RU2303236C2 - Cocoon case for solid-propellant charge and method for its sectional destruction - Google Patents

Abstract

FIELD: manufacture of cocoon, glass-organoplastic rocket engine cases and destruction and salvaging of solid-propellant rocket engines.

SUBSTANCE: at manufacture of a cocoon, glass-organoplastic case of a solid-propellant rocket engine enclosure belts are installed in the points of its future cutting, destruction, they are installed on its inner surface. Each enclosure belt is grooved, a through duct is made in the groove bottom, placed and fixed in which for dismantling is the center body, the side members of the enclosure belt are fastened to the case and made of material, whose resistance to mechanical penetration of the cutting tool is higher than that of the case material. At a destruction of the solid-propellant charge fastened to the case, within the width of the enclosure belt, a strip of the solid-propellant rocket engine case above each enclosure belt is cut out and removed, the enclosure bets are opened up by dismantling of the center body, the slotted duct are opened for an access of a hydrojet tool to the surface of the solid-propellant charge, after that a hydrojet cutting of the solid-propellant charge is performed. After that the sections of the solid-propellant charge fastened to the case are separated.

EFFECT: provided protection of the solid-propellant charge against the cutting tool at a destruction cutting of the case in the points of installation of the enclosure belts, provided easy opening of the enclosure belts by dismantling of the, center body; at a hydrojet cutting of the solid-propellant charge through the slotted ducts of the enclosure belts the offered method makes it possible to obtain, sections of the solid-propellant charge fastened to the case with a maximum open area of its surface.

20 cl, 3 dwg

Description

The invention relates to rocket technology, and in particular, to the field of manufacturing cocoon glass-organoplastic bodies for TPT charges firmly bonded with them and to the field of elimination of solid propellant rocket engines (RTTT). The invention is directed to the creation of such a solid propellant rocket motor housing design and solid propellant liquidation elimination technology that, after the solid propellant rocket life cycle, can eliminate the solid propellant charge in the housing using safe mechanical and hydro-jet methods. The invention can be used in the disposal of TPT charges attached to the housing.

The well-known and taken as an analog solid propellant solid propellant solid propellant charge case with a solidly charged TPT charge, subjected to liquidation according to the method RU No. 2143660 by initial grinding of the annular body shares by ultrahigh pressure of water, has the following disadvantages: at the time of the local destruction of the body, the water jet breaks to the TPT charge and at an ultrahigh speed shock affects it, which is unsafe for any type of solid fuel and, especially, for solid fuels with increased sensitivity to shock; For cutting the body of solid propellant rocket motors, special hydraulic pumping and hydraulic cutting equipment that creates ultra-high hydraulic pressure and operates in these extremely difficult conditions is used, which leads to a high cost of grinding the body.

As a prototype of a glass-organoplastic housing, the rocket engine housing according to the patent RU No. 2042853 is taken, comprising a front frame mounted on the inner cylindrical surface of the housing.

From the point of view of eliminating the charge of the TRT, bonded to the prototype case according to the method RU No. 2143660, the disadvantages inherent in the analogue case mainly apply to the prototype case.

However, the design of the prototype case contains an element - a frame mounted on the inner surface of the body, which performs ambiguous functions in the process of cutting (grinding) the body.

On the one hand, to access the charge of the TRT under the frame, it is necessary to cut this frame, which further increases the complexity of the work and is a disadvantage. On the other hand, when cutting the glass-organoplastic case over the frame, it acts as an obstacle to the path of the ultra-high-speed water jet to the TPT charge and, thus, protects the charge at this stage of cutting the case from its impact, which can be attributed to the advantage of the body design and use this advantage in the present invention.

As a prototype of the TPT charge elimination method, the method according to RU patent No. 2262068 (application No. 2003129676 dated October 16, 2003) was taken, according to which, before cutting the solid propellant rocket motor into large annular fragments, they subcut the flooded jets of cavitating nozzles and extract part of the bonded fluid TPT charge, forming a cavity free of charge, after which annular fragments of the body are mechanically cut off, while the cutting tool body exits into the cavity released from the charge part, not in contact with the remaining charge, which creases safety body cutting its integrated charge TRT.

