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A flexible thermal protection structure

A thermal protection structure and flexible technology, which is applied in the direction of aerospace vehicle heat protection devices, aerospace safety/emergency devices, etc., can solve the problems of increasing the cost of spacecraft and the high quality of thermal protection structures, and achieve the effect of avoiding structural damage

Active Publication Date: 2020-07-14
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] With the rapid development of the aerospace industry, the aerodynamic heat suffered by spacecraft entering the atmosphere is becoming more and more serious. Thermal protection technology has always been a key technology in the development of spacecraft. Traditional thermal protection structures are generally distributed on the surface of spacecraft structures. , its effective resistance area is similar to that of spacecraft, and the mass of traditional thermal protection structures is generally relatively large, which increases the cost of spacecraft launch and recovery

Method used

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preparation example Construction

[0045] In an optional embodiment, the preparation method of the first alumina fiber cotton and the second alumina fiber cotton comprises:

[0046] (1) Immerse the fiber loose cotton made of alumina fiber into the 3-8% pliable solution for pliable treatment, obtain the compliant fiber loose cotton after drying, and the solute in the compliant solution is ethylene glycol and ethylene glycol. Diamine, the solvent is water;

[0047] Specifically, in the embodiment of the present invention, the mass ratio of ethylene glycol and ethylenediamine in the softening solution is preferably 3:5-9; The concentration is 3-8% softening solution, taken out after 30-150 minutes, dried at 75-85 DEG C to obtain fiber loose cotton after softening treatment.

[0048] (2) Immerse the loose fiber cotton after the softening treatment in the nano-sol for a certain period of time, press filter, dry and heat-treat to obtain the fiber cotton semi-finished product with the introduction of nano-particles, ...

Embodiment 1

[0060] This embodiment provides a kind of alumina fiber cotton, and its preparation method comprises:

[0061] (1) First, after carding the alumina fibers, they are needled on the acupuncture equipment to obtain a surface density of 0.4kg / m 2 ~0.8kg / m 2 Alumina fiber loose cotton;

[0062] (2) Immerse the fiber loose cotton obtained in step (1) into a 5% pliable solution for 50 minutes, take it out and place it in a constant temperature drying oven at 80°C for drying, wherein ethylene glycol and ethylene glycol in the compliant solution are The mass ratio of diamine is 3:7;

[0063] (3) Preparation of zirconia and silica nano-sols:

[0064] Using acid and alkali two-step catalytic method, mix zirconia and silicon oxide nanoparticles according to the molar ratio of 1:1, then mix and stir with ethyl orthosilicate and a certain amount of ethanol, and add hydrochloric acid, water and ethanol The mixed solution is subjected to acid catalysis, and after the ethyl orthosilicate i...

Embodiment 2

[0078] This embodiment also provides a flexible heat protection structure, including a heat-resistant layer 2, a heat-insulating layer 3 and a load-bearing layer 4 stacked in sequence, and the heat-insulating layer 3 includes a heat-conducting layer 301, a first lay-up layer 302, the metal foil layer 303 and the second layer 304, the heat-resistant layer 2 is made of ceramic fiber cloth (nextel440), the thickness is 1mm, and the surface density is about 1000g / m 2, the ceramic fiber cloth has excellent heat resistance, and the maximum service temperature can reach 1600K or even higher. The heat conduction layer 301 is graphite paper with a thickness of about 0.1mm, and the surface density is about 100g / m 2 , due to its good thermal conductivity, the heat load can be distributed on the entire surface of the heat insulation layer, and the heat transfer is more uniform. The first layer 302 is paved by alumina fiber cotton (purchased from THERMOST manufacturer), with a thickness of...

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Abstract

The invention provides a flexible thermal protection structure, and belongs to the technical field of thermal protection. The flexible thermal protection structure comprises a heat-resisting layer 2 and a heat-insulating layer 3 which are stacked, and is characterized in that the heat-insulating layer 3 comprises a heat conduction layer 301, a first laying layer 302, a metal foil layer 303 and a second laying layer 304 which are sequentially stacked, the heat conduction layer 301 is graphite paper or metal foil, the first laying layer 302 is first aluminum oxide fiber cotton, and the second laying layer 304 is second aluminum oxide fiber cotton or metallic oxide aerogel. When the structure bears 15 w / m<2> of heat flows, the whole thermal protection layer effectively realizes heat insulation, and is not damaged by high heat flows.

Description

technical field [0001] The invention relates to a flexible thermal protection structure, which belongs to the technical field of thermal protection. Background technique [0002] With the rapid development of the aerospace industry, the aerodynamic heat suffered by spacecraft entering the atmosphere is becoming more and more serious. Thermal protection technology has always been a key technology in the development of spacecraft. Traditional thermal protection structures are generally distributed on the surface of spacecraft structures. , its effective resistance area is similar to that of spacecraft, and the mass of traditional thermal protection structures is generally relatively large, which increases the cost of spacecraft launch and recovery. [0003] The flexible thermal protection structure is light in weight, can be folded and packaged, occupies a small space, and can be unfolded when deceleration is required, which can greatly increase the resistance area and deceler...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/58
CPCB64G1/58
Inventor 黄明星曹旭孙小飞唐明章廖航李少腾
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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