RU2456216C1 - Rocket accelerating engine cryogenic component drain device - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering, particularly, to cryogenic component draining from cryogenic tank of rocket accelerating unit. Said drainage consists of drain valve arranged on cryogenic tank and drain pipeline. Drain pipeline at outlet of accelerating unit is secured to its structural element including guide support and thermal bridge. Darin pipeline incorporates additionally a spherical sleeve arranged inside guide support. Drain pipeline central section is secured on cryogenic tank upper bottom by adjustable bracket. Said adjustable bracket comprises support with threaded end, two half-holders embracing drain pipeline and arranged on said threaded tip, adjusting washer arranged between support and bottom half-holder, and spherical inserts arranged on inner surfaces of top and bottom half-holders. Curved branch pipes are fitted from drain valve into drain pipeline to make U-shape section in drain pipeline. Angular displacement compensator is arranged at drain pipeline central section to compensate, along with bracket and adjustable bracket, mounting and working displacements.

EFFECT: higher reliability.

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Description

The invention relates to rocket and space technology, in particular to the design of drainage of a cryogenic component from a cryogenic tank, and can also be used in structures where the storage and operation of cryogenic components in containers is used.

When filling a cryogenic tank with a cryogenic component, at the initial moment boiling of the cryogenic component occurs with the formation of a large amount of gas, which must be vented in order to provide the necessary pressure in the cryogenic tank. In the process of refueling and preparing a rocket booster block for launch to maintain pressure in the cryogenic tank, it becomes necessary to open the drain valve and relieve pressure from the cryogenic tank. As a result of this process, due to the temperature difference between the external atmosphere and the internal cavity of the drainage line, condensate may form on the inner surface of the drainage line, which, when frozen, can enter the drainage valve and the cryogenic tank, which can lead to an emergency.

Known rocket booster block according to patent RU 2153447 B64G 1/40, 1/00, 1/16, incorporating a drain line, which is a drain valve installed on the oxidizer tank, and a drain pipe connected to the drain valve and brought outside rocket booster block - a prototype.

The disadvantage of the drainage line of the prototype is the following.

In the process of filling the oxidizer tank, the flight of the block as part of the launch vehicle and the autonomous flight of the block:

- in the places of fastenings of the drainage line, relative longitudinal and transverse movements occur. The longitudinal displacements are directed parallel to the longitudinal axis of the block, the transverse ones are in the plane perpendicular to the longitudinal axis of the block. Compensation for movements between the attachment points of the prototype is not provided, as a result of which the reliability of the drainage line is reduced;

- condensation, its accumulation and freezing in the internal cavity of the drainage line can lead to an emergency (due to ice falling into the armature of the propulsion system of the rocket booster unit), the exception of which is not provided for by the prototype.

The objective of the proposed drainage device of the cryogenic component of the rocket booster block is to increase the reliability of operation of the drainage line and, as a result, increase the reliability of operation of the rocket booster block.

The problem is solved due to the fact that in the drainage device of the cryogenic component of the rocket booster block, consisting of a drain valve mounted on the cryogenic tank, and the drain pipe, the drain pipe at the outlet of the rocket booster block is fixed to its power element using a bracket containing a guide support and a thermal bridge, and a spherical sleeve placed inside the guide support is introduced into the drainage pipeline. The middle part of the drainage pipe is supported on the upper bottom of the cryogenic tank using an adjustable bracket containing a support with a threaded tip, which is fixed on the outer surface of the upper bottom of the cryogenic tank, two half clamps covering the drainage pipe and installed on the threaded tip of the support, an adjusting washer located between the support and lower half-clamp, and spherical liners mounted on the inner surfaces of the upper and lower half-clamps. At the outlet of the drain valve, curved pipes are introduced into the drain pipe, which form a U-shaped portion in the drain pipe and prevent condensate from entering the drain valve and the cryogenic tank. An angular displacement compensator is introduced into the middle part of the drainage pipeline, which, together with the bracket and an adjustable bracket, compensates for mounting and working displacements that occur during operation of the drainage device of the cryogenic component of the rocket booster unit.

