Deformation control method in rigid heat-insulating tile coating forming process

A molding process and deformation control technology, which is applied in the field of preparation of aircraft thermal protection materials, can solve the problems of deformation of the base material, the specific size and deformation of the sample are not given, and the deformation of the rigid heat insulation tile is not specifically mentioned. To achieve the effect of reducing thermal stress, reducing deformation, avoiding damage and destruction

Active Publication Date: 2015-12-09
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

For example, the patent US4093771 mentioned in its background technology that the high temperature sintering above 1260 °C used in the previous coating technology will cause deformation of the base material, but in the technology described by it, the sintering temperature is lowered by adding glass flux, and One-time sintering molding, the deformation and shrinkage of the matrix are improved, but the specific size and deformation of the sample are not given.
In addition,

Method used

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  • Deformation control method in rigid heat-insulating tile coating forming process
  • Deformation control method in rigid heat-insulating tile coating forming process
  • Deformation control method in rigid heat-insulating tile coating forming process

Examples

Experimental program
Comparison scheme
Effect test

Example Embodiment

[0047] Example 1:

[0048] The thickness of the sample is required to be 10mm, and the high temperature sintering heat treatment adopts the overall sintering heat treatment method.

[0049] The ceramic matrix material of the rigid insulation tile is made of mixed fibers of 80% oxidized fiber and 20% mullite fiber, with a density of 0.33g / cm 3 , Processed into a 200×200×20mm sample, the mass ratio of each component in the coating slurry is: borosilicate glass powder: boron oxide: tantalum disilicide: clay: water = 60:30:8:2: 500, mixed with a ball mill for 3 hours, and coated on the upper surface (the upper and lower surface area is the largest) and side of the base material after coating, and the side is coated with 6mm, the surface density of the coating obtained after spraying and drying is 0.025g / cm 2 , Carry out integral sintering heat treatment at 1150°C in a high temperature furnace for 15 minutes. After cooling to room temperature, use a milling machine to process the formed ...

Example Embodiment

[0050] Example 2:

[0051] The thickness of the sample is required to be 15mm, and the high temperature sintering heat treatment adopts the overall sintering heat treatment method.

[0052] The ceramic matrix material of the rigid insulation tile is made of mixed fibers of 80% oxidized fiber and 20% mullite fiber, with a density of 0.33g / cm 3 , Processed into a 200×200×20mm sample, the mass ratio of each component in the coating slurry is: borosilicate glass powder: boron oxide: tantalum disilicide: clay: water = 60:30:8:2: 500, mixed with a ball mill for 3 hours, and coated on the upper surface (upper and lower surface area) and sides of the base material after coating, and the side is coated with 10mm, the surface density of the coating obtained after spraying and drying is 0.025g / cm 2 , Carry out integral sintering heat treatment at 1150℃ for 15min in a high temperature furnace, after cooling to room temperature, final processing to a thickness of 15mm by a milling machine. Acco...

Example Embodiment

[0053] Example 3:

[0054] The thickness of the sample is required to be 10mm, and the high temperature sintering heat treatment adopts single-sided heating treatment.

[0055] The ceramic matrix material of the rigid insulation tile is made of mixed fibers of 80% oxidized fiber and 20% mullite fiber, with a density of 0.33g / cm 3 , Processed into a 200×200×20mm sample, the mass ratio of each component in the coating slurry is: borosilicate glass powder: boron oxide: tantalum disilicide: clay: water = 60:30:8:2: 500, mixed with a ball mill for 3 hours, and coated on the upper surface (the upper and lower surface area is the largest) and side of the base material after coating, and the side is coated with 6mm, the surface density of the coating obtained after spraying and drying is 0.025g / cm 2 , The upper surface is sintered and heat-treated at 1150°C at the entrance of the high-temperature furnace for 15 minutes, cooled to room temperature, and finally processed to a thickness of 10m...

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Abstract

The invention relates to a deformation control method in a rigid heat-insulating tile coating forming process, belongs to the technical field of a porous ceramic heat-insulating material, and can be used for preparing a heat shielding material of an aircraft such as a space shuttle and the like. The method comprises: applying coating slurry to the surface of a rigid heat-insulating tile ceramic base body which is initially processed to a certain thickness and shape; after drying, putting the coated base body material at a high temperature to be sintered for thermal treatment; after sintering for thermal treatment, taking out the base body material from the high-temperature environment and cooling the base body material to room temperature; and finally carrying out secondary processing to reduce the base body material to the finally required thickness. Compared to a conventional method which directly processes the base body material to the finally required thickness and then carries out coating forming, deformation of the rigid heat-insulating tile in the coating forming process can be effectively controlled.

Description

technical field [0001] The invention relates to a deformation control method during the forming process of a rigid heat-insulating tile coating, belongs to the technical field of porous ceramic heat-insulating materials, and can be used in the preparation of heat-protecting materials for aircraft such as space shuttles. Background technique [0002] Spacecraft will experience severe aerodynamic heating when passing through the atmosphere or flying in the atmosphere, and its surface temperature will rise sharply. Therefore, it is necessary to rely on thermal protection materials to block the transfer of heat to the interior, so as to ensure that the internal personnel and equipment are at a safe and reasonable temperature. within range. For example, the success of the development of the space shuttle is largely due to advanced and reliable thermal protection materials such as carbon / carbon, rigid insulation tiles, and flexible insulation blankets. Among them, the rigid heat ...

Claims

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Application Information

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IPC IPC(8): C04B41/85
Inventor 杨海龙周洁洁胡子君
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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