. .

-

. .

XIV , - . . (1012 2010, . )

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2010

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: XIV . . ., . .47 .-. . . (1012 . 2010, . -

) : 2 . / . . . . ; . . . -. ,2010. . 1. 364 .

XIV - , - . . , - , , , .

, , -, .

629.7 30 + 2

. . , 2010

,

,

5

629.7.01. . , . .

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. . - , - .

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cx .1.5. A.2.

.2.1. :

1

1 ny y i

i c S k

S = = .

2.2. :

( ) ( )( )

1

1

1

n

y F iiF n

ay i

i

c S k x b Lx

bc S k

a a=

a

=

a + =

a

.

2.3. :

( ) ( )( )

1

1

1

n

y F h iiF h n

ay ii

c h S k x b Lx

bc h S k

a=

=

+ =

.

3. -.

3.1. -:

( ) 1

1 ( )n

x x p x p y iic c c c S

S = = + D .

3.2. - m :

1

1 mx x p j

jc c S

S = = .

4. .4.1. ,

[3]:

( )( )21

114

K h

h

=-

l

.

4.2. :

( ) ( ) ( )2 1

, 1,1n

x y x y xiic c h K h c A c c

=

= + + .4.3.

.

- , .

6

- .

1. . ., . . - . . : , 1978.

2. . . .. : . - . -, 1957.

3. . . - // . . . (, 2002). . : , 2002. . 270272.

P. A. Amplitov, V. V. FrolovKomsomolsk-n-Amure State Technical University, Russia, Komsomolsk-n-Amure

MODEL OF APPROXIMATE CALCULATION OF AERODYNAMICAND MOMENT CHARACTERISTICS OF WIG-CRAFT

The model of approximate calculation of some aerodynamic and moment characteristics is offered. The Model de-scribes WIG-crafts with arbitrary number of the carrying surfaces. A number of the simplifications allows to greatly re-duce labour content of the calculation at early stage of the designing. Model is optimized for machine realization.

. ., . ., 2010

629.7.067.8. . , . .

. . ( ), ,

-

- - -, . - 0,02 .

- . - [1].

- [2], - ( ) - - .

-- [3], , - , - . - , - - , -

, .

-, - . . - . .

- - 0,02 .

1. . . . . : , 1995.

2. . . . . : , 1973.

3. . . - . . : , 2005.

,

7

A. V. Babenko, N. T. Kargin

Samara State Aerospace University named after academician S. P. Korolyov(National Research University), Russia, Samara

DESIGN OF PROTECTION OF SPACE VEHICLES FROM METEORICAND TECHNOGENIC INFLUENCE

The vacuum shield thermal insulation, in which lead foil is established, is used for protection against meteoric andtechnogenic influence. Such design can protect a casing of space vehicle from influence of particles weighting up to0,02 gram.

. ., . ., 2010

621.9.06. . , . .

. . , ,

-, .

- -, (). - - , , . - , - [1].

, - , . SolidWorks SolidWorks Routing. - , 1700 - - . ( - ).

- . - . . -

. - - . , - . , -, -. , , -- , . , . SolidWorks Routing -, . - , .

SolidWorks Routing - COSMOSWorks COSMOSFloWork, , -.

1. . ., . . - . . : - . . . , 2006.

8

L. A. Babkina, L. V. ShumkovaSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

3D-MODELLING OF PIPELINES ELEMENTS

Questions of 3D-modeling of spacecraft pipelines elements having a difficult space design are considered.

. ., . ., 2010

629.78.002.3. . , . . , . . , . .

. . , ,

-

, . - .

() - (). . - . -, , - - .

- . - - - , - , --1000 , - - [1].

- - .

- , , ( 100 ) - 30 , . -, - (, -), , l23, - - ().

. - -3, - , - .

478474 160130 100 . - - : 1 NaOH (5 /) ++ Na2SiO3 (10 /); 2 (5 /) + Na2SiO3 (10 /). 260 - . - SIAM 2.

, - :

1) , l23 + SiO2;

2) , - : -l2 -l2.

- .

. - - . - . - - 3 .

,

9

- :

( t = 30 ); Ik/Ia = 0,8

As - En, , 92-0909-69. - s -59, n -. , - As En - , - . As/En 0,5, .

, , , - .

1. - - - / . . [ .] // . 2(10). 2006. . 4650.

E. V. Vahteev, A. V. Girn, A. E. Miheev, I. V. EvkinSiberian State Aerospace University named after M. F. Reshetnev, Russia, Krasnoyarsk

APPLICATION OF MICRO-ARC OXIDATION COVERINGS ON ALUMINUM FOILTO PROTECT THE STRUCTURE ELEMENTS OF SPACECRAFT

The application of protective micro-arc oxidation covering to aluminum foil of AD mark was done. The proceduresof extracting of protective coverings from aluminum oxide were developed. The tests of coverings samples were carriedout to detect the influence of the plasma jet of a stationary plasma thruster of the spacecraft engine.

. ., . ., . ., . ., 2010

620. 197. . , . . , . .

. . , ,

,

-, , - .

() - - . - -. -

. - , - - - 10 100 , - .

10

- - . , , , . - , , . -, , -- , - .

- , -- - ( ), . - - .

-- , - (, - ). - , - . - -: 10 2.

, - - - - ( ) - . - . - - - - .

E. V. Vahteev, A. Miheev, D. V. OrlovaSiberian State Aerospace University named after M. F. Reshetnev, Russia, Krasnoyarsk

ANALYSIS OF METHODS OF COVERINGS STAINING PRODUCEDWITH MICROARC OXIDATION ON ALUMINUM ALLOYS

An analysis of methods of staining of micro-arc oxidation coverings is carried out. Methods drawbacks are re-vealed, directions for further researches are suggested.

. ., . ., . ., 2010

52.001.18(608.17). .

. . , ,

. .

. . . . . - . , , .

20- . XX . , . . . , - . . 1927 . - .

1920- . - ( ) .

40 . - , , . - . 1928 1932 . - 1600 . - - - - [1, c. 412].

. . -, ,

,

11

. , , -, , , .

1914 . III - . - -. . . , - - . . . - . . -. , . . . , . , . [2, c. 391].

1926 . -. 1928 . , - . , . - , - , . - -. , - , . . - . : , , - , - , ! [2, c. 395].

. - . - . , - , , , ,

, , . .

- . , , . .

. . - - ., - - - - , 1929 . - [3, c. 276].

19411945 . . -. , -. 28 1942 . .

. . . . -. : 1924 - , : , - ? - . : , ! [3, c. 281].

XX . , , , . -- - , - .

1. . . . . : , 2002.

2. . . . : , 1985.

3. . . : , 1972.

D. A. GavrinSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

INTERPLANETARY COMMUNICATIONS PROBLEMS IN N. A. RYNINS WORKS

In this article N. A. Reunin's activity of space flight examination is considered. It was like a fantasy in the twenties.Rynin wrote some papers about space exploration. He believed that in future people will fly into space and over theyears his dream has come true.

. ., 2010

12

629. 783. 05. . , . .

. . , ,

() - () . .

() - () - () - () - - . - () (). - , , - - [1].

:

- , - ;

, - (), , - ;

, ;

- , - ;

- , - - .

, , - , - -.

- () -

, - - 27 0,1 5 , - 100 0,3 2 . 1 - , 50 % .

. - [2] - :

8- 3 27 ;

6- - 2 8- 1 27 ;

4- - 5 27 ;

8- 2 100 .

- , - . - 7- . - 4- .

(). - - (14). - , .

,

13

+100

3 /27 ()

2/100 (.)

+27

3

4

1

2 /1/27 (.)

5/27 ( .)

2

- 27 - . - 55035-171 - , - - () Actel. - - .

- - -, -5,Amos-5, Telkom -300.

-5,6. 16 - 1 . - , , -.

1. - - / . . - [ .] // : XIII . . . : 2 . ; . . -. -. , 2009. . 1. . 2022.

2. . - - // -. 2008. 9. . 23.

A. I. Gornostaev, V. V. ShanavrinaJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

PROBLEMS OF UNIFICATION OF INTERFACE MODULES OF HEATERS CONTROLIN THE ONBOARD EQUIPMENT OF SPACECRAFT ONBOARD CONTROL SYSTEM

Features of construction of interface modules of heaters control in the onboard equipment of spacecraft onboardcontrol system are considered. Possibility of variant construction of interface modules of heaters control from the set ofstandardized circuit cards is shown.

. ., . ., 2010

14

534.121.1. . , . .

. . , ,

, - , . . . c .

, [13].

- . - . - . - , - - (. 1). . 2.

. 1.

-. - . - , -

- .

. 2.

- - . , . - - .

