UA7477U - Docking unit of filling lines of rocket launcher - Google Patents

Abstract

The unit for docking filling lines of rocket launcher contains the carriage with filler necks, which by their front ends interact with the filler necks of the rocket, rotary clamps, which are hinged on the upper filler neck and interact with the pneumatic cylinder with the help of three longitudinal rods. The unit is equipped with cylindrical adapter with a crosspiece, spring compensator with an axle box and the lock with housing, and horizontal stock, which are located consecutively and are fastened on the rear end of upper filler neck coaxially. Cylindrical adapter has three longitudinal cuts for the beams of crosspiece, which are connected with the longitudinal thrusts, the horizontal stock of the lock is located in the axle box of spring compensator and fixed on the crosspiece, and pneumatic cylinder is hinged on the lock housing.

Description

Description of the invention

The utility model refers to the rocket and space industry, and more specifically to ground equipment and 2 can be used to ensure the refueling of a rocket with fuel components.

There is a known unit for connecting the refueling lines of the rocket launcher, which includes a carriage with lower single-channel and upper single-channel refueling nozzles, which interact with the front ends of the rocket refueling nozzles, guide carriages and carriage drive see patent of Ukraine

Mo49712A, IPC 8640 5/00, P428 15/00, 2002. To ensure reliable fastening of the flanges of the 710 refueling nozzles and necks in the process of refueling the rocket, rotary grippers with a pneumatic drive are installed on the refueling nozzles | see author St. USSR Mo1049715, IPC RE16Y 23/02, 1980). The well-known unit provides remote docking of ground lines to the tail compartment of the rocket. At the same time, in order to prepare the rocket for launch, six channels for supplying working bodies should be placed in the tail compartment: - two channels for supplying fuel to the rocket tanks with a pressure of 5-7 kg/cm7; and - one channel for supplying compressed gas to the cylinders located in the oxidizer tanks, with a pressure of 200 kg/cm; - one channel for supplying thermostatic air to the tail compartment with a pressure of 1.1-1.3 kg/cm 2 (see patent

of Ukraine Mo58396А, IPC 8640 5/00, EO4Н 5/02, 2003 |.

The disadvantage of the well-known unit is its low performance due to the small number of channels. Therefore, in order to prepare a rocket for launch, it is necessary to have three known units, which complicates the design of both the rocket and the launcher.

The closest to the proposed technical solution is the unit selected as a prototype for connecting the fuel lines of the rocket launcher, described in the patent of Ukraine Mob9213A, IPC Vb640 5/00, BRATE 3/04, 2003. This unit contains a carriage with lower single-channel and upper multi-channel refueling nozzles, which interact with the rocket's refueling nozzles with their front ends, rotary grippers, which are hingedly mounted on the upper refueling nozzle and interact with the pneumatic cylinder with the help of three tons of longitudinal rods. The upper filling nozzle is made of two channels, while the pipelines of the channels are located in parallel | see author St. USSR Mobb6367, IPC E16! 39/00, 1972...

The disadvantage of the known unit is its poor operational qualities, such as: izo - large dimensions of the unit due to the design of the upper filling nozzle; - insufficient reliability of the pneumatic cylinder, which must ensure high tightness of the connection between the Me fueling nozzle and the rocket's fueling neck during a long time of filling and draining the fuel components "g" (up to 10 hours); - insufficient reliability of the connection of the lower thermostatic filling nozzle, because the mechanism of the Zakhvatov feed has many moving elements.

