and the effective cross -section!
'Caid

A6CESSION NR. AP4043677
of the scattering of electrons by pladmai atoms 0. 4x 10-14 cm kAlso#' the
coefficient of bipolar diffusion (10-20 CM2/SeC) was determined. This data is
compared with results published by*other rebrearchers and discussed. Orig, arte~
has:. 6 figures and 5 formulasi
ASSOCIATION: 1Kiyevskiy,-gosudarstvenny*y univeisitet.'(Kiev State Un&ersity)
SUBMTTED,. 15jun63:,'. ENCL-. 00
SUB CODE.* ME NO REF SOV: 008 OTHER: 008
Card Z1Z

,%,OR,GLT.LIS, N.D.; IfVI7SK-TY, s.M.; PANICHEEVSKIY, V.A.
Detemination of tho parameters of gaL--Uscliarge ceEir-- plaBn-a uz'5,-,,
a microwave technique. Radlotekh. J- elektron. 9 no.8:1433-1439 Ag
164- (MIRA 17:10)
1. Flyevskiy gosudarstvennyy universitet.

PANIGHM.. I. A.
IT voprosu vliyaniya granits. potoka kruglogo poperechnogo secheniYa na aerodinamicheskie
kharakteristiki kryla.11 "On the Question of the Influence of the Edges of a Stream
with Curved Cross-Section on the Aerodynamic Characteristics of the Wing."
Prik. Maty. i. Mekh2 Vol. 9., 11b. 2, pp. 171-178, 1945

I, ~ !, h ,
4~ - ,
- . I 7-1?~~-, ,

PANICHKINt- It- Aq-
"Oprodelenie tairkulyatsLy po razmakhu kryla v otkry-toy i poluotla-ftoy strue
prymougolnogo secheniyu.11 "Determination of the Circulation Cm thn Wing S efid
, pr
in Open and Half-fJpen Stream with Right Angle Gross-Section."
Prik. Hati. i Mekh,.. Vol. 10, No. 4, pp. 529-536~ 1946
T

USSR/Vel6city, Ultrasonic Jan 1947
-Wi~ prof Ilei -Wind ti~nel tests
,"Mr-cis Acting on an Osoillat-Ing Profile in a
.Supersonic Gas Flow," I. A. Panichkin, 4 pp
"Prik YAte i Mekh" Vol XI, No 1, kb- 70
Sapersonio gas flow'past a thin, "lightly bent,
osoillating wing profile, in two cases: a) where
tbi-angle of incidence of the profile varies
according to the harmonic law, b) the case of a
f3jipping wing.

PANIGUIN., I. -A.
0 skose potoka za krylom. (Akademiia Nauk SSST. Institut mekhaniki. Inzherernyi
sboxmik.1, 1949, v. 5., no. 2, p. 164-170, diagrs.)
Title tr.: Angle of downwash past the wing.
Reviewed by-F. H. Giese in Mathematical Reviews, 1951, v. 12, no.8, p. 646)
TAII-17 10V', r.'~
SO: Aeronautical Sciences and Aviation in the Soviet Union, Library of Congress, 1955

PANICHKIN, I.A.
Kvoprosu vliianiia granits potoka kruglogo poperechriogo sechoniia na aerodinarAcheskie
kharakteristiki kryla. (Prikladnaia materatika i mekhanika, 19h5, v.9. no.2. p. 171-
178., diagrs.)
Sumktry in English.
Title tr.: Effect of the boundary of a flow with a circular cross section on aerody-
namic characteristics of the wing.
QA80l-P7 1945
SO: Aeronautical Sciences and Aviation in the Soviet Union, Library of Congress,
1955

PANICIIKIN.9 I.A.
K teorii kryla v strue s kruglym poperechnym secheniem. (Prikladnaia riatematika i
mekbanika, 1945, V-9, no-4, P. 312-317, diagra.)
Summary in English.
Title tr.: On the theory of a vring in a flow of circular cross section
QA801. P7 1945
SO: Aeronautical Sciences and Aviation in the Soviet Union, Library of Gongress,
1955

PANIGHKIN, I.A.
q?redelenie tsirkuliatsii'po razTlakhu kryla V otkr7toi i poluotla7tji Btrue
priamougollnoeo secheniia. (Prikladnai4 matematika i meh-hanika, 19h61 velo., nob, ps
529-536, diagrs.)
Swimary in English.
Title tr. : Determination of the circulation along a span of a wing in an open and dme-
open flow of rectangular cross-section.
Woim 1946
SO: Aeronautical Sciences and Aviation In the Soviet Union, Library of Congress,
19,55

PANICHKIN, I.A.
0 silakh, deistvuiushchikh na kolebliuBhehiisia profill kryla v sverkIz-iukovwrj jotokx
gaza. (Prikladnaia matematika i mekhanika, 1947y v-3-11 no.1, p.165-170)
Summary in English.
Bibliography: p. 170
Title tr.: Forces acting on an oscillating airfoil in a supersonic gas flow.
QA801- P7 1947
SO: Aeronautical Sciences and Aviation in the Soviet Unionj Library of Congressp
1955

.P.MICHKIN, I A.
Vlii;anie granits svob~dnoi strui ellipticheskogo secheniia na aerodinardcheskie
kharakteristiki kryla. (Akademiia I~auk SSSR. Institut mekhanild. Inzhenernyi sbornik
1948, v-4,;no*2, P. 161-173)
Title tr..- Effect of the boundaries of a free elliptical flow on aerodynamic character-
istics of the wing.
Reviewed by J.H. Giese in Mathematical Reviews, 1951, v.12, no*8j* p.646.
TA4.A37 1948, V-4.
SOP Aeronautical Sciences and Aviation in the Soviet Union, Library of Gongress, 1955.

PXNICIEDI, I.A.
O~redelenie tsirkuliatsii po razmakhu kryla v zaki-y-toi strue priamougollnogo secheniia.
(Akademiia Nauk SSSR. Institut mekhaniki. Inzhenernyi sbornik, 19h8, v.5, no.1,
p.189-197, diagrsl, bibliography)
Title tr.: Determination ofthecirculation along wing span in a closed flow of a rect-
angular cross section.
Reviewed by J.H. Giese in Mathema-Ilical. Reviews, 1951, v.12, no.8. pl6h6.
TA, A37 19h8, v-5
SO: Aeronautical Sciences and Aviation in the Soviet Union,, Library of Congress,
1955

PA.IUCHKD4, I.A.
0 skose potoka za krylom. (Akadermia Nauk SSSR. Institut mekhaniki. Inzhenernyi
sbomikj 1949, v.5j no.2) p.164-170) diagrs.)
Title tr.: Angle of downwash past the wing.
Rnviewed by J.H.Giese in Mathematical Reviews, 1951" r.12, no.8, p.646.
TA4.A37 1949, v-5
SO: Aeronautical Sciences and Aviation in the Soviet Union) Library of Congress,
1955

th,;natioal Reviews A, Supem
!4 a gsj5, abotit an oscillit- t
9*110T
.
14 No. 7 y, wing ptrfjIt;. E~Ijr)nj
l
V
o
,
152
July ~- Augustp 1953 2
Oprrational calcillms fiat; bcc-n applied to tile fincarizedi
Meahanioss t%vo-dimensional flow abolit mi aiifoil 1~..rfcrmingr small

('S(Ahlion-r, in a unifoini supcisonic'.-fream j
0

Simplif" ()f t1le I;ft ple%,iomly gi'mn by
t c
audim FAL;id. Nai%~- S~,SR. hikl. Mat., Mch. 11, M-I
;~Qrad. r)iv. Appl. Math, Bro-wit Univ. T;,indati.11
A9-T-21 (1949); 11we 0, atirl
V:a'l N!"tIL- Prill Mal.

