Heat insulation method for embedded wire of solid engine

Abstract

The invention discloses a heat insulation method for an embedded wire of a solid engine, which belongs to the field of engines and comprises the following steps of: flatly arranging and weaving a control circuit; an upper heat insulation layer for protecting the control circuit from high-temperature damage of a combustion chamber of the solid engine is added to the upper part of the control circuit, and a lower heat insulation layer for protecting the control circuit from external pneumatic high-temperature damage of the solid engine is added to the lower part of the control circuit; and a heat insulation coating is sprayed outside the lower heat insulation layer for auxiliary protection. The solid engine embedded wire heat insulation method disclosed by the invention shows remarkable beneficial effects in the aspects of improving the protection performance of a control circuit, enhancing the electromagnetic interference protection capability, reducing the cost and the process complexity and improving the operation safety, and has important significance in promoting the progress and development of a solid engine technology.

Description

Technical Field

[0001] The invention relates to the field of engines, and in particular to a heat insulation method for embedded wires in solid engines. Background Art

[0002] Traditional solid engine control circuits generally use external wiring, which has many problems during processing and use: (1) The control circuit is easily damaged by external forces, increasing the risk of the entire system; (2) The external wiring method requires additional external structures such as fixed supports to be set on the solid engine shell, which will have many adverse effects on the aerodynamic performance of the solid, and the corresponding launch device must also be specially designed for this purpose; (3) The external wiring method requires the control circuit to withstand very high aerodynamic high temperature and humid and corrosive environment; (4) The control circuit of the external wiring method is easily affected by complex electromagnetic environment and requires special protection design. It can be seen that there are many unfavorable factors that need to be considered and overcome in the external wiring method of the control circuit, which not only increases the manufacturing cost of the solid engine, but also invisibly adds many risks to the entire system. Summary of the invention

[0003] In order to solve the above technical problems, the present invention provides a method for heat insulation of embedded wires in solid rocket engines which is simple to operate, safe and reliable.

[0004] The technical solution of the present invention to solve the above technical problems is: a method for heat insulation of buried wires in a solid motor, comprising the following steps: S1: Arrange the control circuit in a flattened manner and weave it; S2: adding an upper insulation layer to the upper part of the control line to protect the control line from being damaged by the high temperature of the solid engine combustion chamber, and adding a lower insulation layer to the lower part of the control line to protect the control line from being damaged by the high temperature of the aerodynamic force outside the solid engine; S3: Spray insulation coating on the outside of the lower insulation layer for auxiliary protection.

[0005] In the above-mentioned method for insulating the buried wires in a solid rocket engine, in step S1, there is no crossing between the single data wires in the control circuit and the distance is maintained, the data wires are arranged equidistantly, and the knitting needle method is adopted to fix the data wires with aramid fiber wires so that the relative positions of the data wires remain unchanged.

[0006] In the above-mentioned method for heat insulation of buried wires in a solid rocket engine, in the step S1, the data wires of the control circuit are arranged in a straight line and woven into a flat plate shape.

[0007] In the above-mentioned solid motor internal wire insulation method, in step S2, the thickness of the upper insulation layer and the lower insulation layer are designed according to the maximum operating temperature inside the solid motor internal combustion chamber and the maximum external aerodynamic temperature.

[0008] In the above-mentioned solid engine internal wire insulation method, in step S2, when the maximum operating temperature in the internal combustion chamber of the solid engine is 2500°C and the maximum aerodynamic temperature outside the solid engine is 350°C, the thickness of the upper insulation layer is 3mm and the thickness of the lower insulation layer is 2mm.

[0009] In the above-mentioned solid motor internal wire insulation method, in step S2, the cross-sections of the upper insulation layer and the lower insulation layer are crescent-shaped, so that the contact positions of the upper insulation layer, the lower insulation layer and the solid motor casing have a smooth transition.

[0010] In the above-mentioned solid motor internal wire insulation method, in the step S2, the upper insulation layer and the lower insulation layer are formed by heating and pressing using a half mold and a vacuum bag with the same size as the solid motor casing.

[0011] In the above-mentioned solid motor internal wire insulation method, in step S3, the edge of the thermal insulation coating is chamfered or polished to ensure a smooth transition between the thermal insulation coating and the outer surface of the solid motor casing.

[0012] In the above-mentioned solid rocket engine internal wire insulation method, in step S3, the thickness of the thermal insulation coating is 1 mm.

[0013] The beneficial effects of the present invention are: 1. Improve the protection performance of the control line: The present invention effectively reduces the buried depth of the control line by flattening and weaving the control line, thereby reducing the impact on the internal structure of the solid engine. At the same time, according to the working temperature of the solid engine, the thickness of the insulation layer on both sides of the control line is designed, so that the insulation layer on the control line can fully protect the control line from the high temperature of the solid engine combustion chamber, and the insulation layer under the control line can effectively resist the damage to the control line caused by the high aerodynamic temperature outside the solid engine, thereby greatly improving the protection of the control line.

[0014] 2. Enhanced electromagnetic interference protection capability: The present invention places the control circuit inside the solid engine casing through the internal buried wire design, which greatly reduces the interference of the external electromagnetic environment on the control circuit, enhances the electromagnetic protection capability of the control circuit, reduces the production cost of the control circuit, and ensures the stable operation of the solid engine control system.