The basis of the useful model is the task of creating an improved design of the unit for connecting the refueling lines of the rocket launcher, which would allow to ensure the improvement of its operational qualities by introducing new elements and technical solutions into it, such as: - the presence of a cylindrical adapter with a cross, a spring compensator with with an axial sleeve and a lock Z 470 With a body and a horizontal rod, which are located in series and fixed on the rear end of the upper c fueling nozzle coaxially, while the cylindrical adapter has three longitudinal slots for the beams of the crosspiece, which are connected to the longitudinal rods, the horizontal rod of the lock is located in the axial sleeve of the spring compensator and is fixed on the crosspiece, and the pneumatic cylinder is hinged on the lock body, which allows the pneumatic cylinder to be used for a short time for fastening rotary grippers, and in the process of refueling and draining fuel components, the tightness of the joint provided with a lock and a spring-I compensator; - the presence of a spring-loaded longitudinal rod on each rotary gripper, one end of which is hingedly connected to an eye mounted on the outer surface of the rotary gripper, and its other end -I is installed in a longitudinal guide fixed on the upper filling nozzle, and a stop is mounted on it , at the same time, the axis that connects the rotary gripper with the longitudinal traction is installed in an additional "M longitudinal guide, fixed on the upper fueling nozzle, which allows simple and reliable means to ensure the spreading and lowering of the rotary grippers without an additional drive; - the presence of a horizontal lever, one end of which is hingedly connected to the free end of the horizontal rod of the lock by means of a horizontal axis, which is installed in the auxiliary longitudinal guides of the body, and (7 od5 of a double-armed lever, hingedly fixed on the body of the lock by means of an axis with the possibility of rotation in the longitudinal vertical plane, at this is the lower end of the biceps la is connected to the pneumatic cylinder, its upper end is hingedly connected to the second end of the horizontal lever, which has a protrusion interacting with its lower surface with the vertical stop of the housing, and the mounting axis of the two-armed lever on the lock housing is located between the ends of the horizontal lever, which allows you to ensure a rational arrangement of the upper filling nozzle; - the presence of a casing that is rigidly fixed to the upper fueling nozzle and in which a lower fueling nozzle is installed with the possibility of longitudinal movement using the rod of an additional pneumatic cylinder, the cylinder of which is fixed on the casing, and a mechanism for fixing the lower fueling nozzle, while at the front end of the lower fueling nozzle, a the bottom in the form of an inverted b5 Cone with a bushing for interaction with a spring-loaded cover installed coaxially inside the rocket’s refueling nozzle, and longitudinal holes are made on its cylindrical surface, the length of which does not exceed the height of the inverted cone, which allows for the docking of the lower refueling nozzle with the rocket’s refueling nozzle without use of a complex mechanism of rotary grips; - the fixing mechanism is made in the form of a vertical spring-loaded rod fixed inside

The lower refueling nozzle, and the lower longitudinal guide, mounted on the casing, in which two vertical holes are made consecutively, which interact on one side alternately with the vertical spring-loaded rod, and on the other side with the corresponding rods of the near and far vertical pneumatic cylinders, while the piston cavity the near vertical pneumocylinder, located on the side of the rocket's fueling neck, connects with the rod cavity of the additional pneumocylinder and the rod cavity /o of the far pneumocylinder, and the piston cavity of the far vertical pneumocylinder connects with the piston cavity of the additional pneumocylinder and the rod cavity of the near vertical pneumocylinder, which allows to reduce dimensions and weight the lower filling nozzle, because the pressure inside it is low; - the two-channel pipeline of the upper filling nozzle is fixed inside the external 7/5 pipeline movably in the axial direction, for example, with the help of a guide sleeve with radial brackets, which allows to increase the tightness of the joint due to the compensation of thermal deformations of the pipelines in the process of filling and draining fuel components.

The task is solved in such a way that the proposed unit for connecting the fuel lines of the rocket launcher, which contains a carriage with lower single-channel and upper two-channel 2o fueling nozzles, which interact with the front ends of the rocket's fueling necks, rotary grippers, which are hingedly mounted on the upper fueling nozzle and interact with the pneumatic cylinder with the help of three longitudinal rods, it is equipped with a cylindrical adapter with a cross, a spring compensator with an axial sleeve and a lock with a body and a horizontal rod, which are located in series and fixed on the rear end of the upper filling nozzle coaxially, while the cylindrical adapter has three longitudinal slots for the beams of the crosspiece, which are connected to the longitudinal rods, - the horizontal rod of the lock is located in the axial sleeve of the spring compensator and is fixed on the crosspiece, and the pneumatic cylinder is hinged on the lock body. Each rotary gripper is equipped with a spring-loaded longitudinal rod, one end of which is hingedly connected to an eye mounted on the outer surface of the rotary gripper, and its other end is installed in a longitudinal guide fixed to the upper filling nozzle, and a stop is mounted on it, when this axis, which connects the rotary gripper with the longitudinal thrust, is installed in an additional longitudinal guide, fixed on the upper filling station - nozzle. The lock is equipped with a horizontal lever, one end of which is hingedly connected to the free end "E" of the horizontal rod of the lock by means of a horizontal axis, which is installed in the auxiliary longitudinal guides of the case, and a double-armed lever, hingedly fixed on the lock case by means of an axis lock with the possibility of rotation in the longitudinal vertical plane, while the lower end of the two-armed lever is connected to the pneumatic cylinder, and its upper end is hingedly connected to the second end of the horizontal lever, which has a protrusion that interacts with its lower surface with the vertical stop of the body, and the mounting axis " double-armed lever on the lock body is located between the ends of the horizontal lever. The unit is equipped with a casing that is rigidly fixed to the upper filling nozzle and in which the lower filling nozzle Z is installed with the possibility of longitudinal movement using the rod of an additional pneumatic cylinder, the cylinder of which is fixed on the casing, and a mechanism for fixing the lower filling nozzle, while on the front end of the lower filling nozzle the nozzle has a bottom in the form of a reverse cone with a custom for interaction with ;" a spring-loaded cover installed coaxially inside the rocket's refueling nozzle, and on its cylindrical surface there are longitudinal holes, the length of which does not exceed the height of the reverse cone. Fixation mechanism