ACHERM, N.S., doktor tekhnicheakikh nauk, professor, glavnyy radaktor;
ANTSTF3ROV, M.S., kandidat flaiko-matematicheskM nauk; ASTAKHOV, K.V..
professor; YUKMVICH, M.P., professor, doktor tekhnlcheakikh w=k;
KORZLIN, A.I., kandidat tekhnicbeskikh nauk; KHIZM, B.S., inzhener;
XAZMV, L.P., kandidat tekhnicheskikh nauk; KAZTRIN. LV., iazhener;
MATTMIN, Y.M., kandidat tekbnichaskikh nauk; NIKITIN, N.N., kandidat
fisiko-matematicheakikh nauk; TV T_A~_, kandidat tekhatcheskikh
nauk; FSTMOV, B.S., katididat tekhniche ,�k1kh nwk; PODVIDZ, L.G.,
kandidat tekhnicheakikh nauk; SIMONOV, A.P.,' inzhener; SHIRYAGIN, A.P.,
kandUat tekhnicheakikh nauk; FATEZILIBER, B.M., professor, doktor
tekhnAcheskikh nauk; KULIZEV, G.P., kandidat t*hnicheskikh nauk;
TANISHIN. B.I., kandidat takhnicheskikh nauk; MARKUS, M.Te., inzhener,
redaktor, X&MANOV, V.G., redalctor grafich6skikh materialov, inzhener;
SOKOWVA, T.F., tekhnicheskiy redaktor.
[A machinebuilder's manual in six volumes] Spravochnik mashinostroitelia
v shesti tomakh. Izd. 2-s, ispr. i dap. Moskva, Goo. nauchno-tekhn.
izd-vo mshiuostroit. lit-ry. Vol. 2. 1954. 559 P. (HLU 8:1)
(Machinery-Construction) (Mechanical engineering)

PANICHNIN, 1.4., Imndidat tekhnioheskikh Abuk, doteent-
- I - -awwww" gas flow in the vicinity Of the critical cross section
investigating -
of the nozzle. [Trudy] KVTU no.32.47-74 '55. (KLU 9': 8)
(G&e flow) (Nozzles)

PANICHKIN, I.A., doktor takhnichaskikh nauk.
-WW
Detached shock waves, [Trudyl XVTU no.67:35-76 '55. (xuu 9: 10)
(Sbock waves)

jj~ASZ I BOOK EXPIXTATION 351
Sinyarev., Gemadly Borisovich and Dobrovolleldy, MAislav VIGA4104 Ch
ZhidkortWe raketnyye dvigate3i; teoriya, I proyektiroveniye (Liquid Fropellut
Rocket Enidin s; Theory and Design) 2d ed.., rev. and enl. Moscow, Oborongiz.,
1957. 579 P. Number of copies printed not given.
Reviewer: Panichkin, I. A. Doctor Of Tecbnical Sciences, Professor; Ed.:
Sealc:O-dn, G. V., neer; Ed. of Publishing House: Petzow ) 1. A.p Tech.
Ed.: 7-udaldn, I. M.; Managing Ed.: Sokolov" A. 1.34ngineer
PURPME: This book was written as a textbook for tekhn'la- , but may also be
useful to students in institutions of higher learning and to workers
specializing in the field of raeket engineering.
COVERIWE: The basic textbook on.liquid proiellant rocket engines Is divided into
two parts. Part one is concerned with "Theory and Themodynamic Calcu-
lation of Liquid Propellant Rocket Engines" where fundamentals of Themo-
dynamics and Thermo~chemieal analysis of the propellant are extensively
Aet
presented. Part two deals with the "Design of Liquid Propell Hoe
Rngines." The authors describe fundamental theories of liquid propit1lant
Card 1/24 1

Liq~dd Propellant Rocket Engines (Cont.) 351
rocke. engines and the design of their basic components. They provide the a"-
essary date for the analyzing thrust and for determining the principal dimmions
of vv~Tlous accessories and assemblies of Uq~xid propellant rocket engines* kx-
=Wles of the application of calculation methods are given. The book covers dL
con.siderable number of subjects,'pertain1ing to rocket engine design and describes
scme equipmt. A number of scientists vho developed rocket propulsion in the USSR
are mentioned. Recent developMts 'in the atu&y of complex phenomena occuring in
Uquid propellant rocket engines have made necessary the revision of same old
concepts presented in the first 'edition of this book. As a result the nev edition
differs from the first in a number of chapters. Its extensive Table of Contents
gives a detailed review of the book. There are 45 references., all of them Soviet
(includ"n 10 translations).
TABLE OF
COMTWS: Preface to the Second Edition 3
Preface to the First EUtion 3
Card 2/24

Liquid Propellant Rocket Engines (Cont.) 351
PART 1. TM= AND THERKODYNAMIC CALCULATION OF LIQUID PROPELLANT ROCKET ENGIM
Ch. I. General Information on Reaction Ensd a 5
1. Liquid propellant rocket engines (zho). 5
2. Reaction forces 6
3. Thrust of a liquid propellant rocket engine, 9
Derivation of the thrust equation 9
Specific thrust 13
4. Reaction engine--an engine with a direct thrt*t 15
Rngln s with direct and indirect thrusts 15
Various types of direct thrust engines 15
Distinguishing characteristics of,rocket and jet angJaes 21
Conversion of energy in a rocket engine 25
5. Classification of Liquid Propellant Rocket Engines .26
Classification according to type of fuel 26
Classification according to method of campreosion and feed of
fuel components 28
Classification according to function 29
Card 3/24

Liquid Propellant Rocket Engines (Cont.)
351
6. Applications of the ZhRD
Interplanetary rockets and artificial earth setelites
Rockets for investigating the upper layers of the
atmosphere (meteorological rockets)
Long-range rockets
Defen4ive missiles with ZhRD
Aircraft liquid-rocket engines
The ZhBD in assisted take-off
7. Abrief historic At survey of liquid propellimt rocket
en ne develoluent
dh. fl. Pert1hent information on Thermodynamics
8. Basic properties of gases
9. .Energy characteristics of gases
Internal. energy and heat content of gases
Chemical energy and total heat content
10. Thermodynamic processes in gases
Changes in the parameters of the state of a gas in
polytropic processes
Work performed in thermodynamic processes
29
29
33
36
41
42
46
r5
65
66
6T
73
74
76
7T
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Liquid Propellant Rocket Engines (Cont.)
351
Aliplication of the first 1w of thermodyneadcwtD processes
III gases
Conversion of energy in polytropie processes
Adisbatic process . -
3-1. Second law of thermodyneatics
Definition of the law
Entropy
Entropy and the probabillty of the state of a gas
Reversibility in theimodYnamic processes
.Calculating the nmerical value of entropy
12'. Thermodynamic processes in chemically active gases
Dissociation of ccmbustion products
Reversibi1ity of chemical reactions
Chemical equilibrium in a gas mixture
Equilibrium constant of a chemical reaction
Effect of temperature and pressure on the composition
.of ccWbustion-products
Card 5/ 24
78
80
81
62
82
83
85
85
87
89
89
90
91
93
9T

Liquid Propellant Rocket Engines (Cont.) 351
13. Balanced and unbalanced expansion of combustion products 98
Balanced expansion 98
Unbalanced expansion 100
Ch, III. Pertinent Information on Gas Dynamics 102
14. Basic.aaws of gas motion 102
Equation of the conservation of 8 102
gq~ation of the conservation of energy 103
15. Speed of sound in a gas 106
Speed of sound 106
Derivation of the formula for computing the speed
of sound 1^9
Ob
Speed of sound in a reactive gas in
Dependence of the speed of sound on temperature in
Speed of soundIn a moving gas L12
Maxium speed of sound U3
16. Critical speed of gas flow and special properties of
supersonic flow 3.14
Critical speed 124
Mach nimber 3.15
Concept of shock vaves 116
card 6/24

Liquid Propellant Rocket Engines (Cont.) 351
Braking temperature 117
17s Blememta;7 theory of supersonic nozzles 118
Shape of a supersonic nozzle 118
Critical drop of pressure 120
Relation between the dimensi&s of the critical section
of the nozzle and the parameters of the gas at the
nozzle intake 121
Changes in the pareaeters of the gas flow along the length
of the nozzle 123
Ch. IV. Thermodynamic Cycle of a Liquid Propellant Rocket
engine 128
18. Cycle of a liquid propellant rocket engine 128
Ideal cycle 128
Relation between the ideal cycle and the actual processes 130
- Relation between the work of.the cycle and the specific
thrust 132
19. Efficiencies of a rocket engine 133
Cycle efficiency 133
card 7/24
Liquid Propellant Rocket Engines (Cont.) 351
Combustion efficiency 134
Expansion efficiency 135
Determining the amount of working substance expenUd on
op3ration of the fuel-feed system 13Z
Energy and impilBe efficiencies 13
20. Therma.3 efficiency of the ideal cycle 13T
Swivation of the equation for thermal efficiency of the
ideal cycle 137
Thermal efficiency of the engine cycle under design
operating conditions (Complete eiamsion) 139
21. Underexpansion and overexpansion In the
(non-design conditions) 141
Possibility-. of non-desiga c6nditions occurring in
the ~pgine 141
Occurx=e of non-desiga conditions with a change in
operating altitude 142
Occurrence of non.design conditions with a change,in
thrust 143
Possibility of the odourrence of overexpansion 145