1. Zenkert D. An Introduction to sandwich construc-tion. London : Chameleon Press, 1995.

2. Vinson J. R. The Behavior of sandwich structuresof isotropic and composite materials. Lancaster : Tech-nomic, 1999.

3. Kollar L. P., Springer G. S. Mechanics of compos-ite structures. Cambridge University Press, 2003.

P. O. Deev, M. V. SnytkovaSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

VIBRATIONS OF SANDWICH PLATE WITH TWO FREE EDGES

There is a solution of the problems for defining of main vibration frequency of sandwich plate with two clampededges and two free edges. The plate consists of two composite similar base layers and of orthotropic filling. Galerkinsgeneralized method was used to solve dynamic problem. The formula for general frequency determination is obtained.

. ., . ., 2010

,

15

629.783.05.. . , . .

. . , ,

() () ( ) . , AMOS-5.

, :

(, -, .);

- (, -, , - .);

. -

, -, , - . , 30 - () - () , , , . - - . - ( ) , - () .

, - . - , - . , - -, .

, . - , AMOS-5.

V V V -

1-20. 20- , 1-20 ( - ).

- 1-20 - - , - - .

- - 2 4. - . -- . - . - - -, . - - - .

- , .

16

Ye. S. Dolganov, I. V. ButkinJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

DEVELOPING HEATER CONTROL MODULESAT THE AREA OF INJECTION INTO ORBIT OF A SPACECRAFT

The area of injection into orbit and heater control module at this area are described for modern space vehicles,produced by JSC ISS. The simplified symbolical circuit for the heater control module at the injection area, developedfor AMOS-5 spacecraft, is presented.

. ., . ., 2010

629.78. . , . . , . .

. . , ,

-

- .

- ( III .), ( .), - .

- , - . : -3, - -2 D-5 (), -12 -, -122 -, -24 - -56 () -100 , -36 ,-362 -29-2 -2 [1; 2; 5].

- () , - . () , . - : , , . , , - : -, ; . , - , - , - . , , - . - , .

, : -, . - - (-), . - - , [15].

() . . 1903 . 1921 . . , 1926 . . 1920- 1930- , . . . , 1931 . - -1 . , .

-:

1. - ( 4 500 / 3 500 / -).

2. : -, - .

,

17

.

3. , , -, - , - , -, - , -, , - , - . - ( ) , , . ( ), . , - , , , - .

:1. ,

, - ( , 1 - ). - -, , ( - ), , , .

2. .

- , , -, .

3. - , - , - , - [15].

, -, - , - , - .

- -, , . .

1. / . . . . . : , 2007.

2. -385, , .. . . / . : . . , . . - ; . . . . . . . : - , 2007.

3. /. . [ .] ; . . . . . :. 1987.

4. - / . . . . . : -, 1984.

5. , . . - : . ; . . .-. , 2007.

M. D. Evtifev, A. A. Raskin, A. S. Suhanov

Siberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

THE COMPARATIVE TECHNICAL AND ECONOMIC ANALYSISOF BALLISTIC MISSILES WITH SOLID AND LIQUID FUEL

In the report about the comparative technical and economic analysis of ballistic missiles with solid and liquid fuelthe conclusion about an opportunity of creation of ballistic missiles using new kinds of fuel were made.

. ., . ., . ., 2010

18

621. .

, ,

, - , . .

- - () -.

- . , , - , , , , [1]. , - , - , - ( ).

, , - . - - , - , , - . -, - - [2].

[3], 1,1 , , , .

[4]:11/

,

exp( )ln (1 ) 1 1

N

Nn

-

a b

- u = -a + - a +b

%% ,

N ; n ; ( 9 000 /); , - .

- . - , ~ 45 %, .

, - ( ) .

[4]

1 N

N = + m

,

N, N ), , , 1015 % , .

, - - . - [5].

, - . - , -, -, - .

- Saturn-1b [6] . , , .

- , - [7]. 1 , , Ares-1.

, - 68 %, . - , , -, Saturn-1b 1,45 /, - Ares-1.

, - -

,

19

, - , . - , -, , .

1. / . . . . . : -, 2009.

2. . . . . : , 2009.

3. . // - . 1998. 17, 18.

4. ( ) / . . . . . :, 1985.

5. . . - . . : -, 1988.

6. Apollo 7 mission report. Manned spacecraft center,1968.

7. - - / . . . . . :, 1991.

B. A. EvtushenkoJSC Krasnoyarsk machine-building plant, Russia, Krasnoyarsk

THE QUESTION OF DESIGNING OF ROCKETS USING A FUEL PAIR OXYGEN-METHANE

The questions of possibility and expediency of designing of rockets, using a methane fuel, their application area areconsidered. Principles of simplification of designing aim of similar rockets are expounded.

. ., 2010

629. 78. 018. 2 (04). .

- , ,

, (), - .

, - , . , - (+90+120 ) - . , - , . - , , - , ,, , . . - , -. , , , - . .

, - , , - : , . , - .

- - . - , - , - .

- :

dm dt k= , (1) m , - . , - . k - - , -

20

, , , - . - .

-

( )( ) ( )0 0 1 1q t tq q q = - - , (2) q ; q - ; 0q ; t 0t -, .

- q , - , - - , , .

- , , . - - - - .

, - , . - -.

, , - , (-, , ), , - . - , -.

M. V. ElfimovaThe Siberian branch of Saint-Petersburg University

of Emergency Situation Ministry, Russia, Zheleznogorsk

RESEARCH OF REMOVAL OF THE MOISTURE FROM TEXTILE MATERIALS,KNOTS AND ELEMENTS SPACE VEHICLES

The basic physical laws of removal of a moisture from nonmetallic products, knots and space vehicles elements,weight change of latexed material with a synthetic threads covering in the process of vacuum-temperature drying arepresented.

. ., 2010

629.7.001. .

. . , , -

() () - , , . , .

- ,

. - - ,

,

21

- .

- . - - , - .

. () , - . - . , . , - . (, , - . .). , , - -.

- , () , , - (). - .

, , - , , , - , . - - . -

, .

- , - - . - - - - (). , , - - , , - -.

, .

, , - : , - .

( ), - . - - .

- , .

- , - .

M. I. KislitskiyArsenal Design Bureau named after M. V. Frunze (Federal State Unitary Enterprise), Russia, Saint-Petersburg

DUAL-USE OF SPACECRAFTS CONCEPTION

Dual-use of spacecrafts is an effective way of receiving of an additional output from the capital that has been in-vested in spacecraft creation, with minimal expenditures. Principles of Dual use of spacecrafts, conceptual scheme andformalization are shown.

. ., 2010

22

624. . , . .

. . , ,

-

, . .

, - , - (. ). - -, - .

, - , - [1]. [2] - - spacecraft and aircraft applications.

, - . - . , - , , -. , . . - [3].

, , - . - . , -

- , - . - - - - . , - , - ANSYS, NASTRAN, ABAQUS, COSMOS/M, - , - - . - - .

- , . , , , - . , , , , - . - - . - , COSMOS/M. - - , - . - -.

1. Vasiliev V. V., Barynin V. A., Rasin A. F. Aniso-grid lattice structures survey of development and appli-cation. Compos Struct. 2001. 54. P. 361370.

2. Vasiliev V. V., Razin A. F. Anisogrid compositelattice structures for spacecraft and aircraft applications.Compos Struct. 2006. 76. P. 182189.

3. Vasiliev V. V. Mechanics of composite structures.Taylor & Francis, 1993.

,

23

A. V. Lopatin, E. A. BarylnikovaSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

FINAl ELEMENT MODELING OF LATTICE CYLINDRICAL SHELLS

The problems of lattice cylindrical shells steadiness loaded by forces and moments are solved. The analysis of theinfluence of shells length and angle of helical ribs on the critical forces and moments is performed.

. ., . ., 2010

539. . , . .

. . , ,

,

, - .

, - - , - . , - . - - . , - , , . - [1; 2] - , - .

- . - - (. ), - .

1. Leissa A. W. Buckling of laminated compositeplates and shell panels : Technical report AFWAL-TR-85-3069. 1985.

2. Blevins R. D. Formulas for natural frequency andmode shape. Krieger Publishing Company, 2001.

A. V. Lopatin, D. M. TereshchenkoSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

VIBRATIONS OF ORTHOTROPIC PLATES FIXED IN CENTRAL POINT

In this article the problem of defining of the fundamental frequency vibrations of rectangular orthotropic plates issolved. In the plates central point there is no deflection and rotation angles of tangent to the coordinate lines.

. ., . ., 2010

24

629.7.023. . , . . , . , . .

. . , ,

.

- , . - , , -.

- , - - . , - - - , . , .

- .

- - . - - .

(. 1) - 1, - 2. - 3 4.

. 1. :

1 ; 2 ; 3 ;4

-. , - , - V . - -. - , .

q 103 /3, I 60200 , U 3545 , 38 . V 0,0050,03 /, Q 50100 /.

-, . , .

. 2 -6, - , - 1, 2 3 - 4.

. 2. -6:1 ; 2 ;

3 ; 4

, - , . 912 , - 4 . -

1

2 4

3

1

23

4

,

25

1,5 . 1 26 .

, V = 0,0050,01 / 100200 .

0,01 / 120 . -

0,03 / - 80 , - - - . 0,005 / 150 , , - .