It is made in the form of a vertical spring-loaded rod fixed inside the lower filling -I nozzle, and a lower longitudinal guide mounted on the casing, in which two vertical holes are made in series, which interact on one side alternately with the vertical spring-loaded rod, and on the other side with o by the corresponding rods of the near and far vertical pneumatic cylinders, while the piston cavity -I of the near vertical pneumatic cylinder, located on the side of the rocket fueling neck, is connected to the -4 50 ShtKov "cavity of the additional pneumatic cylinder and the rod cavity of the far vertical pneumatic cylinder, and the piston cavity of the far vertical pneumatic cylinder is connected to the piston cavity of the additional pneumatic cylinder and the rod cavity of the near vertical pneumatic cylinder.

The two-channel upper filling nozzle is made in the form of two pipelines installed coaxially, while the inner pipeline is fixed inside the outer pipeline movably in the axial direction, (7 55 for example, with the help of a guide sleeve with radial brackets.

To explain the design of the device and its operation, drawings and its detailed description are attached. The drawings show: - fig. 1 - a general view of a launcher with a rocket (the unit is docked to the rocket); - in fig. 2 - general view of the launcher with the rocket (the unit is docked to the rocket); in - in fig. C - general view of the unit; - in fig. 4 - view B fig. C (front view of the unit); - in fig. 5 - view E of fig. 6 (view of the castle from above); - in fig. 6 - remote element Г fig. C (position of the lock when securing the rotary grips); - in fig. 7 - remote element Г fig. C (position of the lock when unfastening the rotary grips); 65 - in fig. 8 - remote element A fig. 1 (general view of the junction of the upper filling nozzle and the filling neck);

- in fig. 9 - section F-F fig. 8 (cross section of the joint); - in fig. 10 - view D of fig. 4 (general view of the lower filling nozzle); - in fig. 11 - remote element B fig. 1 (general view of the junction of the lower filling nozzle and the filling neck); - in fig. 12 - section I-I fig. 10 (general view of the locking mechanism).

The proposed device consists of a unit 1 for connecting fuel lines to the tail compartment 2 of the rocket 3, a niche 4 in the launcher 5 and a protective visor 6 with a seal 7 (Fig. 1, 2).

Unit 1 (Figs. 3, 4) consists of a carriage 8 with radial guides 9, upper 10 and lower 11/o refueling nozzles and a pneumatic drive 12. The upper refueling nozzle 10 is fixed on the carriage 8 with the help of three longitudinal 13 and two vertical 14 spring rods . The following elements are mounted on the upper filling nozzle 10: two guide pins 15, a cylindrical adapter 16 with slots 17 for a three-beam crosspiece 18, a spring compensator 19 with an axial sleeve 20, a lock and a pneumatic cylinder 21. The lock is made in the form of a housing 22, in which, with the help of an axis 23, two double-armed levers 24 are attached (Fig. 5, 6, 7). The upper ends of the two-armed levers 24 are connected by means of an axis 25 to one end of the horizontal lever 26, and its other end is connected to the horizontal rod 27 by means of a horizontal axis 28, which is installed in the auxiliary longitudinal guides 29 of the body 22. On the horizontal lever 26 a protrusion 30 is made, which contacts the vertical stop 31 of the body 22. The lower ends of the two-armed levers 24 are connected by means of an axis 32 to the rod of the pneumatic cylinder 21, which is fixed to the body 22 by means of an axis 33. The horizontal rod 27 is fixed by means of nuts 34 to the crosspiece 18, the beams of which are connected to longitudinal rods 35. Each longitudinal rod 35 is connected to a rotary gripper 36 by means of an axis 37, which is installed in an additional longitudinal guide 38, and a spring-loaded longitudinal rod 39 with a stop 40 is installed in a longitudinal guide 41 and connected to the eye 42 of the rotary grip 36. A cover 43 is installed on the body 22 of the lock (in Fig. 5, the cover 43 is not shown).

