阅读说明：本技术 一种固体火箭发动机装药集束式浇注工装及方法 (Solid rocket engine charge cluster type pouring tool and method ) 是由 代颖军 王鸿宇 张渝 傅嘉治 江屈强 刘爱琴 于 2019-10-14 设计创作，主要内容包括：一种固体火箭发动机装药集束式浇注工装及方法,属于含能材料制备与装填技术领域,包括底盘、接料盘、花板组件,多发发动机安放在底盘上,接料盘与多发发动机及底盘对配合装,接料盘与底盘连接后,对多发发动机形成集中束缚,花板组件与接料盘配合安装。多发发动机在底盘上挨个紧凑排列并定位、集中束缚、整体吊装；底盘及接料盘结构简单,使用方便；花板尺寸较大,其开孔不受单发发动机尺寸限制,覆盖了接料盘中对应的所有空间；利用本发明工装浇注时间可大量缩短,药浆排气更彻底。本发明工装结构简单,提高了装药线的整体生产效率；本发明方法简化了浇注工序作业流程,减轻了工作量,降低了劳动强度,节约了装药成本。(A solid rocket engine charging cluster type pouring tool and a method belong to the technical field of energetic material preparation and filling, and comprise a chassis, a material receiving disc and a pattern plate assembly, wherein multiple engines are placed on the chassis, the material receiving disc is in matched combination with the multiple engines and the chassis, after the material receiving disc is connected with the chassis, the multiple engines are intensively bound, and the pattern plate assembly and the material receiving disc are in matched installation. Multiple engines are compactly arranged on a chassis one by one, positioned, intensively bound and integrally hoisted; the chassis and the material receiving disc have simple structures and are convenient to use; the size of the pattern plate is large, the opening of the pattern plate is not limited by the size of a single engine, and all corresponding spaces in the material receiving disc are covered; the pouring time of the tool can be greatly shortened, and the medicine slurry is exhausted more thoroughly. The tool is simple in structure, and the overall production efficiency of the powder charging line is improved; the method simplifies the operation flow of the pouring procedure, lightens the workload, reduces the labor intensity and saves the charging cost.)

1. A solid rocket engine charge cluster type pouring tool is characterized by comprising a pattern plate assembly, a material receiving disc and a chassis;

the external multi-engine is fixedly arranged between the receiving tray and the chassis; the pattern plate assembly is arranged on the material receiving disc; the receiving tray is provided with a feed opening corresponding to the position of the external multi-engine; the external propellant falls to the receiving disc through the pattern plate assembly and then flows into the external multi-engine through the feed opening;

the card assembly is provided with a plurality of through holes, the diameter of each through hole is phi 3 mm-phi 5mm, and the through holes form a plurality of concentric circles; on any concentric circle, the distance between the centers of two adjacent through holes is 8-20 mm, and in the two adjacent concentric circles, the distance between the through holes on the concentric circle with the larger radius is smaller than that on the concentric circle with the smaller radius.

2. The solid rocket engine charge cluster casting tool of claim 1, wherein the distance between the through hole on the faceplate assembly and the feed opening on the take-up pan is 240 mm-300 mm.

3. The solid rocket engine charge cluster casting tool of claim 1, wherein flanges are arranged on the edge of the base and the edge of the material receiving tray; the flange of the chassis and the flange of the material receiving disc are jointly used for limiting the external multi-engine, so that the external multi-engine is tightly arranged.

4. The solid rocket engine charge cluster casting tool of claim 3, wherein a plurality of vertical hoisting connecting rods are arranged on a flange of the chassis, and the chassis is connected with the flange of the take-up pan through the vertical hoisting connecting rods.

5. The solid rocket engine charge cluster casting tool of claim 4, further comprising a cross bar, wherein the cross bar is located between the chassis and the take-up pan and used for connecting two adjacent vertical hoisting connecting rods.

6. The solid rocket engine charge cluster casting tool of claim 4, wherein the take-up pan is provided with a hoisting connecting block, and the hoisting connecting block is used for being connected with the hoisting connecting vertical rod.