Liquid Propellant Rocket Ragines (Cont.)
351
F,,2. Thermal efficiency of a ZhRD vith a constant nozzle und r
non-design 4perating conditio-na 146
Work losses under non-deg3ign operating conditions 146
Change in the.thermal efficiency of the engine with
a constant nozzle during-change in the degree of
possible expansion 148
23. Regulation of nozzle ares, 149
Regulation of nozzle area vith a -ghange Ii-Utituds 3.49
RegW*Ion of nozzle area with a chmp in thrust
produded 'by. a change in fuel conewption 150
24. Characteristics of the 7-hrd 151
Conewotion characteristics 152
Altitude characteristics 154
Ch. V. PropeLlants for Liquid Propellant Rocket 158
255. Requirements of propellants 159
Basic requirementa.of propellapts 159
Design requirements of propellants 3.65
Operational requirements of.propellwts :L67
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Liquid Propellant Rockert RnIdn o, (Colit.)
w --- %.
351
26. Thersochesical Characteristics of ftels, Oxidizers and
Propellants 168
Weight ratio of fuel and oxidizer IM
Theoretical necessary emouat of oxidizer 171
Coefficleat of exdegs oxidizer 175
Casymition, of propellant by weight 176
27. Heat content of propellairt and combustion products 177
substance
PhYsical heat content of & 1TT
.
Chemical energy and heat of formation 178
Methods'Of computing total heat content 182
Calculation of total hee. content of propellants
,
,
oaddizers and fuels 185
Total beat content of propellant combustion products :L89
R61ation between total heat content and calorific
value ofa propellant 190
28. Propellants based on nitric acid. and other oxygen
compounds of nitrogen 200
Nitric acid 2D0
Additives to nitric acid 201
Tetranitromethane as an arLd:Lzer,, 202
Propellant fuels boned on nitric acid and self-1piting
propellants 202
Card 10/ 24

-Liquid Propellant Rocket Engines (Cont.)
351
29. Propellants based on liquid oxygen and hydrogen peroxide 2C4
Liquid oxygen 204
Propellant fuels based on liquid oxygen 205
Hydrogen peroxide W6
Basic propellants of ZhRD based on hydrogen peroxide 2"
Ur-ie of hydrogen peroxide for the production of stem& 2bB
30- Possible ZhM propellimts 209
Propellants with increased heat producing capacity and
a high specific veight 209
Propellants possessing better thermodynamic properties
Of combustion products 214
Possibilities arising from the use of atcatie power
in rocket engines 215
Cho VI. Thermodynamic Calculation of the Combustion Chamber 224
31. Detenoination of the composition Of Combustion Products
of a simWle propellant 224
Evolving a system of equationsfor datexuining the
composition of combustion products at a given teoersture ee4
Card 12/24
Liquid Propellant Rocket Engines (Cont.)
351
Solving the system of equations for determining the
composition of combustion products 226
Effect of pressure and temperature on the composition of
combustion products 229
32. Evolving a system of equations for determing the
composition and temperature of combustion prodacts in the
engine eb er 230
SetVing up equations for the reactions of dissociation 231
Setting up equations for the equilibrium of elements 234
Suplementary equations for 'determining the composition
and temperature of combustion products 235
Final aspect and solution of the equation system 2
33. Solving a systen of equations for determining the
composition of combustion products of propelleAs not
containing nitrogen 24o
A system of equations for determining the composition
of combustion prodacts 21%0
Sequence in solving a oyotem of equationa for deterMlUiUg
the camposition'of cocibustion products 241
34- Solving a system of equations for determining the
-P -1--tion. -Droducts of propellants containing

Liquid. Propellant Rocket Engines (Cont.) 351
A system of equations for determining the composition of
..combustion products 244
Reducing the obtained equation system to working formajae 2k7
Sequence in solving the system of equations for determining
the composition of embuBtion products 249
ThexuodYnmic caculation. of the combustion ch er 252
32. Determining the composition and temperature of
combustion products in.the coOuation ch ar (nozzle Inlet) 252
Determining the entropy of emibustion. pro&wto in the
ccmbfistion. cb er 253
Analysis of the composition and temperstgre of combustion
products at the nozzle exit 255
Dotermining the total heat content 'of combustion products
st,the exit, ands the theoretical'exhawt velocity 257
Determining theoretical specific thrust, the isentropic
exponent of.'expansi.on, and the nozzle dimensions 257
Thermodynamic calculation of a Zhrd as based on a
Wat/entropy diagrem 259
36. Effect of temperature and pressure in the combustion
chembei and ratio of propeLUnt,components on the parameters
Cag 13 M2- 261

Li(rAa Propellant Rocket Engines (cont.) 351
Effect of temperature 261
Effect of pressure in the combustion.,chamber 262
Effect of propellant componeubs, ratio 265
37- EXperimental, coefficients of an engine and ana3,ysis
of actual specific thrust 266
Spedific-thrudt coefficient
Experimental ditermiuation of chamber and nozzle
ccefficients 267.,
Heat analysi.9 of the engine vith consideration for
experimedtal coefficients 270
38. Examples of combustion and exhwat ana37sis 271
Theinodynamic calculation of a ZhRD using nitrogen;-
containing fuels 2TI
Analysis of the composition of combustion products
of a fuel not containing nitrogen 287
Ch.- VII. Cooling of the ZhRD 292
39. Basic principles from a courie in heat transfer 292
Heat transfer -292
Heat transfe~r byconduction
Heat transier by convection 294
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Liquid Propellan -Rocket Engines (Cont.) 351
Formulm for calculating the heat transfer coefficient
Heat transfer by radiation'
Heat transfer by radiation in gases
40. Heat transfer in the ZWW
Physical picture of the beat transfer process in the ZhRD
Characteristics of heat transfer in the ZhRD
Dependence of fwau temperature on gas side7on the
Ti.
circulation rate of the coolant liquid
Effect of surface boiling of the coolant liquid on the
value of Tg,,.
Dependence of Tg... on the beat conductivity of the
chamber vall
.Del>indenze of T on the, thickness of the
chmber vall
.Rrfect of pressure in the ecobustion chamber on the
value of Tg.s. and 6E L-overall heat flogw-
Effeet.of temperature in the combustion chamber on the
value of Tg.s.
Uard 15/24
Liquid Propellant Rocket Engines (Cont.)
41.
42.
351
Effect of 'engine operating conditions on Tgs.
Analysis of external cooling
External cooling systems
Sequence in the analysis of,external cooling of the
engine chamber
Determining the convective specific heat flow in the
chember vall 1
Determining the radiant specific heat flc%r and the
overall heat flow *in the chamber vall
Checking for the r6quired amount of coolant liquid and
Determining its heating in each sector
Determining the coefficient of heat transfer from the
liquid-coolant wall. to the coolant -liquid CK
Determi*ng the temperature of the Uquid coolant wall
Checking.,t.he-conformity be.tween the assumed and bcmputed
%.s*
Shapes of coolin,9 chann I in the engine chamber
Annular channels
296
300
303
304
305
305
307
308
308
309
309
310
310
311
311
141 q
314
319
320
322.
w
323

Idquid Propellant Rocket Engines (Cont.) 351
Helical channels 324
43. Example of external cooling analysis of the engine
chamber 326
44. Other methods of cooling the 33T
Internal cooling 337
Combed cooling 342
Protecting chamber walls against burn-out by means of
lining or by heat accumulation 342
PART n. LIQUID ROCKET ENGINE DESIGN
Ch. VIII. Enidne Chamber Design 348
45- Combustion process in a ZM coebustion chamber 348
Special features of the ecebustion process in the ZhRD 348
Diagram of the combustion process 350
46. Determining the volume of the ZbRD combustion chaber 351
Deteniining the volume of-the combustion chamber
according to the length of time the propellant remains in it 351
Determining.the vol=e of -the ccabustian. cbmaber according
Card 02oreduced 'Length of chamber 35~

Uquid, Propellant Rocket Engines (Cont.):
Determining the volume of the ccubustion chamber
according to the-heat Liberation per unit volume of
combustion space
Determining the volume of the ccmbustion chamber
according to the liter thrust
47. Combustion chamber shapes
Spherical . chEdbers
Cylindrical chambers
Conical chwnbers
48. Design of the expansion nozzle
Basic requirements in nozzle design
Lo5ses in the nozzle an& meen
of reducing them
Analysis of geometrical Almen ions of various types
of nozzles
Injectors for atomizing propellants
Jet injectors
.,?Design of injectors
Centrifugal injectors
Movement of liquid through the centrifugal injector
Design-of centrifugal injectors
50. Fuel mixing in the ZhRD, and design of combustion
chamber heads
Cara 18/24
351
354
355
356
356
361
366
366
366
ZIP
3bI
370
3Tl
373
374
376-
377
380
381

Liquid Propellant Rocket Engines (Cont.) 351
The mixing process and its requirements 381
Types of ZhRD chamber heads _2
Arrangement of injectors and other devices in the
chamber head
Sequence in the design of heads 388
51. General pmblms in engiAe chanber design 10
Materials'psed,in chowber construction 39.0
Operating con4tifts affecting the material of the
chamber walls 392
Some remarks on cb er design 394
.
Examples of sequence in chamber design .loll
J7~

