RU2528194C1 - Solid-propellant rocket engine body (versions) and its fabrication (versions) - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: rocket engine body comprises structural shell lined with heat-resistant coat with plug-in resilient collars. Joint between collars and heat-resistant coat has circular cavity composed of spaced equidistantly circular belts connected on outer edge side and equipped with conical sections on inner edge side. Interconnected layers of elastoplastic woven material are arranged in circular cavity following equidistantly the cavity surface opposite part. Woven material layers feature variable transverse length increasing from inner to outer edges with, mainly, congruent opposed surfaces of adjacent layers and parts of one layer. Outer layer of woven material is secured over outer surface with said collar and heat-resistant coat. In compliance with the other version, extra layer of elastoplastic material is arranged in collar and heat-resistance coat material bulk. At making the rocket engine body, collar of sheet material is placed on mandrel and, outside said collar, said heat-resistant coat. Lengthwise package of tapes of elastoplastic woven material with width increasing over the package depth. Tape of rubber-like material is applied on package wider side. Said package is compacted at higher temperature unless rubber-like material is embedded in the structure of adjoining fabric. Said package is place on mandrel in collar periphery circle in layer or rubber-like material to cross-link the package end parts. Half of the package is folded from larger radius to smaller one unless two haves contact to release remaining parts of heat-resistant halves. Heat-resistant coat with collet is cured to wind structural shell of polymer composite. In compliance with the other version, set of tapes of woven and rubber-like material are applied, the rubber-like material being applied outward.

EFFECT: higher reliability of solid-propellant rocket engine.

4 cl, 3 dwg

Description

The group of inventions relates to the field of engineering, and in particular to the bodies of solid propellant rocket engines (solid propellant rocket engines) made of polymer composite materials.

The power shell made of polymer composite materials of such a housing has an internal heat-protective coating (TZP) made of rubber-like materials, to which elastic fastening cuffs are attached on the bottoms, designed to protect the end part of the solid fuel from premature ignition during movement (deformation) of the bottom under the influence of internal pressure. The cuff is a thin-walled ring-shaped structure, which is made of a rubber-like material, is connected to the TZP in its outer diameter and is adjacent to the bottom TZP, mainly over the entire surface. The connection of the cuff with the TZP should ensure the operability of the structure with large movements of the bottom - when the cuff and the TZP move away from each other.

Known solid propellant rocket engine made of polymer composite materials with internal TZP and cuffs fastened with it, made on the basis of rubber-like materials [1, p. 61-64]

The well-known solid-propellant solid propellant polymer composite housing made of polymer composite materials containing cuffs fastened with TZP according to the patent [2].

Common disadvantages of such known structures is the low strength of the cuff with the TZP, since with a small radius of transition of their mating surfaces, determined by the thickness of the separation layer of fabric or film, here, like a stress concentrator, a sharp increase in stress occurs under the action of internal pressure and cuff and TZP from each other.

The solid propellant rocket motor enclosure according to [1] is the closest to the claimed one according to the technical nature and the achieved result and is selected as the closest analogue (prototype).

A known method of manufacturing a solid-propellant solid-state housing made of polymer composite materials [3, pp. 434-438, Fig. 6.11.], According to which TPZ with cuffs is laid out from a sheet of rubber-like material, is vulcanized, mounted on a mandrel and wound with a polymer composite material, followed by heat treatment (polymerization).

The known method of manufacturing a solid propellant rocket motor housing does not eliminate the drawback noted in the housing design.

A method of manufacturing a solid propellant rocket motor housing according to [3] is the closest to the claimed technical essence and the achieved result and is selected as the closest analogue (prototype).

The technical problem to which the group of inventions is directed is the development of a relatively simple and technologically advanced construction of a cuff-to-cushion joint design, which allows for a more uniform distribution of stresses in the joints.

The technical result from the use of a group of inventions that are so connected that they form a single inventive concept is to increase the strength of the cuff with the internal TZP, increase the operational and economic efficiency of the design of the solid propellant rocket engine made of polymer composite materials and increase the reliability of the engine as a whole.