7. The solid rocket engine charge cluster casting tooling of claim 1, wherein a positioning ring is arranged on the feed opening, and the positioning ring is used for being embedded into an opening of an engine to complete positioning.

8. The solid rocket engine charge cluster casting tooling of claim 1, wherein the take-up pan is provided with positioning holes on the end surface close to the faceplate assembly, and the positioning holes are used for connecting the take-up pan with the faceplate assembly.

9. The solid rocket engine charge cluster casting tooling of claim 1, wherein the take-up pan is provided with a protrusion at the edge of the end face close to the face plate assembly for limiting the external propellant.

10. A solid rocket engine charge cluster casting method is characterized in that the tool of any one of claims 1 to 9 is adopted, and the method comprises the following steps:

s1, closely arranging and placing multiple engines on the chassis; then the material receiving disc is installed, and a feed opening of the material receiving disc corresponds to the position of the multiple engines;

s2, connecting the chassis with the material receiving tray by using a plurality of vertical hoisting connecting rods; connecting two adjacent hoisting connecting vertical rods by using a cross rod;

s3, connecting the multiple engines, the chassis, the material receiving tray, the hoisting connecting vertical rods and the cross rods into a whole, hoisting the whole into a vacuum casting cylinder, and then installing the pattern plate assembly on the material receiving tray;

s4, pouring propellant, wherein the propellant is scattered to the material receiving disc through the through hole of the pattern plate assembly, one part of the propellant directly flows into the engine through the material outlet of the material receiving disc, and the other part of the propellant flows into the engine through the material outlet after being stacked on the material receiving disc.

Technical Field

The invention relates to a solid rocket engine charge cluster type pouring tool and a method, and belongs to the technical field of energetic material preparation and filling.

Background

The batch charging production of the small solid rocket engine generally adopts a one-cylinder multi-vacuum pouring process, and a plurality of pouring cylinders operate simultaneously. The production mode is as follows: and (3) assembling the auxiliary tool prepared before production with an engine, then placing the assembled auxiliary tool and engine into a casting cylinder, and assembling the auxiliary tool with a pattern plate assembly, a casting cylinder cover, a medicine pouring pipe, a valve, a hopper and other tools. Adding propellant slurry with specified mass into a hopper, and opening a valve for pouring after the vacuum degree in each pouring cylinder reaches a specified pressure value. And after the pouring is finished, the pouring hopper and the valve are disassembled, cleaned and arranged, and part of the pouring tool is disassembled, cleaned, arranged and put in storage.

In the production mode, engines need respective matched tools, the space of a casting cylinder is limited by the arrangement, assembly and operation of the tools, the engines cannot be effectively utilized, and the number of the engines is small; the holes of the pattern plate are limited by the opening of the engine, the number of the holes is small, and the pouring time is long in order to completely remove the gas in the slurry. A large amount of tool preparation, assembly, disassembly, cleaning, arrangement and warehousing work are required for pouring, and more manpower, auxiliary materials and charging work hours are consumed. The traditional production mode has difficulty in meeting the objective requirement of model mass production.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and the solid rocket engine charge cluster type pouring tool and the solid rocket engine charge cluster type pouring method are provided. Multiple engines are compactly arranged on a chassis one by one, positioned, intensively bound and integrally hoisted; the chassis and the material receiving disc are simple in structure and convenient to use, and can avoid independent processing, preparation, assembly and cleaning of multiple engine tools; the size of the pattern plate is larger, the opening of the pattern plate is not limited by the size of a single engine, the number of holes is more, the pattern plate is uniformly distributed and arranged from the center to the outer circle in an effective space circle by circle, and all corresponding spaces in the receiving plate are covered; during pouring, the fine propellant strips dispersed by the pattern plates partially directly fall into an engine through the material receiving disc feed opening, partially fall on the material receiving plate outside the material receiving disc feed opening, and flow into the engine through the feed opening after being stacked, so that the pouring time can be greatly shortened, and the medicine slurry is more thoroughly exhausted.