Figure 1 shows a General view of the drainage device of the cryogenic component of the rocket booster block. Figure 2 presents the U-shaped section of the drainage pipeline. Figure 3 shows an adjustable bracket. Figure 4 shows the bracket for fastening the drainage pipeline to the power element of the rocket upper stage, where:

1. cryogenic tank;

2. drain valve;

3. drainage pipeline;

4. compensator of angular displacements;

5. power element;

6. bracket;

7. guide bearing;

8. thermal bridge;

9. spherical sleeve;

10. the middle part of the drainage pipeline;

11. the upper bottom;

12. adjustable bracket;

13. support;

14. threaded end;

15. half-clamps;

16. adjusting washer;

17. spherical insert;

18. curved nozzles;

19. fasteners;

20. U-shaped area.

In the drainage device of the cryogenic component of the rocket booster block, consisting of a drain valve 2 mounted on the cryogenic tank 1, and the drain pipe 3, the drain pipe 3 at the outlet of the rocket booster block is fixed to its power element 5 using the bracket 6 containing the guide support 7 and a thermal bridge 8, and a spherical sleeve 9 is introduced into the drainage pipe 3, which is located inside the guide support 7. The middle part of the drainage pipe 10 is supported on the upper bottom 11 of the cryogenic tank 1 s with the help of an adjustable bracket 12, containing a support 13 with a threaded tip 14, which is fixed on the outer surface of the upper bottom 11 of the cryogenic tank 1, two half-clamps 15, covering the drain pipe 3 and installed on the threaded tip 14 of the support 13, an adjusting washer 16, located between the support 13 and a lower half-clamp 15 and spherical liners 17 mounted on the inner surfaces of the upper and lower half-clamps 15.

The guide support 7 with a thermal bridge 8, the half-clamps 15 are fastened to each other and to the threaded end 14 using fasteners 19, and spherical inserts 17, for example, can be installed on the half-clamps 15 with glue.

At the outlet of the drain valve 2, bent pipes 18 are introduced into the drain pipe 3, which form a U-shaped portion 20 in the drain pipe 3 and prevent condensate from entering the drain valve 2 and the cryogenic tank 1.

An angular displacement compensator 4 is introduced into the middle part of the drainage pipeline 10, which compensates for the relative displacements of the elements of the drainage device of the cryogenic component of the rocket upper stage mainly in the vertical plane.

The bracket 6, the adjustable bracket 12 and the compensator of angular displacements 4 provide compensation for mounting and working displacements that occur during operation of the drainage device of the cryogenic component of the rocket booster block.

During the installation of the drainage pipe 3, the position of the adjustable bracket 12 is set by turning the half clamps 15 relative to the threaded end 14 of the support 13 and installing the adjusting washer 16 between the lower half clamp 15 and the support 13 so that the drainage pipe 3 can move freely inside the half clamp 15 and inside the guide support 7 brackets 6.

The drainage device of the cryogenic component of the rocket booster block operates as follows.

During the filling of the cryogenic tank 1 with the cryogenic component, the shell of the cryogenic tank 1 cools and contracts, during the pressurization of the cryogenic tank 1, as well as during the flight of the rocket booster block under the influence of overloads in the drain line, relative movements between the drain valve 2 and the power element 5 of the rocket booster blocks that are worked out by slipping and turning the drainage pipe 3 relative to the spherical liners 17 of the adjustable bracket 12, by changing the angle of rotation the mouth of the compensator for angular displacements 4 and slippage and rotation of the spherical sleeve 9 of the drainage pipe 3 relative to the guide support 7 of the bracket 6.

Improving the reliability of the operation of the drainage line is achieved by introducing compensating elements (bracket 6, adjustable bracket 12 and angular displacement compensator 4) into its composition.

Improving the reliability of operation of the rocket booster block is achieved by introducing into the drainage pipeline a U-shaped section 20, which prevents condensate from entering the drainage pipe 3 from the internal cavity into drainage valve 2 and cryogenic tank 1, which prevents the occurrence of an emergency.

Claims (1)

The drainage device of the cryogenic component of the rocket booster block, consisting of a drain valve installed on the cryogenic tank, and a drain pipe, characterized in that the drain pipe at the outlet of the rocket booster block is fixed to its power element using an arm containing a guide support and a thermal bridge, and a spherical sleeve placed inside the guide support is introduced into the drainage pipeline; the middle part of the drainage pipe is supported on the upper bottom of the cryogenic tank using an adjustable bracket containing a support with a threaded tip, which is fixed on the outer surface of the upper bottom of the cryogenic tank, two half clamps covering the drainage pipe and installed on the threaded tip of the support, an adjusting washer located between the support and lower half-clamp, and spherical liners mounted on the inner surfaces of the upper and lower half-clamps; at the outlet of the drain valve, curved pipes are introduced into the drain pipe, which form a U-shaped section in the drain pipe and prevent condensate from entering the drain valve and the cryogenic tank; an angular displacement compensator is introduced into the middle part of the drainage pipeline, which together with the bracket and an adjustable bracket provides compensation for mounting and working displacements that occur during operation of the drainage device of the cryogenic component of the rocket booster block.

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