Solid rocket and engine and thermal protection structure at tail of composite shell of solid rocket and engine

Abstract

The invention provides a thermal protection structure for the tail part of a composite shell of a solid rocket engine, which is characterized in that according to the flowing and heat transfer conditions in the solid rocket engine, a partial area on the outer side of an ablation-resistant layer is arranged as a high-temperature-resistant layer, and the high-temperature-resistant layer is arranged between the ablation-resistant layer and a buffer layer in a sealing manner in advance; a sandwich structure is formed; the buffer layer is located on the outer side of the high-temperature-resistant layer and the ablation-resistant layer, and the molded surface is attached to the composite shell and the high-temperature-resistant layer. The ablation-resistant layer is made of an anti-scouring soft heat-insulating material, the high-temperature-resistant layer is made of a hard heat-insulating material with a low heat conductivity coefficient, and the buffer layer is made of a high-elasticity material. The thermal protection structure is formed in an integrated forming mode, it can be guaranteed that the inner molded surface of the heat insulation structure is smooth, the negative mass is small, the thermal protection performance is obviously improved, meanwhile, the structure is simple, the matching performance with a composite shell is good, the safety coefficient is high, and the design of the sandwich thermal protection structure can meet various flowing and heat transfer requirements.

Description

technical field [0001] The invention relates to the thermal protection technical field of high-temperature and high-pressure pressure vessels, in particular to a thermal protection structure for the tail of a solid rocket motor composite casing. Background technique [0002] With the advancement of technology, the performance requirements of solid rocket motors are getting higher and higher. In order to meet the requirements of low vulnerability and high mass ratio of solid rocket motors, more and more engine shell materials are replaced by composite materials for high strength. Steel, composite casings can perform better than metal casings under higher operating conditions inside the engine. While the high-pressure working environment improves the overall performance of the engine, it also brings about the deterioration of the internal flow and heat transfer conditions of the engine. The flow speed is faster and the heat flux density is higher. This puts forward the thermal...

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Problems solved by technology

[0003] At present, the design method for the thermal protection structure of the tail area of ​​the composite shell generally adopts a thicker single thermal protection material to cope with the harsh thermal environment. The thicker thickness meets the thermal protection requirements, but it will also bring the internal charge of the engine. The space is reduced, the energy is lost, and the negative mass is increased at the same time, which reduces the mass ratio of the engine and weakens the improvement of engine performance brought by the use of composite materials

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