The lower filling nozzle 11 is installed in the casing 44, which is rigidly fixed to the upper filling nozzle 10 with the help of brackets 45 (Fig. 3, 4). The lower filling nozzle 11 has a bottom 46 in the form of an inverted cone, a cap 47, longitudinal holes 48 and a latch 49 with a vertical spring-loaded rod 50. An additional pneumatic cylinder 51 is mounted on the casing 44, the rod of which is connected to the bottom 46, the lower longitudinal guide 52 with two vertical holes 53 and 54, two vertical pneumocylinders: near 55 and M zo far 56 (fig. 10, 11). Each of the pneumatic cylinders 55 and 56 contains a piston 57, a rod 58, a fitting 59 of the pressure supply, a fitting 60 of the piston cavity and a fitting 61 of the rod cavity (Fig. 12). -

The upper 10 and lower 11 refueling nozzles are connected to the refueling nozzles 62 and 63 of rocket 3. "g

The upper filling nozzle 10 is made in the form of two pipelines - external 64 and internal 65, installed coaxially and forming two channels (Fig. 8, 9). The inner pipeline 65 has an annular seal 66 and is fixed in the outer pipeline 64 with the help of a guide sleeve 67 with radial brackets 68. The filler neck 62 has an end seal 69 and two pipelines 70 and 71.

The custom 47 of the lower filling nozzle 11 interacts with the spring-loaded cover 72 and the seal 73, which is installed in the cup 74 with holes 75.

The radial guides U of the carriage 8 interact with the rollers of the risers 76. The protective visor b is installed in the guides 77 and connected to the drive 78. The gate 79 is installed in the niche 4 (fig. 1, 2). Three fuel lines 80, 81, 82 are mounted on unit 1.

The proposed device works as follows. ;" To ensure the launch of the rocket, in the assembly and test case, a quality check of the production of the air-hydro system of the Z rocket is carried out according to the patent of Ukraine Mob63764А, IPC СО01М 33/02, В640 37/24, 2003.

Then the rocket Z is transported to the launch complex and installed on the launcher according to the patent of Ukraine - I Mo297811, IPC B41E 3/052, B640 5/00, 2004.

Before refueling the rocket with fuel components, the proposed device is in its initial state (fig. 2, 6, 10). To ensure refueling of rocket Z, the following operations are carried out in sequence: -I - gate 79 is opened; - with the help of the drive 78, the protective visor b is moved along the guides 77 to the contact of the seal 7 with the tail compartment 2 of the rocket 3; - on the upper refueling nozzle 10, the rotary grippers 36 are deployed with the help of a pneumatic cylinder 21, which turns the two arms of the lever 24 relative to the axis 23 (fig. . 7).As a result, the horizontal lever 26 turns and moves together with the horizontal axis 28 and the horizontal rod 27 along the