The disadvantage of the method adopted for the prototype is that before mechanical cutting of the bottom and the casing from the side of their outer surface, they cut and remove part of the charge of the TRT in the cutting zone of the casing and the bottom from the side of their inner surface. Cutting and removing part of the bonded TRT charge is especially difficult and unsafe on the bottom, because in this case, special hydraulic cutting equipment is used, repeatedly introduced into the internal cavity (channel) of the TRT charge through the pole hole of the bottom. The work performed is complicated by the fact that it is carried out in the position of the housing submerged (flooded) in the working fluid with a charge of TRT. In addition, the cavities released from the part of the bonded TPT charge do not exclude contact (cutting) of the tool cutting the housing with the remaining TPT charge in the housing.

The objective of the present invention is the creation of such a design of the solid-state housing of the solid propellant rocket motor and the technology of eliminating solid rocket motor, in which, after the completion of the life cycle of solid rocket motor, the cutting of the plastic housing with fastened charge TRT is carried out under normal (normal) production conditions, using a universal mechanical method, is safe and does not require preliminary hole, cutting and removing parts of the bonded TPT charge, cutting the TPT charge is carried out in places and after cutting the case is also safe and by the blasting method, in this case, as a result of liquidation cutting, the hull sections are separated with a bonded charge of TRT, the surface of which is open and available for subsequent disposal (grinding, chemical destruction) operations.

The specified problem is solved in two stages as follows. At the first stage, a cocoon glass-organoplastic case is made, in which barrier belts are installed on its inner surface, in places for future liquidation cutting, each of which is made in the form of a groove with a central body placed in it with the possibility of dismantling, while at the bottom of each groove it is made a through channel, predominantly coaxial to it, between the body and the central body, a strip of release material is installed, and the sides of the barrier belt are fastened mainly by adhesive composition with the body and you olneny of a material resistant to mechanical penetration of the cutting tool is higher than that of the body material; barrier belts are installed between the body and the heat-shielding or protective-fixing layer; the gutter of the barrier belt, the channel in the bottom of the gutter and its sides are formed by two Z-shaped profiles, while the channel in the bottom of the gutter is formed by their shelves facing each other, and inserts of heat-protective material in the form of wedges are installed under the side walls of the belt; the central body is made in the form of installed one after another, adjacent inserts; a number of threaded holes are made in the central body to ensure and facilitate its dismantling; channels are made in the central body with the possibility of placing cable lines in them; the central body is made in the form of a package of flat cables and a casing; the width of the barrier belt A and its height B are made with the ratio A: B = (1.5 ... 4) C: (0.05 ... 0.7) C, where C is the width of the gutter at the point of contact with the inner surface housing; on the outer surface of the housing tracing of the barrier belt in the form of coiled and protruding outward reference marks; reference marks on the case are placed and fixed on a guide, for example, a wire string; barrier belts are made ring; in the zones of transition of the bottoms into a cylindrical shell, two annular barrier belts and two adjacent to them, diametrically opposite longitudinal barrier belts are installed; installed "n" longitudinal barrier belts; ring and two- or "n" -adjacent longitudinal barrier belts are installed.

At the second stage - during liquidation, the outside, mainly mechanical, is cut out of the solid-propellant body strips within the width of the barrier belts installed in the manufacture of the body on its inner surface, the cut body strips are removed, the barrier belts are opened, providing access to the TRT charge, hydro-jet cutting of the TPT charge, at the end of which the sections of the TPT charge bonded to the body and / or bottoms are separated; waterjet cutting of the TPT charge begins with cutting a heat-shielding and / or protective-fixing layer; cut the strip of the solid propellant body with a width of (1.0 ... 1.4) C, where C is the opening width of the barrier belt in the place of its contact with the inner surface of the solid propellant body; separation of the TPT charge fastened to the body and / or bottoms is carried out in annular sections; when cutting, two sections of a bonded charge with bottoms are separated, after which two longitudinal sections of a semi-cylindrical shape are separated; when cutting, "n" longitudinal sections of a wedge-trapezoidal shape are separated.

