阅读说明：本技术 一种应用于超声速导弹上的新型隔热贴片 (Novel heat insulation patch applied to supersonic missile ) 是由 刘强 任广为 梁建军 李其畅 陈景鹏 谢雪明 孙永丰 于 2020-06-12 设计创作，主要内容包括：一种应用于超声速导弹上的新型双层隔热贴片。该贴片采用非金属+金属材料制成,通过非金属材料的低导热性高效阻隔外环境热源,通过金属材料的高密度特点降低内环境温度,为导弹结构及舱内仪器设备提供环境温度保护。新型隔热贴片增加了金属层,其防隔热效果强于传统隔热材料,且具备较好的力学性能,可承受一定力学载荷环境。新型隔热贴片适用范围广,可隔导弹内外热。贴片制造工艺简单,无需特殊加工设备。(A novel double-layer heat-insulating patch applied to a supersonic missile. The patch is made of nonmetal and metal materials, the low thermal conductivity and high efficiency of the nonmetal materials are used for blocking an external environment heat source, the high density characteristic of the metal materials is used for reducing the internal environment temperature, and the environmental temperature protection is provided for missile structures and instrument and equipment in the cabin. The novel heat-insulating patch is additionally provided with a metal layer, the heat-insulating effect is better than that of the traditional heat-insulating material, and the novel heat-insulating patch has better mechanical property and can bear a certain mechanical load environment. The novel heat insulation patch has wide application range and can insulate the internal heat and the external heat of the missile. The patch is simple in manufacturing process and does not need special processing equipment.)

1. A novel heat insulation patch applied to a supersonic velocity missile is designed to be of a double-layer structure of nonmetal and metal materials and is tightly attached through a high-temperature resistant adhesive. The paster effectively blocks an external environment heat source through the low heat conductivity of the non-metal material, reduces the internal environment temperature through the high density characteristic of metal, and provides environment temperature protection for missile structures and instrument and equipment in the cabin.

2. The novel thermal insulation patch applied to the supersonic missile according to claim 1, wherein the material is selected from the following materials: 3 kinds of non-metal materials (carbon fiber composite material, ablation-resistant silicon rubber and cork), 2 kinds of metal materials (alloy aluminum and alloy steel) and 2 types of high-temperature-resistant adhesives (XZ-T002 and ZS-1071).

3. The novel thermal patch for supersonic missiles as claimed in claim 1, wherein the patch has a two-layer structure with an optimal thickness distribution. On the premise of setting the total thickness of the patch, the optimal thickness of the two layers can achieve the optimal heat insulation effect. The optimal thickness distribution formula is as follows:

wherein subscripts 1 and 2 represent non-metallic material and metallic parameter, respectively, wherein delta is material thickness (mm), and lambda is thermal conductivity (W/(m.K)),rho is density (kg/m)³) And c is the specific heat capacity of the material (J/(kg. K)). n is₁、n₂As a coefficient, 2.0 and 1.5 were taken, respectively. Considering the lightweight design of the patch, the coefficient n can be properly reduced₁And the concentration is 1.6-2.0.

4. The novel heat insulation patch applied to the supersonic missile as claimed in claim 1, wherein the surface coating mode of different materials is selected to isolate external heat and internal heat in a targeted manner. The outer nonmetal and inner metal layer are adhered and coated on the outer surface of the bullet body and are used for protecting the heating of the bullet body by pneumatic heat; the outer metal and the inner non-metal layer are adhered and coated on the outer shell of the engine and the spray pipe and are used for protecting the engine and the spray pipe from heating the external hanging equipment.

Technical Field

The invention provides a heat insulation scheme applied to supersonic missiles, and belongs to the field of heat insulation design of an aviation aircraft structure.

Background

The supersonic missile flies at high speed at low altitude, the dynamic pressure of the environment is very high, and the pneumatic heating environment faced by the missile structure is severe due to the long-time flight. Research shows that when the flying Mach number of the missile exceeds 2.5, the temperature of the missile wall of the metal material can exceed 400 ℃. The high wall temperature of the missile seriously weakens the strength of the bearing structure of the missile body and brings adverse effects to the normal operation of the internal equipment of the missile compartment, thereby causing the flight performance and the flight quality of the missile to be reduced and even endangering the flight safety. Therefore, the heat insulation prevention design is an indispensable ring in the design of the supersonic velocity missile.

