RU2543890C2 - Removal of propellant from rocket engine bodies - Google Patents

Abstract

FIELD: engines and pumps.SUBSTANCE: invention relates to rocketry. Proposed method comprises mechanical cutting of propellant to separate elements with sector-shape cross-section by drawing the cutting head along the body which has circular and radial cutting edges and removing said propellant elements. Said cutting head is secured at the centre of bar directed in the holes of covers fitted on body ends. Propellant is cut off in several passes of cutting head to decreased head drawing force and to ease of removal of cut propellant elements.EFFECT: safe removal, ruled out rocket body damages.3 cl, 2 dwg

Description

The invention relates to the field of rocket technology, in particular, to the development of methods for cleaning rocket engine bodies from mixed rocket fuel.

Several methods are known for cleaning pipes from various deposits: chemical, hydraulic, hydromechanical, mechanical, electro-hydraulic and others.

Existing patent No. 2394656 of the Russian Federation C2, class. B08B 9/049, 2008, ed. Shishov S.N. to “Method for cleaning gravity pipelines and a device for its use”, which consists in mechanically loosening the sediment in the pipe and removing it from the cleaning zone, where a shaft with a helical surface is used, which converts the rotation transmitted by the flexible shaft into rotational-translational motion, while moves the flexible shaft, and loosens deposits formed in the pipe with a screw surface.

The disadvantage of this method is that the helical shaft moves along the axis of the pipe along an arbitrary path, so when rubbing against the pipe wall in our case, the fuel mass will ignite.

In the field of rocketry, known methods and installations for the destruction of charges of solid rocket fuel by:

a) the use of liquid ammonia (US patent No. 4854982);

b) the use of liquid at high pressures from 40 to 140 MPa (US patent No. 3312231, 344096, 344667, RF patent No. 2195629);

c) the method of drilling a charge of explosives. (L.A. Smirnov, O.V. Tinkov, Conversion, part IV, “Disposal of decommissioned ammunition and solid-propellant rockets”, M., TsNIINTIKPK, 1996, pp. 71-73.

We consider the method (method) of drilling a charge of explosives as the closest analogue.

This method consists in the fact that the product is centered in a frame with guides along which a rotating pen-type drill with sharpening moves along the end surface. When drilling, chips are formed which are removed by water or air.

The disadvantage of this method is its low productivity and the mandatory cooling of the drill with water or air.

The technical task of the invention is to increase productivity while ensuring process safety.

The problem is solved by cutting the fuel mass into individual elements, which are then easily removed from the engine housing, including manually.

Cutting is carried out by moving the cutting head with annular and radial cutting edges along the axis of the housing, while excluding touching the cutting edges of the inner surface of the housing, which prevents sparking and heating of the fuel mass, that is, ensures process safety.

In FIG. 1 shows a General view of the device.

In FIG. 2 shows a cutting head with a sharpening angle of cutting edges 25 ÷ 30 °, which are obtained experimentally.

The device of FIG. 1, consists of a cutting head 1, mounted on a rod 2, a guide rod 3, which secures the head on a rod, two covers 4 and 5, connected to the threads with the ends of the motor housing 6, two bushings 7, seated in the Central holes of the covers 4 and 5.

The work to remove the fuel mass is as follows: the engine housing with a fuel mass of 8 is installed on the lodgment 9 and 10 of the presser 11.

Cover 5 is screwed onto the right end of the engine housing. Rod 2 is inserted through the sleeve 7 of cover 5 into the fuel mass channel. At the exit from the other end of the housing, the cutting head 1 is put on the rod, closed with a cover 4 and fixed with a guide rod 3.

The rod on the right side is secured by a gripper 12 associated with the hydraulic cylinder 13 of the presser.

The hydraulic cylinder through the rod 2 is the movement of the cutting head. There is a cutting process - the separation of the fuel mass into elements with a cross section in the form of sectors along the entire length of the engine block.

After the end of one pass, the guide rod 3 is turned out and the cover 4 is removed. The cover 5 is retracted 200–300 mm along the rod and the cutting head is removed. After that, one by one the elements of the fuel mass are removed manually or remotely mechanically.

To facilitate the removal of cut elements, the movable frame 14 by means of the hydraulic cylinder 15 is tilted by 30 ÷ 60 °.

Next, put the cover 5, the rod 2 is retracted by the hydraulic cylinder 13 in the opposite direction to exit from the end of the engine housing. Then a larger cutting head is put on it and the cutting process is repeated.

The proposed method using the device was tested in an industrial environment at the FKP "Perm Powder Plant", while the efficiency of the method was confirmed.

Claims (3)

1. The method of removing fuel mass from the bodies of rocket engines, which consists in mechanically cutting the fuel mass along the length into elements,
characterized in that the cutting is carried out by moving along the axis of the motor housing an annular cutting head with radial ribs with annular and radial cutting edges, the cutting head is mounted on a rod passing through holes in the covers installed on the ends of the motor housing. 2. The method according to p. 1, characterized in that the annular and radial cutting edges are made with a sharpening angle of 25 ° -30 °, and the elements formed during cutting have a section in the form of sectors. 3. The method according to p. 1, characterized in that the cutting is carried out in several passes by cutting heads of different diameters from smallest to largest.

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