The invention is illustrated by graphic images in figure 1, 2, 3.

Figure 1 shows:

- cocoon housing of the rocket engine with a fastened charge TRT, containing barrier belts between the body and the charge, mounted on the roller lodgement supports and connected to the drive rotation (scroll);

- a scheme for cutting and removing strips of a glass-organoplastic case over two annular and one of the "n" -longitudinal barrier belts;

- hydraulic cutting equipment with hydro-jet tools (schematically), their installation and working movements (arrows).

Figure 2 shows:

- scheme for cutting the TRT charge in places of the opened longitudinal barrier belts and variants of the resulting cross-sectional shape of the longitudinal sections bonded to the TPT charge body;

- equipment for machining (cutting) cocoon, glass-organoplastic body - metal-cutting machine; adjusting and working movements of a mechanical cutting tool (arrows).

Figure 3 shows the options for the construction of the cross section of the barrier belt of the cocoon, glass-organoplastic body (annular and / or longitudinal).

The cocoon housing of the rocket engine with a fixed charge TPT contains a glass-organoplastic body 1, charge TPT 2, heat-shielding coating 3, a protective-fixing layer 4, annular barrier belts 5, longitudinal barrier belts 6.

The annular and longitudinal barrier belts 5, 6 are installed on the inner cylindrical surface of the glass-organoplastic body 1 and contain grooves, through channels in their bottom 7, sides 8, the central body 9 and the strip 10 of release material, for example, Teflon. The troughs, through channels in their bottom 7 and sidewalls 8 are formed by two Z-shaped profiles. Under the sidewalls 8 of the barrier belt, liners 11 are installed in the form of wedges of heat-shielding material. In the central body 9, channels (holes) 12 are made for accommodating cable lines (wires). The central body can be made in the form of a package of flat cables and a casing (not shown). Threaded holes can be made in the central body to facilitate disassembly. Above the barrier belt, for orientation of the location and opening, a protruding reference mark 13 is wound into the glass-organoplastic case.

Production of glass-organoplastic housing, incl. installation and fixing on its inner surface of the barrier belts 5, 6 is fully consistent with the known methods of manufacturing a fuel charge bonded to a cocoon-type housing:

- direct filling of the fuel mass into the prepared engine block;

- winding the finished charge of TRT with a glass tape impregnated with resin, followed by polymerization (Fakhrutdinov I.Kh. and Kotelnikov A.V. Design and design of solid propellant rocket engines. M., 1987, p. 43, subsection 2.2.2).

In the manufacture of a glass-organoplastic case for direct pouring of fuel mass, in a mandrel for winding a glass or organ fiber impregnated with a binder (Fakhrutdinov I.Kh. and Kotelnikov A.V. Design and design of rocket engines of solid fuel. M., 1987, p. 10 11, subsection 1.1.2) carry out the corresponding recesses (troughs), in which flush belts 5, 6 are installed flush with its outer surface. When winding and polymerizing the housing 1, belts 5, 6 are glued to it with pre-applied (installed) adhesive Leave 14 and remain on the inner surface after removal of the mandrel.

In the manufacture of a glass-organoplastic case by winding a finished charge cast in a mold, the barrier belts 5, 6 are stacked at the corresponding places of charge 2 before winding the tape, similarly to laying other devices and elements (Fakhrutdinov I.Kh. and Kotelnikov A.V. Design and engineering solid propellant rocket engines., M., 1987, p. 45, subsection 2.2.2). After completing the winding of the housing, the barrier belts 5, 6 are installed (fixed) between the housing and the charge.

Upon elimination, the TPT charge attached to the housing is installed on the roller bed supports 15, connected to a rotation and scroll drive, for example, by means of a flange shaft 16 coaxial to the housing, after which, using normal mechanical equipment (metal cutting machine) 17, glass is cut under normal workshop conditions -organoplastic body above each barrier belt 5, 6, and when cutting the body over the annular belt 5, the body is rotated with charge, and when cutting over the longitudinal zones 6 - scrolling, fix.