A. Ye. Miheev, S. S. Ivasev, A. V. Girn, D. V. OrlovaSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

METHOD OF SURFACE HARDENING OF TITANIUM ALLOY

Method of surface hardening of titanium alloy by heating of article in nitrogen medium with use concentrated en-ergy source was offered.

. ., . ., . ., . ., 2010

621.396.67. . , . . , . . , . .

. . , ,

- , ISEM3. .

( ), -, - , -. - - () -, - .

, - , :

2 2 22

o 1 o[ sin ( )]4 ( )X Y rZ

F R+= + D + D j-j

j, (1)

X, Y, Z () ; r, j - :

= arctg[(Y Y)/(X X)], (2)X = X + r cos , (3)Y = Y + r sin , (4)

X, Y , ;

2 2 2 2( )

sin cos

abRa b

j =j+ j

, (5)

a, b ; F ; , 1 -, -- , - ; , - .

-- . -, - , . -, - - .

- .

26

- ,. . - . - ISEM3, = 5106 1/.

- , - .

1200 - . -, , , ISEM3, :

, 60 155 , 60 ;

1 3 ; 0,8

1 /2.

- () 500/007 75969440-007-2009 - 596-36-2005.

- CAD-PRO 3D UF Color. 1/0 + 1/45 + 1/45 + 1/90 ( - ). 0,4 .

5056-2,5-23 14311577.237-02 , - -51.180 1-596-212-85. - 21,1 . - .

, - , LKG90CS45.20.12. - - .

, - Y.

- -.

M. M. Mihnev, V. V. Zlotenko, N. N. Ishenina, . A. GordovenkoJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE MOLD PRESSING OF THE THREE DIMENSIONAL CONFIGURATIONCFRP SANDWICH REFLECTOR

The construction and mold pressing processing of the three dimensional configuration CFRP reflector from theISEM3 high-density fine-grained graphite is briefly described. The experimental results are shown.

. ., . ., . ., . ., 2010

629.7.01. . , . .

-- , , --

-, . - .

() -. [1]. - . - ,

- .

- (- ), ,

,

27

. - , , - . - (, , - . .), - .

() , -, -, , , . -:

1) - ;

2) - - , ;

3) - ;

4) ;

5) .

-, , [2], -

- .

-, - [3].

- RRJ (-- ) RRJ75. - . , , -. - - .

- - .

1. . ., . . - . . : ,1982.

2. . ., . . - - : 2 . . : , 1977.

3. . ., . . - . . : -, 1975.

RRJ60 RRJ75 RRJ95 , 38585 42280 45880 **, 6000 7500 9800, 10685 11610 8677, % 15 17 22 0,00076 0,00064 0,00019 0,00042 0,00058 0,00106 16,256 15,988 15,495 **, / 829 829 829 **, / 0,658* 0,670 0,670 0,277 0,275 0,189**, 5000 5000 4600 , 7879 6816 5996

* , RRJ. RRJ60 .

** .

N. B. Prihodko, V. V. FrolovKomsomolsk-n-Amure State Technical University, Russia, Komsomolsk-n-Amure

THE DEFINITION OF WEIGHT AND AERODYNAMIC CHARACTERISTICSOF FAMILY MODIFICATION AIRCRAFTS TAKING INTO CONSIDERATION

THE DEEP UNIFICATION PRINCIPLE

The definition of weight and aerodynamic characteristics of family modification aircrafts got with the help of thedeep unification principle is considered. The connection between geometrical dimension of fuselage and weight andaerodynamic characteristics of aircraft is revealed.

. ., . ., 2010

28

629.783. . , . .

. . , ,

. , - .

- , -. - -. - , - - [1; 2].

1,2 , - - (. 1). - . .

. 1.

COSMOS/M -- . BEAM3D. SHELL4L. - COSMOS/M -, -- .

.

. 2. , . (. 3).

. 2.

. 3.

- - - , - .

1. /. . [ .] // -. 1981. 8. . 93106.

2. Imbriale W. Spaceborne Antennas for PlanetaryExploration. NJ. : John Wiley and Sons, 2006.

M. A. Rutkovskaya, O. V. KoledaevSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

MODEL OF THE SPACECRAFT COMPOUND COMPOSITE ANTENNA

The model of the compound composite antenna of small diameter is developed. Projecting calculations of the con-struction of spacecraft antenna when there are limits that put on vibration frequency and temperature deformationswere carried out.

. ., . ., 2010

,

29

534. .

. . , ,

- .

() (. 1). : 10z g= ; - 6x g= ( g -). , - - 30f = . , - 0 0,5zv = /, 0 0,3xv = /.

() (. 1) , , 150l = , (. 1, ). . - ; -. ( )i ix x t= , 1 6i = - , - (. 1, ), - ( )i iF F t= , 1 6i = - (. 1, ).

- 1 2 6( , ,..., )F F F

1 2 6( , ,..., )T x x x& & & . - ( ) / 0d dt+ =

[ ]{ } [ ]{ } ,R A B A= l [ ]R [ ]B ; l . - ;

( )q t ( ) ( )i k ikx t q t A= , ikA

ix k - . -

( )kq t = 1 cos( )k kC tw + 2 sin( )k kC tw . 1kC 2kC ( )i ix t x

*= ( )i ix t x

*=& & , 1 6i = - , ( )* - .

Aluminum 1060-14. 0,48 . . - 1 1576,96 /w = 2 329,4 /w = ;

5 10 411 /w = 6 442,25 /w = . (0) 0ix = , 1 6i = - ;

1 0(0) xx v=& , 5 0(0) zx v=& (0) 0ix =& 2, 3, 4, 6i = . - (. 2). . 2, .

5( ) ( )z i iN t F q t= . 2, . -

5ozF mv= w = 0, 48 0,5 / 10411 / 2498,6 = . 4( ) ( )x i iM t F q t= z l= 4 3( ) ( ) ( )x i i iM t F F l q t= - - 0z = . 2, .

. - - ; - .

x4x2

x6x5x3x1

xy

z

O

F3

F2F4

O

z

yx

F1

F5 F6

. 1. ():

; , ; ,

30

. 2. : ; ( )zN t ;

( ) ( )

R. . SabirovSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

THE CALCULATION OF ANGELED REFLECTOR TO THE ACTIVITYOF THE VIBROSPEEDING ACTIONS AND THE ASSESSMENT

OF THE FIXING BOLTS STRENGTH

The calculation of proper frequency and free vibrations of angeled reflector in the initial conditions with the calcu-lation of inner efforts for fastening bolts computation sare considered.

. ., 2010

629.78. . , . .

. . ( ), ,

, - .

- . - - .

- : ; - ; - ; . - : -

; , .

; - - ; -; .

- - , , -, , - .

,

31

, . - -. 170 /2. - ( ~ 50 /H), - , , 0,1 - 30 2. - - - . - , , - - .

, - -. -, , . .

, - - -, , - (- ).

-

: TacSat-2(, 2006 .), GOCE (, 2009 .).

, , - - , - .

- - - - , - :

- - ;

, ;

- , - ;

, , - , - ; ;

- , - .

- - , - -.

V. V. Salmin, V. V. VolotsuevSamara State Aerospace University named after academician S. P. Korolev

(National Research University), Russia, Samara

PROBLEM OF CHOICE OF DESIGN PARAMETERS OF THE POWER - PROPULSIONELECTRO-ROCKET MODULE OF A LOW-ORBITING SPACECRAFT

The method to the solution of the problem of design parameters of the power- propulsion electro-rocket module forlow-orbiting spacecraft is described. In the basis of a method the system approach in which possible design solutionsare analysed lies and synthesis of optimum solutions is carried out.

. ., . ., 2010

32

629.78. . , . .

. . ( ), ,

, .

- (), - () , , [1]. - . , , () -. (150400 ).

[2].

, - - . -, -.

- , - .

- , - - . - , , -, -, , . , - . - , - .

. - (. ), - + .

:

( ) ( ) ( ), sign cos ,x m xV u V uy = y0

0

1

0 0

0

0

0 0

sin2arctg

cos 2cos2 21 1 ,

k

mk

k k

x

kk k

i i

rr

i i i iV rV rr r

r r

-

- py =

- - p p - - - + V0 - r0 i0; Vx - ; u ; rk, ik - . - ().

- . - - r*, - . , , r .

,

33

, - - 3 %, .

, - , , - . . , - 250300 ,

7 - 2,53 .

-- .

1. . 2009. . 19, 12. . 40.2. . ., . ., . .

- . : - -. . , 2006.

V. V. Salmin, A. S. ChetverikovSamara State Airspace University named after academician S. P. Korolev

(National Research University), Russia, Samara

SELECTION OF OPTIMAL DESIGNED AND BALLISTIC PARAMETERSOF MULTIPLE-USE INTERORBITAL VEHICLE WITH PROPULSION

INSTALLATION OF MICROTHRUST

The solution of a problem of optimization of design and ballistic parameters of the multiple-use interorbital vehiclewith propulsion installation of microthrust, while flying from a low orbit into the removed orbit, which is accepted asthe geostationary orbit, is shown.