The traditional heat insulation and protection scheme is mainly characterized in that a layer of heat insulation and protection material with low heat conductivity is covered on the outer surface of an elastomer and used for delaying heat conduction to the inside, and more materials including inner heat insulation layer materials, polyurethane foam plastics and cork heat insulation materials are applied. These materials can effectively block heat transfer, but their low density characteristics tend to cause the temperature of the material itself to be too high, resulting in insignificant heat insulation effect when the material is thin. If thicker insulation is used, the options for increasing flight resistance and sacrificing packing space are needed, putting pressure on the overall design of the aircraft. Therefore, the development of a novel thermal protection scheme with high-efficiency heat-proof and heat-insulation capacity is urgent.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and a novel heat insulation patch applied to the supersonic missile is invented. The patch is designed into a double-layer heat insulation structure of nonmetal and metal materials, and the two layers are tightly attached through a high-temperature resistant adhesive. The paster effectively blocks an external environment heat source through the low heat conductivity of the non-metal material, reduces the internal environment temperature through the high density characteristic of metal, and provides environment temperature protection for missile structures and instrument and equipment in the cabin.

The technical solution of the invention is as follows: (in accordance with the claims)

Compared with the prior art, the invention has the beneficial effects that:

(1) the invention adopts a double-layer heat insulation structure of non-metal and metal materials, and the heat insulation effect is higher than that of a pure non-metal heat insulation material. Under the condition of the same thickness of the heat insulation material, the temperature of the inner wall of the scheme of the invention is lower; the structure of the scheme of the invention has thinner thickness under the same heat source.

(2) The metal layer is added, so that the paster has better mechanical property and can adapt to mechanical load environment examination in a certain range.

(3) The invention has wide application range. The outer nonmetal and inner metal layer are adhered and coated on the outer surface of the bullet body in a mode of outer nonmetal and inner metal layer, so that the heating of the bullet body by pneumatic heat can be effectively prevented; the outer metal and the inner non-metal layer are adhered and coated on the outer shell of the engine, so that the heating of the external hanging equipment by the engine shell can be prevented. If the non-metal is made of a large flexible material, the invention can adapt to large curvature surfaces of the front edge of a small rudder, a cable, a clearance heat-proof sleeve of a swinging spray pipe and the like.

(4) The invention has simple manufacturing process, can obtain heat insulation products with different application ranges by using the high-temperature resistant adhesive to attach nonmetal and metal layers with different thicknesses, does not need special processing equipment and has low preparation cost.

Drawings

Fig. 1 is a schematic view of the novel thermal patch of the present invention.

FIG. 2 is an application of the novel heat insulation patch in the supersonic velocity missile, wherein FIG. 2(a) is a layout schematic diagram of each cabin section of the missile; FIG. 2(b) is a schematic view of a heat shield design; FIG. 2(c) is a schematic view of an instrument pod thermal isolation structure; FIG. 2(d) is a schematic view of a heat insulation structure of the cabin-penetrating cable; FIG. 2(e) is a schematic view of the thermal insulation structure of the jet nozzle; fig. 2(f) is a schematic view of the thermal insulation structure of the missile wing.

FIG. 3 is a graph of the temperature profile of the inner wall for different insulation modes for the same material thickness.

FIG. 4 is a graph showing the thickness of materials for different insulation modes at the same inner wall temperature.

Detailed Description

The utility model provides a be applied to novel thermal-insulated paster on supersonic velocity guided missile, the key feature is: the low-thermal-conductivity nonmetal + high-density metal double-layer structure is formed by gluing through a high-temperature-resistant adhesive, and is shown in figure 1.

Based on the requirements of better ablation resistance and heat insulation, a proper non-metal material is selected, and the non-metal material also has the characteristics of lower density and lower material quality. The non-metallic materials used by the patch are as follows: carbon fiber composite material, ablation-resistant silicon rubber and cork. Considering wide sources and low cost, the metal materials used by the patch are as follows: alloy aluminum and alloy steel. The patch is glued by using XZ-T002 and ZS-1071 type binders. Relevant material properties table 1.

TABLE 1 Properties of metallic and non-metallic materials used for Patches

The principle of the patch heat insulation is that an external environment heat source is efficiently blocked through the low heat conductivity of a non-metal material, the internal environment temperature is reduced through the high density characteristic of a metal material, and environment temperature protection is provided for missile structures and instrument and equipment in a cabin. On the premise of giving the thickness delta of the heat insulation layer, the thickness distribution of the nonmetal and metal materials is carried out according to the following formula, so that the optimal heat insulation effect can be achieved.