52- Starting and stopping ~he ZhRD OR
Basic requirements in starting and stopping the ZM 395
Classification of the ZbM according to mode of
operation * 395
Ignition methods 39T
Stopping the engine .398
Vibratory combustion in the ZhHD 399
Card 19/24
Liquid.Propellant Rocket Engines (Cont.) 351
Ch. IX. Feed Systems in Liquid Propellant Rocket Engines 404
53- Feed system types 404
Bake elements of the feed system 404
Punp,feed system 405
Pressure tank and other e-xpellant feed systems 406
Design of tFwk 407
Types of tanks and their requirements 40T
Gecaetrie shape of'tanks and their arrangement
Internal mechanism of tanks 43.1'
Calculation-of-tank volume 413
-Calculation of tanks for strength 416
Materials requirements of trwic 41T
55, Calculation of pressure-tank dimendions and aw,suwp4
in the pressure-feem system. 419*.
Temperature variation of the ccmpressed gas in the
process of feeding 420
Calculation of pressure-tank volume and gas sunly 421
Calculation of ~ressure-tanks for strength 423
Selection of initial pressure 424

Liquid Propellent Rocket Engines (Cont.) 351
56. Analysis of solid and liquid pressurization gas Renerstors .426
Properties of solid propellan a used in the PAR Tiolid
P%Wellant Gas Generator). - 426
Suipercritical and'ouberitical PAD 428
Desigoin the PAM~ 430
Pla for starting 433
Deisigning the liquId gas-generator 434
57. Pressure reducing valves 436
Design and .operation of the reducing valve 436
Inverse-act reducing valves !'37
Characteristics of the Invirse-action rednew 438
DIrect-sition redualng valves
i 443
ect-action rebming T&1V*
ChariwterlsVieB of the d1r 445
Sequence in the design of reducing.valves 446
Deteruining throttling SeAl:on a4iM JOW 447
Determi Ti4mg spring tension q, and Qp md the, memibrane
surface aris, rm 448
449
Card 21/24

Liquid Prope llant Rocket Engines (Cont.) 351
58. Mtample.or TO~hwing val*e design analysis 449
59- PWW8 for feeding of, propellant components 451
Diagram of a-, centrifugaL pump and its basic,
.-characteristics. Specific speed 451
Velocity diagram atAMpelle'r intake.. and, position
of the Mad s 454
Velocity diagram at impeller outlet 459
Theoretical heaA developed by the Via 461
Hydraulic losses and hydraulic effl6itney 463
Power and efficiency of the p=T 466
6o. cavitation and selecting the r3pm of the pmp 467
The Thenamenon of cavitation 467
for cavitation prisaure of the -Uqu:Ld at
Design of a
-
the'intake ofthe tentrifugal pmp, and detexmd*ng the
necessary pressure in theitank 473
61. Design of punps used in the ZbM 478
Sequence in centrifugal paup,design 478
Ex=Wle of centrifugal pmp design 487
Design of gear pumps 493
62. Turbines, Uxbopump assemblies, and stem-gas
generators for the ZhW 495
Card'22/ 24

Liquid Propellant Rocket Engines (Cont.) 351
Single-stage impulse turbine 495
Impulse turbine with two velocity stages 498
Turbopump.- unit of the A-4 rocket engine 499
units for aircraft ZhRD
Turbopump 501
-
P = s for the R-3395 and R-3390 engines 5o6
Steam-gas generators of the ZbRD 512
Sequence in the design of a turbo-p=y unit and of a
steam gas generator 523
63- Elements of the ZhRD feed system 525
Tank-elements 526
Cutoff and reverse valves 527
Other elements 530
Determin~tion of hydraulic losses in the ZbR1) feed system 533
Determination of hydraulic losses in the cooling circuit
of the engine chamber 533
Deterbduation of hydraulic losses in the conduits and
fittings 537
Ch. X. Description of Systems of Some Existing Liquid.
Rocket Engines_ 541
65. Di of the A-4 rocket engine
= 541
Re
g the engine for starting 542
Card 23/24

Liquid Propellant Rocket Engines (Cont.) 351
$tarting the engine and its entry into the niain stage 544
In-flight operation and stopping the engine 545
66. Engine diagrams of some defensive missiles 546
The "WasserfalV' engine. 546
The "Schmetterling!' engine 548
The "Tayfunifunguided defensive missile 550
67. Diagrams of aircraft rocket engines for various purposes 550
The "Walter" engine 550
An aircraft superperformance engine 55g
A flying-bomb engine 55
The "AhTnIMing' ejigine 557
The assisted take-off unit "Super Sprite" 557
Appendixes:
1. Tabled of ammon logarithms of equilibrium constants 560
2. Equilibrium constants 564
3. Total heat content of combustion'products of ZhHD propellants 566
4. Table of entropies of embustion products orMD'propellants 568
Bibliography 570,
Rectumended references 571
AV&LABLE:Libraxy of Congress
Card 24/24
IS/gMp
8-20-58

L 25586-66 EWT (I )IEVIP (,M)/EWA (d )IFWA (h)/ETC (m)-6/1FWA (I Jr~TAij
C/o
_~_ACCAR#. A146007342 Monograph UR/
P,,nichkin, Ivan Aleksandrovich; L
Zakhov, Andrey Borisovich
Privexjes of gas dXnamics and its application to the supersonic wind
tunnels Psnovy gazovoy dinamiki i ikh.prilozheniye k raschetu averkhzvul:ovykh
aerodinamicheskikh trub) Kiev, Izd-vo Kievsk. univ., 1965. 150 p. illus., biblia
3600 copies printed.
TOPIC TAOS: aerodynamics, gas dynamics, shock waveo oblique shock wave, s per-.
sonic wind tunnel, shock wave reflection, velocity measuring instrument
:'PURPOSE AND COVERAGE: This book is intended for engineers engaged in the field
of high-speed aerodynamics and also for senior students irL schools of higher
It' contains __ an- account of th(,, theory of one-dimensional, steady
ion of t is t eory-- _t e-de i n-of-ga.s dy-
mot o -
i n of an ideal gas and applicat .1~ h tq
namic proper,ites of supersonic wind tunniels. It presents a more detailed treat-'
nt of the gas dynamic problems related to wind tunnels than is found iri* the
me
known textbooks on gas dynamics. It is divided into three main'sections dealing
with the theoretical aspects of gas motionj the gas dynamics of supersonic wind
tunnels, and calculations of gas dynamic characteristics of the letter.
Card 1/3

25586-66
ACC VR: Am6007342
TABLV. OF CONTENTS: jabridged]
ion of an ideal gas*
Section 1. One-Dimensional mot
Introduction 3
Equation of motion 5
7
-tion of continuity
2.: Equa
10
lations
3. Basic thermodynamic re
4. Equation of energy -- 12
15
5. Speed of sound
f the energy equation 20
6. Different forms 0 r
7. Equation of isentropic gas floW 25:
8. Specific flow rate -- 28
9. Geometric representation Of the,pressure versus velocity relation 31
10. Flow of gas from a reservoir 32
11. Nozzles -.- 34
39
12. Straight shocks
13. Oblique shocks 48
14. The shock volar 64
34
Card 2/3

--- -------
25586-66
ACC HR-.* AM6007342
15. Entropy jump -- 70
16. Reflection of-oblique shocks 77
waves in a nozzl6 -- 81
18.1 Shock waves in an Ideal gas with heat supply 88
19. Measurement of flow velocities -- 90

Section II. Gas Dynamics of Supersonic Wind Tunnels

Introduction 98
-- 1'. Basic--coinponents- of a -wind -tunnel 98
-26 Classificalton of wind tunnels 104 7

ation of gas dynamic characteristics,of supersonic.wind
3. Calcul nnels 114,
tu
Biblio raphy 140
9
Appendix
~UB CODE: !"20/ SIJBM DATEI IlNov65/ ORIG REFt- 004/, OTH REF-. 001/
Card 3/3JL

ORLOV, Boris Viktorovich, doktor tekbn. muk prof.; MAZING,
Georgiy Yurlyevich, kcand. tekhn. nZko date.; PANICER1,
.I-,A.t doktor tekbn. naukp retsenzent; SIMXKW, G.G.p
doktor tekhn. naukp retsenzent; GOROKHOV, M.S., doktor
tekhn. nauk., retsenzent; KOTELINIKOV,, A.V.p kand. tekhn.
nauk., red.
[Thermodynamic and 'ballistic bases for the design of
solid-propellant rocket engIneo] Termodidibicheskie i bal-
listichaskie 6snovy proaktirovaniia raketnykh dvigatelei
na tverdom toplive. Moskva., Masbinostroenia., 1964. 406 p.
(MIRA 17:11)

