A method for forming internal embedded wires in a solid rocket motor

Abstract

The present invention discloses a method for forming embedded wires in a solid motor, belonging to the field of motors, and comprising the following steps: applying an interface adhesive to the bonding surface of the control circuit prefabricated part and the area of embedded wires in the solid motor; assembling the control circuit prefabricated part in place in the solid motor; and pressurizing the control circuit prefabricated part through an airbag at normal temperature to fix the control circuit prefabricated part at a predetermined design position. The embedded wire method adopted in the present invention promotes the full play of the performance of the solid motor through improvements in aspects such as enhancing aerodynamic performance, strengthening wire protection, and simplifying the design of the launch device. Compared with the traditional external wire routing method, the embedded wire method enables the solid motor to be more stable and reliable while maintaining high thrust, providing a strong guarantee for the flight safety of the solid motor.

Description

Technical Field

[0001] The present invention relates to the field of engines, and particularly to a method for forming an embedded wire in a solid engine. Background Art

[0002] In traditional solid engines, the control lines are arranged in an external wiring manner, which requires the design of special fixing supports for fixing the control lines, thus sacrificing part of the aerodynamic performance. In addition, corresponding designs need to be made for the launch device to adapt to the shape of the solid engine. Moreover, in the case of external wiring, the lines are easily damaged by external forces, damaged by aerodynamic high temperatures, and interfered by complex electromagnetic environments, which puts high requirements on the physical damage resistance, high temperature resistance, corrosion resistance, and electromagnetic interference resistance of the control lines. Summary of the Invention

[0003] In order to solve the above technical problems, the present invention provides a method for forming an embedded wire in a solid engine that is easy to implement, safe and reliable.

[0004] The technical solution of the present invention for solving the above technical problems is: a method for forming an embedded wire in a solid engine, comprising the following steps:

[0005] S1, applying an interface adhesive: applying an interface adhesive to the bonding surface of the control line prefabricated part and the area of the embedded wire in the solid engine;

[0006] S2, assembling the control line prefabricated part: assembling the control line prefabricated part in place in the solid engine;

[0007] S3, cold pressing and shaping: pressurizing the control line prefabricated part through an airbag at normal temperature to fix the control line prefabricated part at a predetermined design position.

[0008] In the above method for forming an embedded wire in a solid engine, in step S1, an interface adhesive is applied to the bonding surface of the control line prefabricated part and the area of the embedded wire in the engine, and auxiliary adhesives are spot-applied at set intervals.

[0009] In the above method for forming an embedded wire in a solid engine, in step S1, a wire passing hole is reserved at the same generatrix position at the front end and the tail end of the cylindrical section of the solid engine housing, and the control line embedded in the combustion chamber of the solid engine passes through the wire passing hole; the control line prefabricated part is bonded to the straight line between the two wire passing holes in the solid engine.

[0010] In the above method for forming an embedded wire in a solid engine, in step S1, the control line prefabricated part includes a control line and a heat insulation material wrapped outside the control line, and the distance between the part of the control line wrapped with the heat insulation material in the middle and the wire passing holes at the front and rear ends of the solid engine is equal.

[0011] In the above method for forming embedded wires inside a solid rocket motor, in step S1, the cross-section of the prefabricated control circuit is crescent-shaped, which is conducive to the bonding surface of the prefabricated control circuit fitting against the inner wall of the solid rocket motor, and there are no bulges or trapped air.

[0012] In the above method for forming embedded wires inside a solid rocket motor, in step S2, the prefabricated control circuit is assembled in place inside the solid rocket motor, and the tooling is installed in place to complete the assembly of the prefabricated control circuit. The specific process is as follows:

[0013] First, align and fix the front end of the prefabricated control circuit with one end of the tooling. Then, jointly send the prefabricated control circuit and the tooling to the predetermined position inside the solid rocket motor, ensuring that the wire harness inside the prefabricated control circuit is directly opposite the front and rear wire passing holes, the prefabricated control circuit and the two wire passing holes are on the same straight line, the front and rear ends of the part of the control circuit wrapped with thermal insulation material just abut against the two wire passing holes, and the part of the control circuit not wrapped with thermal insulation material is not exposed inside the solid rocket motor. Finally, snap the protruding rectangular blocks at the front and rear ends of the tooling into the two wire passing holes.

[0014] In the above method for forming embedded wires inside a solid rocket motor, in step S2, the tooling is a long strip-shaped plate, which is used to ensure that the prefabricated control circuit is straight inside the solid rocket motor and to ensure that the prefabricated control circuit is not moved when the airbag is inserted and removed.

[0015] In the above method for forming embedded wires inside a solid rocket motor, in step S3, in a normal temperature environment, the airbag is sent into the solid rocket motor. After sealing the front and rear ends of the solid rocket motor, the airbag is inflated, and the pressure of the airbag is used to press and fix the prefabricated control circuit at the predetermined designed position on the solid rocket motor shell.

