a heat shield
A technology of heat shield and heat insulation layer, applied in the aerospace field, can solve the problems of water vapor infiltration, ice accumulation, insufficient wrapping ability of opening parts, etc., and achieve the effect of reducing the joints between blocks, improving the heat insulation ability, and having a light structure.
Active Publication Date: 2019-09-03
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0003] The purpose of the present invention is to solve the problem that the existing heat shield has insufficient ability to wrap complex curved surfaces and open-hole parts, and the problem that water vapor infiltrates easily to generate ice accumulation in low temperature environment, and provides a heat shield
Method used
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Embodiment Construction
[0021] The present invention is described in detail below in conjunction with accompanying drawing and specific embodiment:
[0022] see figure 1 and figure 2 , a heat shield, comprising a plurality of heat insulation units, the heat insulation unit includes an inner layer 1, a heat insulation layer 2, a waterproof layer 3 and an outer layer 4 arranged in sequence, the inner layer 1 is a basalt plain weave, The heat insulation layer 2 is basalt needle-punched felt with a thickness of 6mm, the waterproof layer 3 is glass fiber cloth, and the outer layer 4 is basalt fiber aramid blended; The heat layer 2 is connected with the heat insulation layer 2 by lap seams, the waterproof layer 3 is connected with the waterproof layers 3 with flat seams, and the outer layer 4 is connected with the outer layers 4 with blind seams to form a cover body. When sewing, the seams between the adjacent heat insulation layers 2 and the heat insulation layers 2 are lined with basalt plain weave 5 ...
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Abstract
The invention belongs to the technical field of aerospace and particularly relates to a heat-insulating cover. The problems that an existing heat-insulating cover has the insufficient wrapping abilityfor complex curved surfaces and parts with holes, and water vapor is prone to permeating into the heat-insulating cover under the low temperature environment and thus accumulated ice is generated aresolved. According to the technical scheme, the heat-insulating cover comprises a plurality of heat-insulating units comprising inner layers, heat-insulating layers, waterproof layers and outer layerswhich are arranged in sequence; the inner layers are basalt plain cloths, the heat-insulating layers are basalt needled felt, the waterproof layers are glass fiber cloths, and the outer layers are basalt fiber aramid mixture yarn; and the inner layers, the heat-insulating layers, the waterproof layers and the outer layers of the adjacent heat-insulating units are directly stitched together to form a cover body. According to the heat-insulating cover, the high temperature performance and low temperature performance are stable, the water vapor is not prone to permeating into the heat-insulatingcover under the low temperature environment, thus the accumulated ice is avoided.
Description
technical field [0001] The invention belongs to the field of aerospace technology, and in particular relates to a heat shield. Background technique [0002] Engines or large equipment in the aerospace field need to block internal and external heat exchange, so heat shields are required for temperature isolation. Combined with the use requirements of aerospace engines, the heat shield needs to have the characteristics of small thermal conductivity, light weight, high temperature resistance, low temperature resistance, and easy disassembly and reuse. With the development of rocket engines, the volume of the low-temperature oxygen chamber is getting larger and larger, and the flow rate is getting higher and higher during operation. When facing a new generation of engines, the existing heat shield has a long pre-cooling time and poor local coating ability. , the publication number is CN203476511U disclosed in a kind of heat shield, each heat insulation layer material is suitabl...
Claims
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IPC IPC(8): F02C7/24B32B9/00B32B9/04B32B17/02B32B17/06B32B27/02B32B27/12B32B27/34B32B5/06B32B3/08
Inventor 巨龙王猛裴曦张相盟杨亚龙
Owner XIAN AEROSPACE PROPULSION INST