[0015] 3. Reduce costs and process complexity: The traditional solid engine control line layout requires the design of complex fixed supports and line directions, which increases manufacturing costs and process complexity. The present invention simplifies the line layout and reduces manufacturing costs through the internal line design; at the same time, the internal line method also reduces the complexity of line maintenance and improves the overall reliability of the solid engine.

[0016] 4. Improve operational safety: The present invention places the control circuit inside the solid engine through the internal wire design, avoiding direct damage and interference from the external environment, and improving the operational safety of the solid engine. In addition, according to the actual situation, a certain thickness of thermal insulation coating is sprayed on the outside of the lower insulation layer for auxiliary protection, which further enhances the adaptability of the solid engine to extreme environments and improves operational safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The present invention is a flow chart of the thermal insulation method for embedded wires in a solid rocket engine.

[0018] Figure 2 It is a cross-sectional schematic diagram after the implementation of the present invention. DETAILED DESCRIPTION

[0019] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0020] like Figure 1 , Figure 2 As shown, a method for heat insulation of buried wires in a solid motor comprises the following steps: S1: The control circuit 2 is arranged in a flat shape and braided, and the data lines of the control circuit 2 are arranged in a straight line and braided into a flat plate shape.

[0021] The single data lines in the control circuit 2 do not cross each other and keep a distance between each other. The data lines are arranged equidistantly and fixed with aramid fiber lines using a knitting needle method to keep the relative positions of the data lines unchanged.

[0022] S2: An upper insulation layer 3 is added to the upper part of the control line 2 to protect the control line 2 from being damaged by the high temperature of the solid engine combustion chamber, and a lower insulation layer 4 is added to the lower part of the control line 2 to protect the control line 2 from being damaged by the external aerodynamic high temperature of the solid engine.

[0023] The thickness of the upper insulation layer 3 and the lower insulation layer 4 is designed according to the maximum operating temperature inside the solid engine combustion chamber and the maximum external aerodynamic temperature. When the maximum operating temperature inside the solid engine combustion chamber is 2500°C and the maximum external aerodynamic temperature of the solid engine is 350°C, the thickness of the upper insulation layer 3 is 3mm and the thickness of the lower insulation layer 4 is 2mm.

[0024] The cross-sections of the upper insulation layer 3 and the lower insulation layer 4 are crescent-shaped, so that the contact positions of the upper insulation layer 3, the lower insulation layer 4 and the solid engine casing 1 have a smooth transition.

[0025] The upper insulation layer 3 and the lower insulation layer 4 are formed by heating and pressing using a half mold having the same size as the solid engine casing 1 and a vacuum bag.

[0026] S3: Spray a thermal insulation coating 5 on the outside of the lower thermal insulation layer 4 for auxiliary protection.

[0027] The edge of the thermal insulation coating 5 is chamfered or polished to make a smooth transition between the thermal insulation coating 5 and the outer surface of the solid engine casing 1. The thickness of the thermal insulation coating 5 is 1 mm.

Claims

1. A method for heat insulation of buried wires in a solid rocket engine, characterized in that: The following steps are involved: S1: Arrange the control circuit in a flattened manner and weave it; S2: adding an upper insulation layer to the upper part of the control line to protect the control line from being damaged by the high temperature of the solid engine combustion chamber, and adding a lower insulation layer to the lower part of the control line to protect the control line from being damaged by the high temperature of the aerodynamic force outside the solid engine; S3: Spray insulation coating on the outside of the lower insulation layer for auxiliary protection.

2. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S1, the single data lines in the control circuit do not cross each other and keep a distance between each other, the data lines are arranged equidistantly, and the data lines are fixed by knitting needles and aramid fiber lines to keep the relative positions of the data lines unchanged.

3. The method for heat insulation of embedded wires in a solid rocket engine according to claim 2, characterized in that: In the step S1, the data lines of the control circuit are arranged in a straight line and woven into a flat plate shape.

4. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S2, the thickness of the upper insulation layer and the lower insulation layer are designed according to the maximum operating temperature inside the combustion chamber of the solid motor and the maximum external aerodynamic temperature.

5. The method for heat insulation of embedded wires in a solid rocket engine according to claim 4, characterized in that: In step S2, when the maximum operating temperature in the combustion chamber of the solid engine is 2500°C and the maximum aerodynamic temperature outside the solid engine is 350°C, the thickness of the upper insulation layer is 3mm and the thickness of the lower insulation layer is 2mm.

6. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S2, the cross-sections of the upper insulation layer and the lower insulation layer are crescent-shaped, so that the contact positions of the upper insulation layer, the lower insulation layer and the solid engine casing have a smooth transition.

7. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S2, the upper insulation layer and the lower insulation layer are formed by heating and pressing using a half mold and a vacuum bag with the same size as the solid engine casing.

8. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S3, the edge of the thermal insulation coating is chamfered or polished to ensure a smooth transition between the thermal insulation coating and the outer surface of the solid engine casing.

9. The method for heat insulation of embedded wires in a solid rocket engine according to claim 1, characterized in that: In step S3, the thickness of the thermal insulation coating is 1 mm.

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