Forming method of multi-phase thermal insulation layer of filament winding solidified rocket motor
A technology of a rocket engine and a molding method, which is applied to household appliances, other household appliances, household components, etc., can solve the problems of long-term insulation materials, more stringent requirements for oxidation resistance and anti-scour performance, and reduced engine quality. Negative mass, improve mass ratio, prevent the effect of bulging
Active Publication Date: 2021-08-31
湖北三江航天江北机械工程有限公司
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Problems solved by technology
[0003] In recent years, with the new demand for high-performance rocket engines, high-speed and high-overload are becoming an important development trend of high-performance tactical missiles, and the requirements for long-term, oxidation resistance and erosion resistance of thermal insulation materials are more stringent; if the engine's Ablation resistance can be achieved from two aspects. On the one hand, it can be increased by increasing the thickness of the insulation material, but the increase in thickness will increase the negative mass of the engine, resulting in a decrease in engine quality; on the other hand, it can be achieved by using more ablation-resistant materials for insulation layer preparation
Method used
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Embodiment
[0088] 1) Environmental temperature and humidity control and core mold surface treatment
[0089] Use an air conditioner or dehumidifier to adjust the ambient temperature of the multi-phase insulation layer to 25±3°C and relative humidity ≤75%; and clean the dust on the surface of the core mold used for engine casing molding, and wrap or paste a layer on the surface PTFE layer;
[0090] 2) Preparation of EPDM film
[0091] 2a) Film output: first adjust the roller spacing of the rubber mixing machine to 2.5mm, pretreat the EPDM insulation material through the rubber mixing machine and mix it back and forth for 3 times, then adjust the roller spacing, according to 0.5mm, 2mm Make several sheets of EPDM film according to the thickness dimension;
[0092] 2b) Cutting: Determine the overall expansion size of the EPDM film according to the outer diameter and length of the mandrel, and take 10 EPDM films according to the circumferential direction, and cut each EPDM film to be paste...
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The invention discloses a method for forming a multi-phase thermal insulation layer of a fiber-wound solidified rocket engine. The multi-phase thermal insulation layer is composed of ablation-resistant EPDM and a three-dimensional braided body of carbon fiber impregnated with phenolic resin. On the one hand, the thermal insulation layer does not increase In the case of thinner layers, the ablation resistance of the heat insulation material can be improved, the negative mass of the engine casing can be reduced, and the mass ratio of the engine can be improved; The phase insulation material has good manufacturability; two pre-pressings, on the one hand, discharge the gas between the two insulation materials and between the EPDM film layers, and on the other hand, ensure that the phenolic resin impregnated carbon fiber three-dimensional braid and the upper, The interface of the insulation layer at the lower position is well bonded to prevent defects such as bulges, air inclusions, and debonding between EPDM and phenolic resin-impregnated carbon fiber three-dimensional braided multi-phase insulation materials.
Description
technical field [0001] The invention belongs to the field of making thermal insulation materials in fiber-wound solid rocket motors, and specifically refers to a method for forming multi-phase thermal insulation layers of fiber-wound solid rocket motors. Background technique [0002] As the protective layer of the combustion chamber of the solid rocket motor, the inner insulation layer material has high temperature ablation resistance, high-speed heat flow resistance and good mechanical properties, preventing high temperature and high pressure gas from reducing the strength of the shell and endangering its structural integrity. The shell plays the role of heat insulation and heat protection, and is a key component to ensure the normal operation of the rocket engine. [0003] In recent years, with the new demand for high-performance rocket engines, high-speed and high-overload are becoming an important development trend of high-performance tactical missiles, and the requireme...
Claims
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IPC IPC(8): B29C70/34B29C70/24B29C70/54B29L31/30
CPCB29C70/24B29C70/34B29C70/54B29C70/545B29L2031/3097B29L2031/749
Inventor 肖雯静谭云水黄泽勇邓德凤
Owner 湖北三江航天江北机械工程有限公司