Thermal insulation material for aircraft cabin interlayer, and preparation method therefor

Abstract

The present invention relates to the technical field of high-performance materials. Disclosed are a thermal insulation material for an aircraft cabin interlayer, and a preparation method therefor. A main material comprises the following raw material components in part by weight: 8-20 parts of allyl Isocyanate, 2-6 parts of 1-tricyclic [3.3.1.1(3.7)] decanol, 5-7 parts of sodium citrate, 6-10 parts of copper oxide, 16-22 parts of polyoxyethylene-8-octyl phenyl ether, 8-16 parts of tert-butyl allylcarbamate, 15-20 parts of straw fiber, and 40-60 parts of an ethylene-vinyl acetate copolymer. An auxiliary material comprises the following raw material components in part by weight: 20-40 parts of sodium acetate, 5-10 parts of divinylbenzene, 2-8 parts of tween-20, 3-5 parts of tetrachloroethane, and 1-8 parts of azodicarbonamide. Upon test, it is found that the thermal insulation material has excellent mechanical property, low thermal conductivity and good thermal stability, and satisfies the basic fireproof requirement of a cabin.

Description

Thermal insulation material for aircraft cabin interlayer and preparation method thereof Technical Field

[0001] The present invention belongs to the technical field of high-performance materials, and in particular relates to a heat-insulating material for an aircraft cabin interlayer and a preparation method thereof. Background Art

[0002] High-temperature gases ejected from an aircraft's engine nacelle, through thermal radiation and convection, create large, high-temperature zones in the rearward-facing components. Temperatures can reach 2000K or even higher, exceeding the thermal limits of the materials used in these components. This can cause significant damage and impact their performance and service life. Modern aircraft often employ three measures to reduce rearward-facing engine nacelle temperatures: 1. Nacelle ventilation cooling: This utilizes auxiliary air intakes to provide cooling air to the nacelle, removing some of the heat transferred from the engine. 2. Improving the heat resistance of component materials: This improves the heat resistance of rearward-facing engine nacelle components based on the heat dissipation profile of the rearward-facing engine nacelle, though this increases aircraft manufacturing costs. 3. Radiation shielding: This involves installing radiation shielding structures in the rearward-facing engine nacelle to protect components from direct radiation heating. For both economical and practical reasons, radiation shielding is commonly used in modern aircraft to cool rearward-facing engine nacelle components. Heat shields are the most common radiation shielding structure, directly protecting the rearward-facing engine structure from high-temperature exhaust gases. Integrally formed heat shields can better meet operational requirements. Advanced international aviation companies have successfully developed integrated heat shields, which are now used on numerous advanced aircraft, including the Boeing 787. Traditional pod heat shields consist of sheet metal components, such as skins and reinforcement frames, and machined parts. Each component is formed and manufactured separately, then assembled through welding and mechanical connections. This process is complex, with high mold costs and long processing cycles. The forming process is difficult to control, prone to forming defects and deformation, and detrimental to the surface quality and dimensional accuracy of thin-walled components.

[0003] Thermal insulation materials generally refer to materials or material composites that can block heat flow transfer. They have low thermal conductivity, are loose, and porous, and can be used in aerospace, energy, chemical, and other fields. Thermal insulation materials can generally be divided into three categories: organic, ceramic, and metal-based composites. Organic thermal insulation materials have good mechanical properties, but they are flammable and have poor high-temperature resistance, which limits their application in high-temperature environments above 650°C. Ceramic thermal insulation materials have the advantages of being non-flammable, resistant to chemical corrosion, and resistant to high temperatures, and are often used in high-temperature fields. Metal-based composite thermal insulation materials have good machinability and mechanical strength, but their high thermal conductivity makes them unsuitable for use under high-temperature conditions. For example, the Chinese invention patent, application number: CN202310253118.4, discloses a nano-scale high-temperature thermal insulation ceramic fiber component, which has two formulas: the first, above 1300 degrees: 60% polycrystalline mullite fiber, 25% ceramic fiber cotton, 10% silica sol, 3% alumina powder, 2% brown corundum, white corundum fine powder, and steel fiber; the second, below 1300 degrees: 20% polycrystalline mullite fiber, 60% ceramic fiber cotton, 15% silica sol, 3% alumina powder, 2% brown corundum, white corundum fine powder, and steel fiber. It uses the latest energy-saving thermal insulation material ceramic fiber as raw material, and after being extruded by a hydraulic press to improve the density and strength, the ceramic fiber components are installed after cutting and polishing. After all the ceramic fiber components are connected, they are wrapped around the components with heat-resistant steel plates to achieve protection. Finally, the surface of the component is evenly coated with a ceramic fiber zirconium-containing protective layer and silica sol to achieve better thermal insulation effect. However, after analysis, it can be seen that its stability is poor and the mechanical properties brought by the actual use of ceramics are average.

