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Repair material for repairing composite material and method for repairing composite material with repair material

A composite material and repair material technology, which is applied in the field of composite material repair, and can solve the problems of cumbersome and unsuitable repair process operation steps.

Active Publication Date: 2017-02-22
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, US5985433, like US 4358480, also has the disadvantages of cumbersome repair process steps, a large amount of small molecular substances, and is not suitable for on-orbit repair in space.

Method used

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  • Repair material for repairing composite material and method for repairing composite material with repair material
  • Repair material for repairing composite material and method for repairing composite material with repair material
  • Repair material for repairing composite material and method for repairing composite material with repair material

Examples

Experimental program
Comparison scheme
Effect test

preparation example Construction

[0026] The present invention has no particular limitation on the preparation of the first composition, for example, hydroxyl-terminated silicone rubber prepolymer and first inorganic fillers such as hollow glass microspheres, rigid thermal insulation tile scraps and hydrophobic gas phase two Silica is prepared by grinding it in a mortar for 10 to 60 minutes so that each component is thoroughly mixed uniformly.

[0027] The present invention also has no particular limitation on the preparation of the second composition. For example, the second composition can be described as inorganic fillers such as hollow glass microspheres and crushed material of rigid thermal insulation tile scraps and cross-linking agents such as orthosilicic acid. The ethyl ester and catalyst such as dibutyltin dilaurate are ground in a mortar for 30 to 60 minutes so that the ingredients are thoroughly mixed and prepared.

[0028] The room temperature curing silicone rubber continuous phase used in the me...

preparation example 1

[0034] Preparation of the first composition in the repair compound for repairing rigid thermal insulation tiles

[0035] Weigh 50 g of hydroxyl-terminated polydimethylsiloxane with a viscosity of 12,000 cst, 15 g of hollow glass beads, 10 g of crushed material of rigid heat-insulating tile scraps and 5.5 g of hydrophobic fumed silica, and place them in a 250-mL grinder. In a bowl, grind for 10 minutes to fully mix the above components uniformly to prepare the first composition of the repairing material.

[0036] Preparation of second composition in repair compound for repairing rigid thermal insulation tiles

[0037] Weigh 15g hollow glass microspheres, 10g rigid thermal insulation tile scraps, 5g ethyl orthosilicate and 0.5g dibutyltin dilaurate, place them in a mortar with a volume of 250mL, and grind for 30 minutes to make the above The ingredients are thoroughly mixed and uniform to prepare the second composition of the repair material.

[0038] Preparation of room tempe...

preparation example 2 to 10

[0041] It was carried out in substantially the same manner as in Preparation Example 1 except for the contents shown in the table below.

[0042] After testing, the density of each repairing material thus obtained before curing is 0.35-0.55g / cm 3 , the density after curing is 0.45~0.65g / cm 3 .

[0043]

[0044] Repair example 1

[0045] like figure 1 As shown in (a), a 150mm×150mm×25mm rigid thermal insulation tile with a high emissivity coating on the surface is installed on a titanium alloy metal load-bearing structure substrate through strain isolation pads and room temperature curing silicone rubber. The surface of the heat insulating tile has an irregular pit-shaped damage with a maximum diameter of 30mm and a depth of 20mm. CNC tools are used to machine the place into a regular cylindrical pit with a diameter of 30mm and a depth of 20mm, and then a piece of diameter 29.8mm high 18mm rigid thermal insulation tile column, the side and bottom surface of the thermal i...

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Abstract

The invention relates to a repair material for repairing a composite material and a method for repairing the composite material with the repair material. The repair material is prepared from a room temperature cured silicone rubber continuous phase and inorganic filler, wherein the room temperature cured silicone rubber continuous phase contains a hydroxyl-terminated silicone rubber prepolymer, a crosslinking agent and a catalyst. The invention further provides the method for repairing the composite material, such as rigid thermal protection tiles, with the repair material. With the adoption of the repair material, a low-density and high-strength material can be formed in a repaired composite material matrix, and the rigid thermal protection tiles for an aircraft can be repaired both in orbit and on the ground.

Description

technical field [0001] The invention belongs to the technical field of repairing composite materials, and more particularly, the invention relates to repairing materials and repairing methods of composite materials. Background technique [0002] Composite materials, such as rigid thermal insulation tiles, have many advantages such as light weight, reusability, high temperature resistance, and good thermal insulation effect as a large-area thermal protection material on the outer surface of aircraft. However, the impact resistance of rigid thermal insulation tiles is poor, and the rigid thermal insulation tiles may be damaged during ground installation, transportation, launch, in-orbit flight or re-entry of the aircraft. Therefore, how to repair the damaged rigid thermal insulation tile is one of the important auxiliary technologies in the engineering application process of the large-area thermal protection system of the rigid thermal insulation tile. [0003] Rigid insulati...

Claims

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Application Information

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IPC IPC(8): C08L83/06C08K7/28C08K3/36C08K5/5415C08K3/38C08K5/5419B64C1/00
CPCB64C1/00B64C2001/0072C08K3/36C08K3/38C08K5/5415C08K5/5419C08K7/28C08L83/06
Inventor 鲁胜张凡郭慧吴宪刘斌赵英民
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH