CN216477610U - Solid rocket engine submerged nozzle blanking cover structure - Google Patents
Solid rocket engine submerged nozzle blanking cover structure Download PDFInfo
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- CN216477610U CN216477610U CN202123025490.5U CN202123025490U CN216477610U CN 216477610 U CN216477610 U CN 216477610U CN 202123025490 U CN202123025490 U CN 202123025490U CN 216477610 U CN216477610 U CN 216477610U
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Abstract
The utility model provides a solid rocket engine dive formula spray tube blanking cover structure, include: a front plugging cover combination body (2) and a rear plugging cover (3); the front blanking cover assembly (2) comprises: a glass fiber layer (21), a metal mesh layer (22) and a sealing layer (23); the front plugging cover assembly (2) is connected with the end face of the submerged section of the submerged nozzle (1) in a bonding mode, and the submerged nozzle (1) is connected with the engine shell (4) through threads; the glass fiber layer (21) is connected with the metal mesh layer (22) in a sticking way, and the glass fiber layer (21) is arranged towards the head of the engine; the sealing layer (23) is arranged between the metal mesh layer (22) and the end face of the submerging section; the rear plugging cover (3) is a circular sheet with an annular flanging, and the annular side edge of the rear plugging cover (3) is connected with the expansion section of the spray pipe through gluing. The multilayer structure has better sealing property and anti-vibration capability, thereby being suitable for complex combat service environment.
Description
Technical Field
The utility model belongs to the technical field of aerospace, concretely relates to solid rocket engine dive formula spray tube blanking cover structure.
Background
Nozzle clogs are one of the important components in solid rocket engines. The working principle is as follows: after the engine is normally ignited, the propellant charge in the combustion chamber is ignited to generate high-temperature and high-pressure gas, so that the pressure in the blanking cover is higher than an opening value, and the blanking cover is opened. The effect of blanking cover is that when lighting a fire, the pressure in the combustion chamber is built up faster through the blockage spray pipe, and the propellant grain should be opened in time after being lighted normally, so as to avoid influencing the normal work of the engine.
At present, a solid rocket engine submerged nozzle blanking cap is taken as a key technology and is mostly bonded to a nozzle submerged section or an expansion section in a bonding mode, and the method has the following problems: the blanking cover structure is easily affected by the change of the external pressure. When the plugging cover is bonded to the submerged section of the spray pipe and is launched in the barrel, the phenomenon that the external pressure of the engine is higher than the internal pressure easily occurs, so that the plugging cover bonded to the submerged section is reversely debonded; and for the blocking cover which is bonded on the expansion section and is launched at high altitude, the blocking cover arranged on the expansion section is easy to be debonded because the external pressure is lower than the internal pressure.
SUMMERY OF THE UTILITY MODEL
The utility model provides a solid rocket engine dive formula spray tube blanking cover structure solves current blanking cover structure and easily receives the influence of external pressure change and the problem that drops.
The utility model provides a solid rocket engine dive formula spray tube blanking cover structure, include: the front plugging cover combination body 2 and the rear plugging cover 3; the front blanking cover assembly 2 includes: a glass fiber layer 21, a metal mesh layer 22, and a sealing layer 23; wherein the content of the first and second substances,
the front blanking cover assembly 2 is connected with the end face of the submerged section of the submerged nozzle 1 in a bonding mode, and the submerged nozzle 1 is connected with the engine shell 4 through threads; the glass fiber layer 21 and the metal mesh layer 22 are adhered and connected, and the glass fiber layer 21 is arranged towards the head of the engine; the sealing layer 23 is arranged between the metal mesh layer 22 and the end face of the submerged section;
the rear plugging cover 3 is a circular sheet with an annular flanging, and the annular side edge of the rear plugging cover 3 is connected with the nozzle expansion section through gluing.
Alternatively, the glass fiber layer 21 is a circular thin sheet, and the thickness is determined according to the opening pressure of the plug cover.
Optionally, the metal mesh layer 22 is an aluminum metal mesh structure for supporting the glass fiber layer 21.
Optionally, the sealing layer 23 is a rubber O-ring, the metal mesh layer 22 has an annular flange, and the sealing layer 23 is sleeved on a side surface of the flange of the metal mesh layer 22.
Optionally, the rear cover 3 is a thin sheet of aluminum metal.
Optionally, the thickness range of the glass fiber layer 21 is 1-2mm, and the wire diameter range of the sealing layer 23 is 1.8-3.55 mm.
The utility model provides a solid rocket engine dive formula spray tube blanking cover structure, include: the front plugging cover combination body 2 and the rear plugging cover 3; the front blanking cover assembly 2 includes: a glass fiber layer 21, a metal mesh layer 22, and a sealing layer 23; the front blanking cover assembly 2 is connected with the end face of the submerged section of the submerged nozzle 1 in a bonding mode, and the submerged nozzle 1 is connected with the engine shell 4 through threads; the glass fiber layer 21 and the metal mesh layer 22 are adhered and connected, and the glass fiber layer 21 is arranged towards the head of the engine; the sealing layer 23 is arranged between the metal mesh layer 22 and the end face of the submerged section; the rear plugging cover 3 is a circular sheet with an annular flanging, and the annular side edge of the rear plugging cover 3 is connected with the nozzle expansion section through gluing. By adopting the double-plug-cover mode, when the engine is ignited, the front plug cover and the rear plug cover simultaneously act to prevent the non-designed state from being debonded and opened under the condition of relatively complex external environment pressure. And the front plugging cover assembly 2 consists of three parts, namely a glass fiber layer 21, a metal mesh layer 22 and a sealing layer 23, and has better sealing property and vibration resistance by adopting a multilayer structure, so that the front plugging cover assembly is suitable for complex combat use environments.