[0004] Summary of the Invention

[0005] In view of the above-mentioned deficiencies in the prior art, the object of the present invention is to provide an insulating material for an aircraft cabin interlayer and a preparation method thereof. The present application designs two components, a main material and an auxiliary material, wherein the main material includes raw materials such as 1-tricyclo[3.3.1.1(3.7)]decanol, tert-butyl N-allylcarbamate, and straw fiber, and the auxiliary material includes raw materials such as divinylbenzene and Tween-20. After polymerization and covalent coupling reactions and treatment, the insulating material for an aircraft cabin interlayer is obtained. The insulating material for an aircraft cabin interlayer has been tested and found to have excellent mechanical properties, which can meet the strength requirements of the aircraft cabin interlayer, and has a low thermal conductivity and good thermal stability, meeting the basic fire protection requirements of the cabin. In addition, it is speculated that copper oxide may play a role in increasing the molecular weight and cross-linking of insulation materials used in aircraft cabin interlayers, and covalently couple with 1-tricyclo[3.3.1.1(3.7)]decanol during the reaction process, thereby improving physical properties and thermal insulation effects. At the same time, the cross-linking between straw fibers, divinylbenzene, etc. realizes the continuation of the condensation reaction, and by strengthening the overall network skeleton structure, prevents excessive shrinkage and cracking of the material during the later drying process, maintaining a certain degree of integrity.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A thermal insulation material for aircraft cabin interlayer,

[0008] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3);

[0009] The main ingredients include the following components in parts by weight:

[0010] The auxiliary materials include the following raw materials in parts by weight:

[0011] The thermal insulation material for the aircraft cabin interlayer,

[0012] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3); the main materials, in parts by weight, include the following raw material components:

[0013] The auxiliary materials include the following raw materials in parts by weight:

[0014] The thermal insulation material for the aircraft cabin interlayer,

[0015] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3); the main materials, in parts by weight, include the following raw material components:

[0016] The auxiliary materials include the following raw materials in parts by weight:

[0017] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0018] The following steps are involved:

[0019] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 80° C.-90° C. and 1 MPa-2 MPa for 10 h-24 h;

[0020] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C.-120° C., the reaction time is controlled at 4 h-8 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0021] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 60°C-70°C for 8h-12h; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 160°C-200°C for 4h-7h; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0022] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0023] The mixing parameters are as follows:

[0024] Stir at 85°C and 1 MPa for 16 h.

[0025] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0026] The parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa.

[0027] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0028] The parameters of the water bath are as follows: heating in a water bath at 70° C. for 8 h.

[0029] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0030] The parameters of the second reaction were as follows: reaction at 180°C for 6 hours.

[0031] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0032] The parameter conditions of the granulation drying are as follows:

[0033] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0034] Compared with the prior art, the present invention has the following beneficial effects:

[0035] This application designs two components: main materials and auxiliary materials. The main materials include 1-tricyclo[3.3.1.1(3.7)]decanol, N-allylcarbamic acid tert-butyl ester, straw fiber and other raw materials, and the auxiliary materials include divinylbenzene, Tween-20 and other raw materials. After polymerization and covalent coupling reactions and treatment, the thermal insulation material for aircraft cabin interlayer is obtained. The thermal insulation material for aircraft cabin interlayer has been tested and found to have excellent mechanical properties, which can meet the strength requirements of the aircraft cabin interlayer, and has a low thermal conductivity and good thermal stability, meeting the basic fire protection requirements of the cabin. In addition, it is speculated that copper oxide may play a role in increasing the molecular weight and cross-linking of insulation materials used in aircraft cabin interlayers, and covalently couple with 1-tricyclo[3.3.1.1(3.7)]decanol during the reaction process, thereby improving physical properties and thermal insulation effects. At the same time, the cross-linking between straw fibers, divinylbenzene, etc. realizes the continuation of the condensation reaction, and by strengthening the overall network skeleton structure, prevents excessive shrinkage and cracking of the material during the later drying process, thereby maintaining a certain degree of integrity. DETAILED DESCRIPTION

[0036] The technical solutions in the embodiments of the present invention are described in detail below. The described embodiments are only some embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art fall within the scope of protection of the present invention. The present invention is further described below in conjunction with specific embodiments.

[0037] Example 1

[0038] Thermal insulation materials for aircraft cabin interlayers,

[0039] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2;

[0040] The main ingredients include the following components in parts by weight:

[0041] The auxiliary materials include the following raw materials in parts by weight:

[0042] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0043] The following steps are involved:

[0044] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 80° C. and 2 MPa for 10 hours;

[0045] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 8 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0046] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 60°C for 12 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 160°C for 7 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0047] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0048] The parameter conditions of the granulation drying are as follows:

[0049] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0050] Example 2

[0051] Thermal insulation materials for aircraft cabin interlayers,

[0052] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:3;

[0053] The main ingredients include the following components in parts by weight:

[0054] The auxiliary materials include the following raw materials in parts by weight:

[0055] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0056] The following steps are involved:

[0057] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 90° C. and 1 MPa for 24 hours;

[0058] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 120° C., the reaction time is controlled at 4 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0059] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 200°C for 4 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0060] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0061] The parameter conditions of the granulation drying are as follows:

[0062] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0063] Example 3

[0064] Thermal insulation materials for aircraft cabin interlayers,

[0065] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2;

[0066] The main ingredients include the following components in parts by weight:

[0067] The auxiliary materials include the following raw materials in parts by weight:

[0068] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0069] The following steps are involved:

[0070] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 80° C. and 1 MPa for 10 hours;

[0071] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 4 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0072] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 60°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 160°C for 4 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0073] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0074] The parameter conditions of the granulation drying are as follows:

[0075] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0076] Example 4

[0077] Thermal insulation materials for aircraft cabin interlayers,

[0078] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:3;

[0079] The main ingredients include the following components in parts by weight:

[0080] The auxiliary materials include the following raw materials in parts by weight:

[0081] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0082] The following steps are involved:

[0083] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 90° C. and 2 MPa for 24 hours;

[0084] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 120° C., the reaction time is controlled at 8 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0085] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 12 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 200°C for 7 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0086] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0087] The parameter conditions of the granulation drying are as follows:

[0088] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0089] Example 5

[0090] Thermal insulation materials for aircraft cabin interlayers,

[0091] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0092] The main ingredients include the following components in parts by weight:

[0093] The auxiliary materials include the following raw materials in parts by weight:

[0094] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0095] The following steps are involved:

[0096] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0097] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0098] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 180°C for 6 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0099] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0100] The parameter conditions of the granulation drying are as follows:

[0101] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0102] Comparative Example 1

[0103] Thermal insulation materials for aircraft cabin interlayers,

[0104] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0105] The main ingredients include the following components in parts by weight:

[0106] The auxiliary materials include the following raw materials in parts by weight:

[0107] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0108] The following steps are involved:

[0109] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0110] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0111] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 180°C for 6 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0112] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0113] The parameter conditions of the granulation drying are as follows:

[0114] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0115] Comparative Example 2

[0116] Thermal insulation materials for aircraft cabin interlayers,

[0117] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0118] The main ingredients include the following components in parts by weight:

[0119] The auxiliary materials include the following raw materials in parts by weight:

[0120] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0121] The following steps are involved:

[0122] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0123] After the mixing operation is completed, the sodium citrate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0124] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 180°C for 6 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0125] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0126] The parameter conditions of the granulation drying are as follows:

