RU2640941C2 - Missile upper stage - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: missile upper stage comprises a cryogenic oxidant tank with additional near-bottom partitions, a sampling device, a rod of a cryogenic fuel level sensor, a propulsion engine. The cryogenic oxidant tank is provided with a drip reflector consisting of an inner truncated cone with a bottom in a small base. Its larger base is facing towards the upper bottom of the cryogenic oxidant tank, and an outer truncated cone, the larger base of which is facing towards the lower bottom of the cryogenic oxidant tank. The outer truncated cone is faired with the larger base of the inner truncated cone with a smaller base, holes uniformly distributed along the conjugation circumference are made in the conjugation of the inner truncated cone with the outer truncated cone. In the bottom of the inner truncated cone of the drip reflector, a central hole is made, through which the rod of the cryogenic fuel level sensor passes. The drip reflector is fixed to the rod of the cryogenic fuel level sensor above the additional near-bottom partitions.

EFFECT: ensuring a reliable launch of the propulsion engine of the upper stage and its subsequent operation.

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Description

The invention relates to rocket and space technology, and in particular to means for launching spacecraft into predetermined orbits.

The use of a booster block in a space-rocket system, which includes a cryogenic tank refueled with liquid cryogenic fuel, can lead to a problem that is associated with the processes that take place in the cryogenic tank of the oxidizer. Namely, in outer space, between the launches of the main engine of the rocket booster block, zero gravity occurs, and cryogenic fuel due to capillary forces is distributed around the periphery of the oxidizer cryogenic tank, forming a gas spheroid in its central part. When an overload is created before the last launch of the main engine of the rocket booster block, cryogenic fuel moves to the area of additional bottom partitions and the intake device, as a result of which gas cryogenic fuel is separated, the fluid calms down, and the liquid in the area of the intake device becomes conditioned to start the main engine. But when creating a pre-start overload from in-tank devices located in the upper part of the oxidizer’s cryogenic tank, cryogenic fuel in the form of droplets formed in zero gravity and having a sufficiently large volume falls onto the formed surface of the cryogenic fuel in the area of the intake device, causing it to re-gasify, which may lead to failure when starting or operating the main engine.

Known rocket booster block RU 2412088 C1 (B64G 1/22 (2006.01), published 02/20/2011), the cryogenic oxidizer tank of which contains the main longitudinal and additional bottom partitions, the intake device, the cryogenic fuel level sensor rod and the main engine prototype.

The disadvantage of the prototype is the following.

When creating a prestarting overload, it is possible to re-gasify cryogenic fuel when it falls from in-tank devices in the form of droplets formed in zero gravity and having a sufficiently large volume onto the formed surface of cryogenic fuel in the region of the intake device of the cryogenic oxidizer tank.

The objective of the invention is the creation of an accelerating unit that provides high reliability when starting the main engine and its subsequent operation.

The technical result of the proposed invention is the elimination of re-gasification of cryogenic fuel in the cryogenic tank of the oxidizer when cryogenic fuel gets in the form of droplets formed in zero gravity and having a sufficiently large volume and falling from the tank devices located in the upper part of the cryogenic tank of the oxidizer onto the formed surface of the cryogenic fuel in the zone capture of gas inclusions of the intake device of the cryogenic oxidizer tank and, as a result, ensuring reliable launch of marshes engine and its subsequent operation.

The technical result is achieved in that in a rocket booster block containing a cryogenic oxidizer tank with additional bottom baffles, a suction device, a rod of a cryogenic fuel level sensor, the main engine, the cryogenic oxidizer tank is equipped with a droplet deflector, consisting of an internal truncated cone with a bottom in a small base, this, its larger base faces the upper bottom of the cryogenic oxidizer tank, and the outer truncated cone, the larger base of which faces the lower bottom of the cryogenic about the oxidizer tank, with the smaller base the outer truncated cone smoothly mating with the large base of the inner truncated cone, in the pairing of the inner truncated cone with the outer truncated cone, holes are made evenly distributed around the mating circumference, a central hole is made in the bottom of the inner truncated cone of the droplet deflector through which passes the cryogenic fuel level sensor rod, while the droplet deflector is mounted on the cryogenic fuel level sensor rod over additional idon partitions.

The invention is illustrated by drawings.

In FIG. 1 is a perspective view of a rocket booster unit; FIG. 2 shows a cryogenic tank of an oxidizer of a rocket booster block, where:

1. cryogenic oxidizer tank;

2. additional bottom baffles;

3. intake device;

4. rod cryogenic fuel level sensor;

5. marching engine;

6. droplet reflector;

7. inner truncated cone;

8. bottom;

9. the upper bottom;

10. outer truncated cone;

11. bottom bottom;

12. holes;

13. capture zone of gas inclusions;

14. cavity reflector;

15. gas cavity of the cryogenic oxidizer tank;

16. bottom part.