Pull the longitudinal guide 29 up, the crossbar 18, the longitudinal rods Z5 and the axis 37 in the additional longitudinal guides 38 are also moved (Fig. 8). At the same time, the stops 40 of the spring-loaded rods 39 are in contact with the longitudinal guides 41 and turn the rotary grippers 36 relative to the axes 37; - with the help of a pneumatic cylinder 12, the carriage 8 is moved along the radial guides 9 (Fig. 1, 2). The guide pins 15 are inserted into the conical guide bushings of the rocket 3, which are not shown in the drawings, and a joint is formed (Fig. 8, 9); - erect rotary grippers 36 with the help of a pneumatic cylinder 21, which rotates the double-armed lever 24 relative to the axis 23 (Fig. 5, 6). As a result, the horizontal lever 26 returns to the contact of the protrusion 30 with the vertical stop 31 and moves down together with the horizontal rod 27, the crosspiece 18, the longitudinal rods 35. At the same time, the rotary grippers 36 are reduced under the action of the springs of the longitudinal rods 39, and the spring 65 Compensator 19 is compressed and creates a fastening force of the upper refueling nozzle 10 with the refueling neck 62. This fastening force is perceived by the horizontal lever 26, located coaxially, and unloads the pneumatic cylinder 21 in the process of refueling the rocket 3. The axial sleeve 20 excludes the contact of the compensator springs 19 with the horizontal rod 27; - connect the lower refueling nozzle 11 with the refueling neck 63 of rocket 3. For this, pressure is applied to the far vertical pneumatic cylinder 56 (Fig. 10, 12). At the same time, the piston 57 with the rod 58 rises and moves the vertical spring-loaded rod 50 from the vertical opening 53, the piston 57 with the rod 58 in the nearest vertical pneumatic cylinder 55 is lowered, and the additional pneumatic cylinder 51 moves the lower filling nozzle 11. In the process of this movement, the vertical spring-loaded rod 50 slides along the lower longitudinal guide 52. At the end of this movement, the lower filling nozzle 11 squeezes the 7/0 spring-loaded cover 72 and enters the cup 74 (Fig. 11), and the vertical spring-loaded rod 50 enters the vertical hole 54 and fixes the lower filling nozzle 11; - refueling the Z rocket with fuel. At the same time, the fuel line 80 (Fig. 3, 4), the external pipeline 64 and the pipeline 70 is fed into the tank of the first stage, and through the fuel line 81, the internal pipeline 65 and the pipeline 71 - into the tank of the second stage; 15 - thermostating of the tail compartment 2 is carried out. For this purpose, thermostatic air is supplied through the fuel line 82, the casing 44, the lower fuel nozzle 11 and through the holes 75 in the cup 74. The presence of the bottom 46 with a reverse cone and the execution of longitudinal holes 48 within the length of the reverse cone allows to ensure the minimum hydraulic resistance of the pipeline with the minimum dimensions of the cup 74; - the rocket is refueled with oxidizer and compressed gas in a similar way using the second unit; - after refueling the rocket, the proposed device is brought to the initial state (Fig. 2) in the reverse sequence.

Thus, the proposed device, which has a simple and reliable design, ensures docking and undocking of fuel lines in automatic mode, without the presence of people at the launch site. - and cha 30 7 cha 6 « also chs lchanh in GB s ryy:

January 2

ATO SCHE: to her She vT| ИЗШШЗ-- svi B shshch

What else?

APV 79 s MA "7 these I 6-7 . and I | / 5 ni G - StT- ! this. What from t sh- i" ry NV; Zx zashchshny 5 sho mm ni ko "420 in

Fig.1.

So 60 b5

B sh-5I3YV05- 70 tu di sh 79 ; 77 вн 63 "2-5 1 5 -0 ий Z С- » ne И Й и -0 и знеше НИ ия бях рани г- ГГ,

DU pt Z

S y- z0 Z y

Fig. 2. and

In y k y I y

But I "

Ki y t y N- ma Z a 5A-) yr - 5 Ob NO

And" I blew

KB-IrE

Y S p SK p i not goats shE. oo 470 te- - 9

SHI

M sia 3AS SY i u v g IC nsnnnnya ivan: no 60 80

Fig. 3. 65

13 at 10 - Y and in! 2 5-2 But 9 with U 45 and i

Od yu her dya || Uch "i and in Y i Te i

KA i ee wai hop nya nya gu

Fig. 4. 27 shchi 22 it y 29 or viGA with v: And I and V / With other 26 Sh | - yuch-

Fig. 5. "I g m y shi 17 ---- then " "in ШХЗВЗ8- О--2525Б55---0Й525223 З

OVEN Te ate

ОЧАКВ с ЧЕ и щ--о I GUEST What FO what oy: KD Fr.

MB with 7 in vo; re he 7 vena vi | | more Ii 2 yrsa Ai 28 pn! KK ekt age Fo - 5 IC "m 20 E 26 ! With thanks

TU

Two 24 s E g 500 I AT and ts 23

KV

Still x 60 43 and SCHO - cy 30 22 65 Fig.b.

y y Sh upavshnishnyh 10 mon shshshishn

IV Y vosha en

SASCOENV D EE 16

And that's not And now 1v not Owls and she: and x Che eV ee te; eh nn ER shchi s. Ko x / 28 25 . to 7 ru with ur; / aa t la R Z de iv no

IA I- and o o ich-

BI / k 22 "

Fig. 7. "a v 7 7 0 66 --571 2 y 2-5? ry 5 zb M I 57 -o

Y and vv in lk, TK b- s | : same 62 . ZV chu IC and va

I" o d fu ya shi shi shu v i shk B; 39 o'clock, sleeps 65 - I TYA "to. "m 50 y Fig. 8. 35 f-ff 58 36 1 62

AAU bo va s i / l

IN

65 Fig. 9.

yes

And a Christmas tree

YM: Tr 55

Furnace is more than 1. in vet SEE t, on 7 shu. sh.