The technical problem is solved, and the technical result is achieved by the fact that:

- in an RDTT case containing a power shell made of polymer composite materials with flanges in the pole holes, lined on the inner surface with a heat-shielding coating with reinforcing elastic cuffs from rubber-like materials, according to the invention, the connection of the cuff and the heat-shielding coating contains an annular cavity formed by spaced equidistant, annular bands of their opposite surfaces, conjugated in an arc from their outer edges and provided with intersecting conic areas on the inner side, in which layers of elastic-elastic woven material are fastened to each other, each of which equidistantly repeats the opposite part of the cavity surface, the layers being made variable, growing from the inner to the outer, transverse length, mainly with a congruent arrangement facing each other surfaces of adjacent layers or parts of one layer, the location of the edges of each layer and all together spaced, and the outer layer along its entire outer surface with it is secured due to the introduction of a rubber-like material into its structure, with a cuff and heat-protective coating (option I);

- in an RDTT case containing a power shell made of polymer composite materials with flanges in the pole holes, lined on the inner surface with a heat-shielding coating with reinforcing elastic cuffs from rubber-like materials, according to the invention, the connection of the cuff and the heat-shielding coating contains an annular cavity formed by spaced equidistant, annular bands of their opposite surfaces, conjugated in an arc from their outer edges and provided with intersecting conic areas on the inner side, in which layers of elastic-elastic woven material are fastened to each other, each of which equidistantly repeats the opposite part of the cavity surface, the layers being made variable, growing from the inner to the outer, transverse length, mainly with a congruent arrangement facing each other surfaces of adjacent layers or parts of one layer, the location of the edges of each layer and all together spaced, the outer layer over its entire outer surface eplen, by introducing into its structure a rubber material with a cuff and a thermal coating, and the array of the cuff material and a thermal barrier coating is situated equidistantly cavity surface, at least one layer of elastic material (variant II);

- a method of manufacturing a rocket engine housing (according to option I), which consists in laying out on the form of heat-resistant coatings the bottoms with cuffs, from rubber-like sheet material, vulcanizing them, installing on the mandrel and winding a power shell made of a polymer composite material, according to the invention, they are laid out from sheet a rubber-like material, the cuff and, partially outside the cuff, a heat-insulating coating, collect a longitudinal package of tapes of elastic-elastic woven material of different widths with successively increasing being wide in thickness, they are fastened together, a tape of rubber-like material is laid on a wide side, the package is pressed at an elevated temperature until the rubber-like material is embedded in the structure of at least one layer of adjacent fabric, laid on the mold around the circumference of the cuff with a layer of rubber-like material , they sew together the end parts of the layers of the package, bend half of the package from a larger radius to a smaller one until the two halves touch each other, and then lay out the remaining parts heat-shielding coating (option I);

- a method of manufacturing a rocket engine casing (according to option II), which consists in laying out on the form of heat-resistant coatings the bottoms with cuffs, from rubber-like sheet material, vulcanizing them, installing on the mandrel and winding a power shell made of a polymer composite material, according to the invention, they are laid out from sheet a rubber-like material, the cuff and, partially outside the cuff, a heat-insulating coating, collect a longitudinal package of tapes of elastic-elastic woven material of different widths with successively increasing they are fastened with a width in thickness, they are fastened together, a tape made of rubber-like material is laid on the wide side, and at least one set of tapes of woven and rubber-like materials, the last outward, is pressed into the bag at elevated temperature until the rubber-like material is embedded in the structure of at least one layer of adjacent tissue, laid on the mold around the circumference of the cuff border with a layer of rubber-like material to the mold, sew together the end parts of the packet layers, bend half the packet from a larger radius to m less until the two halves come into contact with each other, and then lay out the remaining parts of the heat-shielding coating (option II).

Distinctive features of the prototype of the solid rocket motor housing are as follows:

according to option I

- the connection of the cuff and heat-protective coating contains an annular cavity formed by spaced equidistant annular belts of their opposite surfaces, conjugated in an arc from their outer edges and provided with interspersed conical sections from the inside,

- in which the layers of elastic-elastic woven material are fastened to each other,

- each of which equidistantly repeats the opposite part of the surface of the cavity,

- moreover, the layers are made of a variable, growing from internal to external, transverse length,

- mainly with a congruent arrangement facing each other of the surfaces of adjacent layers or parts of one layer,

- the location of the edges of each layer and all together spaced,

- and the outer layer is bonded over its entire outer surface, due to the introduction of rubber-like material into its structure, with a cuff and heat-protective coating;

according to option II

- the connection of the cuff and heat-protective coating contains an annular cavity formed by spaced equidistant annular belts of their opposite surfaces, conjugated in an arc from their outer edges and provided with interspersed conical sections from the inside,

- in which the layers of elastic-elastic woven material are fastened to each other,

- each of which equidistantly repeats the opposite part of the surface of the cavity,

- moreover, the layers are made of a variable, growing from internal to external, transverse length,

- mainly with a congruent arrangement facing each other of the surfaces of adjacent layers or parts of one layer,

- the location of the edges of each layer and all together spaced,

- the outer layer is bonded over its entire outer surface, due to the introduction of rubber-like material into its structure, with a cuff and heat-protective coating,

- and in the array of cuff materials and the heat-shielding coating, at least one layer of elastic material is located equidistant to the cavity surface.