Drawings
FIG. 1 is a schematic view of a submerged nozzle blanking cap structure of a solid rocket engine;
FIG. 2 is a schematic sectional view of a front cover assembly;
FIG. 3 is a schematic view of a metal mesh structure of a front plugging cover assembly;
description of reference numerals:
1-a submerged nozzle; 2-front blocking cover assembly;
3, rear plugging cover; 4-engine housing;
21-a glass fiber layer; 22-a metal mesh layer;
and 23, sealing layer.
Detailed Description
The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
The utility model provides a solid rocket engine dive formula spray tube blanking cover structure, it includes preceding blanking cover assembly 2 and back blanking cover 3. The front blocking cover assembly 2 is composed of three parts, namely a glass fiber layer 21, a metal mesh layer 22 and a sealing layer 23. The front blanking cover assembly 2 is connected with the end face of the submerged section of the submerged nozzle 1 in a bonding mode, and the submerged nozzle 1 is connected with the engine shell 4 through threads.
The glass fiber layer 21 is made of glass fiber sheets, the thickness of which is determined by the design opening pressure of the blocking cover, and the function of the glass fiber layer is to quickly establish the pressure in the combustion chamber.
The metal mesh layer 22 is made of aluminum, is tightly attached to the glass fiber layer 21 for supporting, and is glued at the edge. The net-shaped aluminum wires are distributed in a crossed manner, and the net is flanged backwards in the circumferential direction.
The sealing layer 23 is made of rubber O-shaped sealing ring and is sleeved on the side face of the flanging of the metal mesh layer 22 to play a role in sealing.
The rear plugging cover 3 is made of an aluminum metal sheet, and the side end face of the rear plugging cover is connected with the expansion section of the spray pipe through gluing.
The utility model discloses a two blanking cover modes for when the engine was igniteed, under the more complicated condition of external environment pressure, the blanking cover simultaneous action prevented that non-design state from debonding and opening around. And the front plugging cover assembly 2 consists of three parts, namely a glass fiber layer 21, a metal mesh layer 22 and a sealing layer 23, and has better sealing property and vibration resistance by adopting a multilayer structure, so that the front plugging cover assembly is suitable for complex combat use environments.
The utility model discloses a work flow: when the engine is stored, the front blocking cover assembly 2 and the rear blocking cover 3 play a role in sealing together, and the propellant is prevented from being damped. When the engine is ignited, under the condition that the external environment pressure is relatively complex, the front plugging cover combination body 2 and the rear plugging cover 3 simultaneously act to prevent the debonding and the opening. After an ignition instruction of the solid rocket engine is sent, the igniter is ignited, so that the propellant grains are introduced, the pressure in the combustion chamber is rapidly increased, after the pressure in the combustion chamber is greater than the pressure born by the front plugging cover assembly 2, the joint of the front plugging cover assembly 2 and the submerged nozzle 1 is debonded, and the front plugging cover assembly 2 is opened. And then the back blocking cover 3 is opened by the gas in the same way, so that the solid rocket engine works normally to generate thrust.
Claims (6)
1. A solid rocket engine submerged nozzle blanking cover structure, characterized by comprising: a front plugging cover combination body (2) and a rear plugging cover (3); the front blanking cover assembly (2) comprises: a glass fiber layer (21), a metal mesh layer (22) and a sealing layer (23); wherein the content of the first and second substances,
the front plugging cover assembly (2) is connected with the end face of the submerged section of the submerged nozzle (1) in a bonding mode, and the submerged nozzle (1) is connected with the engine shell (4) through threads; the glass fiber layer (21) is connected with the metal mesh layer (22) in a sticking way, and the glass fiber layer (21) is arranged towards the head of the engine; the sealing layer (23) is arranged between the metal mesh layer (22) and the end face of the submerging section;
the rear plugging cover (3) is a circular sheet with an annular flanging, and the annular side edge of the rear plugging cover (3) is connected with the expansion section of the spray pipe through gluing.
2. Structure according to claim 1, characterized in that the glass fibre layer (21) is a circular sheet, the thickness being determined according to the opening pressure of the closure.
3. A structure as claimed in claim 1, characterized in that the metal mesh layer (22) is an aluminium metal mesh structure for supporting the glass fibre layer (21).
4. A structure according to claim 1, characterized in that the sealing layer (23) is a rubber O-ring, the metal mesh (22) has an annular bead, and the sealing layer (23) is fitted over the bead side of the metal mesh (22).
5. Structure according to claim 1, characterized in that the rear flap (3) is a foil of aluminium.
6. A structure according to claim 1, characterized in that the thickness of the glass fibre layer (21) is in the range of 1-2mm and the wire diameter of the sealing layer (23) is in the range of 1.8-3.55 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123025490.5U CN216477610U (en) | 2021-12-03 | 2021-12-03 | Solid rocket engine submerged nozzle blanking cover structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123025490.5U CN216477610U (en) | 2021-12-03 | 2021-12-03 | Solid rocket engine submerged nozzle blanking cover structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216477610U true CN216477610U (en) | 2022-05-10 |
Family
ID=81418865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123025490.5U Active CN216477610U (en) | 2021-12-03 | 2021-12-03 | Solid rocket engine submerged nozzle blanking cover structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216477610U (en) |
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2021
- 2021-12-03 CN CN202123025490.5U patent/CN216477610U/en active Active
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