SCIENTIFIC ABSTRACT BOGDANOV, A. P. - BOGDANOV, B.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R000205820005-9
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: June 9, 2000
• Sequence Number: 5
• Publication Date: December 31, 1967
• Content Type: SCIENCEAB

S/124/62/000/002/010/014
Stress state in a non-uniformly .,*. D234/D301
proposed by the abstracter shows a good coincidence of the results even
in the case of the width being divided into a relatively small numberof
longitudinal elementary strips. [Abstracterts note; Complete translation'17~
I/
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'R 0 !b D A " 0 IJ , 'N I "Z-
BOGDANOV,_,A,P.,. insh,
Self-unloading barges of new design. Rech.transp. 16 no#9;14-17
S '37. (MIRA 10-.12)
(Barges)

I
BOGDkNOV,, Boris Vladimirovich,, inzh..-. GAJAOVSWA, Hariya Grigorlyevna,,
kand. tekhn.nauk; YEFRIZ-1,07, G.V., retsenzent.; NPjHML,-Aj-$--
red.; SHIRRUKOVA, Z.V.p red, izd-va; BODROVAY V.A,p tekbn.red,
(Sectional barge traims for propulsion by pushing) Sektsionrqe
sostavy dlia vozhdeniia sposobom tolkaniia. Moskva, Izd-vo
ffReebnoi transport," 1961, 144j* (IMU 15:2)
(Inland imter transportation (Twing)

-BO 410VL Al_starshiy inzhener-loytenant
The flier made an observation. Vest. Vozd. Fl. no.11:73-75 N
,61. (MIRA 15:2)
(Airplanes, Military--Maintenance and repair)

