CN114893323A - Anti-adhesion reinforced framework end-burning charge and preparation process thereof - Google Patents

Abstract

The invention provides an anti-debonding and reinforcement framework end-burning charge, and belongs to the technical field of charge structures. This anticreep glues reinforcing skeleton end and fires the powder charge and include: heat insulating layer, lining and grain; further comprising: reinforcing the skeleton; the reinforced framework comprises a framework A embedded in the coating sleeve and a framework B embedded in the grain; the framework B is connected with the framework A in the circumferential direction of the framework A. Under the action of the same load (internal pressure, temperature, acceleration and the like), the charge with the structural form can improve the axial compression resistance of the explosive column, reduce the interface debonding risk and improve the interface bonding quality, thereby improving the working safety coefficient of the solid rocket engine. In addition, the invention also provides a preparation process of the anti-viscidity reinforced skeleton end-burning charge.

Description

Anti-adhesion reinforced framework end-burning charge and preparation process thereof

Technical Field

The invention relates to a charge structure, in particular to an anti-debonding reinforced framework end-burning charge, and belongs to the technical field of charge structures.

Background

The solid rocket engine can cause the debonding of the charging interface (the debonding refers to the separation of the bonding interface between the explosive column and the heat insulating layer) through the links of pouring, curing, cooling, assembly, transportation and the like and the environment of temperature circulation, temperature gradient and the like possibly existing in the delivery.

The most accident easily occurs to the rocket engine containing debonding solid during ignition, and the main reason is that when the engine is ignited and pressurized, fuel gas can enter a debonding crack cavity to cause the exposed combustion of a non-designed combustion surface of a propellant; for end-burning charge, the designed burning surface is an axial end surface, and if the interface is debonded, the outer circumferential surface serving as the non-designed burning surface of the propellant can be exposed and burned; thereby causing accidents such as internal ballistic performance change, fire penetration or explosion of the engine. Therefore, the quality of the engine charge interface adhesion is one of the key factors influencing the working safety of the engine.

The existing method for firmly bonding the charging interface inside the combustion chamber of the solid rocket engine mainly depends on the mechanical property of a lining layer and ensures the bonding strength, the bonding area and the like of process implementation. In order to ensure the bonding quality, a lining layer and a cladding sleeve material which are matched with the performance of the propellant are preferably selected during material selection, and the requirements on bonding strength, bonding area and the like are high. In general, the interface bonding quality is improved by the traditional method, and the improvement capability has certain limitation.

Disclosure of Invention

In view of the above, the invention provides an anti-debonding reinforced framework end-fired charge, which is characterized in that a reinforced framework is embedded in a heat insulation layer and a charge column on the basis of not changing the formula of the heat insulation layer and the charge column, so that the mechanical properties of the charge column and the heat insulation layer are effectively improved, the axial compression resistance of the charge column is improved, and the interface debonding risk is reduced, thereby improving the working safety coefficient of a solid rocket engine.

The technical scheme of the invention is as follows: an anti-de-sticking enhanced skeleton end-fire charge comprising: heat insulating layer, lining and grain; the grain is adhered with the coating sleeve through the lining; further comprising: reinforcing the skeleton; the reinforced framework comprises a framework A embedded in the coating sleeve and a framework B embedded in the grain;

the framework B is connected with the framework A in the circumferential direction of the framework A.

Preferably, the skeleton A is consistent with the heat insulating layer in shape and comprises a cylindrical surface and an outward convex arc-shaped surface arranged at one end of the cylindrical surface; which is opened at the initial end face side of the burning of the explosive column.

Preferably, the framework B is a disc-shaped structure which is arranged inside the cylindrical surface of the framework A and is circumferentially connected with the inner circumferential surface of the framework A.

Preferably, the reinforcing framework is of a thin-wall hollow-out type net structure.

Preferably, the reinforcing framework is of an integral and integrally formed structure.

Preferably, the skeleton and the framework can also be prefabricated and formed respectively and then fixed together to form the reinforced framework.

Preferably, the reinforcing framework adopts resin or/and rubber as a matrix material, and adopts fiber wires or/and metal wires as a reinforcing material.

Preferably, more than two frameworks B are distributed at intervals along the axial direction of the framework A.

Preferably, the framework B is perpendicular to the axial direction of the framework A.

In addition, the invention provides a preparation process of the anti-viscidity reinforced skeleton end-burning charge, which comprises the following steps:

firstly, prefabricating and molding the reinforced framework;

when the heat insulation layer is manufactured, embedding a prefabricated reinforced framework into the heat insulation layer;

fixing the prepared heat insulating layer embedded with the reinforced framework by a mould, firstly spraying or brushing a lining layer on the inner wall surface of the heat insulating layer, and then pouring a propellant into the heat insulating layer to be cured to form the explosive column.