ANTS7711ROV, U.S., kand.fiz.-mat.nauk; VULZOVIGHO H,F46 prof., doktor
tekhn.nauk, laureat Leninskoy premii; KRIFETS, B.S., inzh.;
LAZA V, L.P., prof., doktor tekhn.nauk; KAZYRIN, I.V., inzh.;
NIXITIN, N.H., kand.fiz.-mat.nsuk; OCHKIN, A.V., inzh.; FANIGHKIffo
14--prof.. doktor tekhn.nauk; PETUEHOV, B.S., prof.,--d-6EEor
'takhn.nauk; PODVIDZ, L.G., Imnd.tekhn.nauk; SIHONOV, A.F.p.inzho;
SHIRYAGIN, A.P.0 kand.tekhn.neuk; TOKMAKOV, G.A.,,ksnd.tekhn.nauk;
PAYNMIBER, B.H., prof., doktor tekhn.nauk; XMIM, G.P., kaa.
tekha.nauk; CHESICONKO, T.F., kand.takhn.nauk; TANIMIN, B.I.,
kand.tekhn.nauk; AORV-WA , H.S., prof., doktor tekhn.nauk, red.;
KMYAVTSU, V,A., prof., doktor tekhn.nauk, red.; PONOMAIMV,
S.D., prof., doktor tekhn.nauk, laureat Leninskoy premii;-.red~;'6ATZ',
S.A., prof., doktor tekhn.nauk, red.; S3MSER, S.Y., akademik, red$;
RESMOV, D.N., prof., doktor telchn.nauk, red.; WGANOV, V.G.,
inzh., red.grafichaskikh materialov; GILOIGIMLUG, M.I., red.izd-va;
=OLOVA, T.F., tekhn.red.
(Manuel of a mechanical engineer in nix volumes] Spravochnik me-
shinostroitelia v shesti tomakh. Red.sovet N.S.Acharken i dr.
Izd.3., ispr. i dop. Moskva, Gos.nauchno--takhn.izd-vo mashino-
stroit.lit-r.y. Vol.2. 1960. 740 p. (MIRA 14:1)
1, AN USSR (for Serensen).
(Mechanical engineering) (Machinery-Construction)

GUTTSAYT, Z.I.; KRAVCHMO. V.A.; NIKITIN, N.S.; PANICHEVI, A.G. Prini-
Mali uchastiye: GOLIDSED3YU, R.I.; RAI~OV~AO.-H-.T--SAMEMAYA.
V.G. KORYAGIN, I.D., kand.ekonom.nauk, red.
(Petroleum industry of the capitalist countries of Western
Europe, the Near, Middle, and Far Za5t, Canada, and Latin
America] Neftiansia promyshlennosti knpitalisticheskikh stran
Zapadnoi Evropy, Blizhnego i Srednego VOBtoka, Dallnego Vostoka,
Kanady i Latinskoi Ameriki; kratkii obzor statiatichaskikh danaykh.
Pod red. I.D.Koriagina. Moskva, 1959. 302 p.
(MIRAI 13:11)
1. Moscow. Gosudarstvennyy nauchno-itsoledovateliskiy in5titut
nauchnoy i tokhnicheakoy informataii.
(Petroleum industry)

PANICHKIN9 I -A-
-- ... Soluti-on,'of a pwetial differential equation- L-ruu,,, -'--
no..88:103-107 158. ~(mm 12:4)
(Differential equations, Partial)

10(2)P'2 (1); 29(l) PHASE I BOOK EXPLOITATION sov/1603
Moscow. Vyssheye tekhnicheskoye uchilishche imeni Baumana
Nekotoryye voprosy mekhaniki; sbornik statey (Some Problems
in Mechanics; Collection of Articles) Moscow, Oborongiz,
1958- 197 p. (Series: Its [Trudy] vyp. 88) Number of
copies printed not give7n-.
Ed. (Title page): V.I. Feodoslyev, Doctor of Technical Sciences,
Professor; Ed. (Inside book): A.S* Ginevskiy, Candidate of
Technical Sciences; Ed. of Publishing House: L. Ye Serebrennik;
Tech* Ed.: L.A. Garnukhtna; Managing Ed.: A.S. Zaymovske,ya.,
Engineer.
PURPOSE: This collection is Intended for scientific workers,
Aspirants and students of advanced courses who are interested
in problems of aero- and gas dynamics and in the theory of
directional control of aircraft.
COVERAGE: The collection contains reports on various problems
I a 1i d mechanics. A large portion of the articles is
Card 1 8

Some Problems in Mechanics (Cont.) SOV11603
devoted to aerodynamic and gas dynamic investigations. In
the first article of the collection, the author, Professor
K.P. Stanyukovich, considers the laws of motion of a gas-drop-
let medium- in particular, the laws of motion of a mechanical
mixture of a liquid and a gas with liberation of energy. His
conclusions are applicable to the investigation of the motion
of a burning fluid jet, The two reports by N.F, Krasnov
deal with the aerodynamics of bodies of revolution. In the
first, he develops briefly the method of characteristics as
applied to the calculation of nonsymmetrical flow about bodies
of revolution. In his second report., which treats the base
drag of bodies of revolution moving at both subsonic and
supersonic speeds, he presents an approximate formula derived
for the calculation of the base-drag coefficient In the case
of turbulent flow about a body at supersonic speed. V. F.
Mikhaylina presents in her report the approximate formulas
she obtained for determining the distance between an isolated
compression shook and the vertex of a blunt-nosed body of
arbitrary form in supersonic flow, and also for determining
the velocity and pressure nearthe critical point. Professor
Panichkin presents in his report the partial and general so-
lutions of the differential equation used in the investigation
Card 2/8

Some Problems in Mechanics (Cont.) SOV/1603
of the flow about bodies of revolution at high subsonic
speeds. Kovalev's article is concerned with the investi,.
gation of the damping moment associated with the banking of
an aerodynamic surface in a supersonic gas flow. He proposes
a method for calculating an arbitrary damping moment for
wings of rectangular, triangular, and trapezoidal forms.
Yesiyev's article is concerned with the damping moment pro-
duced by the gas flow from a jet engine nozzle opposing the
rotation of the vehicle (if the axis of rotation is not
parallel to the nozzle axis). Pobedonostsev and Stanyukovich
investigate in their article the problem of optimum ratios
of the stages of a multistage rocket. In another report,
Stanyukovich generalizes Tsiolkovskiy's ratio in the re-,
lativistic sense. The last three articles of the collection
are devoted to problems of directional control of aircraft
and the theory of automatic control. Shumilov investigates
an unsealed control mechanism with cam transmission. Samoylov
considers another variety of a control mechanism based on the
use of a so-called stream tube. In the last report,
Card 3/8

Some Problems in Mechanics (Cont.) sov11603
MimgLavlev investigates the motion characteristics of one.
of the automatic control systems used, especially in air-
craft and in ship's steering gears.
TABLE OF CONTENTS:
Preface 3
Stanyukovich, K.P., Doctor of Physical and Mathematical
Sciences, Professor. Some Problems of the Aerodynamics
of a Fluid Jet in Free Flight 5
1. Motion of a jet in a vacuum 5
2. Some remarks on the motion of a jet in a re-
sisting medium 12
3. Basic laws of motion of a gas in the presence
of internal energy sources 21
4. Basic laws of motion of a mechanical mixture
of a liquid and a gas 35
5. Basic laws of motion of a mechanical mixture
of a liquid and a gas with liberation of energy 47
Card 4/8

Some Problems in Mechanics (Cont.) SOV/1603
Krasnov, N.F., Candidate of Technical Sciences, Docent. On the
Method of Characteristics and Its Aplication to
the Calculation of the Pressure Distribution About Pointed
Bodies of Revolution Moving at Supersonic Speed.at an
Angle of Attack 55
1. Accepted symbols 55
2. Characteristic equation 56
3. Conditions of conformity 60
4. Calculation of the flow about a body of
revolution at an angle of attack 67
Mikhaylina, V.F., Engineer. A BLunt-nosed Body of
Revolution With an Arbitrary Generatrix in Supersonic
Flow 76
1. Determination of the distance between the
compression shock and the body in a flow 76
2. Velocity and pressure distribution along the
surface of the body of revolution near the
critical point 90
Card 5/8

Some Problems in Mechanics (Cont.) SOV11603
Krasnov, N.F., Candidate of Technical Sciences, Docent.
On the Problem of Base.Drag of Bodies of Revolution 95
1. Accepted symbols 95
2. Base drag at subsonic speeds 9
3* Base drag at supersonic speeds 97
Panicgijn._j_,,A.., Doctor of Technical Sciences,,
Professor. Solution of a Differential Equation With
Partial Derivatives 103
Kovalev, Ya. G., Candidate of Physical and Mathe-
matical Sciences,, Docent.' Damping Moment in Roll
of a Wing Area in a Supersonic Gas Flow 108
1. Statement of the problem 108
2. Distribution of the pressure differences
along a triangular wing which performs '
rolling motion 109
3., Damping moment in roll of a triangular wing 114
4. Damping moment in roll of a rectangular wing n6
5. Damping moment in roll of a trianguldr and
trapezoidal wing in inverse flow 119
Card 6/8

