Composite heat insulation structure resistant to long-time ablation overload

An adiabatic structure, long-term technology, used in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as good thermal insulation performance, poor erosion resistance, and incompatibility between thermal insulation structure anti-scour performance and thermal insulation performance. , to achieve the effect of improving performance and reducing thickness

Active Publication Date: 2019-05-03
内蒙动力机械研究所
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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 performa

Method used

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  • Composite heat insulation structure resistant to long-time ablation overload
  • Composite heat insulation structure resistant to long-time ablation overload
  • Composite heat insulation structure resistant to long-time ablation overload

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Embodiment

[0019] See figure 1 . The thickness ratio of the two layers of insulation materials is: GZ46-3 material thickness is 4mm, GZ46-2 material thickness is 6mm, that is, the thickness ratio is about 2:3. After molding the two layers of material insulation layers separately, use adhesive The two layers of material insulation are bonded together, and the airbag is used to pressurize and solidify the shape.

[0020] According to the thickness distribution, the tester was designed and tested on the ground for 200s. The wall of the combustion chamber of the tester was only affected by the change of ambient temperature throughout the whole process, and there was no temperature rise caused by the heat in the combustion chamber. After the test, the thickness of the remaining thermal insulation structure (without the carbonization layer, the thickness of the carbonization layer is about 4mm) was measured, see figure 2 . In the range of 60mm to 160mm from the end face of the heat insulat...

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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 ...

Claims

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Application Information

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IPC IPC(8): F02K9/32B32B9/00B32B9/04B32B33/00B32B7/12
Inventor 王铁栋照日格图展杰孙健
Owner 内蒙动力机械研究所
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