. ., . ., 2010

629.78.08. . , . .

. . , ,

- . .

, - (), - . - - () [1]. - .

- - () . - () . - - , . - - , . -

- : ; - ; . (- ; ; - ; -, ; -). .

, -, - . - - , . . - .

34

- (. ). :

1 1 1 1 2 2 1 1 1 2 0

2 2 2 2 1 3 3 2 1 1 2 2 2 3

3 3 3 3 2 2 2 3

( ) sin ( ),( ) ( ) ( ) ( ) 0,( ) ( ) 0,

m x c x c x x ( x x ) F tm x c x x c x x x x x xm x c x x x x

+ - - + - = + - - - - - + - = + - - - =

&& & &&& & & & &&& & &

F0 F; 1 2 , -; w ; t -.

m1 ; m2 m3 ; 1 ; 2 3

, , ;F ; x1 ;

x2 x3

:) () -; ) - , -

( - ); ) .

: ) , xi = ai sin (wt) ++ bi cos (wt), i = 13; ) xi - ; ) - Maple 13 ai bi; ) - xi. - , - m2 m3 m1 , 1, 2 3, - 1 2 - F w .

[2] - . - : ) - 230 000 , 3 000 - -; ) ; ) ( ), , - - / .

-: ) , , - (, ), , - ; ) - (, ).

1. - : / . . [ .] ;. . . -. , 2009.

2. /. . [ .]. : , 2000.

L. A. Semenova, . Ye. LysenkoSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

UNIVERSAL VIBRATORY SYSTEM FOR COMMUNICATIONSATELLITES TESTING

The choice method of universal vibratory system for dynamic testing of communication satellites using the Tandemscheme example is offered. The system parameters are detected and recommendations for its application are given.

. ., . ., 2010

F

c1

c2

c3

m1

m2

m3

x1

x2

x3

:

,

35

681.51. . , . .

, ,

, . - .

. - , - (, , , -) -, -. - . - - -, - ( , ). - - - , , , - . - -

-, , - ( ) . - - . - - /GPS - -, . - , . , , , .

- . - - .

N. S. Senyushkin, R. R. YamalievUfa State Aviation Technical University, Russia, Ufa

APPLICATION OF MULTIPLE-ROTOR UNMANNED AIRCRAFTFOR NEAR AIR WORKS

In this work started works by our initiative group are described. The application of multiple-rotor air platforms aslight UAV is explained.

. ., . ., 2010

36

621.396.67. . , . . , . .

. . , ,

. . -. .

- () : () 30 , 1820 , , () 160 . . , - - (Ku-, - ), - .

. . - , - . -- , - 35 , - -- . - , - ( ~ 1 , ~ 0,5 ) . - , - . , -. -, - . -, -, . , -. - , . -,

, , , . -, - - .

, - , . 1. .6, 0,5 .

. 1. :1 ; 2 ; 3 ; 4 ; 5, 6 ; 7 ; 8 -

-, - - (. 2). .

. 2. , :

1 ; 2 ;3 ; 4

,

37

. - 2, - . , , - 1, 24 - , , . ( -) 4 - . - - , - -. -

, - . - - , . , - - , -.

, , , - . - 5 - 0,1 . , , , .

V. B. Taygin, Ye. Yu. Uzolin, V. Ye. ChichurinJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

COMPOSITE MATERIALS IN CORRUGATED HORN CONSTRUCTIONOF SPACECRAFT ANTENNAS

Method of manufacturing horn emitter with corrugated inner surface is shown. Method of manufacturing of hornfrom with corrugated inner surface with the help of automatic coil or manual placing of carbon fiber is offered. Hornemitter from carbon fiber with corrugated inner surface is a result of using cutting-edge technology and advanced ma-terials. This makes it possible to reduce mass of spacecraft and improve reliability of wireless link and antennas radio-technical characteristics.

. ., . ., . ., 2010

539. .

. . , ,

, . .

- . - - , - . - . , - - .

- Hui D. Du [1], Tabiei A., Simitses D. J. [2]. ,

l/R 0,5 20. - 45. - , - . , - . , - 45.

- - .

38

0 90 - l/R 0,5 20. , - , - , - 90. , -.

1. Hui D. Du. Initial post buckling behavior of imper-fect ant symmetric cross-ply cylindrical shells under tor-sion // ASME : J. Appl. Mech. 1987. 54.

2. Simitses D. J., Tabiei A. Buckling of moderatelythick, laminated sylindrical shells under torsion // AIAA.1994. 32.

A. V. TomilovSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

STABILITY OF ORTHOTROPIC CYLINDRICAL SHELL UNDER TORSION

In this article the problem of stability of orthotropic cylindrical shell loaded with torque is solved. The influence ofthe angles of reinforcement on the critical parameters of an orthotropic cylindrical shell loaded with torque is ana-lyzed.

. ., 2010

629.76. . , . . , . . , . .

, ,

*

- - .

- - () .

- () - - (. 1).

[1] - - () () , , . - , . - - .

. 1.

- .

- , - .

* 02.740.11.0178 10-08-00064-.

,

39

- - [2]:

.

1 2 0

kt

Q c W c m i dtS = + , S S , ic , - -; W - , -

; .

m i ; kt , ; S - .

- .

, - :

1) (2025 %);2) (510 %);3) , -

(510 %);4) (2530 %). -

, 5575 %, - - () .

: -

;

, , -;

.

- (. 2).

. 2.

- 3040 %, , , 1520 % - 710 %.

1. - - : (.) / ; . . . . ; . : . . [ .]. , 2010.145 . 01200960927 ( -0 3).

2. . . - . . : - ,2000.

V. I. Trushlyakov, V. Yu. Kudentsov, A. Yu. Kazakov, I. Yu. LesnyakOmsk State Technical University, Russia, Omsk

MODERNIZATION OF THE EXPERIMENTAL STAND TAKINGINTO ACCOUNT MINIMIZATION OF POWER EXPENSES

The problem of power expenses of the existing experimental stand for modeling of processes of gasification of therests of liquid rocket fuel in tanks of a step of the carrier rocket is considered and ways of their minimization taking intoaccount available material means for modernization are offered.

. ., . ., . ., . ., 2010

40

629.735.025.1. .

(), , . .

-, ,

. , - , . . 1,52 /. , .

- , -, , - . - . . 45 Flow Vision, -, - , - [1].

- - -. , , -- - , , - [2].

- , - - ,

- , - - [3].

- , - , , Star CCM - - , -, -.

, - - 1, , 2 - 3, 4. 5 - , , - - - 1,52 /.

Star CCM:1 ; 2 ; 3 ; 4 ; 5

,

41

- -, , - . - , - , - . - 180.

- .

, - .

1. . // .2001. 5.

2. - : . 2362707 . : (51) 64 11/00 (2006.01) 64 27/18 (2006.01) / . ., . . .29.10.2007 ; . 27.07.2009, . 21.

3. : . 2269028. : (51) F 03 D 3/00 (2006.01) / . ., . . . 12.11.2002 ;. 27.01.2006, . 03.

N. U. UshakovUlyanovsk Higher Aviation School of Civil Aviation (Institute), Ulyanovsk, Russia

A. L. ShpadiCJSC Helicopter-MI, Kazan, Russia

UNCLOSED AIRFOIL WINGS

Original structures of non-standard geometry wings are offered. Operating components interacting with outdoorenvironment are designed as a kind of unclosed wing airfoil. An example of such wing airfoil application in rotor-typewindmill model is given. High efficiency of rotor-type windmill at a wind speed of 1.52 m/s is shown. Application areais aircrafts, light sail, rotor-type windmills.

. ., . ., 2010

623.783. . , . .

. . , ,

.

- , , - , . . . , - , .

. 1

(. 1).

(. 2).

. 2

42

, - , . 3.

. 3

- (. 4).

. 4

L. V. Shumkova, A. A. Grunin

Siberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

DESIGN OF COMPOSITE FRAME OF SOLAR ARRAY WING

Questions of projecting of composite frame of solar array wing are considered.

. ., . ., 2010

,

43

45

629.783. . , . .

. . , ,

, .

- () (), - - , , . , . . - - () . - .

, - . , - - , , , , . , - - - - - .

-

. -. , - .

- , . . , . , . , - - - .

. - - - .

A. V. Balanovsky, A. O. KuznetsovaJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

CONSTRUCTIONAL IMPROVEMENT OF ENERGY RESOURCESFOR SPACECRAFT BREAKUP

The constructive improvement of energy resources which leads to improved performance parameters of spacecraftbreakup is presented.

. ., . ., 2010

46

629.783.017. . , . .

. . , ,

, .

( -) - - . , - NASA, - -, . - .

- -1000, -2000 () . (), () () . 1.

() - , , - . , ()., , (). - - .

- , - .

, , , - . . 2.

- . , , , - . . 3.

- , - , , , - .

. 1.

47

A. V. Balanovsky, S. V. RomaschenkoJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

SYSTEM OF DETACHABLE JOINT FOR ISOGRID PRIMARY STRUCTURES

The system of detachable joint for divided junctions in isogrid primary structures gained a wide use in the field ofspace engineering industry is presented.

