Combined core mould structure for forming grain of rocket engine and use method thereof

A technology of rocket motor and grain, which is applied in rocket motor devices, machines/engines, mechanical equipment, etc., can solve the problems of inability to meet disassembly requirements, difficulty in mold assembly and demoulding, and achieve stable structure, good physical performance, and economical operation. effect of space

Active Publication Date: 2019-12-13
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to meet the requirements of thrust ratio and mass ratio, a special-shaped rocket motor propellant was developed, and its three-dimensional structure is as follows figure 1 As shown, there are multiple special-shaped gaps on the side of the grain. Since the maximum width of the special-shaped block is greater than the maximum demoulding space, it cannot meet the disassembly requirements, resulting in difficulties in mold assembly and subsequent demoulding.

Method used

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  • Combined core mould structure for forming grain of rocket engine and use method thereof
  • Combined core mould structure for forming grain of rocket engine and use method thereof
  • Combined core mould structure for forming grain of rocket engine and use method thereof

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Embodiment Construction

[0025] Hereinafter, the present invention will be further described in conjunction with the embodiments, but the scope of protection claimed by the present invention is not limited to the scope of the embodiments.

[0026] Such as Figure 1-4 As shown, a composite core mold structure used for rocket engine grain molding, a plurality of special-shaped notches are provided on the side of the grain, the structure includes multiple sets of special-shaped components, and the multiple sets of special-shaped components cooperate with the special-shaped notches of the grain to form a cylinder Each group of special-shaped block components is provided with a first special-shaped block 1 and a second special-shaped block 2 along the circumferential direction. The first special-shaped block contacts the grain to be formed and is a metal piece; the second special-shaped block is located on the side of the first special-shaped block away from the grain , And the second special-shaped block is ...

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Abstract

The invention discloses a combined core mould structure for forming a grain of a rocket engine and a use method thereof. A plurality of special-shaped notches are formed in the side surface of the grain; the structure comprises a plurality of groups of special-shaped assemblies; the groups of special-shaped assemblies are matched with the special-shaped notches of the grain to form a cylinder; each group of special-shaped block assemblies is provided with a first special-shaped block and a second special-shaped block in the circumferential direction; the first special-shaped block contacts a to-be-formed grain and is a metal piece; the second special-shaped block is located on one side, away from the grain, of the first special-shaped block; the second special-shaped block is made of silicon rubber material; and the size of the thickest part of the first special-shaped block is smaller than the minimum size of a demoulding opening in the forming of the grain of the rocket engine; the structure further comprises a forming rubber sleeve and a positioning transition ring; the end face of the forming rubber sleeve is clamped against the end face of the second special-shaped block; andthe end face of the positioning transition ring is clamped against the end face of the first special-shaped block and the forming rubber sleeve. By adopting the structure and the metho9d, the propellant charge of a small inner bore grain configuration engine can be well adapted, the assembly efficiency is high, the quality is stable, and the reliability is good.

Description

Technical field [0001] The invention belongs to the technical field of rocket engine charge, and in particular relates to a combined core mold structure for rocket engine grain formation and a use method thereof. Background technique [0002] In order to make the solid rocket motor have good internal ballistic performance, a special type of conical groove type and wing column type has appeared in the design of a small engine type. The engine type usually adopts a metal composite core mold to form the surface. The existing metal composite core mold includes wings, connecting pieces, fixed cylinders, cover parts, positioning rings and transition rings. The above-mentioned pieces are spliced ​​to form a complete core mold structure; the metal core molds before charging are reasonably combined in the engine combustion chamber , The connection is a whole, and when demolding, it is divided into blocks and divided into pieces to form a complete medicine structure. For the special-shape...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/24
CPCF02K9/24
Inventor 邱奇陈永钊刘美珍邓安华程山李钦刘相鹏鄂鹏飞龙祥源李换朝赵碧娟鲁华丽张伟刘迪
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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