The cutting of the glass-organoplastic case is performed within the width of the barrier belt, while: during cutting, a mechanical tool, for example, a disk cutter 18, cutting through the thickness of the glass-organoplastic case meets an obstacle in the form of a barrier belt - sidewalls 8 and the central body 9, which exclude it contact with the fuel charge 2. In addition, the mechanical characteristics of the material of the sidewalls 8 and the central body 9 are made with a higher resistance to mechanical penetration than the glass-organoplastic body nd it a cutting tool, which, in turn, does not allow a pass-through tool to charge TRT, such as blunt instrument; the thermal effect that occurs during mechanical cutting of the body is dissipated by the constituent elements (parts) of the barrier belt, insulated by heat-shielding and protective-fixing layers 3, 4, as well as heat-shielding inserts 11 installed under the sidewalls 8, and is not dangerous for the TPT 2 charge from the point of view its ignition; in this way, a strip of the glass-organoplastic case is cut out and removed above each of the belts 5, 6, and more precisely above the dismantled central body 9 of each belt.

After dismantling the strip 10, the central body 9 (opening the barrier belts) through the grooves and through channels in their bottom 7, using hydraulic cutting equipment 19 with a waterjet tool - nozzle 20 and the working and installation movements of the case with TRT charge, which are the same as during mechanical cutting, carry out cutting of the TPT 2 charge, as a result of which sections of the TPT 21, 22, 23, 24, 25 of a different shape bonded to the body are obtained (21, 22, 23 — ring sections, 24, 25 — longitudinal sections of a semicylindrical and wedge-trapezoidal shape).

The advantage of the proposed solid rocket motor housing with barrier belts installed on its inner surface and the method of sectional elimination of the TPT charge bonded to the housing is:

- safety of cutting a glass-organoplastic case with a fastened TPT charge by the universal mechanical method by eliminating the contact of the cutting tool and the TPT charge with barrier belts;

- ease of opening the barrier belts by dismantling the central body, providing convenient access to the charge of the TRT for its hydro-jet cutting;

- obtaining large sections of the TPT charge bonded to the body with the maximum open surface area thereof.

The proposed design of the solid-propellant solid-propellant rocket housing with barrier belts between the power shell and the TRT charge, and the method of liquidation cutting of such a solid mass with the TRT charge, solve one of the urgent problems of eliminating and subsequently disposing of the solid-state solid propellant charges attached to the housing without burning or undermining it, or which remains always difficult and hazardous, butchering the TRT charge inside the solid propellant rocket case.

Information sources

1. Patent RU No. 2143660, MKI 6 F42B 33/06. The method of eliminating charges of solid rocket fuel (TRT), 1999.

2. Patent RU No. 2042853, MKI 6 F02K 9/08, 9/34. Rocket engine, 1995.

3. Patent RU No. 2262068 C2 (application No. 2003129767 dated 06.10.2003), IPC F42B 33/06, F42D 5/04, С06В 21/00. The method of eliminating the charge of solid rocket fuel (TRT), 2005.

4. Patent RU No. 2230925, IPC 7 F02K 9/34, 9/08, F42B 12/72. Organoplastic rocket body.

5. Fakhrutdinov I.Kh. and Kotelnikov A.V. Design and engineering of solid propellant rocket engines. M., 1987, pp. 10-11, 43-45, subsections 1.1.2, 2.2.2.

