RU138381U1 - MULTI-STAGE LIQUID FUEL FUEL TANK - Google Patents

Abstract

A fuel tank of a multi-stage liquid-fuel rocket containing a cylindrical shell, a lower bottom with an intake device, an upper double separation bottom with an adjacent tank, a flow line of an adjacent tank passing inside the tank, enclosed in a tunnel pipe equipped with zigs and a bellows, characterized in that on the external the surface of the supply pipe of the adjacent tank mounted support in the form of a spiral rib of polyurethane foam in contact with the inner surface of the tunnel pipe.

Description

The utility model relates to the field of rocket technology, and more particularly to the design of the fuel tank of a multi-stage rocket using liquid fuel.

Known designs of fuel tanks of multi-stage rockets for liquid fuel Ρ - 1 (8А11), Р - 2 (8Ж38), Ρ - 12 (8К63), Ρ - 13 (4К-50), Р - 21 (4К-55) [1, 2, 3], containing bottoms (upper and lower), a cylindrical shell and a flow line of an adjacent tank, which is enclosed in a tunnel pipe, passing inside the tank with the fuel component.

In accordance with GOST 22350-91 [4], the tunnel pipe of the fuel tank of the liquid rocket body serves as protection against the temperature effects of the fuel components between each other and the elimination of their connection, which is especially important when using self-igniting substances as fuel components.

In the case of the use of self-igniting components of the fuel, the gap between the tunnel pipe and the flow pipe provides reliable protection of the rocket structure from explosion in the event of (discontinuity) in the materials of both the tunnel pipe and the flow pipe.

In case of unauthorized penetration of fuel components through micropores of the materials of the tunnel pipe and the supply line and their subsequent interaction with each other, microexplosions occur in the gap between the tunnel pipe and the supply line, which do not affect the explosion safety of the rocket.

Known patented technical solutions of the carrier rocket and propulsion system [5, 6], in which consumable lines (pipelines) enclosed in tunnel pipes are laid in tanks with fuel components. In the above structures, thermal protection is installed on the outer surfaces of the supply lines (see, respectively, Fig. 5 and Fig. 1 to the above patents), while, as can be seen from the drawings, the tunnel pipes and consumables with thermal protection applied are installed with a gap between them.

Known patented design [7], in which the flow pipe is installed in the tunnel pipe passing through the oxidizer tank (Fig. 6 to the patent of Russia 2406660), also with a gap, as in the above structures.

The disadvantages of the structures mentioned above is that the tunnel pipes which are structurally unrelated and the supply lines located in them work independently from each other in terms of strength and stability, and therefore have increased thicknesses and, accordingly, weight.

Also known is the design of the oxidizer tank of the rocket Ρ - 17 (8K14) [8], which is a power element of the rocket design. The outer surface of the tank coincides with the theoretical outline of the rocket, and the inner cavity of the tank is designed to store the oxidizer. The tank is equipped with front and rear bottoms. A fence is mounted at the rear bottom, providing a reliable oxidizer fence. A tunnel pipe passes in the tank, inside of which a fuel feed pipe is placed. The tunnel pipe has ridges that increase its stability. The structure of the tunnel pipe includes a bellows, which is a compensator for the deformation of the tank during operation.

The design of the product tank 8K14 [9], is the closest analogue and can be taken as a prototype.

The objective of the patented utility model is to obtain a technical result that enables the tunnel pipe and the flow pipe to work together as a single strength scheme, and to control the annular gap between the tunnel pipe and the flow pipe for fuel components.

This technical result is achieved in that in the fuel tank of a multi-stage liquid-fuel rocket containing a cylindrical shell, a lower bottom with a suction device, an upper double separation bottom with an adjacent tank, a flow line of an adjacent tank passing inside the tank, enclosed in a tunnel pipe equipped with zigs and bellows, on the outer surface of the supply pipe of an adjacent tank mounted support in the form of a spiral rib of polyurethane foam in contact with the inner surface of the tunnel Pipes.

This design ensures the joint operation of the flow pipe and the tunnel pipe as a single strength scheme, which can significantly reduce the thickness (and therefore weight) of the tunnel pipe and flow pipe, increase the strength and stability of the tunnel pipe during operation, while providing the ability to control the annular gap between a tunnel pipe and a supply pipe for the presence of fuel components in it.

The essence of the utility model is illustrated by graphic materials, where: - in FIG. 1 shows a sectional view of a rocket fuel tank;

- in FIG. 2 shows the extension element I in FIG. one.

The fuel tank 1 of a multi-stage liquid fuel rocket contains a cylindrical shell 2, a lower bottom 3 with a suction device 4, an upper double dividing bottom 5 with an adjacent tank 6, passing inside the tank 1, a flow line 7 of an adjacent tank 6, enclosed in a tunnel pipe 8, which serves as protection against the temperature effects of the fuel components between each other and eliminates their connection. To increase strength and stability under operational loads (external overpressure and vibration), the tunnel pipe is equipped with zigs 9, and to compensate for temperature expansion - with a bellows 10. On the outer surface of the flow pipe 7 of adjacent tank 6, a support is installed in the form of a spiral rib 11 made of polyurethane foam in contact with the inner surface of the tunnel pipe 8.

Patented design is easy to manufacture. So, for example, after applying a spiral rib 11 of polyurethane to its external surface and then curing it, the ribs of polyurethane are machined to the inner diameter of the tunnel pipe, after which the tunnel pipe 8 is tightened (or by sliding fit) to the machined surface ribs 11.

Other technologies can also be applied. For example, put a prefabricated spiral rib 11 onto the supply line, and then install the tunnel pipe.

This design ensures the joint operation of the flow pipe and the tunnel pipe as a single strength scheme, which can significantly reduce the thickness (and therefore weight) of the tunnel pipe and the flow pipe.

The utility model allows to generally reduce the weight of the fuel tank structure, increase the strength and stability of the tunnel pipe during operation.

Information sources:

1. The last reincarnation of the FAU-2. Equipment and weapons nnre. com> transport_i_aviacija ... vooruzhenie_2010_01 ...

2. Missile system Ρ - 12 (11K63).

3. Catalog. Ballistic missiles of the naval strategic nuclear forces of the USSR of Russia 1947-2012. - M: Publishing House "Arms and Technologies", 2012. - 108 s; silt.

4. GOST 22350-91 Liquid fuel missile body. (Terms and Definitions).

5. Patent RU 2331550. Launch vehicle, cl. IPC B64G 1/00, B64G 1/40 (2006.01). Priority January 9, 2007

6. Patent RU 2238422. Propulsion system of the first stage of the launch vehicle of the aerospace system, cl. IPC F02K 9/44. Priority November 10, 2002

7. Patent RU 2406660. Layout of a multi-stage launch vehicle, cl. IPC B64G 1/00 (2006.01). Priority December 20, 2010

8 Technical description of the product 8K14 (8K14-1) (OP / 8K14) Chapter V. Middle part. 2. Tanks and feed pipe. http: // raketa-http: //8kl4.narod.ru/indexl_5_2.html, 04/03/2013

Claims (1)

A fuel tank of a multi-stage liquid-fuel rocket containing a cylindrical shell, a lower bottom with an intake device, an upper double separation bottom with an adjacent tank, a flow line of an adjacent tank passing inside the tank, enclosed in a tunnel pipe equipped with zigs and a bellows, characterized in that on the external the surface of the supply pipe of the adjacent tank mounted support in the form of a spiral rib of polyurethane foam in contact with the inner surface of the tunnel pipe.

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