Some Problems in Mechanics (Cont.) SOV/1603
Yesiyev, M.K., Engineer. On the Problem of Determining
the Gas Dynamic Damping Moment 121
1. Description of the test setup 123
2. Sequence of the test procedure 135
Pob&donostsev, Yu. A., Doctor of Technical Sciences,
and K, P. Stanyukovich, Doctor of Physical and Mathe-
matical Sciences, Professor. On the Calculation of the
Optimum Ratio of the Stages of a Multistage Rocket 144
Stanyukovich, K.P,, Doctor of Physical and Mathematical
Sciences, Professor. Relativistic Generalization of
Tsiolskovskiyls Formula 156
Shumilov, I.M., Candidate of Technical Sciences. Un-
sealed Pneumatic Control Mechanism With Cam Distri-
bution 162
1. Basic system of differential equations 162
2. Initial conditions 165
Card 7/8

Some Froblems in Mechanics (Cont.) SDV/1603
3, Motions for small displacements and
pressure drops 168
4. Analysis of thb effect of leakage 172
5. Control mechanism with additional inputs 176
Samoylov, V. Ye., CazjAidate of Tebhnical Sciences.
Stability of an Electrop4eumatic Servomechanism 179
1. Equ&ti on - of .:koti orl- 6f '.4 sex-voMbehahism. 180
2. On the.effect..of~'.friction on the stability
of a servomechanism 182
3. Effect of the pa.rameters of a servo-
mechanism on its stability 182
4. Stability of a mechanism taking into account
the nonlinearity of the characteristics of
the amplifier and relay 186
5. Amplification factor of a sermechanism 192
Miroslavlov, Ye. N., Candidate of Physical and
Mathematical Sciences. On the Problem of the
Stability of a Nonlinear System 193
AVAILABLE: Library of Congress
Wrg

Card 8/8 6- "
9

RAKM,'A'-PULD*, Khalil Akhiwdovl-h-~ Ar-"Lr YS-ko-,r-L$-IviChz
~6,1,ljj~--()VTCH, Abrar- ZVERM!, luor' Nikolavevich.
PUTYATE, V- I, , dots, re-,3~-nzerjtl?, F-'Of.
re-tsenzent.5 G11.E-VSKILY, AS,., kano, tekiin. nauk,, red.
[Gas dynamics] Gazovala Mosir.-vil, Vy.,3shuia shkolftl*
1965. '122 p. (111RA 19:10)

UTKINAf N.; PANICHKIN, Yu.
.4~~
Eciampsia in the first half of pregancy in partial hydatid mole.
Zdrav.Bel. 7 no-11:55-56 N 161. (MIFLA 15:11)
1. Iz Pogost-Zagoroaslcoy uchaetkovoy bollnitsy (glavnyy vrach
S.P,Loginov).
(FIJERPERAL CONVUISIONS) (PPMNANGY, YDLAR)

SKOROKHODO
Electric conductivity of porous aintered materials rada of
fiber. Porosh, met. 5 no.308-61 Mr 165.
(MIRA 18:5)
1. hatitut problem materialovedeniya AN UkrSSR.

FANICHKIN, S.Ye.; IONATOV, U.N.; RLRASOV, T.M.
Now developments In the processing of fine tableware. StekA ker.
13 no.6:24-23 Je 156. (MM 9:8)
(Grinding and polAshing) (Pottery) I

PANICHKINA, E. (Rharlkov)
.. I-!, - ---
Acetylene from a spark. Izobr. i rats. no.12:3 163.
(WRA 17:2)
1. Spets'ialinyy korrespondent, zhurnala "Izobretatell i
ratsionalizator".

PANICHKIIIA, E. (Miar Ikov)
Acetylene from a spark. Izobr. i rats. no.121.3 163.
(MIRA 17:2)
1. SpetsialInyy korrespondent zhurnala, "Izobretatell i
ratsionalizator".

RAUTEISHMYNt Ya.I.; KLL?PIKOVA,,F.S.; ZHUNMVA, V.V.~ PANICBKINA,, T.B.
Cbaracteristies of the lysogenic culture of Actinamyces
spheroides strain 35 producing novobiocin and its temperate
actinophage. Mikrobiologiia 34 no&5;828-834 S-0 165-
(MIRA 18:10)
1. Vessayuznyy nauchnorisaledovatel'skly institut antibiotikov
Ministerstva zdravookhraneniya SSSRj, i Institut mikrobiologii
AN SSSR*

PANICHKINA, V.V.; UVAPOVA, I.V.
Determining the specific slurface of finely disFers--,~ --;cIrel
an& hungsten pawders. Forosh. met. A, no.9:10-22 S 165.
(MITU, 1,0'.. 9)
Institut problem Tnaterelovedeniya All TJIrFSR.

kIDR=SKIY, R.A., kand.telchn.naul.-I PANICH~A,_V.V,, inzh.;
FEDORCHEIIKO I.M.0 akademik
p
Sintering of ceramic metal iron in hydrogen with small additions
of hydrogen chloride. Metalloved. i term. obr. met. no.7:1+8-52
Jl 161, (MIRA 14:6,,
1. Inatitut metallokeramiki i spetsiallnykh splavov AN USSR.
2. AN USSR (for Fedorchenko).
(Sintering)
(ceramic metals)

ACC NR- AP7006397 SOURCE COD.H: Ull/0226/67/000/002/0001/0005
AUTHOR: Pani,~Wna.,_V_.-
ORG: Institute of the Problems of the Science of Materials (Institut
problem materialovedeniya AN UkrSSR)
TITLE: On the activated sintering of tungsten-with small additions of
nickel
SOURCE: Poroshkovaya metallurgiya, no. 2, 1967, 1-5
:TOPIC TAGS: Dowder metal, Dowder metal sintering, tungsten
.;.=nickel alloy, /72,c7,)4,
ABSTRACT. Compacted specimens of tungsten with snall (up to 0.5107)
additions of nickel, pre-pared by nechanical mixing of tunpsten and
nickel Dowders with sebsequent reduction of nickel with addition of
5 vol'o" ethyl alcohol, or by vacuum impregnation of presintered -oure
';tungsten with an agueous solution of nickel nitrate and subsequent
1i annealing in a hydrogen atmosphere at 6000C for 2 hr, were sin-tered i n,
!a hydrogen atmosphere at a tem-aerature of uD to 12000C. Comnacted
sDecimens from mixed mowders had a porosity of 40- 41%., while the
;impregnated specimen'; porosity was 385. The porosity re-mained
lunchanged vita sintering at temperatures'below 9000C, but decreased
Card 1/2 UDC: none

A-CC-NR:- Xffff6~97
~with sintering at �50- 12000C. Sintered specimens with 0.25 and 0-5,0j
e, regardless of the method of DreDaring the
iNi had a porosity of 13j,
comDacts. However, the inpregnated specimens exhibited a higher rate
of shrinkage than the specimens from mixed Dowders. In all investigeted
s-oecimens the grain boundaries had a thin layer of a solid solution
of tungsten in nickel with the highest tungsten content possible for
solid solution. Thus, it can be concluded that at 12000C, nickel
ienergetically.diffuses along the surface of tungsten particles and
ialong grain boundaries, while tun-gsten penetrates into nickel. The
combined process appears to result in the formation of the second phase,
la saturated solid solution of t4ngs~en in nickel. A significant
decrease in the sintering temperature and a higher shrinkage rate in
sintering tungsten with nickei can be ascribed to an increasing number
!of defects in the base-metal (tungsten) structure, possibly caused by
;preferencial di-ffusion of tungsten into nickel. In any case, the
;.mechanism of activated sintering of tungsten cannot be explained by
diffusion processes and requires further research. I.' Ya. Dzykovic
and G. 111. Gordmdn (IES im. Ye. 0. Paton) participated in the*work.
Orig. art. has: 5 figures.
L MS
SUB CODE: 1l/ SUB*.14 DATE: l4jul60"
Card 2 /2

, C~.4- - 414 +,-'i
~ri+A
Mill

S/129AZ/000/007/013/016
YO'3/E535
AUTHORSI, Andrivc,vsk--y-, R A I Candidf~ti~ of Techiiical Sciencoa,
pall.1 ~, hk ~ na V V- Floolls~i~i qnd F(tdol-vthvnko,, 1,M--
--L -- - "',- S. S I Z
I a
T I TLE S-1 111 r-,Q; Wycl cogan wi th
Addi~l~~Tl~!
PERIODICAL'. teririch,~slraya obrabotka metallov,
1961, pp.k8 'S2
TLXTI- Daia- or ~h~- metheds of
activated st -,, -tn th,~- vreperties -af- slnte--i~d
Lnr~iqui-llzes and &lso On th~I,.-, surfact i's) and carbon
content fArr. qxicit~d cf authors ~Refl,
inciallev No.,12, 3-96o i
lt was I.,ound th~.-r hydrog-m chloride intc the
sinter.Lng 'Itmosiln'CrIl, rli.4~ ;n,7--5x f.---vourable influence on the
magnetit proper,;,c:,r; tli-z- !itzilltced izov. and th-is is attributed
tv smoc~thlng tht~ ot the pores ~~nrd rel'in.-xng the admixtures,
The experiment.1i F, Qut with an icon powder of the
owing i~ cpmpc, I cn:
0 SI7. 0,009-~, ll~.
Card 1/~