[0016] In the above method for forming embedded wires inside a solid rocket motor, in step S3, the tooling is made of flexible fiberglass or hard plastic. The length of the main body part is equal to the distance between the two wire passing holes. There are protruding rectangular blocks for positioning at both ends of the main body part, and the protruding rectangular blocks are inserted into the wire passing holes.

[0017] In the above method for forming embedded wires inside a solid rocket motor, in step S3, after fixing the prefabricated control circuit inside the solid rocket motor shell, the tooling is removed.

[0018] The beneficial effects of the present invention are as follows: By adopting the method of embedded wires instead of the external wiring method of the traditional solid rocket motor control circuit, the present invention brings significant beneficial effects, which are specifically reflected in the following aspects:

[0019] 1. Improve aerodynamic performance: The method of embedded wires adopted in the present invention does not require additional fixed supports, thus maintaining the integrity of the solid rocket motor shell, which is beneficial to improving the aerodynamic performance of the solid rocket motor, and further improving the flight efficiency and thrust of the solid rocket motor.

[0020] 2. Enhanced circuit protection: In the present invention, the control circuit is buried in the heat insulation layer. The heat insulation layer itself has corrosion resistance, and the solid rocket motor casing can resist most electromagnetic interference, thus effectively protecting the control circuit from damage by the external environment and improving its performance in terms of physical damage resistance, high temperature resistance, corrosion resistance, and electromagnetic interference resistance.

[0021] 3. Simplified launcher design: The present invention does not require additional design adjustments to the launcher. Only minor adjustments to the heat insulation layer are needed to make the control circuit adapt to the high-temperature environment inside the solid rocket motor, thereby simplifying the design process of the launcher and reducing the manufacturing cost.

[0022] 4. Improved performance of solid rocket motor: The internal wire embedding method adopted in the present invention, through improvements in terms of enhancing aerodynamic performance, strengthening circuit protection, and simplifying launcher design, jointly promotes the full play of the performance of the solid rocket motor. Compared with the traditional external wire routing method, the internal wire embedding method enables the solid rocket motor to be more stable and reliable while maintaining high thrust, providing a strong guarantee for the flight safety of the solid rocket motor. Description of the Drawings

[0023] Figure 1 It is a flowchart of the method for forming internal wire embedding in the solid rocket motor of the present invention.

[0024] Figure 2 It is a longitudinal cross-sectional schematic diagram after the implementation of the present invention.

[0025] Figure 3 It is a cross-sectional schematic diagram after the implementation of the present invention.

[0026] Figure 4 It is a structural schematic diagram of the tooling. Detailed Embodiment

[0027] The following further describes the present invention with reference to the drawings and embodiments.

[0028] As Figures 1-4 shown, a method for forming internal wire embedding in a solid rocket motor includes the following steps:

[0029] S1, applying the interface adhesive: Apply the interface adhesive 7 on the bonding surface of the control circuit prefabricated part and the internal wire embedding area inside the solid rocket motor. The interface adhesive 7 is any adhesive suitable for bonding metal interfaces and non-metal interfaces, and the auxiliary adhesive 6 is applied by dotting at set intervals. The auxiliary adhesive 6 is any adhesive with good bonding performance with the control circuit prefabricated part 3 and the interface adhesive 7.

[0030] At the front end and the same busbar position at the tail end of the cylindrical section of the solid rocket motor casing 1, a wire passing hole is reserved respectively. The control circuit buried inside the solid rocket motor combustion chamber passes through the wire passing holes; the control circuit prefabricated part 3 is bonded on the straight line between the two wire passing holes inside the solid rocket motor, and this is the predetermined installation position of the control circuit prefabricated part 3.

[0031] The control circuit prefabricated part 3 includes a control circuit 5 and a heat insulation material 4 wrapped outside the control circuit 5. The tensile strength of the heat insulation material 4 is ≥8 MPa, and the oxyacetylene linear ablation rate is ≤0.05 mm / s. The length of the part of the control circuit 5 wrapped with the heat insulation material in the middle is equal to the distance between the front and rear wire passing holes of the solid rocket motor. The lengths of the parts of the control circuit 5 at both ends not wrapped with the heat insulation material are not less than 500 mm.

[0032] As Figure 3 shown, the cross-section of the control circuit prefabricated part 3 is crescent-shaped, which is conducive to the bonding surface of the control circuit prefabricated part 3 fitting with the inner wall of the solid rocket motor, and there is no bulging or air entrapment.

[0033] S2, Assemble the control circuit prefabricated part 3: Assemble the control circuit prefabricated part 3 in place inside the solid rocket motor, and install the tooling 2 in place to complete the assembly of the control circuit prefabricated part 3; the specific process is as follows:

[0034] First, align and fix the front end of the control circuit prefabricated part 3 with one end of the tooling 2; then jointly send the control circuit prefabricated part 3 and the tooling 2 to the predetermined position inside the solid rocket motor, ensuring that the wire harness inside the control circuit prefabricated part 3 is facing the front and rear wire passing holes, the control circuit prefabricated part 3, and the two wire passing holes are on the same straight line. The front and rear ends of the part of the control circuit 5 wrapped with the heat insulation material 4 are just in contact with the two wire passing holes, and the part of the control circuit 5 not wrapped with the heat insulation material 4 is not exposed inside the solid rocket motor; finally, snap the protruding rectangular blocks at the front and rear ends of the tooling 2 into the two wire passing holes.

