Composite heat insulation structure resistant to long-time ablation overload

Abstract

The invention relates to a composite heat insulation structure resistant to long-time ablation overload. According to the composite heat insulation structure, a structure with a composite heat insulating layer is adopted. The composite heat insulating layer is structurally composed of two layers, namely an outer heat insulating layer and an inner heat insulating layer. The outer heat insulating layer is made of a GZ46-2 material, and the inner heat insulating layer is made of a GZ46-3 material. The thickness of the GZ46-3 material is 4 mm, the thickness of the GZ46-2 material is 6 mm, and in other words, the thickness ratio of the GZ46-2 material to the GZ46-3 material is 3: 2. After the outer heat insulating layer and the inner heat insulating layer are molded through die pressing, the inner heat insulating layer is bonded to the inner side surface of the outer heat insulating layer through adhesive. According to the composite heat insulation structure, the ablation rate is decreasedby about two magnitude orders compared with the maximum ablation rate of a common EPDM material heat insulating layer; and under the same working conditions, the thickness of the heat insulation structure can be effectively reduced, and the performance of a solid rocket engine is improved.

Description

technical field [0001] The invention relates to a composite heat-insulation structure, in particular to a composite heat-insulation structure for a solid rocket motor against long-time ablation overload. Background technique [0002] The solid rocket motor mainly relies on the adiabatic structure under the action of high-temperature gas to continuously ablate, carbonize, and peel off heat to take away heat and slow down the heat transfer of the pressure-bearing shell for thermal protection. When the carbonized layer is peeled off, the thermal insulation structure below continues to decompose and carbonize. Therefore, the thickness design of the thermal insulation structure is mainly based on the ablation rate of the thermal insulation structure and the exposure time in the gas. [0003] At present, the commonly used heat insulation structure adopts a single material such as EPDM rubber, silicone rubber, etc., and carries the functions of anti-scouring and heat insulation at ...

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Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a composite thermal insulation structure resistant to long-term ablation overload, so as to solve the difficulty in compatibility between the anti-scouring performance and thermal insulation performance of the existing thermal insulation structure, which often leads to improved anti-scouring performance but fast heat transfer or insulation Problems with good thermal performance but poor washout resistance

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