RU2336259C2 - Armor cover for insert charge of composite solid propellant and method of its manufacture - Google Patents

Abstract

FIELD: defense equipment; weapons and ammunition.

SUBSTANCE: armor cover for insert charge of composite solid propellant (CSP) contains double-layer material. The first layer heat-shielding cover with thickness of 0.5...2.0 mm is made in the form of rubber that is backed up with asbestos or asbestos-lavsan cloth, and the second layer the forming one is made in the form of organoglass armor with thickness of 0.1-0.2 mm and width of 15-50 mm impregnated with heat resistant epoxide binder. Onto cloth base of heat-shielding cover organoglass armor is wound, which is impregated with heat resistant epoxide binder in 1...3 passes with layers overlapping in 1...3 mm. Consumption of heat resistant epoxide binder amounts to 250...500 g/cm².

EFFECT: provides manufacture of high quality items with required level of operational characteristics without additional investment.

2 cl, 1 dwg, 3 tbl

Description

The present invention relates to the field of rocket technology and relates to the creation of an armor case for an external charge from a mixed solid fuel (CTT) to a rocket engine (RD) and a method for its manufacture.

One of the known methods for booking TPT charges is the filling method, which consists in installing the armored checker in the mold and filling the gap between the checker and the mold with liquid armored personnel, followed by its polymerization and removing the reserved charge from the mold. The well-known technological scheme for the manufacture of charges using a metal or fiberglass body consists in preparing the inner surface of the body by shot peening, applying glue of the Leikonat type, laying out a heat-protective coating (TZP), vulcanizing it, roughening the surface of the TZP, degreasing with solvent, drying and filling with a mixed solid fuel. This cycle is long, time-consuming, energy-intensive and does not exclude the occurrence of defects (non-glueing) when gluing the heat-transfer compound to the surface of the body, which will subsequently lead to the destruction of the engine.

There is a method of manufacturing a fiberglass bronchial cover (USSR author's certificate No. 132806 of November 14, 1959) based on modified epoxy resins, but this material has the ability to form high-strength coke at high temperatures, which gives increased brittleness to the material, and the presence in the binder of the solvent is acetone contributes to the appearance of air bubbles and shells in the glass material. The use of this method of manufacturing an armor shell for a rocket engine is impossible due to the occurrence of defects, violation of the integrity of the armor shell and low heat resistance.

The closest technical solution to inventions is the booking method in the process of charge formation using ready-made armored covers of two-layer material consisting of rubber duplicated with asbolavsan or nylon fabric according to the method described in the concise encyclopedic dictionary “Energy Condensed Systems” edited by Academician B .P. Zhukova, p. 264, 236 (prototype), which notes the difficulty of mounting the armor shell in the mold. In addition, the armored shell does not give the formed charge additional rigidity for its stable operation under conditions of aerodynamic heating.

The technical task of the claimed inventions is the development of an armored cover and a method for its manufacture with improved technological and operational properties, providing:

- ease of installation and fastening of the bronchial cover in the mold during charge formation;

- the exception of the machining operation and technological losses of CTT;

- reliability of the charge from the CTT to the taxiway under the influence of aerodynamic heating.

This problem is solved due to the fact that the bronchial cover for an additional charge from CTT to RD consists of two layers:

1st layer - a heat-protective coating (TZP) with a thickness of 0.5-2.0 mm, consisting of rubber based on nitrile, ethylene propylene, divinyl isoprene or fluorine rubbers, duplicated with asbotkan or asbolavsan fabric, and connected to the 2nd layer;

The 2nd forming layer is made of organoglass reinforcement with a thickness of 0.1-0.2 mm and a width of 15-50 mm, impregnated with a heat-resistant epoxy binder.

The technical result is achieved due to the method of manufacturing an armored cover for an additional charge from STT to RD, which consists in laying layers of organoglass reinforcement, impregnated with a heat-resistant epoxy binder composition of hot curing, directly on the fabric base of the heat-transfer agent (1st layer) in 1-3 passes with an overlap of 1 -3 mm, and the consumption of heat-resistant epoxy binder is 250-500 g / m ² , depending on the geometric dimensions (thickness and width) of organoglass reinforcement.

The claimed inventions are so interconnected that they form a single inventive concept. Indeed, when creating an armor case with the required properties, a method for its manufacture was invented.

The use of an armored cover made by the proposed method allows us to solve the problem with obtaining the required technical result - to obtain an armored cover that provides reliable mounting of the CTT to the TZP and guarantees reliable operation of the taxiway. Therefore, the claimed invention satisfy the requirement of unity of invention.

The invention consists in the following.

The heat-resistant epoxy binder composition for impregnation of organoglass reinforcement is prepared in conventional mixers as follows: epoxy resins with molecular weights 390-450 and 480-540 (epoxy resins ED-20 and ED-16, respectively), the product of the condensation of ethriol with epichlorohydrin (resin brand EET -1) and the epoxy cyanuric resin is mixed at a temperature of 80-100 ° C for at least 15-30 minutes at a stirrer rotation speed of 125-158 rpm, the temperature of the mixture is reduced to 50-60 ° C and a portion of isomethyl tetrahydrophthalic anhydride is introduced, mixed When a temperature of 55 ± 5 ° C for 15-30 minutes at a speed of 125-158 rev / min while evacuating under a residual pressure less than 20 mmHg

The viscosity of the uncured epoxy binder at a temperature of 20-60 ° C according to the B3-1 viscometer is not more than 60 seconds, survivability is 2-6 hours at a temperature of 60 ° C.

Prepared rubber blanks made of rubber (ethylene-propylene, nitrile, divinylisoprene or fluorine-rubber) duplicated with asbot cloth or asbolavsan fabric are laid on a special mandrel wrapped with fluoroplastic tape. Laying is carried out on a fluoroplastic tape with a rubber surface, which provides strong bonding of TZP with CTT, and the fabric base is turned to impregnated organoglass reinforcement, this provides reliable bonding with the 2nd molding layer. The thickness of the 1st layer of TZP is 0.5-2.0 mm. The 2nd forming layer of organo-fiberglass made of organo-glass reinforcement with a thickness of 0.1-0.2 mm and a width of 15-50 mm, impregnated with a heat-resistant epoxy binder composition, followed by curing with increased temperature (see drawing, pos.2).

Laying organoglass reinforced with heat-resistant epoxy binder is carried out in 1-3 passes with an overlap of 1-3 mm. The consumption of the impregnating composition is 250-500 g / m ² .

The finished bronchial shell is cured at a temperature of 150-155 ° C for 5 hours, then without using additional special equipment it is installed in the mold and filled with mixed solid fuel.

The invention is illustrated in the graphic material and the test results of the organo-fiberglass material of the bronchial cover made by the proposed method.

The drawing shows the constituent elements of the bronchial cover.

1 - rubber based on nitrile, ethylene propylene, divinyl isoprene or fluorine rubber, duplicated with asbestos or asbolavsan fabric;

2 - organoglass reinforced with heat-resistant epoxy binder.

Table 1 The characteristics of the material manufactured by the proposed method Indicator, units Indicator value Viscosity of uncured heat-resistant epoxy binder, sec per B3-1 60 Tensile strength, σ, kgf / cm ² at a temperature of 20 ° C 500 100 ° C 500 145 ° C 450 Elongation, ε,% at a temperature of 20 ° C 8.5 100 ° C 8.5 145 ° C 11.0 The modulus of elasticity, E _2% , kgf / cm ² at a temperature of 20 ° C 6500 100 ° C 7000 145 ° C 6000

table 2 Mechanical properties of the material depending on the geometric parameters of the 2nd molding layer Physico-mechanical properties of the 2nd layer Geometrical parameters of the 2nd forming layer σ, kgf / cm ² ε,% E _2% , kgf / cm ² Width of organoglass reinforcement, mm Thickness of organoglass reinforcement, mm Overlap, mm Count aisles Flow binder, g / ^m2 507 8.5 6570 fifteen 0.10 one one 250 500 8.9 6500 fifteen 0.15 2 2 375