9/61/000/007/0113/oi 6
F017 3I/E;535
97,7% F- ThE~ m- t c pf c, t% rz in e a su r e d b y a
b 11 , s t. ~ -,. m- & iva ~ d ~ 11 ft -F, Airf~k~.,e wAs mt-asured by the
p,-..rmtab-lljL'y m.,~~thad Tht chaag4~- an the specific surface,, the
fe-res.. and the "75 of the volume concentra-
t'lon 4ar the hydrogctl -111101-.-A-z :;n the hydiogen were measured using
the same mt-th~~,dzf is 'ireye used n the earl.:er- work (Ref.1), Fi�,2
~!IlGws the change --~n lkhi~~ cif the spec:imen, s, m /g.
dur-ing sinter-~Pg it funzt-~on of' the valume concentration o-f
JJCI ~,poros-ity cf the prtisFd spe.- -~Lm,3~ns about 30%-~ 5pe--Ific
surfat,Fi of the non-s.,ntered specamrns 0:.17 m /g, sintering at
1200'.'r. for 15 mill) PiL;~ '5 shows the cocrcive forceu . H Oe, of
-.,olume concentration of the
br2quettes as a Function of the
HCI in the sxntering atmosphvre, sintering at 1200'~C- curve I -
15 min., 2.ni.tial porosity 30%. curve 2 - 15 min, -initial porosity
23%, curve 3 - 3-4 hours, initial PONOS-ity 10%, FigA shows
the change in the strength., u kg/mm-. of rolled ztIrL.p apecimens
(7 x 60 =0 os a fUlUtIc,11 uf the HCJL concentration in the
sz-ntf-r~.ng atinosphere for an in.-v.xal Porosity of 30%, a s:intering
temperature of 1200-. C and a sinlexing .irn!L- of 30 min,, The
Card 2/5

24198
Simtering of Iron Povder in S/129/61/000/007/013/0!6
RO 7 5 / Y'5 3 5
presence of hydrogen chlorlde in t he sintering atmosphere leads
~o the "'Ormation t~t` chlarides en the activti- seZt;ons of thf,
e~iid to thevir evaporation-. The
ne",efirtre ~jmoothew-o 4;ut, rfdursng
the tqpoi-.:'ic surface ann iiisn
lilt! -vcri-lve tilt! mognitude of which depends not niilv -.in thi,
qui~ntxTv oi fpo.-es) but also on their shape., I he
.%t I f%gth 1!1~:'4 ql~tokv- kitio. t o ;, (17,op t ri t he role of si vess voni,( tit ra-
ffydr,sj~t n -h!c tie t)ri ab uitt mor-e int ensz ve ro.' ! ti: ixLE of
thc i ron spti!c -,mcn~, 'ind silicon form eas i ly c,fAoorat ing
11 : 1.; . ~ ~.' r --i ~ri- r i n:izig ai.sc. Linpr oves tht- rn,gn~,t . t chai-.-Z7 t -, - -
5~ ~ Z~N" Thi- i~ut mim 1.oncenx rar . on of hyo, ,.S!.n ;~'_hi (tv i de -tur -, niz
1111 cozil-.nucTus (rv4 flow .s ~v -he hC1 i;ctncen-
is h,
'ej:-ises f~icvt w
n the surfaz:t' ut th- .41)er.-Mett
du ~_' to tit*- -. ot% Ily )vi;d,-,kgerj Oiloriciv -&-noursi
Pue zo their h:,izl-. the Itt.1 vapour.'- have 1v 1-t,
removed by os* hv ~'rt;lzen a', the C-11-1 of the Stntc-r-
.~.f thts is 1~,nir 1'or a dur.~~
ng. .(jrj oi aDout ~-~ nin ( to',A
~jUt Lj (I,_, ofr he f7intering pio-iss 'j-,: m.;i:, tit. si,c-tiu.,ns will have
tt atm~:-snfiv.-ric c-riision ~ s spectmellf.
~,iritered in hydrogeii: Usual IV a S - 11g, El PI'C.,Sing atil; sini ei ing
ard

2h193
`;,interin% of Iron Powder in
'17 3 1
-is not z~,.,uffic__~ent tr, obtair. sintered iron. components
with p-ropert.i-es approaching. t he pr~.-~iu t -i v-, ~.j ~ ~~;jjpav t cotn.*~onenta
and, thcrefore.. v. t. spec.tmen.-~ are u,:").tlty and
sinteri--t, IJhe. inil.UoC~nE-e Of 1--intei.Lng on
properties of the coinpanent,,, tilt4,r ": and Was
;nVest0c;kted and lift T-eAulti ar; *.abitfated- [n tmnr,t-,vmvnt ,n
Lhe -r1ropertLes On S!.T11er1n:W ;n -ttmo:~pb~-z-c wa,
obacTypit only after s,~Iltering uvd,ng, 10 to 1~1 nt-in,
since shortr-r ti.irivs, azc not .;-nt for the reactitar. to
nrac4~ed to nny appe-c-c-aable f.-o ijuotoNs~riient All the PrOTerttes
by 25 to 110-,--* can be achieved, lie '~-..operties ot the Uinal product
%,ilill be the bettez- the highe- thc rit-,perti-e--i of the specimen-s
after the first sintering- )'i'v using .-sn atnuisullel-e (it' 11, 4 .10;~! fit1
in the preliminary sintering t min at 1.1.--OcC to J_~60~'C);
properties equall-ing those of' sltel D iE) can br
,-.chieved after fina.l nressinlzr to f, ~IcnsltY of 7.7-7-6 and sinti~v-
.-ng at 12001 L- foi- tabics and
refercnces. 3 SL;v~k,*" and
Joutnol stq,1A1liYs
94 9
4/5

,7
PANICIMINAl ". V.
Panichkina-, Z. V. "The connecti--nh~tween visibility distance and dust
and condensati-cn centers") Trudy Tashk. pp-f4z. o-:se.,-vr-,torJi, Issue w,
.1 L -
lg/,g, p. 62-65.
SO: U-43%, 19 August 53, (Letopis 'Zhurml Iny1di Statey, No 21, 1949).

JOIA IV / 'I'' -
(InGELY, K.;KASSAY, P.)?A]!,i M.
Time3,v treatment of atelectasis in the premature. Qyerm ogyassat
4 no.9:263-269 Sept 1953. (OLML 25:5)
1. Doctors,
L

VAYSER, V.L.; RYABOV, V.D.;-PANIDI, I.S.
Ammonolysis of 1,1-di(chlorophenyl)-ethane. Dokl. AN SSSR 140
no.1:118-121 S-0 161. (YJRA I-',:g)
1. Institut neftekbimicheskoy i gazovoy promyshlennosti im. I.M.
CyubRina. Predstavleno akademikom A.V.Topchiyevym.
(Ethane) (Ammonolysis)

CCESSION NR: AT4008697 S/2982/63/000/044/0033/0038
A
AUTRORi Pauohkin, Ya. M. I Vanidt, 1. S.
TITLE: Synthesis of boroii-nitrogen-containing compounds from boric acid
SOURCE: Moscow. Institut neftekhimicheskoy i gazovoy promy*shlennosti. Trudy*,
no. 44, 1963. Neftekllimiya, pererabotka nefti i gaza, 33-38
TOPIC TAGS: nitrogen containing organoboron compound, boric acid, boric acid.
nitrogen derivative, boric acid derivative, boric acid.*aryl,-unino derivative, boric acid.
alkylamino derivative, boronic acid.anilino-. polymer with urea
ABSTRACT: A new class of compounds containing the boron-nitrogen bond, the arylamino-;
boric acids, has been synthesized by direct condensation of boric acid with alllwniiies.
The course of this reaction was found to depend primarily on the temperature at which zinc,
chloride is added to the mixture of boric acid and arnine, as well as on the quantity of the
condensation agent (aniline, p-toluidine, o-toluidine, or p-anisidino). Temperatures
ranging from 130-170C were tested to determine which particular arylamino-boric acid
would result and whether the end-product would be an adhesive resin. Aliphatic aminos
did not react, but allcylamino-boric acids could be obtained by an exchange reaction with
an arylamino-boric.acid. Tdo reaction is very exothermio and, with methylamine, takes
C'rd 1/2
ACCESSION NR; AT4o081597
place at the relatively low temperature of
_15C.
urea and tile allPhafic diaininea ethylenediamine a7bc experiment was also conducted with i
I
nd haxamethylenediamine. The polymers;
Of tile boric acid deri-?ati,es were fractionated by treatment with acetone and
hio"h-Molecular components were found to be soluble while the low the resultant
not. These findings _mole
are significant because of the need for cular Ones were
high temperatures and or8anjo solvents, materials Which can withstand
chemical formulas. Orig. art. has: 3 tables, 2 figures, and 6
ASSoCrATION.. Institut nettekhimicheBkoy i
Pstitute of petroleum 9azOv0Y PrOmY*Bhlennosti, Moscow
Ch4mistry and the Gas Industry)
SUBMrrTED: 00 DATE ACQ: 16jan64
EXCL: 0o
SUB CODE: cH
NO REF SOV.- 000
OTHER: 004

PUSHKIN, Ya.111.; PANIDT, I.S.
Syntheaiv Cf brjrorj-,;jt,r-igen contup-ln.Ing coZpuunds tn
borlo acid. Tnidy KINKIMP no.44:33-39 163.
OMI W~ 8: 5)

HALYSHEVA, N.G.; STJiRCHIYp L.P.;-.p IDI,.J.-S-.; PAUSHKIN, Ya.M.
Application of,the method of neutron absorptiometry for
determining the boron content of organoboron compounds.
Zhur. anal,, khim. ~,~jio.11:1367-1369 N 163. (KRA 17; 1)
1. Institut neftekhmicheakoy i gazovoy promyshlennosti imeni
I.M. Gubkiria, Moskva.