Has the advantages that:

(1) on the basis of not changing the formula of the heat insulating layer and the explosive column, the reinforced frameworks are embedded in the heat insulating layer and the explosive column, so that the heat insulating layer and the explosive column have stronger capability of bearing external mechanical load and stronger capability of bearing internal and external pressure difference during working under the condition of the same load (internal pressure, temperature and acceleration), the risk of debonding between the explosive column and the heat insulating layer is effectively reduced, and the working safety coefficient of the solid rocket engine is improved.

(2) The framework A is set to be consistent with the shape of the heat insulating layer, so that the reinforced framework can play a good role, and the debonding of a charging interface is avoided.

(3) The reinforcing framework is a hollow net structure, so that the weight of the reinforcing framework can be effectively reduced; meanwhile, due to the hollow structure, the heat insulating materials at the two hollow sides in the heat insulating layer can be connected into a whole, so that the environmental tolerance of the heat insulating layer is improved; the explosive columns on two sides of the reinforcing framework are connected into a whole through the hollowed-out through holes when being poured and cured, so that the influence on the combustion performance of the explosive columns is reduced, and the structural integrity and the axial compressive capacity of the explosive columns are improved.

(4) The reinforcing framework is of an integral integrated structure, and the use reliability of the reinforcing framework is guaranteed.

(5) More than two frameworks B are distributed at intervals along the axial direction of the framework A, so that the uniformity of the axial compression resistance of the explosive column can be ensured.

Drawings

FIG. 1 is a schematic structural view of an anti-debonding enhanced scaffold end-fire charge of the present invention;

fig. 2 is a schematic structural diagram of a reinforcing cage.

Wherein: 1-coating sleeve, 2-reinforcing framework, 3-lining layer and 4-grain

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following detailed description and accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Example 1:

the embodiment provides an anticreep glues reinforcing skeleton end and fires powder charge, and under the same load (interior pressure, temperature, acceleration etc.) effect, this kind of structural style's powder charge can improve the powder column axial compressive capacity to reduce the interfacial debonding risk, improve the interfacial adhesion quality, thereby improve solid rocket engine factor of safety of operation.

As shown in fig. 1, the anti-debonding enhanced framework end-fire charge comprises: a heat insulating layer, a reinforcing framework 2, a lining 3 and a grain 4; in this example, the insulating layer is a sheathing 1.

The coating sleeve 1 is adhered to the outer part of the medicine column 4, and the lining layer 3 is arranged at the interface of the medicine column 4 and the coating sleeve 1 to enhance the adhesive strength between the medicine column 4 and the coating sleeve 1.

The reinforcing framework 2 is a prefabricated thin-wall hollow-out type net structure and is embedded in the coating sleeve 1 and the medicine column 4.

As shown in fig. 2, the reinforcing cage 2 is a unitary, continuous structure; the reinforced framework 2 is provided with two parts, namely a framework A embedded in the coating sleeve 1 and a framework B embedded in the grain 4; wherein the framework A is a semi-closed continuous structure (i.e. a tuck net shape), and the semi-closed structure means that one end of the framework A is opened, i.e. one side of the combustion initial end surface of the grain 4 is opened and has no reinforced framework; specifically, the shape of the framework A is consistent with that of the coating sleeve 1, and the framework A comprises a cylindrical surface and an outward convex arc-shaped surface arranged at one end of the cylindrical surface.

The framework B is an annular net structure which is arranged inside the cylindrical surface of the framework A and is used for circumferential connection along the circumferential direction of the framework A; i.e., the former B has an annular surface which is continuous with the inner circumferential surface of the former a. In this example, the skeleton B is a disc-shaped structure with grids, and a plurality of mutually parallel skeletons B are uniformly distributed at intervals along the axial direction of the skeleton A; and the frameworks B are all perpendicular to the axial direction of the framework A.

The reinforced framework 2 adopts more than one of resin and rubber as a base material, adopts more than one of fiber and metal wire as a reinforced material, the fiber comprises Kevlar, aramid fiber, carbon fiber and the like, and also can adopt high silica/phenolic aldehyde and carbon fiber/phenolic aldehyde molding materials.

Preferably, the reinforcing framework 2 is an integral molding structure, and the prefabrication molding mode can adopt composite material winding molding, hot press molding, weaving molding, compression molding and other modes.

The framework A and the framework B can also be respectively prefabricated and molded and then fixedly connected together to form a reinforced framework 2; however, in order to ensure that the reinforced framework 2 can well play a role and avoid debonding of a charging interface, the connection strength between the framework A and the framework B is higher than the bonding strength between the coating sleeve 1 and the explosive column 4.

Example 2:

on the basis of the above embodiment 1, specifically:

the two-direction fiber of the cylindrical surface part of the reticular framework A embedded in the coating sleeve 1 is respectively arranged along the circumferential direction and the annular direction of the coating sleeve 1, namely the two-direction fiber is arranged at 90 degrees (the grid is square at the moment), and also can be respectively arranged at a certain angle with the circumferential direction and/or the annular direction of the coating sleeve 1. The grid of the arc-shaped surface part of the framework A can also be square or prismatic.