Continuation of table 2 Physico-mechanical properties of the 2nd layer Geometrical parameters of the 2nd forming layer σ, kgf / cm ² ε,% E _2% , kgf / cm ² Width of organoglass reinforcement, mm Thickness of organoglass reinforcement, mm Overlap, mm Count aisles Flow binder, g / ^m2 515 9.0 6700 fifteen 0.20 3 3 500 518 8.7 6495 thirty 0.10 one one 250 525 8.6 6650 thirty 0.15 2 2 375 505 8.8 6900 thirty 0.20 3 3 500 520 8.9 6700 fifty 0.10 one one 250 510 8.4 6800 fifty 0.15 2 2 375 500 8.5 6500 fifty 0.20 3 3 500

Table 3 The fastening strength of the 2nd molding layer of the bronchial cover, depending on the thickness of the 1st layer of TZP The thickness of the 1st layer - TZP, mm The fastening strength of a two-layer TZP with CTT, kg / cm ² The nature of the destruction of adhesive samples * 0.5 9.8 Cohesive for fuel, with an 8-9 mm layer of CTT on a rubber surface 1,0 9.0 1,5 11.5 2.0 12.0 *) Adhesive samples “organo-glass-reinforced plastic (organo-glass reinforcement impregnated with heat-resistant epoxy binder) + two-layer TPP (rubber dubbed with asbot cloth or asbolavsan fabric) + CTT”

From the presented data it is seen that the use of heat-resistant epoxy binder provides high physicomechanical characteristics of the obtained material (organo-fiberglass plastic), so, for example, elongation is at a high level in the range of 8.5-11.0% depending on temperature, which is much higher known fiberglass, with high tensile strength of 500 kgf / cm ² at a temperature of 20 ° C and 450 kgf / cm ² at a temperature of 145 ° C. The bronchial shell has a significantly low modulus of elasticity at a temperature of 20 ° C - 6500 kgf / cm ² and 7000 and 6000 kgf / cm ² at temperatures of 100 ° C and 145 ° C, respectively.

The high physical and mechanical characteristics of the obtained material (organo-fiberglass plastic) change insignificantly when using organo-glass reinforcement with various geometric parameters (width, thickness and overlap of organo-glass reinforcement, number of passes). The consumption of heat-resistant epoxy binder directly depends on the geometric parameters of organoglass reinforcement (width, thickness and overlap, number of passes).

The thickness of the 1st layer (TZP) of 0.5-2.0 mm provides high adhesive strength of the fastening of TZP to CTT, which is in the range of 9-12 kgf / cm ² and determined by the strength of CTT.

The use of heat-protective coating (TZP) allows to reduce the technological process of manufacturing hulls for filling and manufacturing plug-in charges from mixed solid fuel to rocket engines, while preserving all the required characteristics presented to the taxiway hulls. The manufacturing quality of organo-glass-plastic bronchial covers with TZP using organo-glass reinforcement impregnated with a heat-resistant binder composition ensures high reliability of charges from CTT to RD during the entire warranty period. An armored cover for an extra charge from CTT to RD is prepared using various types of rubbers, such as 51-2166, 51-2180, 51-2185, 51-1667, etc.

Thus, the claimed inventions simplify the technological process of forming a charge, exclude the operation of mechanical processing of the charge, and also exclude the technological losses of mixed solid fuel, all this reduces the complexity. The claimed inventions provide reliable fastening of mixed solid fuel to the TZP, thereby guaranteeing trouble-free operation of the input charge from the mixed solid fuel to the rocket engine during the entire warranty period of storage.

Claims (2)

1. An armored cover for a plug-in charge from a mixed solid fuel to a rocket engine, containing a two-layer material, characterized in that the first layer in the form of a heat-protective coating with a thickness of 0.5 ... 2.0 mm is made of rubber dubbed with asbestos or asbolavsan fabric, and the second layer, forming, is made in the form of organo-glass reinforcement with a thickness of 0.1 ... 0.2 mm and a width of 15 ... 50 mm, impregnated with a heat-resistant epoxy binder. 2. A method of manufacturing an armor case for a plug-in charge from a mixed solid fuel to a rocket engine, including laying layers, characterized in that a layer of organo-glass reinforcement impregnated with heat-resistant epoxy binder in 1 ... 3 passes with an overlap of layers in 1 ... 3 mm, and the flow rate of heat-resistant epoxy binder is 250 ... 500 g / m ² .