[0127] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0128] Comparative Example 3

[0129] Thermal insulation materials for aircraft cabin interlayers,

[0130] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0131] The main ingredients include the following components in parts by weight:

[0132] The auxiliary materials include the following raw materials in parts by weight:

[0133] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0134] The following steps are involved:

[0135] The allyl isocyanate, the ethylene-vinyl acetate copolymer and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0136] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0137] The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 180°C for 6 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0138] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0139] The parameter conditions of the granulation drying are as follows:

[0140] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0141] Comparative Example 4

[0142] Thermal insulation materials for aircraft cabin interlayers,

[0143] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0144] The main ingredients include the following components in parts by weight:

[0145] The auxiliary materials include the following raw materials in parts by weight:

[0146] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0147] The following steps are involved:

[0148] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0149] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0150] The polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the water bath parameters are as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing insulation material for a second reaction, wherein the second reaction parameters are as follows: reacting at 180°C for 6 hours; after the second reaction is completed, cooling to room temperature, granulating and drying.

[0151] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0152] The parameter conditions of the granulation drying are as follows:

[0153] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0154] Comparative Example 5

[0155] Thermal insulation materials for aircraft cabin interlayers,

[0156] The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:2.5;

[0157] The main ingredients include the following components in parts by weight:

[0158] The auxiliary materials include the following raw materials in parts by weight:

[0159] The preparation method of the thermal insulation material for the aircraft cabin interlayer,

[0160] The following steps are involved:

[0161] The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 85° C. and 1 MPa for 16 hours;

[0162] After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise to carry out a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C., the reaction time is controlled at 6 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a thermal insulation material;

[0163] The copper oxide, the polyoxyethylene-8-octylphenyl ether, and the Tween-20 were transferred to a constant temperature water bath, wherein the water bath parameters were as follows: heating at 70°C for 8 hours; then slowly adding the sodium acetate dropwise, and transferring to a high-temperature and high-pressure stainless steel reactor containing a heat-insulating material for a second reaction, wherein the second reaction parameters were as follows: reacting at 180°C for 6 hours; after the second reaction was completed, cooling to room temperature, granulating, and drying.

[0164] The method for preparing the thermal insulation material for aircraft cabin interlayer described above,

[0165] The parameter conditions of the granulation drying are as follows:

[0166] Spray fluidized bed, air inlet temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

[0167] Application Solutions

[0168] The thermal insulation materials prepared in Examples 1-5 and the thermal insulation materials prepared in Comparative Examples 1-5 were selected and tested for mechanical properties and thermal insulation properties, respectively.

[0169] (1) Mechanical properties

[0170] After being formed into a 5 cm × 0.5 cm shape, the sample was dried and balanced under standard atmospheric conditions for 1 day. Then, a tensile test was performed on the sample at a tensile speed of 10 mm / min using an electronic universal testing machine.

[0171] Table 1 Mechanical properties

[0172] (2) Thermal insulation performance

[0173] The thermal conductivity is tested using the transient plane heat source method. During the test, a temperature probe with a self-heating function is placed in the sample, and a constant heating power is applied to the probe to increase its temperature within the range of 25-300°C.

[0174] The thermal stability was determined using a thermogravimetric analyzer. The temperature was raised from room temperature to 800°C at a rate of 10°C / min.

[0175] Table 2 Thermal insulation performance

[0176] In summary, the present application designs two components, the main material and the auxiliary material, wherein the main material includes 1-tricyclo[3.3.1.1(3.7)]decanol, N-allylcarbamic acid tert-butyl ester, straw fiber and other raw materials, and the auxiliary materials include divinylbenzene, Tween-20 and other raw materials. After polymerization and covalent coupling reactions, and after treatment, the thermal insulation material for the aircraft cabin interlayer is obtained. The thermal insulation material for the aircraft cabin interlayer has been tested and found to have excellent mechanical properties, which can meet the strength requirements of the aircraft cabin interlayer, and has a low thermal conductivity and good thermal stability, which meets the basic fire protection requirements of the cabin. In addition, it is speculated that copper oxide may play a role in increasing the molecular weight and cross-linking of insulation materials used in aircraft cabin interlayers, and covalently couple with 1-tricyclo[3.3.1.1(3.7)]decanol during the reaction process, thereby improving physical properties and thermal insulation effects. At the same time, the cross-linking between straw fibers, divinylbenzene, etc. realizes the continuation of the condensation reaction, and by strengthening the overall network skeleton structure, prevents excessive shrinkage and cracking of the material during the later drying process, maintaining a certain degree of integrity.