. ., . ., 2010

629.78.08.018. . , . .

. . , ,

, , , . , - .

- . , - - . , - - . , - , - . - , (- - ).

- . - : , -, - .

. - .

. , -, - , .

. 2.

. 3.

48

() , -

, .

( ), - , - ( ), - ( ), - (. ).

. -, 3- , , - , -, , .

. , - (, (- ), ), .

S. S. Bezrukih, A. A. KuptsovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

MODELING THE WORKPLACE FOR MAKING LARGE-SIZETRANSFORMED AERIALS

Modeling is used to create models, diminished copies of large-size constructions that increases productiveness notcarrying heavy expenses for production and assembling. Scale-adjusted modeling the workplace for welding, measuringand working off the large-size transformed aerials is presented.

. ., . ., 2010

620.1.08. . , . . , . . , . .

, , -. .

. . , ,

- - . . .

- - . - (, ) - .

- , , ,

-. [1].

- API Tracker T3, . (-), - .

49

-. . 1, - . 2.

- - :, , , - (. 3), , , . - - : , - ; -, ; -

. , . 4.

-. - , , - . - , , - , - OA (. 4).

. 1.

. 2. ()

. 3.

50

. 4.

, , - , , . , -, , . . - - OA. - , - , A, . . ( ), - .

, -, , - , - .

- 25 . - - ( 400 ). - , - -

. 1,55 0,63 , - . - - .

, , 25 .

1. . ., . ., . . - - - // : XIII . . . : 2 . ; . . . . ; . . -. -. , 2009. . 1.

D. N. Vasiliev, S. L. Druzhinin, I. M. Evdokimov, M. A. ZaitsevLaser Systems Ltd., Russia, Saint-Petersburg

V. M. MikhalkinJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

HIGH-PRECISION MEASUREMENTS OF GEOMETRICS OF SIZE-STABLE STRUCTURESIN THERMAL AND VACUUM CONDITIONS

The design of laser measuring instrument for high-precision measurements of geometrics of size-stable structuresin thermal and vacuum conditions is proposed. The features of measurement procedure are considered. The resultsof preliminary tests are shown.

. ., . ., . ., . ., . ., 2010

51

681.7:004.4. . , . . , . .

- , ,

. . , . . , . .

. . , ,

- , . - ~ 0,1 . - ~ 37 2 - ~ 0,1 110 .

. - [1]

D = d L / f,

d -; L ; f - .

, - :

22,3 14,9 ; 4,7 4,7 .

CANON EOS 500D , 18 200 . , , 100 % -, 0,2 . - - .

- - .

. CANON EOS 500D 18 200 .

, 0,1 , 10 , . 1.

. - , 21 , - . 2.

: -

( - 4 ), .

. 1. 0,1

. 2. - , 21

. - ~37 2 - ~ 0,1 110 . - -

52

( - 2) - ~0,1 .

1. ., . . . :- , 2006.

A. G. Verhoglyad, S. V. Kalichkin, V. S. BazinTechnological Design Institute of Scientific Instrument Engineering

of Russian Academy of Sciences, Siberian Branch, Russia, Novosibirsk

V. I. Halimanovich, V. M. Mihalkin, V. V. HolodovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

VIDEO MONITORING SYSTEM OF LARGE-SIZE TRANSFORMABLECONSTRUCTION DEPLOYMENT

Producing large-size transformable constructions requires to solve the problem of video monitoring their surfaces at highspace resolution in real time while the constructions are being deployed. It is important to control the parts of ~ 0,1 mm sizeat the whole product surface. The goal of the research is to search a technical solution for designing video monitoring sys-tem to register images of objects of ~ 0,1 mm size while the distance to the object points is within 110 m.

. ., . ., . ., . ., . ., . ., 2010

629.7. . , . . , . .

- , ,

. . , . .

. . , ,

. , - , .

- . , - ( , - , ).

, - .

- , - , - .

- -.

, .

- , - .

. , , - - [1], - . - - , . , - , - , , . . . -

53

- .

- ( ) [2] .

1. :. / . . . . . : ,2004.

2. Numerical Recipes. The Art of Scientific Comput-ing / H. P. William [et al.]. 3d ed. ; Cambridge UniversityPress. Cambridge, 2007.

A. G. Verhoglyad, I. A. Vyhristyk, S. N. MakarovTechnological Design Institute of Scientific Instrument Engineering

of Russian Academy of Sciences, Siberian Branch, Russia, NovosibirskN. S. Zinin, V. V. Christich

JSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

ALGORITHMS OF HEAT TRANSMISSION RATE CONTROLIN THE THERMOVACUUM PROBATION PROCESS

Algorithms to control temperature distribution at the tested object surface are given. Control process is repeated,each iteration includes empirical linear thermal process model and performance of linear regulation made within themodel adequacy.

. ., . ., . ., . ., . ., 2010

061.61:629.78. .

, , -. . , . . , . . , . .

. . , ,

-. , , , , , .

- -- . , - 2010 . - , . . ( ), -: , .

- : - , - , , , - .

, , . , . , , - . - - .

-, , , , -, -.

, -

54

( ) . - . - , - . - . - -. , , - , - , -.

: -

; -

; -

, - ;

- - -.

: ; .- : -

, - , , -;

- - .

- .

- - :

- ;

- , - , , , -;

- ;

, ;

- , - ;

, - - ;

- ;

- , - - .

, , - - , - -- .

V. V. GolovanovaArsenal, Construction Department, Russia, Saint-Petersburg

V. V. Dvirniy, S. G. Kukushkin, D. A. Matronitskiy, R. P. TurkenichJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

SOME FEATURES OF FORMATION OF SCIENCE-INTENSIVE ENTERPRISESINTEGRATED STRUCTURES

The article describes formation features of science-intensive enterprises integrated structures. A large integratedstructure provides ample opportunities to accelerate the release of science-intensive products using human resources,financial and information support, corporate manufacturing and quality support.

. ., . ., . ., . ., . ., 2010

55

629.76.036.5:66.07. . , . .

. . , ,

- .

- , - (100140 /2), -, -. - . - 60 /2, 16,8 .

- , ( - )

. , - , , , - , -, . - . - - - .

- .

V. I. Dorokhov, A. P. LadyginJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

REASONS OF UNSTABLE FUNCTIONING THE GAS SUPPLY BLOCKUNDER XENON THROTTLE CONTROL IN POSTCRITICAL

STATE AND STEAM-AND-FLUID AREA

The reasons of output pressure instability in the process of xenon throttle in postcritical state or steam-and-fluidarea are studied.

. ., . ., 2010

621.396.67. . , . .

. . , ,

-.

- , - .

: -. - .

56

- .

1 (. 1) - 0,30,5 , , - , . - 2, -, , , , , - . - .

4 3 2 1

. 1.

(-) (. 2), - .

4 (. 1)

. , - . - , - . - 4 .

. 2.

- - , - .

D. A. Zhevlochenco, V. I. KuzoroJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

DESIGNING OF THE VARIABLE SECTION BAR FOR LARGE-SIZEDTRANSFORMED REFLECTORS

A variant of design of a bar of disclosing for large-sized transformed reflectors is considered.

. ., . ., 2010

621.372.83.001.24. . , . .

. . , ,

-

- .

- . . - - - .

-

311 630670 . . -12 580600 . , ( , .).

57

-. , - , ( 115,5 6110 ). - 66 , . - , -, , - , .

. . - (. 1, 2).

. 1

, - , - .

, , . . - - (. . 1). , . 1, . 2: . - , -

-, . -, 60 , - 311 5070 .

. 2

(. 3).

. 3

, - (- ), - cos ().

R. V. Zaitsev, M. M. MikhnevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

DIFINITION OF THE OPTIMAL CONSTRUCTION OF INDUCTORFOR SOLDERING OF WAVEGUIDE DISTRIBUTIVE SYSTEMS

OF SPACE COMMUNICATION SATTELITES

The technology of definition of the optimal construction of inductor for soldering of waveguide distributive systemsof space communication satellites is presented.

. ., . ., 2010

58

629.78:531.395. . , . .

. . , ,

*

- .

, , : - , - , - . . -, -, , -, - , , - , - . , , , -, -.

, , - - , : , -. , , , . , - - -. - - -, - , - - .

- , -

, - . - , - - - , - . - , -- , - . - () . - : - ; , - , , ; , - , ; - , -; , ( ) - - ( ) .

, - , , - , - .

* - ( 776 20 2010 .) - 20102013 .

59

- , - . 20 . , , - . - (- )

(), . - - . - - . - , , - -. - - . - - .

V. N. Zimin, A. N. SdobnikovBauman Moscow State Technical University, Russia, Moscow

THE FEATURES OF LARGE TRANSFORMABLE SPACESTRUCTURES DYNAMIC SIMULATION

Some features of mathematical model formulation for analysis of large transformable space structures deploy dy-namics are considered.