Ei itall. diatij.-fie
~f
~4bfs (ditithyiamino)bor
4-4
od

Or
"/-'7 _t-10/24-k _PPJV
ACCEsIS
lig Ap"45016
AUTH S/0191/64/00o
v0~1 ~PAU"Ohkfn
p ~Ya
hn ako ' . ; DOchar 10091000311fnno.0~5.
a ~;
V,
_UiLni~M ; I __ 0- ~Ilv : S
T'TLE, Pr.par.ti 1~ . - .
C12 ~U -AXUd-. On-of PGIYVLnylons
With C_8ft1:b_0_ny comPOundo by the r ... t A6'
,j.OmPQuOd,
SOURCL, Plastic Lon Of
hoskiye~m&asy*.
T
TopIC TACs, no. 90 1964. 3-5
Vinylen,,a rganIc jmlc~o ductor,
I-rbony PC a
I llkRICOnducti
Co OPnd' calcium c ___ --,-.'ng
ABSTRACTv A ~ t .'' pol,_
ated 01 a . iouto 05 be-o
ato 0'0
carbid more. t rea n found for the
car 'blde;I
motho a- n a t , -ct -On Of Carbo!jyj com prepa
'.a td
no
in t at to. to 'airdpjj-~-Lj- TP?unda atlon Of con u-
dof "on ~u_
uc m
t0f
duct calc uno reactants Lsy.~ W4 , 'th calcium
Ca advan ). So of this
7 ro_
r
iIpI
ncl Pig
carbido du t
roduction
PrLnjca tt Cal U Tho math
a
L.t he
and is thereby car Ida Od is P A waste pro-
the,rc rem busod t~~ - .
thenat_ zodf);Odcl Ovea water from C,,bonylupon thO
vt t1i carbo barge acetylan
ompo
!Card 1/3 olpouna-:8 0 aca trio,: of
-i;;d stas t c4a
0 foraj

-L 889o, 65
AP4045016
ACCEMON NR:
conjugated polymers. The carbonyl C-Pmpoundo-acatona, acatophenons
acetaldohyde,- and aqat-ylfarroceno-,reactad with calcium carbide in
color ratio$ of 1/0.5 to 1/1 at 150-200C. The polymers produced
were only partly soluble in organic solvents Th;,soluble fraction,!
whose yield was 13.3-38%, woo studied by'cr;ooco c molecular
weight determination and by: elemental analysis. I
All of the volymerq~
were also studied by EPR and IR spectroscopy. The polymer structures
were assumed to ba'.of the type
-[CII-C-CH-CHI-
x
A~ Pblyzer of thejypa
-CH.C-CII-CIf
X,
Cord'2/3

8890-65
ACCBSSION NRs AP4045016
r
won synthesized for the first time. Most of tho soluble polymers
were black or oranga poiideri, except for the polymer from acetone,
which was a viscous resin.' 'Halting points varied from 50 to 500C.
The acetylfarrocone polymcr!malted at SOOC and had a molecular
waight.of 2405; it* yiold van 38Z. So;%itiona of all the polymors
formed strong films irith hirghadhanionkto metal wood, or porcelain
substrates., OrLso art* boo: 2_taVblielx~. 1 figur:, and 4 formulas*
ASSOCIATIONS none
SUBMITTEDi 00 ATD ?RzSSt 3109 ENCLs 00
SUB CODES MT -NO. REF SOVt 002 OTHERt 003
i'Cord 3/3,

PAUSHM, 7a*M,; PANIDI, I.S.; PLARVOYA, L.A.
Synthesis of semisYmmetrical tris-amides of boric acid.
DOkl- AN SM 159 noJe612-61,4 N 164 (MIRA 18c1)
1. Institut neftekhinicheskoy i gazovoy promyshlernosti imeni
I.M. Gubkina. Predr-tarleno akademikom A.N. Nesmeyanorym .

Oil
MIN
6 W-vill Z7

-AT5

PAUSHKIN, YcOt.
Simple mbtbod of preparing bio (diethylamino) boron chloride
and syntheses based an it. DAL AN Arm. SM 41 no- 4t226-229
065 (MIRA 19:1)
1. Moska7skiy institut neftekhimicbeskoy i gazovoy promysh-
lennoisti imeni Oubkinao

PAUSHRIN, Ya.1'.J.; BXHARov, B.V.; SMIRNOV, A.P.; VISHINAKOVA, LIP.; I,L4C'JUS)
1~
F.F.; PANIDI, !.S. -
Production Of polyvinyl compounds k; means of the reactior of
calcium carbide with carbonyl compounds. Plast.m;a-s,,-,.v no.':---r,
164. 2,7f.--,O)

'01M.M ft"Nim-1
MIMI
R. I
ON
hu, III

OVUM va t
, ~71
IN=
1t. mol
Lahl"S EM

PANI-nI, Ye.V,
AlkYlation nf phenol ethers with isobutylene
Trudy 14jl,'KHiGP no.37:137-141 62, on a KU-2 cationite.
UfIRA 17:3)

ISAGUMM, V.I.; PANIDIj, 70*V.
t
Alkylation of phenol with isobutyl alcohol iA the, presence
of a catio'n axchdnge renin (vow method of preparing tertiary
butylphonol)o Zhur.priklekhim. 34 no.8-.1849-1852,Ag 161.
(MJA 3.4:8)
(Phenol) (Isobutyl alcohol)

PANUNDOV
-ldritea).
Oomblnation track Ijign. pat,
I Put. khOz- n0-5:28 W 57.
1. Z~ma-stitell nachall (MLRA 10.-6
dorogi. '11ka. ldritskoy dista?ltsii
(Railroade,signalin.) Puti Kalininakoy

RtK4M/Cultivated Plants - General problems. L-1
Abs jour : Ref Zhur - Biologiya, No 16, 25 Aug 1957, 69186
Author : Panigiants
Inst
Title
Water plants- and linportant Source Of Industrial Rav
Material.
Orig -Pub Nature (Romin.), 1956, 81 NO 1, 108-112
Abstract No abstract.
Card I/I
ISAGULYARTS,, V.I.; PANIDI, Ye.V.
Alkylation of phenolic others with olefins in the presence of cation
exchange resins as catal,"ts. Zhur.priklokhime 34 no-7t1578-1582.
i1 161. (MiRA 1411)
(Ethera) (olefins)

21(l), 24(7)
1
SOV/51-6-5-2j5/34
AUTEIORS Glasko, V.B., Maslov, V.P., Panikar, VJ. and Sokolov, 'N.D. I
4
TITLEs On the Type of Correlation Function for the Helium Atom (0 vide
kor,relyatsionnoy funkt6ii dlya atoma FOliya)
PE111MICAL: Optika i Spektroskopiya, 1959, Vol 6, Nr 5, pp 693-700 (USSR)
ABSTRACT: In molecular calculations correlation in the motion of electrons is
allowed for bv introducing into the vave-Dunct-.ion an add.-itional
factor dependent on Inter-electron distance r
. (Ref. 11._
i
In analogy .,.,Ith the fir,t approximation in the he2ium atom cL--Lcu1.;ttion;
carried out by Hylleraas (Ref 2), this ?maltiplier can be vrittan for a
two-oloctron system in the fom
f(rl2) = I + 4--'2
vvhere a in a variational parameter. In the general case the corrolation
function shauld depend on three correlation variable,7 aiyl f can be) thon
represented as a series in powers of those variables (Rofs 2, 3). 1.7hon
only one correlation variable is used the choice of the fla&Aion f(rJ2)
in the form given by Eq (1) is an arbitrary one. The question arisos~
as to rhother this choice is best possible onto. 'nAr, ques-d on In
ansver(id by detoxvilitinG tfte corrt!lation Dinetion f(r,2) for tho helium
.,a rd 1/2