6. Monroe J.W. et.al. U.S. Patent No. 3312231, 1967.

7. Scott L.B. U.S. Patent No. 3440096, 1969.

8. T.M. Melkushov, N.I. Melik-Pashaev, P.G. Chistyakov, A.G. Shiukov. Rocket engines. M., 1968, pp. 485-487.

Claims (20)

1. The cocoon body of a rocket engine with a charge of solid rocket fuel (TRT), made of glass-organoplastic fiber and containing a heat-shielding and / or protective-fixing layer, characterized in that barrier belts are installed on the inner surface of the body in places for future liquidation cutting, each of which is made in the form of a groove with a central body placed in it with the possibility of dismantling, while at the bottom of each of the grooves a channel is made through, mainly coaxially to it, between the body and the central body of the mouth Credited strip of release material, and a sidewall barrier belts are fastened, preferably an adhesive composition to the body and made of a material resistant to mechanical penetration of the cutting tool is higher than that of the body material. 2. The cocoon body according to claim 1, characterized in that the barrier belts are installed between the body and the heat-shielding or protective-fixing layer. 3. Cocoon casing according to any one of claims 1 or 2, characterized in that the gutter of the barrier belt, the channel in the bottom of the gutter and its sidewalls are formed by two Z-shaped profiles, while the channel in the bottom of the gutter is formed by their shelves facing each other, and under the sidewalls of the belt there are liners made of heat-protective material in the form of wedges. 4. Cocoon casing according to any one of claim 1 or 2, characterized in that the central body is made in the form of installed adjacent to each other, adjacent inserts. 5. Cocoon casing according to any one of claims 1 or 2, characterized in that a number of threaded holes are made in the central body to provide and facilitate its dismantling. 6. Cocoon casing according to any one of claims 1 or 2, characterized in that in the central body channels are made with the possibility of placing cable lines in them. 7. Cocoon casing according to any one of claims 1 or 2, characterized in that the central body is made in the form of a packet of flat cables and a casing. 8. Cocoon casing according to any one of claims 1 or 2, characterized in that the width of the barrier belt A and its height B are made with the ratio A: B = (1.5-4) C: (0.05-0.7) C, where C is the width of the trough in the place of contact with the inner surface of the housing. 9. Cocoon casing according to any one of claims 1 or 2, characterized in that on its outer surface a trace of the barrier belt is made in the form of wound and protruding outward reference marks / signs. 10. The cocoon body according to claim 9, characterized in that the frames / signs on the body are placed and fixed on a guide, for example, a wire string. 11. Cocoon casing according to any one of claims 1 or 2, characterized in that the barrier belts are circular. 12. Cocoon casing according to any one of claims 1 or 2, characterized in that in the transition zones of the bottoms into a cylindrical shell, two annular barrier belts and two adjacent, diametrically opposed longitudinal barrier belts are installed. 13. Cocoon casing according to any one of claims 1 or 2, characterized in that "n" longitudinal barrier belts are installed. 14. Cocoon casing according to any one of claims 1 or 2, characterized in that the ring and two - or "n" - adjacent to them longitudinal barrier belts are installed. 15. The method of sectional elimination of the charge of solid fuel (TRT), bonded to the cocoon housing of a solid propellant rocket engine (solid propellant rocket engine), including cutting, mainly mechanical, solid propellant rocket motors, hydro-jet cutting of the solid propellant rocket charge and separation of charge fragments and housing, characterized in that cutting out the strip of the solid propellant rocket housing made according to one of claims 1-14, within the width of the barrier belts, and removing them above each of the barrier belts, then opening the barrier belts to provide access to the surface of the TRT charge and at the end of hydrojet cutting of the TPT charge, sections of the TPT charge bonded to the body and / or bottoms are separated. 16. The method according to clause 15, wherein the hydro-jet cutting charge TPT start with cutting heat-protective and / or protective-fixing layer. 17. The method according to any one of p. 15 or 16, characterized in that the separation of the charge fastened to the housing and / or bottoms is carried out in annular sections. 18. The method according to any one of p. 15 or 16, characterized in that when cutting, two sections of a bonded charge with bottoms are separated, after which two longitudinal sections of a semi-cylindrical shape are separated. 19. The method according to any one of p. 15 or 16, characterized in that a strip of the solid propellant canister is cut out with a width of (1.0-1.4) C, where C is the opening width of the barrier belt at the point of contact with the internal surface of the solid propellant canister. 20. The method according to p. 15, characterized in that when cutting is separated "n" of the longitudinal sections of the wedge-trapezoidal shape.

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