In the proposed rocket booster block (Fig. 1) containing a cryogenic oxidizer tank 1 with additional bottom baffles 2, a suction device 3, a rod of a cryogenic fuel level sensor 4, the main engine 5, the cryogenic oxidizer tank 1 is equipped with a droplet deflector 6, consisting of an internal truncated cone 7 with a bottom 8 in a small base, with an open larger base facing the upper bottom 9 of the cryogenic oxidizer tank 1, and an external truncated cone 10, an open larger base facing towards the lower bottom 11 the riogenous oxidizer tank 1, with the smaller base, the outer truncated cone 10 smoothly mating with the open large base of the inner truncated cone 7, the holes 12 are uniformly distributed around the mating circumference in the interface of the inner truncated cone 7, and the bottom 8 of the inner truncated cone 7 of the droplet deflector 6, a central hole is made through which the rod of the cryogenic fuel level sensor 4 passes, while the droplet deflector 6 is mounted on the rod of the cryogenic level sensor The fuel over 4 additional bottom wall 2.

The taper of the outer truncated cone 10 and the diameter of the droplet deflector 6 should provide a reflection of the falling drops of cryogenic fuel outside the capture zone of the gas inclusions 13 when the cryogenic fuel is re-gassed, while the capture zone of the gas inclusions 13 is determined by the axial overload at the moment the main engine 5 starts, the cryogenic fuel consumption , the design of the intake device 3, the size of the gas inclusions, etc.

When refueling the cryogenic tank of oxidizer 1 with cryogenic fuel, when passing the level of cryogenic fuel of the droplet deflector 6 in its cavity 14, gas cryogenic fuel may accumulate. Using the holes 12 in the droplet deflector 6, the gas cryogenic fuel is transferred from the cavity of the droplet deflector 14 to the gas cavity of the cryogenic oxidizer tank 15.

The proposed rocket booster block operates as follows.

After the separation of the rocket booster block from the previous stage of the space rocket, after repeated launches of the mid-flight engine 5 and before the last launch of the mid-flight engine 5, the fuel level in the cryogenic tank of oxidizer 1 is located in its bottom part 16.

When turning off the mid-flight engine 5 in space conditions, practical zero-gravity occurs. Under the action of capillary forces and wetting, cryogenic fuel moves along the inner surfaces of the shell of the cryogenic tank of oxidizer 1 and its internal tank devices. As a result of this, a gas spheroid is formed in the center of the cryogenic tank of oxidizer 1, and cryogenic fuel is located on the surfaces of the internal tank devices and on the shell of the cryogenic tank of oxidizer 1.

When creating prestarting overload, partial deposition of cryogenic fuel is provided towards the intake device 3. When the main engine 5 is turned on, cryogenic fuel flows to the bottom part 16 of the cryogenic oxidizer tank 1.

From intrabank devices located in the central part of the cryogenic tank of oxidizer 1, droplets of cryogenic fuel fall on the droplet deflector 6 and are used to be thrown into the bottom part 16 of the cryogenic tank of oxidizer 1 outside the capture zone of gas inclusions 13, providing the required condition of the cryogenic component in terms of gas content at the inlet in the marching engine 5, its reliable start-up and its subsequent operation.

The creation in the cryogenic tank of the oxidizer 1 of the rocket booster unit in the form of a droplet deflector 6 eliminates the ingress of cryogenic fuel in the form of droplets formed in zero gravity and falling from the internal devices into the capture zone of the gas inclusions 13 of the intake device 3 of the cryogenic tank of the oxidizer 1, and, as a result, provides reliable start of the mid-flight engine 5 and its subsequent operation. In addition, the openings 12 made in the upper part of the droplet deflector 6 allow avoiding the accumulation of a gas cryogenic component in the cavity of the droplet deflector 14 located near the capture zone of the gas inclusions 13.

Claims (1)

A rocket booster block containing a cryogenic oxidizer tank with additional bottom baffles, a suction device, a rod of a cryogenic fuel level sensor, a marching engine, characterized in that the cryogenic oxidizer tank is equipped with a droplet deflector, consisting of an internal truncated cone with a bottom in a small base, with a larger base it faces the top of the cryogenic tank of the oxidizer, and the outer truncated cone, the larger base of which faces the bottom of the cryogenic tank of the oxidizer, with a smaller base, the outer truncated cone smoothly mates with the large base of the inner truncated cone; in the pairing of the inner truncated cone with the outer truncated cone, holes are made evenly distributed around the mating circumference; a central hole is made in the bottom of the inner truncated cone of the droplet deflector through which the rod of the cryogenic fuel level sensor passes while the droplet deflector is mounted on the rod of the cryogenic fuel level sensor above the additional bottom partitions.

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