CN210152806U

CN210152806U - Composite fusible core for manufacturing solid rocket engine charging grain

Info

Publication number: CN210152806U
Application number: CN201920187933.4U
Authority: CN
Inventors: 王君祺; 吴刚; 熊飞
Original assignee: Beijing Smart Flying Power Technology Co Ltd
Current assignee: Shaanxi Lingdong Aerospace Power Technology Co.,Ltd.
Priority date: 2019-02-03
Filing date: 2019-02-03
Publication date: 2020-03-17
Anticipated expiration: 2029-02-03

Abstract

The utility model provides a compound fusible core for making solid rocket engine powder charge grain adopts the demoulding problem that this compound fusible core can solve all kinds of types of medicine, satisfies the manufacturing of all kinds of complicated types of medicine, has solved and has kept somewhere various drawbacks that combustible filler produced. The composite fusible core comprises a core and a fusible core; the core is consistent with the size of a central through hole of the engine charge grain to be manufactured and is used for forming the central through hole of the charge grain; the mold core is made of structural materials; the fusible core is made of low-melting-point alloy; the fusible core is arranged on the mold core, so that the outer profile structure of the composite fusible core is consistent with the inner profile structure of the engine charging grain to be manufactured; when preparing the explosive-filled grain: pouring a propellant outside the composite fusible core, wherein the propellant is solidified to form a grain, and the composite fusible core is arranged inside the grain; and then heating the grain containing the composite fusible core together to enable the fusible core to flow out of the charging hole after being melted, and then drawing out the core to obtain the grain with the required structure.

Description

Composite fusible core for manufacturing solid rocket engine charging grain

Technical Field

The utility model relates to a fusible core, concretely relates to compound fusible core for making solid rocket engine powder charge belongs to solid rocket engine technical field.

Background

Solid rocket engines achieve different internal ballistic performance through the design of the charge form, and the production of the charge form depends on the design of the core mold. The core mould for charging solid engine at present mainly has an integrated core mould and a detachable core mould according to the shape of the charge, the former is used for the shape of the charge which can be directly demoulded after being cured, and the latter is used for the shape of the charge which can not be demoulded directly.

The use of the detachable core mould has certain requirements on the structural size of the engine, the large-size engine can be applied to the detachable core mould with large space, and the small-size engine can only adopt a scheme of retaining combustible fillers for solving the problem due to limited space.

As shown in figure 1, the solid rocket engine charge model containing the circumferential groove is composed of a shell 1, a heat insulating layer 2, a lining 3 and a charge column 4. The inner circumferential surface of the shell 1 is sequentially provided with a heat insulating layer 2 and a lining layer 3, the medicine column 4 is filled in the central hole of the shell 1, and the medicine column 4 is provided with a central through hole and a circumferential groove which is distributed along the axial direction of the central through hole. The charging scheme adopted by the existing medicine type structure is mature as shown in figure 2, combustible filler 5 (such as celluloid) and a core mould 6 are combined for production, after charging 4 is solidified in the production process, the core mould 6 is demoulded to form a medicine column 4, the combustible filler for forming a circumferential groove is left, and the combustible filler 5 is added in a final product as shown in figure 3 compared with figure 1. Although the method realizes the charging shown in fig. 1, the existence of the combustible filler 5 has the following disadvantages:

(1) the combustible filler prevents the fuel combustion surface which is arranged in the annular groove in a split mode from participating in combustion at the initial ignition stage, changes the fuel charge combustion rule, deviates from the design state and influences the ballistic performance.

(2) The combustible filler has certain mass, and under the action of a series of temperatures and mechanical loads in the subsequent service process of the engine, the filler and nearby local charging have complex mechanical behaviors, so that local fatigue of charging is caused, and the combustible filler becomes a weak link in service life.

(3) Since the combustion characteristics of the combustible filler itself have an effect on engine performance, it becomes a factor that must be considered in the charge design, increasing design constraints.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a compound fusible core for making solid rocket engine powder charge grain adopts the demoulding problem that this compound fusible core can solve all kinds of types of medicine, satisfies the manufacturing of all kinds of complicated types of medicine, solves and keeps somewhere various drawbacks that combustible packing produced.

The composite fusible core for manufacturing the solid rocket engine charging grain comprises a core and a fusible core; the core is consistent with the size of a central through hole of the engine charge grain to be manufactured and is used for forming the central through hole of the charge grain; the melting core is made of an alloy material with a melting point higher than the curing temperature of the propellant and lower than the safety temperature of the propellant; the fusible core is arranged on the mold core, so that the outer profile structure of the composite fusible core is consistent with the inner profile structure of the engine charging grain to be manufactured.

The fusible core is made of alloy material with the melting point of 70 ℃.

The core material is steel.

When the engine powder charge grain is the solid rocket engine powder charge grain that contains the circumferential groove, when the grain has central through-hole and follows the circumferential groove of central through-hole axial distribution promptly: the core is a cylindrical structure with the size consistent with that of the central through hole of the grain, the fusible core is an annular bulge which is arranged on the circumferential surface of the core and axially distributed along the circumferential surface of the core, and the size and the position of the annular bulge are consistent with those of an annular groove which is axially distributed along the central through hole on the grain.

Has the advantages that:

the composite fusible core is used for preparing rocket engine charge, the composite fusible core is prepared from low-melting-point alloy, and can flow out of a charge hole after being melted at a set temperature, so that the film can be smoothly removed, the problem of removal of various types of medicines can be solved, the manufacturing of various complex types of medicines is met, and various defects caused by retention of combustible fillers are effectively avoided.

Drawings

FIG. 1 is a schematic illustration of a prior art solid rocket engine charge containing circumferential grooves;

FIG. 2 is a schematic representation of a prior art method of manufacturing a charge using a combustible filler;

FIG. 3 is a finished charge made by the method of manufacture of FIG. 2;

FIG. 4 is a composite fusible core used in the examples;

FIG. 5 is a schematic view of a charge manufacturing method using a composite fusible core;

wherein: 1-a shell; 2-a heat insulating layer; 3-a lining layer; 4-carrying out grain treatment; 5-a combustible filler; 6-core mold; 7-composite fusible core, 71-core; 72-fusible core.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings by way of examples.

The embodiment provides a composite fusible core for manufacturing a solid rocket engine charging grain, and the method for manufacturing the solid rocket engine charging grain is the solid rocket engine charging grain containing the circumferential grooves shown in figure 1.

The solid rocket engine explosive-charging model containing the annular groove comprises a shell 1, a heat insulating layer 2, a lining 3 and explosive columns 4; the inner circumferential surface of the shell 1 is sequentially provided with a heat insulating layer 2 and a lining layer 3, the medicine column 4 is filled in the central hole of the shell 1, and the medicine column 4 is provided with a central through hole and a circumferential groove which is distributed along the axial direction of the central through hole.

In order to charge the explosive type, a composite fusible core shown in figure 4 is adopted, and the composite fusible core is composed of a core 71 and a fusible core 72; the mold core 71 has a cylindrical structure with the same size as the central through hole of the grain 4, and annular bulges are axially distributed on the circumferential surface of the mold core and are consistent with the annular grooves axially distributed on the grain 4 along the central through hole in size and position. The mold core 71 is a structural material, and No. 45 steel is adopted in the implementation; the fusible core 72 is a low-melting-point alloy, the curing temperature of the propellant is 50-60 ℃, the safe temperature is 108 ℃, the melting point of the fusible core 72 is higher than the curing temperature of the propellant and lower than the safe temperature of the propellant, and is as close to the upper limit value of the working temperature of the engine as possible, based on which, the low-melting-point alloy with the melting point of 70 ℃ is adopted in the embodiment, the low-melting-point alloy comprises 50% of bismuth, 25% of lead, 12.5% of tin and 12.5% of cadmium, and the melting point is 70 ℃. The preparation method of the composite fusible core comprises the following steps: firstly, machining and manufacturing the core 71, then casting low-melting-point alloy liquid at 75 ℃, solidifying the alloy to form a fusible core 72, and ensuring the external dimension of the fusible core 72 by a casting mould.

The manufacturing method of the charge using the composite fusible core is shown in fig. 5: and (2) pouring a propellant outside the composite fusible core 7 according to a traditional method, solidifying the propellant to form the grain 4 containing the composite fusible core 7, then heating the grain 4 containing the composite fusible core 7 to 75 ℃ together, enabling the fusible core 72 to flow out of the charging hole after being melted, then drawing out the core 72, and finally restoring the grain 4 to the environmental condition. The molten liquid alloy from the wick 72 is recovered and can be used to continue the manufacture of the composite wick.

In summary, the above is merely a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A compound fusible core for making solid rocket engine powder charge grain which characterized in that: the method comprises the following steps: a core and a fusible core; the core is consistent with the size of a central through hole of a charge grain of the solid engine to be manufactured and is used for forming the central through hole of the charge grain; the melting core is made of an alloy material with a melting point higher than the curing temperature of the propellant and lower than the safety temperature of the propellant; the fusible core is arranged on the mold core, so that the outer profile structure of the composite fusible core is consistent with the inner profile structure of the engine charging grain to be manufactured.

2. The composite fusible core for use in the manufacture of a charge for a solid rocket engine as recited in claim 1, wherein: the fusible core is made of alloy material with the melting point of 70 ℃.

3. The composite fusible core for use in the manufacture of a charge for a solid rocket engine as recited in claim 1, wherein: the core material is steel.

4. The composite fusible core for use in the manufacture of a charge for a solid rocket engine as recited in claim 1, wherein: when the engine powder charge grain is the solid rocket engine powder charge grain that contains the circumferential groove, when the grain has central through-hole and follows the circumferential groove of central through-hole axial distribution promptly: the core is a cylindrical structure with the size consistent with that of the central through hole of the grain, the fusible core is an annular bulge which is arranged on the circumferential surface of the core and axially distributed along the circumferential surface of the core, and the size and the position of the annular bulge are consistent with those of an annular groove which is axially distributed along the central through hole on the grain.