Wherein subscripts 1 and 2 represent composite material and metal parameters respectively, wherein delta is material thickness (mm), and lambda is thermal conductivity (W/(m.K)),rho is density (kg/m)³) And c is the specific heat capacity of the material (J/(kg. K)). n is₁、n₂As a coefficient, 2.0 and 1.5 were taken, respectively. To lighten the heat insulating layer and reduce the mass of the heat insulating material per unit area, m is min [ rho ]₁δ₁+ρ₂δ₂]Considering the heat insulation efficiency, the coefficient n is properly reduced in the distribution of the thickness₁And the concentration is 1.6-2.0.

The nonmetal and metal materials are tightly glued through an XZ-T002 or ZS-1071 high-temperature adhesive to form the patch.

According to the characteristics of the non-metal material and the metal material, different thickness ratios are designed to form the specification customization of the patch. Taking carbon fiber composite material + alloy steel, ablation-resistant silicone rubber + alloy aluminum, cork + alloy aluminum as an example, the customized specifications are shown in table 2. When the square heat insulation scheme is designed, the corresponding patch types and specifications can be selected according to the table 2 based on the shapes and thermal environment conditions of all parts of the missile.

Table 2 different thickness customization scheme for patches

The coating mode of the patch is different according to different heat sources of missile parts. The pneumatic heating of the bomb body is insulated, and the outer surface of the bomb body is pasted and coated with a non-metal layer and an inner metal layer outside the patch in a mode of protecting the bomb body structure and equipment in a cabin. The heat in the elastomer (such as a combustion chamber of an engine and a spray pipe) is insulated, and the outer metal and the inner non-metal layer are adhered and coated on the outer side of the engine outer shell and the outer side of the spray pipe to protect external equipment.

In addition, the non-metal layer is made of ablation-resistant silicon rubber materials with high flexibility facing to the front edge of the small rudder, the cable, the clearance heat-proof sleeve of the swinging spray pipe and other large-curvature surfaces.

Taking a conventional supersonic velocity winged missile as an example, a hood, an instrument cabin, a cable penetrating through an engine cabin, a spray pipe and missile wings all need to be subjected to heat insulation treatment, and the figure 2 shows. The hood is made of cork and alloy aluminum materials, the instrument cabin and the missile wing are made of carbon fiber composite materials and alloy steel materials, and the cable and the spray pipe penetrating through the engine cabin are made of ablation-resistant silicon rubber and alloy aluminum materials. The specific parameters are shown in Table 3.

TABLE 3 supersonic missile insulation scheme

The actual effect of the invention is tested by predicting the temperature of the inner wall surface of the instrument chamber according to the aerodynamic and material heat conduction principles and comparing with the non-heat-insulation measures. Table 4 shows the ballistic environment required for the test.

TABLE 4 supersonic missile trajectory

Fig. 3 is an inner wall temperature curve under different heat insulation schemes in the same ballistic thermal environment, wherein the Mode1 scheme is a pure metal material (alloy steel), the Mode2 scheme is a pure non-metal material (carbon fiber composite), the Mode3 scheme is a patch (carbon fiber composite + alloy steel) of the invention, and the thicknesses of the materials in the three schemes are all 4 mm. Fig. 3 shows that the Mode1 scheme is adopted, the temperature of the inner wall can reach about 300 ℃ at most, the structure safety is seriously influenced, and the normal work of the equipment is damaged. The pure non-metal heat insulation material scheme adopting the model 2 has the inner wall temperature of about 195 ℃ at most, and can still affect equipment in an instrument chamber, and the model 2 heat insulation scheme has a common effect. By adopting the scheme of the invention, the Mode3 has the highest temperature of the inner wall of about 110 ℃, the temperature is lower, and the heat insulation effect is higher.

Fig. 4 is a thickness delta curve of the material used in the Mode2 solution and the Mode3 solution under the same wall temperature thickness, and it can be seen that the material used in the patch solution of the invention has a thinner thickness. For example, when the wall temperature is reduced to 200 ℃, the use of the model 2 scheme requires a material with a thickness of 4mm, while the use of the scheme of the invention only requires a material with a thickness of 2 mm. The invention makes the heat insulation material thinner, and further optimization space is obtained for the resistance characteristic and the filling envelope of the missile.

The invention is not described in detail and is within the knowledge of a person skilled in the art.