Distinctive features of the prototype signs of a method of manufacturing a solid propellant rocket motor housing are as follows:

according to option I

- a cuff is placed on the mold from a sheet of rubber-like material and, partially outside the cuff, a heat-shielding coating;

- collect a longitudinal package of tapes of an elastic elastic woven material of different widths with a successively increasing width in thickness;

- fasten together;

- from a wide side they lay a tape of rubber-like material;

- prepress the package at elevated temperature until the introduction of rubber-like material in the structure of at least one layer of adjacent tissue;

- stack on the mold around the circumference of the cuff border with a layer of rubber-like material to the mold;

- stitch together the end parts of the layers of the package;

- bend half of the packet from a larger radius to a smaller one until the two halves come into contact with each other;

- and then lay out the remaining parts of the heat-shielding coating;

according to option II

- a cuff is placed on the mold from a sheet of rubber-like material and, outside the cuff, partially, a heat-protective coating;

- collect a longitudinal package of tapes of an elastic elastic woven material of different widths with a successively increasing width in thickness;

- fasten together;

- from a wide side they lay a tape of rubber-like material;

- and at least one set of tapes of woven and rubber-like materials, the last outward;

- prepress the package at elevated temperature until the introduction of rubber-like material in the structure of at least one layer of adjacent tissue;

- stack on the mold around the circumference of the cuff border with a layer of rubber-like material to the mold;

- stitch together the end parts of the layers of the package;

- bend half of the packet from a larger radius to a smaller one until the two halves come into contact with each other;

- and then lay out the remaining parts of the thermal barrier coating.

These distinctive features of the claimed group of inventions are significant, because each of them individually and jointly aimed at solving the problem and obtaining a new technical result.

The RDTT case, in contrast to the prototype case, is more versatile and effective in operational characteristics, since by varying the cavity geometry, it is possible to ensure the cuff connection with the transformer substation in a wide range of operating loads due to smoothing out large deformations and stresses that occur during engine operation. The provision and preservation of the necessary cavity geometry during the entire production and operation cycle is determined by the number of layers used and their fixed location. The bonding of the outer elastic elastic woven layer with the material of the cuff and TZP ensures the reliability of the location of the woven layers during the entire cycle of manufacturing and operation of the engine, and also reduces the possibility of surface cracks during engine operation, with large deformations with heating.

According to the body of the solid-propellant solid propellant (option II), in addition to the features of the housing (option I), at least one layer of elastic material of the woven material located in the cuff and TPP material array provides additional reinforcement of the joint and prevents the propagation of possible cracks, which together expand the range of possible perceived loads.

Distinctive essential features are new, since their use in well-known technical solutions, analogues and prototype was not found, which allows us to characterize the proposed solid propellant rocket engine made of composite materials according to the criterion of ″ novelty ’.

A single set of new distinctive essential features with common known allows us to solve the problem and achieve a new technical result, which characterizes the proposed technical solution by significant differences from the prior art, analogues and prototype. The new technical solution was obtained without the use of standards and recommendations of a general technical nature and of any well-known projects. It is the result of a creative contribution, research and experimental development of the design of cases, materials and technology, which makes it possible to characterize “inventive step” by its criterion.

The invention is illustrated by a description of a specific, but not limiting, example of implementation and the accompanying drawings.

In Fig.1 shows a cross section of the body of the solid-propellant rocket engine with the location of the cuff and TZP, Fig.2 - the connection of the cuff with the TZP according to option I, in Fig. 3 - the junction of the cuff with the TZP according to option II.

Figure 1 shows: the power shell 1, the flange 2, the internal TZP 3, the cuff 4, the annular cavity 5 in the connection of the cuff with the TZP.

For options I and II (FIGS. 2, 3): an annular cavity 5 at the junction of the cuff 4 with TZP 3 and the ring girdles 6 and 7 forming its surface, the conjugation arc 8, the diverging conical sections 9 and 10, the layers of elastic fabric 11 .

The number of layers is selected depending on the transverse width of the cavity and the thickness of the used elastic material.

According to option II: a layer of elastic material 12 in the array of rubber-like material of the cuff and TZP

Experimental verification confirmed the high strength and reliability of the proposed design.