[0035] The tooling 2 is a long strip-shaped plate, which is used to ensure that the control circuit prefabricated part 3 is straight inside the solid rocket motor, and to ensure that the control circuit prefabricated part 3 is not moved when the airbag is sent in and taken out.

[0036] S3, Cold pressing and shaping: In a normal temperature environment, send the airbag into the solid rocket motor, seal the front and rear ends of the solid rocket motor, and then inflate the airbag. Use the pressure of the airbag to press and fix the control circuit prefabricated part 3 at the predetermined design position of the solid rocket motor casing 1. The airbag pressure is 0.6 MPa - 0.8 MPa.

[0037] As Figure 4As shown, the tooling 2 is made of flexible fiberglass or hard plastic. The length of the main body part is equal to the distance between the two wire passing holes and is slightly wider than the prefabricated control circuit 3. At both ends of the main body part, there are protruding rectangular blocks for positioning. The protruding rectangular blocks are inserted into the wire passing holes. The width of the protruding rectangular blocks is slightly smaller than the width of the wire passing holes, and the length of the protruding rectangular blocks is 5 mm to 30 mm.

[0038] After fixing the prefabricated control circuit 3 into the solid rocket motor casing 1, the tooling 2 is removed.

Claims

1. A method for forming a wire embedded in a solid rocket engine, characterized in that: The following steps are involved: S1, applying interface adhesive: applying interface adhesive on the bonding surface of the control circuit prefabricated component and the wire embedding area in the solid engine; S2, assembling the control circuit prefabricated component: assembling the control circuit prefabricated component into place in the solid engine; In step S2, the control circuit prefabricated part is assembled in place in the solid engine, and the tooling is installed in place to complete the assembly of the control circuit prefabricated part; the specific process is: First, align and fix the front end of the control circuit prefabricated part with one end of the tooling; then work together to send the control circuit prefabricated part and the tooling to the predetermined position in the solid engine, ensure that the wire harness in the control circuit prefabricated part is directly opposite to the front and rear end wire holes, the control circuit prefabricated part and the two wire holes are kept in the same straight line, the front and rear ends of the control circuit part wrapped with insulation material are just tightly against the two wire holes, and the control circuit part not wrapped with insulation material is not exposed in the solid engine; finally, the protruding rectangular blocks at the front and rear ends of the tooling are inserted into the two wire holes; S3, cold pressing and shaping: pressurizing the control circuit prefabricated component through the air bag at room temperature to fix the control circuit prefabricated component at the predetermined design position.

2. The method for forming a wire embedded in a solid rocket according to claim 1, characterized in that: In the step S1, the interface adhesive is applied on the bonding surface of the control circuit prefabricated component and the wire embedding area in the engine, and the auxiliary adhesive is applied at set intervals.

3. The method for forming a wire embedded in a solid rocket according to claim 1, characterized in that: In the step S1, a wire passing hole is reserved at the same busbar position at the front end and the rear end of the cylindrical section of the solid engine casing, and the control line embedded in the solid engine combustion chamber passes through the wire passing hole; the control line prefabricated part is bonded to the straight line between the two wire passing holes in the solid engine.

4. The method for forming a wire embedded in a solid rocket according to claim 1, characterized in that: In step S1, the control circuit prefabricated component includes the control circuit and the heat-insulating material wrapped around the outside of the control circuit, and the distance between the middle part of the control circuit wrapped with the heat-insulating material and the front and rear end wire holes of the solid engine are equal in length.

5. The method for forming a wire embedded in a solid rocket according to claim 4, characterized in that: In the step S1, the cross section of the control circuit preform is crescent-shaped, which is conducive to the bonding surface of the control circuit preform to fit with the inner wall of the solid engine.

6. The method for forming a wire embedded in a solid rocket according to claim 1, characterized in that: In step S2, the tooling is a long strip plate, which is used to ensure that the control circuit preform is straight in the solid engine and to ensure that the control circuit preform is not moved when the airbag is put in and taken out.

7. The method for forming a wire embedded in a solid rocket according to claim 1, characterized in that: In step S3, at room temperature, the airbag is sent into the solid engine, the front and rear ends of the solid engine are sealed, the airbag is inflated, and the control circuit preform is pressed and fixed at a predetermined design position of the solid engine casing by the pressure of the airbag.

8. The method for forming a wire embedded in a solid rocket according to claim 7, characterized in that: In step S3, the tooling is made of tough fiberglass or hard plastic, the length of the main body is equal to the distance between the two wire holes, and protruding rectangular blocks for positioning are provided at both ends of the main body, and the protruding rectangular blocks are inserted into the wire holes.

9. The method for forming a wire embedded in a solid rocket according to claim 7, characterized in that: In step S3, the control circuit prefabricated component is fixed into the solid engine casing and then the tooling is removed.

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