. ., . ., 2010

621.372.83.001.24. .

. . , ,

- .

. . 31 - .

( ):

- (0,651,4 ) - ( 6 ) ;

- ;

, -;

;

1520 %, - 22,5 .

, - . - (66 ), , - , - , , (. ).

- - - .

60

:1 ; 2 ; 3 - ; 4

; 5 ; 6 ;7

: -

; -

- .

. - , , -, , . -. - , - , - .

S. K. ZlobinJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

SOLDERING OF ALUMINIUM THIN-WALL WAVEGUIDE STRUCTURESWITH THE USE OF RADIO-FREQUENCY HEATING

The equipment and technology of assembling with soldering of elements of waveguide distributive systems of spacecommunication satellites using radio-frequency heating are presented.

. ., 2010

629.78.08.018. . , . .

. . , ,

, - .

- , - , - .

, - , - -, . - . 1.

- -

- , - .

, - , - , - - - , - , -

61

- , - - - . (-). - , -, - , - .

- - . 2( 118 ).

- - - , .

. 1.

. 2. -

P. A. Koltunov, A. A. DrozdovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

FORMATION OF THE CURVILINEAR REFLECTING SURFACE OF ANTENNAS

In this article the device applied at assemblage of a power skeleton of aerials and control of a profile of a curvilin-ear reflecting surface is described.

. ., . ., 2010

62

629.78.064.55. . , . . , . . , . .

. . , ,

, (), .

() (), - - ().

- -. - (-68), -. - Ga-In ( = 15,3 ) Ga-Sn( = 20,4 ).

- , - - ( ) , .

. -.

, -. , - -. - . - . ( ) - .

5,9r = /3, 6,1r = /3, . . .

, . , , ( ) , - . , - , . - - 0,01 .

, - . - ().

I. A. Kravchenko, A. A. Konovalov, L. M. Borodin, A. V. LekanovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

CREATION OF THE BASE TEMPERATURE STANDARD FOR THE SFD WORKINGOFF THE SYSTEM OF PRECISION THERMOSTABILIZATION

The device ensuring highly stable temperature on the board of the space flying device (SFD) which can adjust tem-peratures of all elements SFD is considered.

. ., . ., . ., . ., 2010

63

531.010. . , . . , . .

. . , ,

-, .

. - , - , , . - , , , . - . . 1.

. 1.

- () - , - (, . .). - 2 3 (. 2). , - , - 1. , , . - 24 .

24 5, 6. -

15, - 3. , 7. - , - 24 . - 8, 9, .

. 2.

- . - 7 8. - - ( -). - 14. , - - 13.

,, - , - - , -.

64

P. A. Kraevsky, E. A. Shevtsov, E. A. DavletbaevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

PRECISION DEPLOYABLE MECHANISM OF THE MAIN MIRROROF MILLIMETRON SPACE OBSERVATORY

The authors submitted Precision Deployable Mechanism of the main mirror of Millimetron Space Observatorybased on screw-nut principle.

. ., . ., . ., 2010

629.78:531.395. . , . .

. . , ,

.

- - - . - .

- , . , , . - , , - -, , . - - .

- - -

. , - , - - , - .

- , , - . - -, - . - , ( ), - , , , - . - . EULER MD.Adams. - .

A. V. Krylov, S. A. ChurilinBauman Moscow State Technical University, Russia, Moscow

SIMULATION OF DEPLOYMENT OF LARGE SPACE ROD STRUCTURES

Simulation of deployment of large space rod structures using modern bundled software is discussed.

. ., . ., 2010

65

629.78.023.222:533.599. . , . .

. . , ,

-71-3, - . - , , 13,2 . - , -2, - -5.

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, - - , , -. , - , , . ., , . , , ~103 . . - , , () (). , - , -. , , . - - . , , - [1].

- -71-3. - 175907 .

.

- 50 100 /. 150 , - 80 200 . -5. - - . MPS 15/10 PC, - 13,2 . - - 15 - 700 . , , - . - - 2- . - - -2. - -, . . . - , - 0,64 IJ = .

-71-3

- -

,

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-,

,

/-

230 2,5 130 1,6

260 4 120 1,8

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66

, - . -71-3 - - , .

1. . . - // - . : , 2008.

S. D. Kryuchek, V. A. HarlamovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

UPGRADING OF THE VACUUM COATER FOR LABORATORY ADJUSTMENTOF THE TECHNOLOGIES OF SPACECRAFT TEMPERATURE-CONTROLLING

COATING MANUFACTURING

Upgrading of the vacuum coater UVN-71P-3 designed for laboratory adjustment of the technologies of tempera-ture-controlling coating manufacturing is presented. The coater has a magnetron coating system that is supplied with apower unit working at the frequency of 13, 2 KHz. Temperature, resistance sensors, precision system of gas puffingSNA-2, thickness and coating speed measuring system Micron-5 are installed.

. ., . ., 2010

629.78.08.018. .

. . , ,

, -, .

- - - -.

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. - 17 - .

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67

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) -.

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- , - .

- - - , - , , , , -, , .

A. A. KuptsovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE INTELLIGENCE SYSTEM OF WEIGHTLESSNESS IMITATION

The system of weightlessness for performance monitoring, weight item determination, verifications of stability ofwork of large-size transforming constructions.

. ., 2010

68

621.867. . , . . , . . , . .

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. . , . . , ,

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2 3

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z z

=-

.

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- - .

- - .

- 160 625, 60 , 52 520 .

- 1,5 3065.

- 5000.

1 1,75 - 30 % .

, , , .

- , 1,52,5 , - .

69

A. V. Lekanov, V. G Porpylev D. A. Cherepanov, P. V. IlyinJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

P. N. Silchenko, D. E. GruzdevSiberian Federal University, Russia, Krasnoyarsk

THE FEATURES OF CALCULATION AND DESIGNING OF REDUCERS WITH TOOTHEDGEARINGS ON THE BASIS OF GEARING ON PASCAL SNAILS FOR DRIVE GEARS

OF DISCLOSING OF LARGE-SIZED DEVICES OF SPACE VEHICLES

The features of calculation and designing of reducers with tooth gearings on the basis of gearing on Pascal snailsfor drives of single action are considered at disclosing of large-sized transformed designs of space vehicles are pre-sented.

. ., . ., . ., . ., . ., . ., 2010

629.78:621.8. . , . . , . . , . .

. . , ,

. . , . . , ,

-

- - (, .) .

- -, .

- , -- , - , .

- , - ( ) .

- , .

; ; - .

2K-h. - -, . - 3 , 2K-h.

- - - ; - - - , - .

70

A. V. Lekanov, V. G. Porpilev, D. A. Cherepanov, P. V. IlynJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

P. N. Silchenko, E. S. NovikovSiberian Federal University, Russia, Krasnoyarsk

SUBSTATION OF DESIGN DECISIONS OF PLANETARY DRIVES OF DISCLOSINGOF LARGE-SIZED DEVICES WITH THE BIG INERTIAL WEIGHTS

Methods of maintenance of demanded functional-operational indicators of planetary transfers for drives of disclos-ing of large-sized devices (aerials, batteries solar, etc.) with the big inertial weights are considered.

. ., . ., . ., . ., . ., . ., 2010

629.783. . , . . , . .

. . , ,

-. , .

(. 1) - [1]. - , . - (. 2), - [2].

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. 3.

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-, . , - (. 5). - (. 6).

. 4. . 5.

71

, - - , - . - - .

. 6.

. - , - . - . - . - , - . -

COSMOS/M - . - . 7.

. 7.

1. Next Generation UltraFlex Solar Array forNASAs New Millennium Program Space Technology 8 /B. Spence [et al.] // IEEE Aerospace Conference,Big Sky, Paper-NGU ST8. 2005.

2. Stribling R. Boeing High Power Thin Film SolarArray // Proceedings of the 4th Int. Energy ConversionEngineering Conference and Exhibit (2629 June 2006,San Diego). San Diego, 2006.

A. V. Lopatin, V. A. Nesterov, L. V. ShumkovaSiberian State Aerospace University named after academician M. F. Reshetnev, Russia, Krasnoyarsk

MODEL OF THE ANISOGRID COMPOSITE FRAME OF A SPACECRAFTDEPLOYABLE SOLAR ARRAY

A model of the anisogrid composite frame for the spacecraft solar arrays is presented. Modelling and design optimi-sation of the frame solar arrays is shown.

. ., . ., . ., 2010

621.372.83.001.24. . , . .

. . , ,

. . , . . , . . , ,

-

- - , -- .

- () - -, - (-

) , , [1].

- - - , -

72

[2; 3]. - , - - , - .

-- - - - .

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- , - -. , - .

- . - - , - - .

- , - -, - .

, - DHC - , . - , - .

- - - , - - . - - - - , .

[3] - - - -, - - .

- , - , - - , .

- - . . - - - .

1. . ., . ., . .- - // . 2006. 9. . 5357.

2. . 2317184 . - / . . , . . -, . . [ .] ; - . . . . . 2005133293/02 ; . 28.10.2005 ; .20.02.2008, . 5.