Thus, the new technical solution is reproducible under production conditions, provides a solution to the problem and the achievement of a new technical result, in the proposed set of features meets the criterion of "industrial applicability", that is, the level of the invention.

Literature

1. Designs of solid propellant rocket engines. / Under total. ed. Corr. Russian Academy of Sciences, Doctor of Technical Sciences, prof. L.N. Lavrov. - M.: Mechanical Engineering, 1993. - 215 p., Ill.

2. The housing of the rocket engine of solid fuel. RF patent 2302546 from 08/10/2005.

3. Bulanov I.M., Vorobey V.V. Technology of rocket and aerospace structures from composite materials: Textbook. for universities. M.: Publishing House of MSTU. N.E. Bauman, 1998 .-- 516 p., Ill.

Claims (4)

1. The housing of a rocket engine of solid fuel, containing a power shell made of polymer composite materials with flanges in the pole holes, lined on the inner surface with a heat-shielding coating with unfastening elastic cuffs from rubber-like materials, characterized in that the connection of the cuff and the heat-shielding coating contains an annular cavity formed by spaced equidistantly annular belts of their opposite surfaces, conjugated in an arc from their outer edges and equipped and overlapping conical sections from the side of the inner edges, in which layers of elastic-elastic woven material are fastened to each other, each of which equidistantly repeats the opposite part of the cavity surface, the layers being made variable, increasing from the inner to the outer, transverse length, mainly with a congruent arrangement of the inverted to each other of the surfaces of adjacent layers or parts of one layer, the location of the edges of each layer and all together spaced apart, and the outer layer across its outer surface bonded, by introducing into its structure a rubber material with a cuff and thermal barrier coating. 2. The housing of a rocket engine of solid fuel, containing a power shell made of polymer composite materials with flanges in the pole holes, lined on the inner surface with a heat-shielding coating with unfastening elastic cuffs from rubber-like materials, characterized in that the connection of the cuff and the heat-shielding coating contains an annular cavity formed by spaced equidistantly annular belts of their opposite surfaces, conjugated in an arc from their outer edges and equipped and overlapping conical sections from the side of the inner edges, in which layers of elastic-elastic woven material are fastened to each other, each of which equidistantly repeats the opposite part of the cavity surface, the layers being made variable, increasing from the inner to the outer, transverse length, mainly with a congruent arrangement of the inverted to each other the surfaces of adjacent layers or parts of one layer, the location of the edges of each layer and all together spaced apart, the outer layer on all its outer surface bonded, by introducing into its structure a rubber material with a cuff and a thermal coating, and the array of the cuff material and a thermal barrier coating is situated equidistantly cavity surface of at least one layer of elastic material. 3. A method of manufacturing a rocket engine housing, which consists in laying out the bottoms on the form of heat-protective coatings with cuffs of sheet rubber-like material, vulcanizing them, installing on the mandrel and winding a power shell of polymer composite material, characterized in that a cuff is laid out of the sheet rubber-like material on the mold and, outside the cuff, partially, a heat-protective coating, they collect a longitudinal package of tapes of an elastic elastic woven material of different widths with a successively increasing width n thickness, fasten together, on a wide side lay a tape of rubber-like material, compress the bag at elevated temperature until the rubber-like material is embedded in the structure of at least one layer of adjacent fabric, lay on the mold around the circumference of the cuff with a layer of rubber-like material to the mold, sew between themselves the end parts of the layers of the package, bend half of the package from a larger radius to a smaller one until the two halves touch each other, and then lay out the remaining parts of the heat-shielding of coverage. 4. A method of manufacturing a rocket engine case, which consists in laying out the bottoms with cuffs of sheet rubber-like material on the form of heat-protective coatings, curing them, installing on the mandrel and winding a power shell of polymer composite material, characterized in that a cuff is laid out of the sheet rubber-like material on the mold and, outside the cuff, partially, a heat-protective coating, they collect a longitudinal package of tapes of an elastic elastic woven material of different widths with a successively increasing width across the thickness is fastened together, a tape of rubber-like material is laid on the wide side, and at least one set of tapes of woven and rubber-like materials, the last outward, is pressed into the bag at an elevated temperature until the rubber-like material is embedded in the structure of at least one layer of adjacent fabric , they are placed on the mold around the circumference of the cuff border with a layer of rubber-like material to the mold, the end parts of the packet layers are sewn together, the half of the packet is bent from a larger radius to a smaller radius to fit and the base of the two halves between each other, and then lay out the remaining parts of the thermal barrier coating.

Images