86-58-4-16/27
AUMOR: Vinogradovy R. I.) Engineer, Lt Col., Docent, Candidate of Tech-
nicial Sciences; Bogdanov, A.. P., Env-C&Yt
TITIZ: Aerodynamical configuration of a Supersonic Aircraft (kerodyna-
micheskeys kcmTonovka sverkhzvukoYoS6 samoleta)
ODICAL: Vestnik vozdushnogo flota, Nr - 4., 1958~ VP 55-63j, (USSR)
ABSTFACT: First the author discusses the general peculiarities of the configuration
of a supersonic aircraft and presimts in Fig. 1 a table of classified
aerodynamical configuration of such an aircraft based on two mainfea-
tures: the configuration of the wing and the arrangement of the empen-
nage. He divides the vhole range of speeds into subsonic) trmsonic,
supersonic and hypersonic regions and describes each region seperately.
He indicates that the transition from subsonic to supersonic speeds is
bound with the problem of overcoming the additional (wave) resistance
vhich increased greately in the transonic region, and that the character
and the magnitude of the change of the coefficient of wave resistance of
an airoraft~ with respect to velocipy: depend on the vuve resistance of
the parts ancl their loc-aticm on that aircraft.
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66-58-4-16/27
~erodynsmic Configuration of a Supersonic Aircraft
The author also discusses how the form and the aspect ratio of a wing, the form and
relative thickness of an #4rfoil &ffect the character of the flow of wave resist-
ance of a wing. In Fig. 2 he presents a6diWam showing the dependence of the coeffi-
cient of head resistance4of an aircratt on M at zero lift force. In Fig- 3 the
graph shows the interaeondence between the relative thickness of the airfoil and M
critical for an arrow a4d a rectilinear wing. In Fig. 4 he shows '
the influence of the relitive thickness of airfoil on the coefficient of vave resist-
ance at its maxium value.
Further the author analyzes the aircraft with respect to their wing form. He am-
4ws seperately virious,aircraft,, Aircraft vith a triangular wing, rectilinear wing,
arrav wing, an aircraft with a wing in the form of a ring (Fig- 5), an aircraft with
a circular wing (aircraft-saucer Fig.' 6)p an aircraft without a horizontal empennage
(tailless.-Aircraft, or'flying wing), an aircraft with the horizontal eml;ennage located
in the rear., and an aircraft with the horizontsa empennage located ii2 thefront.
-jaircraft-duck)
Finally the author mentions the constructional changes.in the vings vhich should im-
prove their aerodynamical characteristics during take-off and landing at low speeds
and which he calls the mechanization of the wing. He discusses also the following
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Aerodynamic Configuration of a Supersonic Aircraft
86-58-4-16/27
.prospective means of mechanization of aujpersonic aircraft: the jet flay, the control
of the boundary layer, the variable sweep-back of the wing (Fig. 7), and the varia-
tion of the angle of a wing's setting.
There are three schematic drawings, three diagrams, and one photo.
MIMIZ: 'Library of Congress
AYA
1. Airplanes - Supersonic charaoteristlcq 2. Airfoils -
Supersonic characteristics 3. Airplanes - Aerodynamic
characteristics
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1(2);1(3) PHASE I BOOK EXPLOITATION SOV/2307
Bogdanov, Aleksandr Pavlovichp Rostislav Ivanovich Vinogradov, and
---fftnmtVffffn Ift ye-VU(I-H-Wrtov
.Sbornik zadach po konstrukt'sii i proqhnosti samoletov (Collection of
Problems on Aircraft Gonstructipn and Strength) Moscow, Oborongiz,
1959. 230 P. Errata slip inserted, 7vOO0 copies printed.
Reviewer: Kh. S. Rh'azanov, Candidate of Technical Sciences, Docent;
Edi: A.M. Yarunint Engineer; Ed. of Publishing House: L.A.
Belyayeva; Tech. Ed.: N.A. PUkhlikova; Managing Ed.: A.I. So-
kolovp Engineer.
PURPOSE: This text book was approved by the Ministry of Higher
Education of the USSR for studentSof aeronautics vuzes and depart-
ments.
COVERAGE: This collection of problems on the design and strength of
aircraft was compiled for the courseE-."Strength analysis of air-
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Collection of Problems on Aircraft (Cont.) SOV/2307
craft" and " Construction and design of aircraft". it is intended
to aid students to:solve engineering and analytical probl ems under
the supervision of instructors and independently.
TABLE OF CONTENTS:
Procedural instructions 3
Ch. 1. Forces Acting on Aircraft 5
1. Forces and overloids acting on aircraft in flight 5
2..Flight loading conditions and maximum characteristics
lCh. 11. Wing 27
1. Wing load and stresses in wing sections 27
2. Calculations for frame elements 45
3. Stresses in wing sections 51
4. Analysis of wing'compdnen'ts 66
Ch. III. Aileronso Empennages, Control 102
1. Ailerons 102
2. Tall unit ill
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Collection of Problems on Aircraft (Cont) SOV/2307
3. Control 116
Ch. IV. Empennage and Wing Vibration. Aeroelasticity 125
Ch. V. Fuselage and Engine Mounts 130
1. Fuselage 130
2. Engine mounts 151
Ch. VI. Landing Gear 16o
1. Analysis of shock absorbers 16o
2. Strength analysis of landing gears 168
Ch. VII.,- Aircraft Control 178
Ch. VIII. Emergency Crew Rescue Devicesp Air-tight Cabins) De-
termindtion of Aircraft Parametersp and Centering 18q
Appendixes
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Collection of Problems on Aircraft (Cont.)
I. Table of the International Standard Atmosphere
II. Characteristics of Aeronautic Airfoils
III. Graphs for Longitudinal Bending Analysis of Bars
IV. Values of the Coefficient k in Relation to Conditions of
Support and Loading of Plates
AVAILABLE: Library of Congress
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SOV/2307
196
199
218
228
IS/bg
9-18-59

2~4
d Vttr
1) in an electron-
ion PlasWa when an ultrasonic fieldeis present. The investigation is done 11H7 ~e
linear approximation with regard to electron-electron and ion-ion collisions. It is
shown that resonance excitation of oscillations takes place in the plasma at frequen-
cies which satisfy the law of dispersion of magnetohydrodynamic and magnetoacoustic
waves when ultrasonic waves are propagated at an angle 6 to the magnetic field
(0