The two-directional fibers of the net-shaped framework B embedded in the grain 4 are preferably arranged in a staggered way at 90 degrees, and can also be arranged in a staggered way at other angles, namely the net in the net-shaped framework B can be square or prismatic.

Example 3:

in this example, a process for preparing an anti-debonding enhanced bone end-fire charge is provided.

In this example, the propellant (i.e., the grains 4) is a hydroxyl propellant, the reinforcing framework 2 is a composite structure, butadiene rubber with good compatibility with the hydroxyl propellant is preferably used as a base material, so that the interface performance of the reinforcing framework 2 and the grains 4 can be improved, the deformation coordination matching of the grains 2 and the reinforcing framework 4 is improved, and the whole carbon fiber is used as a reinforcing material, so that the carbon fiber can bear larger mechanical load.

The reinforced framework 2 forms a prefabricated part through a composite material laying process to form the reinforced framework 2 with a hollowed-out mesh composite structure, and the mesh size is suitable for construction without influencing the lining 3.

When the coating sleeve 1 is manufactured, the prepared reinforced framework prefabricated part is embedded into the coating sleeve;

then pouring the explosive column 4, when the explosive column 4 is poured and molded, fixing the prepared coating sleeve 1 embedded with the reinforced framework 2 through a mold, firstly spraying or brushing a lining layer on the inner wall surface of the heat insulation layer, and then pouring a propellant into the coating sleeve 1 to form the explosive column 4; the propellant at the two sides of the framework B in the reinforced framework 2 is connected into a whole (because the framework B is of a grid structure, the propellant at the two sides of the framework B can be connected into a whole), the influence on the combustion performance of the explosive column 4 is reduced, and the structural integrity of the explosive column 4 and the axial compression resistance of the explosive column 4 are improved simultaneously. Thereby forming the anti-debonding enhanced framework end-fire charge.

The reinforcing framework embedded into the coating sleeve 1 and the reinforcing framework embedded into the explosive column 4 are of a continuous integral composite structure, under the condition of the same load (internal pressure, temperature and acceleration), the coating sleeve 1 and the explosive column 4 are stronger in the capacity of bearing external mechanical load, and are also stronger in the capacity of bearing internal and external pressure difference during working, the risk of debonding between the explosive column 4 and the coating sleeve 1 is effectively reduced, and the working safety coefficient of the solid rocket engine is improved.

The foregoing is a more detailed description of the present invention that is presented in conjunction with specific embodiments, and the practice of the invention is not to be considered limited to those descriptions. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.

Claims (10)

1. An anti-de-sticking enhanced skeleton end-fire charge comprising: heat insulating layer, lining and grain; it is characterized by also comprising: reinforcing the skeleton; the reinforced framework comprises a framework A embedded in the coating sleeve and a framework B embedded in the grain;

the framework B is connected with the framework A in the circumferential direction of the framework A.

2. The anti-sticking enhanced framework end-fire charge of claim 1, wherein the framework a conforms to the shape of the thermal insulation layer and comprises a cylindrical surface and an outwardly convex arc surface arranged at one end of the cylindrical surface; which is opened at the initial end face side of the burning of the explosive column.

3. The anti-de-sticking enhanced-skeleton end-fire charge of claim 2, wherein the skeleton B is a disc-shaped structure disposed inside the cylindrical surface of the skeleton a and circumferentially connected to the inner circumferential surface of the skeleton a.

4. The anti-debonding enhanced framework end-fire charge according to claim 1, wherein the enhanced framework is a thin-walled hollowed-out mesh structure.

5. The anti-de-sticking enhanced-scaffold end-fire charge of any of claims 1-4, wherein the enhanced scaffold is of unitary integrally-formed construction.

6. The anti-de-sticking enhanced-scaffold end-fire charge of any of claims 1-4, wherein said scaffold A and said scaffold B are each pre-formed and then affixed together to form said enhanced scaffold.

7. The anti-de-sticking reinforced skeleton end-fire charge according to any one of claims 1-4, wherein the reinforced skeleton uses resin or/and rubber as a matrix material and uses fiber wires or/and metal wires as a reinforcing material.

8. The anti-de-sticking enhanced-framework end-fire charge of any one of claims 1-4, wherein two or more frameworks B are spaced apart axially along the framework A.

9. The anti-de-sticking enhanced-scaffold end-fire charge of any one of claims 1-4, wherein the scaffold B is perpendicular to the axial direction of scaffold A.

10. A process for the preparation of an anti-viscogenic enhanced skeleton end-fire charge, characterised in that it is used for the preparation of an anti-viscogenic enhanced skeleton end-fire charge according to any of the claims 1-9:

firstly, prefabricating and molding the reinforced framework;

when the heat insulation layer is manufactured, embedding a prefabricated reinforced framework into the heat insulation layer;

fixing the prepared heat insulating layer embedded with the reinforced framework by a mould, firstly spraying or brushing a lining layer on the inner wall surface of the heat insulating layer, and then pouring a propellant into the heat insulating layer to be cured to form the explosive column.

Images