3. - - / . . [ .] // . 2008. 2. . 5358.

73

M. M. Michnev, V. U. GusevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

P. N. Silchenko, I. V. Kudryavcev, V. I. IvanovSiberian Federal University, Russia, Krasnoyarsk

MAINTENANCE OF THE TECHNOLOGY OF BLOCK ASSEMBLAGEWITH SOLDERING OF LARGE-SIZED WAVEGUIDE-DISTRIBUTIVE

SYSTEMS OF SPACE VEHICLES

The technique of settlement-analytical support of the technology of assemblage by soldering from separate elementsof wave-distributive systems of space vehicles, for the purpose of minimization of the technological errors saved up attheir manufacturing and maintenance of the improved functional-operational characteristics is offered.

. ., . ., . ., . ., . ., 2010

629.78.01. . , . . , . . , . .

. . , ,

95

- .

-2000 - , 95 - 1.

95 -. - -, , . - ,, .

95 - 6 , - . - - , .

1269 2,5 , - 95 .

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80 , - 95 .

:

1) 5 ;

2) ;3) ;4) 2

;5) ;6) ;7)

-;

8) ;9) ;10) . -

- 15163, : 0,3 /, 1 .

- 3 - , - 1.9007385.

2 - 15163, : 0,3 /, 1 .

74

-.

- .

-:

1) ( - ) ;

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- , 0,05 .

. - , 0,1 , 0,05 .

- - 15163 0,1 /.

, 95 6:

- 4,8 0,5 ;

- 3,9 0,46.

- 95 - :

- - , -, ;

- - - ;

- - (- 3) 2,3 ;

- - - - 1.9007385.

M. M. Mihnev, V. V. Zlotenko, N. N. Ishenina, A. G. MasanovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE FEATURES OF THE PRODUCING TECHNOLOGY OF FRAMETYPE PARTS FORMED OF ALUMINUM ALLOY V95

The technology of production of large dimension frames with machining division into phases and the use of heat-and cold treatment technology is presented.

. ., . ., . ., . ., 2010

621.396.67. . , . . , . . , . .

. . , ,

32

, - .

- () -- , 32.

32 - = 1106 1

100 . - , - . (

75

s = 46 /2; - ( ) = 41 %; ( ) = 72 %).

32 , - . - - . - .

1. .

- W508S Willemin-Macodel. 36 - (. 1).

, , MITSUBISHI, - ( 0,5;0,8 ).

- , - .

2 ( 2- ); 30 000 /; - 40 /; 0,01 .

. 1.

2. . -

: ; - -

, .

. , . - . -

. - -, (. 2).

-- . - .

: - () - - .

-, - (. 3).

. 2.

. 3. -

:

- , ;

- 32 ;

- .

76

M. M. Michnev, V. V. Zlotenko, N. N. Ishenina, T. L. NekrasovaJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE PECULIARITIES OF THE PRODUCTION TECHNOLOGY OF FINE-SIZEDWAFFLE COVER TYPE DETAILS MADE OF 32NKD-ALLOY

The article presets the results of searching the technology of fine-sized Waffle cover type details production, in-cluding determination of a mechanical processing mode and choosing an optimal method for removing wire-edges.

. ., . ., . ., . ., 2010

658.5.011.56. . , . . , . .

. . , ,

- -

- - -.

- - - . - , , - .

, - -, -- -.

. - - - , , , .

. , - - -: , , , - . , - , .

. - - . - -:

1) , - ; (- ); ( );

2) -, ; - , -; -;

3) , ; ; ; .

- - - -, - -; - ; .

-

-

,

77

M. M. Mikhnev, V. V. Zlotenko, K. N. PolyaevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

INFORMATION SEARCHING SYSTEM OF TECHNOLOGICALPROVIDING GLOBUS-M RESOURCES

The assignment and structure of the original Information search system of technological providing GLOBUSMresources are considered.

. ., . ., . ., 2010

621.372.83.001.24. . , . . , . . , . .

. . , ,

. . , . . , ,

-

- - - - .

- - () , , [1], , .

- - , - [2; 3]. - , - - - .

- , , - , - - - , .

- - . -- - , - - ()

, -.

- - , - -. , - , .

- -, ().

- , - , - . - , - , -, , - .

- [2; 3], -, -

78

- .

- - - , - - .

- [3].

- . , -, - Ansys (Nastran .) - . .

, -

- .

.

1. . 2317184 . - / . . , . . -, . . [ .] ; - . . . . -. 2005133293/02 ; . 28.10.2005 ; .20.02.2008, . 5.

2. . ., . ., . .- - // . 2006. 9. . 5357.

3. - - - / . . [ .] // . 2008. 2. . 5358.

M. M. Michnev, V. N. Nagovitsyn, O. B. Gotseluk, V. U. GusevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

P. N. Silchenko, I. V. KudryavcevSiberian Federal University, Russia, Krasnoyarsk

THE MAINTENANCE OF DURABILITY OF WAVE-DISTRIBUTIVE SYSTEMSFOR LARGE-SIZED TRANSFORMED DESIGNS OF SPACE VEHICLES

The issues of settlement-theoretical support of assemblage by soldering from separate elements of wave-distributivesystems of space vehicles for maintenance of conditions of their general and local durability taking into account thetechnological errors saved up at manufacturing are considered.

. ., . ., . ., . ., . ., . ., 2010

629.76/.78.001.63. . , . . , . .

- - -, ,

, - , . - .

- () - - -

- .

70-

79

, - - , - , - . 0,01 - R = 1,25 80 , 235 , 0,2.

- - - ( ) 0,5 , -, , - ( , ).

( - ), - , , .

-- - , - , - .

, , , :

- - 2- - ;

;

- -, , ;

- m = 0,3 .

- - - :

- ;

- ;

m = 0,3 ;

(), .

- , , - - , - :

0,997;

0,2 0,5;

- ;

5 ( 80 400 ) - -;

235 2100 , - - 0,5 5 .

- - (. -) , (. ), - - .

, , - , , - .

, - : - .

- , , . - , - , , .

80

D. V. Nazarov, S. V. Tyulevin, N. V. EreminFSUE State Research & Production Space Rocket Centre TsSKB Progress, Russia, Samara

THE CREATION OF A NEW GENERATION OF ELECTROMECHANICALWAVE DRIVE GEARS OF TRANSFORMED SYSTEMS OF SPACECRAFTS

WITH LONG-TERM ACTIVE EXISTENCE

In the article the necessity of creation of electromechanical wave drive gears of new generation is proved, the basicconstructive-technological decisions applied at their modernization are described. The applicability of wave toothedgearings of new generation as double purpose technologies is considered.

. ., . ., . ., 2010

621.396.67: 629.78. . , . . , . . , . .

. . , ,

, - , .

- . : (), , .

- , - , - - . - 6 , 12 , 6 6 - .

-, ,

, .

- -: , - , -. , .

, -. - : , -. 3 : -, . - .

, -, - . - , - (), .

Maxon MC-32 SKF - :

100 ; 204 ; 0,02 ; 0,005 .

81

(70+80 ), - .

(, ) 6 . - - . - . -, .

, . . , . - -

- .

-, - , . - , - 6 - , - . , - .

, - , - . - - .

A. A. Pesternikov, S. A. Komarov, S. O. Boyko, S. G. HaritonovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

REFLECTOR POSITIONER

In this article the main problems of the six degrees of freedom electromechanical reflector positioner for space ap-plications designing are considered.

. ., . ., . ., . ., 2010

629.78.023.222. . , . . , . . , . .

. . , ,

-

(), - (). - - (As) .

- () As - . , - - As - ( ). - .

.

, - -

4, - .

:

1 - (); 2 ; 3 - ; 4 ; 5 ; 6 -

;

82

Ast (Is) - ( - ):

4

s cos( )n d

td

E T QAs

I Fs -=

j, (1)

Ast As ; n ; d 4 , ; Q - .

As

Ast = Ast As0, (2) As0 As ;Ast As.

Q Q = (k d), (3)

k , ; C -

, / ( , ).

As (Ast) - - :

( )1tAs A e b-atD = - , (4) , , As ; t - .

- - - - . - 4 - As .

M. M. Polevshikov, I. V. Yevkin, A. B. Kuznetsov, S. G. AntonovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

PHYSICOMATHEMATICAL MODELING OF ABSORPTANCE AUGMENTATIONOF THERMAL CONTROL COATINGS IN FULL-SCALE CONDITIONS

The calorimetric sensor (CS) used for full-scale tests of thermal control coatings (TCC) is presented. The physico-mathematical modeling of solar radiation absorptance (As) augmentation of TCC procedure is presented.

. ., . ., . ., . ., 2010

629.76/.78.001.63. . , . . , . . , . .

- - -, ,

, - . , .

[1] () . - [1], - . (0,20,4), 0,50,7 , - 1020 , , - , -. : - -

. - .

-, - - .

-, , , - .

-, [2] , -

83

. , , . - . .

-, , - , - - .

, -, - (. . - -, - ) - . () () : - ( ) ( - , , - ).

1. , - = 0,50,7

( ) .max .K R = -r -

.max max K Wr = r + + D

( ) ( ).max max 2 2K D D D Dr = r + - + - .2. d -

() () :

.minRd = -r

( ) ( ) min 2 2R D D D D d = - r + - + - d = 0,30,4 .3. (

) .

, . -

. - - 1020 :

;

0 20; 0 20.4. . -

, . .

. > ,

, ( ) -. , - .

< , - . , , .

5. .

, , .

- - , - . - .

, . .

-, , - , - .

1. . . :. . . : . ., 1981.

2. 1038781 - . ., 1981.

. P. Prudnikov, S. V. Tyulevin, D. V. Nazarov, . V. LivochkinFSUE State Research & Production Space Rocket Centre TsSKB-Progress, Russia, Samara

THE SELECTIVE ASSEMBLY OF WAVE GEARS DRIVESOF SOLAR BATTERIES OF THE SPACE VEHICLE

The technique of selective assembly of wave gear drives of the solar batteries using five criteria for an estimation ofgeometry and mutual interface of elements of drive is offered. These criteria, their calculation and the results of theirpractical use are described.

. ., . ., . ., . ., 2010

84

621:53.08. . , . .

. . , ,

.

(), -, , - , - , - - .

- .

- - , , . - - .

- . , :

- ;

, - -;

- ( - - (). - 30 % , , , ).

:

;

- - .

S. V. Romaschenko, A. V. BalanovskyJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE ISSUES OF DEFINITION OF HIGH-ACCURACY CENTER OF MASS COORDINATEOF LARGE-SIZE TRANSFORMABLE REFLECTORS

The issues of definition of high-accuracy center of mass coordinate of large-size transformable reflectors and themethod to deal with that kind of problem are presented.

. ., . ., 2010

621.396.67. . , . .

. . , ,

.

, 6, - . - , , .

. , - . , -.

85

E. A. Sapronov, E. A. LaptevJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE DESIGNING OF THE PIN-AND-EYE CONNECTIONWITH HIGH ACCURACY DEPLOYMENT

An optional construction of pin-and-eye connection with high accuracy deployment is presented.

. ., . ., 2010

629.7.01:539.4. . , . . , . .

- ,,

- , . , - .

() - () , - . , - , - .

- , . -, - . - , - [1; 2].

, - , , -, -.

- 5 2- 20 50 .

(),Plascore (), - () 5052, 5056 18 127 .

, , - , , , - - .

- () [35] -, .

- - 1 0118892 . [6].

18 , 20 .

, .

. -, , -.

- , , - .

1. . ., . ., . . . . : -, 1975.

2. . ., . . - : . . : , 1991.

3. : 2 . . 2 / . . ; . . . . - [ .] ; . . . . . : -, 1988.

4. Properties of Honeycomb Materials TSB120 //Hexcel. 1984. Revision. (USA).

5. Honeycomb Core and Engineered Products //Plascore. 2010.Inc. All Rights Reserved.

6. 1 0118892. -. . ., 1992.

86

, ,

t

, , , , d,

g, /3,

h,

xz yz Gxz Gyz

(PAMG-XRI-2.0-3/16-0007P-5056)

5056 2,75 18 36,5 18 3,1 11,4 2,4 1,6 410 234

36,3 4,1 - 2,9 1,8 440 27337,5 3,3 12,7 2,5 1,6 439 27137,9 3,8 - 2,9 1,9 368 21938,5 3,7 - 3,0 1,8 474 24539,0 3,6 13,0 2,9 1,7 472 25039,2 3,9 - 2,7 1,7 423 215

2,5 23

40,2

20

3,4 11,5 2,5 1,6 366 222

5056

3,0 23 32,5 20 3,4 - 2,5 1,7 431 277 (PAMG-XRI-3.1-3/16-001P-5052)

5052 2,75 25,4 53,85 18 3,7 8,5 2,5 1,5 429 266

50,2 3,7 10,0 2,8 1,5 480 23723949,3 3,7 10,0 2,7 1,6 456 24750,6 - - 2,8 1,6 487 25551,4

20

4,1 9,0 2,7 1,6 442 2612- 2,5 30

46,7 18 4,5 - 2,7 1,6 487 267

V. I. Slyvynskyi, . O. Karpikova, G. V. TkachenkoUkrainian Research Institute of Engineering Technique OJSC, Ukraine, Dniepropetrovsk

COMPARATIVE CHARACTERISTICS OF THE DOMESTICAND FOREIGN ALUMINIUM FOIL HONEYCOMBS

The comparative analysis of specific comparative characteristics of aluminium foil cellular fillers produced by for-eign firms and the Ukrainian manufacturer is carried out. The problems allowing to raise the competitiveness of theUkrainian honeycombs in the world market are defined.

. ., . ., . ., 2010

621.396.67:629.78. . , . . , . . , . .

. . , . .

. . , ,

, , . , , .

, , - - , , .

, 1, 2, (. 1). - - .

87

, , - -. -.

. 1

- . , , - . . , - .

, , - , - ( ) . - , , (. 2).

. 2

, , - . 3.

, - 1; 2, 3. 2, - 4, 5.

. ( ) - (. 4).

. 3

, - , . 15, - (. 5).

. 4

. 5

1, 5 . 5 -, 1. 1 -, - . , 24 1, - , - . - . , - .

, , , .

88

V. A. Semenkov, V. V. Shalkov, A. V. Mashukov, O. K. Valishevski, D. O. Shendalev, A. K. ShatrovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE SYNCHRONOUS DEPLOYMENT OF THE TRANSFORMEDREFLECTOR ARM SECTION

The creation of the mechanical system which connection joints may be used in similar constructions almost without anycorrection is rather an interesting problem. Even its partial solving may greatly reduce their designing labour intensity.

. ., . ., . ., . ., . ., . ., 2010

621.396.67. . , . . , . . , . .

. . , ,

. - . - .

- , .

, , - - - . - - - , , - , - .

- - . - , 39 - 0,3 .

- - , - , - . - . - i- -, , - :

1 21 21 1

1 2

;i i

i i ii i TE E

s se = -m +a

2 12 12 2

2 1

;i i

i i ii i TE E

s se = -m + a 121212

,i

iiG

te =

1iE , 2

iE - ; 12

iG ; 12im , 21im

; 1ia , 2ia

- .

- () .

- - Lami-nate, MSC/PATRAN.Laminate , : , -, . -. : 1 - X, Y, Z; 2 X, Z; 3 , Y, Z. - - 3330 3025 . - - , - - MSC/NASTRAN. -. - 60 90 .

- ,

89

.

- . - , . - - . - .

, -, - .

- +60 ; +90 . - - - .

, -, . - .

- +60 - , 5 %, +90 C - 4 %. - +60 C 0,35 , 0,37 . +90 C 0,65 , 0,66 .

- - .

- -- .

N. A. Testoedov, V. M. Mikhalkin, G. V. Dvirnyi, M. Yu. PermyakovJSC Academician M. F. Reshetnev Information Satellite Systems, Russia, Zheleznogorsk

THE IDENTIFICATION OF THERMOELASTIC DEFORMATIONSOF SANDWICH PANEL FOR COMMUNICATION SATELLITE

The features of modeling of the sandwich panel are considered. The thermoelastic analysis of the panel is carriedout. The finite element model of the panel based on the results of termoelastic tests is verified.

. ., . ., . ., . ., 2010

629.78.023.222. . , . .

. . , ,

. . , - . , - - .

- () - - . - . .

. - , - , - , - -. , - -

90

r 1010/2 ( 108 /2). - . - - - - (, .) .

- - -. - (15 ).

(In2O3), - - -- . - , 0,010,02 . , - - RS n(. ).

,

- In2O3 (. ).

0,06 , - ( 0,1 ). , - - 5105 /2 - ( r = 5105 /2 0,25 , r = 2103 /2 2,5 ). - 0,020,05 .

- - , 6 . - .

- , - (1 ) 1,13,1 , - , (1,11,3 ). - 1108 /2, - In2O3.

, ,

. RS tS AS Er,

/2 2,22,4 371 Ge 0,61 0,15 0,24 0,69 2,2108 0,01 0,022 Ge + SiOx 0,59 0,14 0,27 0,67 2,1108 0,01 0,023 In2O3 + Ge 0,58 0,10 0,32 0,69 2106 0,01 0,064 In2O3 + Ge + SiOx 0,61 0,12 0,27 0,68 1,1106 0,03 0,065 In2O3 +Ge/-/Ge 0,67 0,05 0,28 0,68 1,6107 0,03 0,056 In2O3 + Ge + SiO2/-/Ge 0,67 0,05 0,28 0,68 1,1107 0,03 0,05

()

1,00E+05

1,00E+06

1,00E+07

1,00E+08

1,00E+09

1,00E+10

0 1 2 3 4 5 6

r ,

/

2

Ge + SiOx

Ge

2O3 + Ge+SiOx

In2O3 + Ge(2- )