Adhesive filler for splicing light porous composite material and preparation method of adhesive filler

A technology of porous composite materials and fillers, applied in the direction of adhesives, adhesive additives, polymer adhesive additives, etc., can solve the problems of poor ablation resistance and erosion resistance that cannot meet the needs of aerospace vehicles, and achieve good chemical properties. And physical compatibility, excellent bonding performance, excellent anti-oxidation effect

Active Publication Date: 2021-02-02
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of the performance and service environment characteristics of high-porosity and low-density porous composite materials, the existing adhesive system cannot meet the needs of aerospace vehicles in aerodynamic heating environments due to their poor ablation resistance and erosion resistance.

Method used

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  • Adhesive filler for splicing light porous composite material and preparation method of adhesive filler
  • Adhesive filler for splicing light porous composite material and preparation method of adhesive filler
  • Adhesive filler for splicing light porous composite material and preparation method of adhesive filler

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preparation example Construction

[0046] According to a second aspect of the present invention, a method for preparing an adhesive filler for splicing lightweight porous composite materials is provided, comprising the steps of:

[0047] (1) Weigh 100 parts by mass of hydroxyl-terminated polysiloxane and put it into a mixing container;

[0048] (2) Weigh 0 to 30 parts by mass of white carbon black, 10 to 40 parts by mass of chopped fibers, 10 to 50 parts by mass of hollow spheres, 5 to 15 parts by mass of antioxidant fillers and 0 to 30 parts by mass of Put the diluent in the mixing container in step (1), and carry out physical stirring and mixing at room temperature with a planetary strong agitator for 5 to 30 minutes, and the stirring speed is 800 to 1200r / min;

[0049] (3) Weigh 3 to 10 parts by mass of crosslinking agent and 0.5 to 2 parts by mass of catalyst, add them to the mixed material in step (2), and continue to stir for 3 to 8 minutes. stitching.

[0050] In the present invention, the adhesive fil...

Embodiment 1

[0055] Weigh 100 g of hydroxyl-terminated polymethylphenylsiloxane (brand: 108 silicone rubber), put it into a 500 ml plastic beaker, weigh 15 g of white carbon black, 20 g of chopped quartz fibers with a length of 1 mm, and 10 g of phenolic pellets ( The average particle size is 50 μm) and 15 g of zirconium silicide (median particle size D50 is 7 μm), put into 108 silicone rubber, mix and stir with a planetary mixer for 10 minutes, and the speed is controlled at about 800 r / min. After the stirring is completed, add 1 g of dibutyltin dilaurate and 10 g of tetraethyl orthosilicate, and continue stirring for 3 minutes. Apply the mixed adhesive filler to four 100×100mm lightweight silicon hybrid phenolic-impregnated quartz fiber composites (DMS6, density 0.55g / cm3) with a syringe gun or manually. 3 , porosity 70%), spliced ​​into a 200mm × 200mm composite splicing board, after curing at room temperature for 72 hours, as figure 1 shown. The average density of the adhesive filler...

Embodiment 2

[0057] Weigh 100g of hydroxyl-terminated polymethylsiloxane (grade: 107 silicone rubber), put it into a 500ml plastic beaker, weigh 15g of white carbon black, 30g of chopped quartz fibers with a length of 3mm, and 15g of phenolic pellets (average particle size 50 μm in diameter), 5 g of zirconium silicide (median particle size D50 is 7 μm), 15 g of ethanol diluent, put into 107 silicone rubber, mix and stir for 10 min with a planetary mixer, and control the speed at about 800 r / min. After stirring, add the POSS coupling agent of the dibutyltin dilaurate of 1g and 8g, molecular formula is ((CH 3 O) 3 SiC 3 h 6 S-C 2 h 4 -SiO 1.5 ) 8 , continue stirring for 5min. Apply the mixed adhesive filler to the gaps of four 100mm×100mm lightweight silicon hybrid phenolic-impregnated quartz fiber composites (DMS6) with a syringe gun or manually, and splice them into a 200mm×200mm composite splicing board , Cured at room temperature for 50 hours. The average density of the adhesive...

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Abstract

The invention provides an adhesive filler for splicing a light porous composite material and a preparation method of the adhesive filler. The adhesive filler is obtained by the following steps: weighing 100 parts by mass of hydroxyl-terminated polysiloxane, and putting the hydroxyl-terminated polysiloxane into a mixing container; weighing 0-30 parts by mass of white carbon black, 10-40 parts by mass of chopped fibers, 10-50 parts by mass of hollow spheres, 5-15 parts by mass of an antioxidant filler and 0-30 parts by mass of a diluent, putting the above weighed materials into the mixing container, and conducting physical stirring and mixing at room temperature; and weighing 3-10 parts by mass of a cross-linking agent and 0.5-2 parts by mass of a catalyst, adding the cross-linking agent andthe catalyst into the mixed material, and continuously conducting stirring to be used for splicing the light porous composite material. The adhesive filler has good chemical and physical adaptabilitywith a low-density composite material matrix, and meanwhile, has the characteristics of high-temperature ablation resistance, oxidation resistance, high-temperature sealing, low density and low thermal conductivity, and meets the requirements of splicing, bonding, gap filling and repairing of the light porous composite material.

Description

technical field [0001] The invention relates to an adhesive filler for lightweight porous composite splicing and a preparation method thereof, which belongs to the field of functional composite materials and is mainly used in the manufacture of lightweight thermal protection systems for aerospace vehicles. Background technique [0002] With the continuous weight reduction requirements of aerospace vehicles, the most important heat-resistant materials for re-entry / entry vehicles (such as spacecraft, return satellites, etc.) are gradually changing from traditional dense structures to loose and porous structures. Taking carbon / phenolic ablation heat-resistant materials as an example, the density of traditional dense carbon / phenolic composite materials is 1.5g / cm 3 Above, and in the advanced thermal protection system of modern aerospace vehicles, the density of carbon / phenolic composite materials can be as low as 0.25g / cm 3 , such as NASA's PICA material (density about 0.25g / cm...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C09J183/04C09J11/04C09J11/06C09J11/08
CPCC09J183/04C09J11/04C09J11/06C09J11/08C08L2205/025C08L2205/20C08L2201/08C08L61/06C08K13/04C08K7/26C08K7/10C08K3/34C08K5/5415C08L83/04
Inventor 师建军孔磊王伟李弘瑜杨云华李俊宁王金明刘登瑶孙福瑞
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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