[0177] The above is a schematic description of the present invention and its embodiments. This description is not restrictive and only illustrates one embodiment of the present invention. The actual structure is not limited thereto. Therefore, if a person skilled in the art is inspired by this and, without departing from the purpose of the present invention, designs structures and embodiments similar to this technical solution without creatively designing them, they shall fall within the scope of protection of the present invention.

Claims

1. A thermal insulation material for an aircraft cabin interlayer, characterized in that: The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3); the main materials, in parts by weight, include the following raw material components: The auxiliary materials include the following raw materials in parts by weight:

2. The heat insulating material for aircraft cabin interlayer according to claim 1, characterized in that: The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3); the main materials, in parts by weight, include the following raw material components: The auxiliary materials include the following raw materials in parts by weight:

3. The heat insulating material for aircraft cabin interlayer according to claim 1, characterized in that: The raw materials include main materials and auxiliary materials, and the mass ratio between the main materials and the auxiliary materials is 10:(2-3); The main ingredients include the following raw materials in parts by weight: The auxiliary materials include the following raw materials in parts by weight:

4. A method for preparing the thermal insulation material for aircraft cabin interlayer according to any one of claims 1 to 3, characterized in that: The following steps are involved: The allyl isocyanate, the ethylene-vinyl acetate copolymer, the divinylbenzene and the azodicarbonamide are mixed, wherein the mixing parameters are as follows: stirring at 80° C.-90° C. and 1 MPa-2 MPa for 10 h-24 h; After the mixing operation is completed, the sodium citrate, the tert-butyl N-allylcarbamate, the 1-tricyclo[3.3.1.1(3.7)]decanol and the tetrachloroethane are added dropwise for a first reaction, wherein the parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110° C.-120° C., the reaction time is controlled at 4 h-8 h, and the reaction pressure is controlled at 800 kPa; after the first reaction, the mixture is cooled to room temperature to obtain a heat insulating material; The copper oxide, the polyoxyethylene-8-octylphenyl ether, the straw fiber, and the Tween-20 are transferred to a constant temperature water bath, wherein the parameters of the water bath are as follows: heating in a water bath at 60°C-70°C for 8h-12h; then slowly adding the sodium acetate dropwise, transferring to a high-temperature and high-pressure stainless steel reactor containing a heat-insulating material for a second reaction, wherein the parameters of the second reaction are as follows: reacting at 160°C-200°C for 4h-7h; cooling to room temperature after the second reaction, granulating and drying.

5. The method for preparing the heat insulating material for aircraft cabin interlayer according to claim 4, characterized in that: The mixing parameters are as follows: Stir at 85°C and 1 MPa for 16 h.

6. The method for preparing the heat insulating material for aircraft cabin interlayer according to claim 4, characterized in that: The parameters of the first reaction are as follows: a high-temperature and high-pressure stainless steel reactor is used, the reaction temperature is controlled at 110°C, the reaction time is controlled at 6h, and the reaction pressure is controlled at 800kPa.

7. The method for preparing the heat insulating material for aircraft cabin interlayer according to claim 4, characterized in that: The parameters of the water bath are as follows: heating in a water bath at 70°C for 8 hours.

8. The method for preparing the heat insulating material for aircraft cabin interlayer according to claim 4, characterized in that: The parameters of the second reaction were as follows: reaction at 180°C for 6 hours.

9. The method for preparing the heat insulating material for aircraft cabin interlayer according to claim 4, characterized in that: The parameter conditions of the granulation drying are as follows: Spray fluidized bed, inlet air temperature 145℃, material layer temperature 92℃, spray gun pressure 0.22MPa, discharge temperature 65℃.

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