The purpose of the invention is realized by the following technical scheme:

a solid rocket engine charge cluster type pouring tool comprises a pattern plate assembly, a receiving disc and a chassis;

the external multi-engine is fixedly arranged between the receiving tray and the chassis; the pattern plate assembly is arranged on the material receiving disc; the receiving tray is provided with a feed opening corresponding to the position of the external multi-engine; the external propellant falls to the receiving disc through the pattern plate assembly and then flows into the external multi-engine through the feed opening;

the card assembly is provided with a plurality of through holes, the diameter of each through hole is phi 3 mm-phi 5mm, and the through holes form a plurality of concentric circles; on any concentric circle, the distance between the centers of two adjacent through holes is 8-20 mm, and in the two adjacent concentric circles, the distance between the through holes on the concentric circle with the larger radius is smaller than that on the concentric circle with the smaller radius.

Preferably, the distance between the through hole in the faceplate assembly and the feed opening in the receiving tray is 240-300 mm.

Preferably, flanges are arranged on the edge of the bottom plate and the edge of the material receiving plate; the flange of the chassis and the flange of the material receiving disc are jointly used for limiting the external multi-engine, so that the external multi-engine is tightly arranged.

Preferably, a plurality of vertical hoisting connecting rods are arranged on a flange of the chassis, and the chassis is connected with the flange of the material receiving disc through the vertical hoisting connecting rods.

Preferably, the lifting device further comprises a cross rod, wherein the cross rod is located between the base plate and the material receiving disc and used for connecting two adjacent vertical hoisting connecting rods.

Preferably, the material receiving disc is provided with a hoisting connecting block, and the hoisting connecting block is used for being connected with the hoisting connecting vertical rod.

Preferably, a positioning ring is arranged on the feed opening and used for being embedded into an opening of an engine to complete positioning.

Preferably, the material receiving disc is provided with a positioning hole on the end surface close to the flower plate assembly, and the positioning hole is used for connecting the material receiving disc with the flower plate assembly.

Preferably, the material receiving disc is provided with a protrusion at the edge of the end face close to the card assembly, and the protrusion is used for limiting the external propellant.

A solid rocket engine charging cluster type pouring method adopts the tool and comprises the following steps:

s1, closely arranging and placing multiple engines on the chassis; then the material receiving disc is installed, and a feed opening of the material receiving disc corresponds to the position of the multiple engines;

s2, connecting the chassis with the material receiving tray by using a plurality of vertical hoisting connecting rods; connecting two adjacent hoisting connecting vertical rods by using a cross rod;

s3, connecting the multiple engines, the chassis, the material receiving tray, the hoisting connecting vertical rods and the cross rods into a whole, hoisting the whole into a vacuum casting cylinder, and then installing the pattern plate assembly on the material receiving tray;

s4, pouring propellant, wherein the propellant is scattered to the material receiving disc through the through hole of the pattern plate assembly, one part of the propellant directly flows into the engine through the material outlet of the material receiving disc, and the other part of the propellant flows into the engine through the material outlet after being stacked on the material receiving disc.

Compared with the prior art, the invention has the following beneficial effects: 1. simple structure through concentrating the mode of constraint, has broken through traditional technology space and time limitation, has realized single mass pouring production, very big improvement the whole production efficiency of powder charge line. 2. The operation flow of the pouring procedure is simplified, the workload is reduced, and the labor intensity is reduced; 3. the auxiliary material allowance, the energy consumption, the labor cost of repeated operation and the processing cost of the tool matched with the multiple engines independently are avoided, and the charging cost is saved.

Drawings

FIG. 1 is a schematic view of a beam casting tool;

FIG. 2 is a schematic view of the chassis;

FIG. 3 is a schematic view of a take-up pan;

FIG. 4 is a schematic view of a card;

FIG. 5 is a schematic view of a cluster vacuum casting process.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.