Solid rocket motor combustor insulation layer injection or injection molding tooling and its process

A solid rocket and injection molding technology, applied in the direction of coating, etc., can solve the problems of low accuracy of shape and size, difficult operation of size and structure, and low pass rate at one time, and achieve high quality consistency, high stability and dimensional accuracy High, fast glue injection effect

Active Publication Date: 2021-09-07
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Generally, the thermal insulation layer of the combustion chamber of small and medium-sized solid rocket motors is usually formed by prefabricating the parts and pasting them on the inner wall of the prepared shell by hand, and then adopting the airbag pressurization of the cavity in a vacuum state or the pressurization of a tooling mold that can be realized. At present, It is the mainstream airbag pressurization process that requires highly skilled operators, but the accuracy of the shape and size of the molding is not high, the efficiency is low, and the first pass rate is not high, and the molding of the tooling mold is also limited by size, structure, and expansion after loading. Difficult process operation has limitations

Method used

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  • Solid rocket motor combustor insulation layer injection or injection molding tooling and its process
  • Solid rocket motor combustor insulation layer injection or injection molding tooling and its process
  • Solid rocket motor combustor insulation layer injection or injection molding tooling and its process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0041] When the insulating casing is vertical, the structure of the injection molding tooling for the thermal insulation layer of the solid rocket motor combustion chamber is as follows: figure 1 As shown in (a), it includes a pouring integrated plate 1, a heat-insulating shell pressure-bearing limit assembly, a split-type combined mold core 5, a limit cone 6, and a heat-insulating shell. The detailed design of each part is as follows:

[0042] The pressure-bearing limit assembly of the heat-insulated shell is used to provide pressure-bearing support for the outside of the heat-insulated shell during the process of injecting or pressing the heat-insulating material inside the heat-insulated shell; it includes a plurality of heat-insulated shell limit pressure-bearing blocks 2, 7, 8, 9, 10, the inner side of these limit bearing blocks of the heat insulating shell are sintered with polytetrafluoroethylene coating, the thickness of the polytetrafluoroethylene coating is 0.05mm ~ 0...

Embodiment 2

[0048] When the heat insulation casing is horizontal, the structure of the injection molding tooling for the heat insulation layer of the solid rocket motor combustor is as follows: figure 2 As shown in (a), it is basically the same as that of Embodiment 1. The pouring integrated board 1 is on the side of the heat-insulating shell. From the left sectional view, the distribution of the runners 12 on the pouring integrated board 1 is as follows figure 2 As shown in (b), a plurality of heat-insulating shell space-limiting pressure-bearing blocks 2, 4, 7 of the heat-insulating shell pressure-limiting assembly protect the heat-insulating shell from the periphery; From the port on one side of the heat-insulating shell, enter the cavity inside the heat-insulating shell where the molding and the heat-insulating shell form an insulating layer.

[0049] The molding process adopts a high-pressure injection method, and the heat-insulating material is injected into the cavity between the...

Embodiment 3

[0051] When the heat insulation shell is a vertical heat insulation shell with its own feeding chamber, the structure of the injection molding tooling for the heat insulation layer of the solid rocket motor combustion chamber is as follows: image 3 As shown, it is basically the same as Example 1, the difference is that the tooling mold has its own feeding chamber, which can be implemented when there is no pressurization or injection function on the equipment, and is generally suitable for heat insulation of small or micro engines

[0052] The molding process adopts the injection pressure method, and the heat insulating material is injected into the cavity between the heat insulating shell and the split-type combined mold core 5 with a pressure of 3Mpa-20MPa. The schematic diagram of the heat insulating material formed in the heat insulating shell is as follows: Figure 8 shown.

[0053] In the above-mentioned examples 1-3, in order to ensure that compared with ordinary rubbe...

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Abstract

The invention belongs to the technical field of manufacturing thermal insulation layers of solid rocket motor thermal protection structures, and provides a solid rocket motor combustion chamber thermal insulation layer injection or injection molding tooling, which includes a pouring integrated board (1), a thermal insulation shell pressure-bearing limit assembly , split-type combined mold core (5), stopper cone (6) and heat-insulating shell; the pressure-bearing limit assembly of the heat-insulating shell is used for injection or injection of heat-insulating material inside the heat-insulating shell to provide for the outside of the heat-insulating shell Pressure-bearing support; the split-type combined mold core (5) cooperates with the limit cone (6), is placed in the heat-insulating shell and forms a cavity with the heat-insulating shell, and the cavity and the heat-insulating layer to be injected or injection-molded The shape and size are consistent for high-pressure injection of heat-insulating materials; the pouring integrated plate (1) is provided with a heat-insulating material injection channel, so that the heat-insulating material enters the heat-insulating shell and the split-type combined mold core through the pouring integrated plate (1) and the cavity formed between the limit cone.

Description

technical field [0001] The invention belongs to the technical field of heat-insulating layer manufacturing for thermal protection structures of solid rocket motors, and in particular relates to an injection or pressure-injection molding tool and technology for making a solid rocket motor combustion chamber heat-insulating layer. Background technique [0002] Solid rocket motor is one of the most important power sources configured in various missile weapons and equipment. As an important component, the high-quality, high-efficiency, and low-cost molding of the combustion chamber insulation layer has always been the bottleneck in the manufacturing process. With the traction of manufacturing quantity, high performance, high efficiency, and low cost requirements, it is becoming more and more difficult to adapt to its development needs by using traditional molding methods. [0003] Generally, the thermal insulation layer of the combustion chamber of small and medium-sized solid r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C45/14B29C45/26B29C45/27
CPCB29C45/14B29C45/14065B29C45/26B29C45/27
Inventor 彭正贵王江詹穹胡俊杰孙笑然李洋伍政彭琴李月常陈亚格
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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