A composite material solid rocket motor insulation layer structure and its preparation method

Abstract

The invention provides a composite material solid rocket engine heat insulation layer structure and a preparation method thereof. The heat insulation layer structure comprises a heat insulation structure bottom layer, a heat insulation structure cover layer, an anti-ablation structure layer and a metal joint, wherein the heat insulation structure cover layer is attached to the inner side of the heat insulation structure bottom layer, the anti-ablation structure layer is arranged at the spray pipe connecting end of the heat insulation structure bottom layer and is attached to the outer side ofthe heat insulation structure bottom layer, and the metal joint is arranged on the outer side of the anti-ablation structure layer. The preparation method comprises the following steps that the anti-ablation structure layer and the heat insulation structure cover layer are prefabricated respectively; after the metal joint and the prefabricated anti-ablation structure layer are assembled, a film isarranged on the anti-ablation structure layer, and a prefabricated heat insulation structure bottom layer is integrally formed; and the prefabricated heat insulation structure cover layer is arrangedon the prefabricated heat insulation structure bottom layer, and integral compression molding is carried out. The composite material solid rocket engine heat insulation layer structure and the preparation method thereof are high in production efficiency, controllable thicknesses of all parts of the heat insulation structure layer can be guaranteed, the artificial debonding layer depth is accurate, and the product quality is high.

Description

technical field [0001] The invention belongs to the technical field of rocket motor thermal insulation structure manufacturing, and in particular relates to a composite material solid rocket motor thermal insulation layer structure and a preparation method thereof. Background technique [0002] The solid rocket motor is composed of combustion chamber, propellant, igniter, nozzle and other components. Among them, the combustion chamber is used to store propellant and provide combustion space. In order to avoid damage to the combustion chamber shell due to high-temperature and high-pressure airflow, it is necessary to set up an insulating layer structure on the inner surface of the combustion chamber shell. [0003] At present, the domestic methods for manufacturing the inner heat insulation layer of solid rocket motors mainly include manual patch molding and compression molding. Chinese patent document CN102632683B discloses a manual patching method for the thermal insulatio...

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Problems solved by technology

Chinese patent document CN102632683B discloses a manual patching method for the thermal insulation layer of the fiber-wound engine case. The thermal insulation layer of the engine case is made by the manual patching method, which can ensure the manual patching of the thermal insulation layer of the fiber-wound engine case. Thickness size, however, the manual patch production method is inefficient and prone to defects such as bulges, pits, and debonding, and is easily eroded by hot air flow, resulting in thermal protection failure

For this reason, the overall compression molding technology has been developed and utilized, and its advantage is that the manual patch can be seamed to the cylinder section of the combustion chamber. However, the modern combat environment has higher and higher requirements on the performance of the missile, resulting in the structure of the heat insulation layer appearing In order to complicate the trend, the difficulty of molding is increasing day by day. The molding process is limited by the size of the solid rocket motor and the structure of the insulation layer. The traditional integral molding process is difficult to meet the needs of development, and cannot guarantee the thickness of the insulation structure layer, external dimensions and internal quality

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