There are more ! and 56

In I and

Y "SHY and your m 7

And at 1! ! -28В8-А- and ; a shi sh and vi ST Z iz- from Fig. 10. in -

ІІ «

MV Sh ey Sh y--- 75 73 seh | | g « rn! nya z ura, NV cancer with thyroid gland) with

Fig. 11. shk -I 61 shchi i la OKA -4 A x KT sha OH o - sh- i Ichschu H yu ee KI ee» o

Su ZHAKKKUK" K h

SUMI

58 57 At 60

Fig. 12.

Claims (5)

The formula of the invention b5 1. Unit for connecting the fuel lines of the rocket launcher, containing a carriage with lower one-channel and upper two-channel fuel nozzles, which interact with the front ends of the rocket fuel nozzles, rotary grippers, which are hingedly mounted on the upper fuel nozzle and interact with the pneumatic cylinder with the help of three of longitudinal rods, which is distinguished by the fact that it is equipped with a cylindrical adapter with a cross, a spring compensator with an axial sleeve and a lock with a housing, and a horizontal rod, which are located in series and fixed on the rear end of the upper filling nozzle coaxially, while the cylindrical adapter has three longitudinal slots for the beams of the crosspiece, which are connected to the longitudinal rods, the horizontal rod of the lock is located in the axial sleeve of the spring compensator and is fixed on the crosspiece, and the pneumatic cylinder is hinged on the body of the lock. 2. The unit according to claim 1, which is characterized by the fact that each rotary gripper is equipped with a spring-loaded longitudinal rod, one end of which is hinged to an eye mounted on the outer surface of the rotary gripper, and its other end is installed in a longitudinal guide fixed on the upper filling nozzle, and a stop is mounted on it, while the axis that connects the rotary gripper with /5 longitudinal thrust is installed in an additional longitudinal guide fixed on the upper filling nozzle. C. The unit according to claim 1, which is characterized in that the lock is equipped with a horizontal lever, one end of which is hingedly connected to the free end of the horizontal rod of the lock by means of a horizontal axis, which is installed in the auxiliary longitudinal guides of the housing, and a two-armed lever, hinged on The body of the lock with the help of an axis lock with the possibility of turning in the longitudinal vertical plane, while the lower end of the double-armed lever is connected to the pneumatic cylinder, and its upper end is hingedly connected to the second end of the horizontal lever, which has a protrusion that interacts with its lower surface with a vertical stop of the body, and the axis of attachment of the double-armed lever on the lock body is located between the ends of the horizontal lever. 4. The unit according to claim 1, which is distinguished by the fact that it is equipped with a casing that is rigidly fixed to the upper filling nozzle and in which a lower filling nozzle is installed with the possibility of longitudinal movement using the rod of an additional pneumatic cylinder, the cylinder of which is fixed on the casing, and a mechanism fixation of the lower refueling nozzle, while at the front end of the lower refueling nozzle, a bottom is installed in the form of a reverse cone with a base for interaction with a spring-loaded cover, M. zo installed coaxially inside the refueling neck of the rocket, and on its cylindrical surface, longitudinal holes are made, the length of which does not exceed height of the reverse cone. - 5. The unit according to claim 4, which is characterized by the fact that the fixing mechanism is made in the form of a vertical spring-loaded rod, fixed inside the lower filling nozzle, and a lower longitudinal guide, mounted on the casing, in which two vertical holes are made in series, which interact with one sides in from 5 rows with a vertical spring-loaded rod, and on the other side with the corresponding rods of the near and far vertical pneumatic cylinders, while the piston cavity of the near vertical pneumatic cylinder, located on the side of the rocket’s refueling neck, is connected to the rod cavity of the additional “4, pneumatic cylinder and the rod cavity of the far vertical pneumatic cylinder , and the piston cavity of the far vertical pneumatic cylinder is connected to the piston cavity of the additional pneumatic cylinder and to the brick cavity of the near vertical pneumatic cylinder. c 6. The unit according to claim 1, which differs in that the two-channel upper filling nozzle is made in the form of two pipelines installed coaxially, while the internal pipeline is fixed inside;" the external pipeline is movable in the axial direction, for example, with the help of a guide sleeve with radial brackets. -I Official Bulletin "Industrial Property". Book 1 "Inventions, useful models, topographies of integrated microcircuits", 2005, M 6, 15.06.2005. State Department of Intellectual Property of the Ministry of Education and Science of Ukraine. -I -4 70 Su; 60 b5