CN117514526A - Jet pipe of solid rocket engine without jet - Google Patents
Jet pipe of solid rocket engine without jet Download PDFInfo
- Publication number
- CN117514526A CN117514526A CN202311364746.6A CN202311364746A CN117514526A CN 117514526 A CN117514526 A CN 117514526A CN 202311364746 A CN202311364746 A CN 202311364746A CN 117514526 A CN117514526 A CN 117514526A
- Authority
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- China
- Prior art keywords
- blanking cover
- section
- spray pipe
- jet
- insulation layer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007787 solid Substances 0.000 title claims abstract description 25
- 239000007921 spray Substances 0.000 claims abstract description 72
- 238000009413 insulation Methods 0.000 claims abstract description 38
- 230000007547 defect Effects 0.000 claims abstract description 37
- 238000009792 diffusion process Methods 0.000 claims abstract description 33
- 239000007789 gas Substances 0.000 claims abstract description 18
- 238000002485 combustion reaction Methods 0.000 claims abstract description 6
- 239000002737 fuel gas Substances 0.000 claims abstract description 5
- 230000017260 vegetative to reproductive phase transition of meristem Effects 0.000 claims abstract description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 235000007164 Oryza sativa Nutrition 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 238000007689 inspection Methods 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 235000009566 rice Nutrition 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 240000007594 Oryza sativa Species 0.000 claims 1
- 230000007423 decrease Effects 0.000 claims 1
- 230000000903 blocking effect Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 241000209094 Oryza Species 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/978—Closures for nozzles; Nozzles comprising ejectable or discardable elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a jet pipe of a solid rocket engine without a jet object, which comprises a jet pipe convergent section heat insulation layer, a jet pipe convergent section shell, a back lining, a throat liner, a front blanking cover, a rear blanking cover, a jet pipe divergent section heat insulation layer and a jet pipe divergent section shell; after the engine is ignited, high-temperature high-pressure gas is impacted onto the front blanking cover through the converging section of the spray pipe, and the film front blanking cover is instantaneously ablated into gas; the rear blanking cover can bear the ignition pressure of the engine, and after the preset ignition pressure is reached in the combustion chamber, high-temperature and high-pressure gas generated in the engine is flushed by the jet pipe convergent section and then is opened to the jet pipe outlet in a flowering shape along a preset defect groove to form fan-shaped petals; the fan-shaped petals are turned around the root part and attached to the heat insulation layer of the diffusion section of the spray pipe under the impact of high-temperature and high-pressure air flow, and then are ablated and gasified from the edge under the impact of high-temperature and high-pressure fuel gas.
Description
Technical Field
The invention relates to the field of solid rocket engines, in particular to a jet pipe of a solid rocket engine without a jet.
Background
The nozzle blocking cover is one of key structural parts of the civil solid rocket engine, and has the function of covering the nozzle during the storage of the solid rocket engine, and air does not enter the solid rocket engine from the outlet of the nozzle during the storage; and secondly, in the ignition of the solid rocket engine, the pressure climbing stage can bear certain ignition pressure, the blocking cover can effectively reduce ignition delay time and improve ignition performance. When the plug cover is opened, the acting force F of the fuel gas to the plug cover of the spray pipe under the opening pressure is applied 1 Is equal to the bonding acting force F between the nozzle blocking cover and the inner surface of the nozzle diffusion section 2 But the adhesive force F between the nozzle blocking cover and the inner surface of the nozzle diffusion section 2 Is smaller than the shearing force bearing capacity F of the blanking cover body 3 I.e. F 1 ≈F 2 <F 3 . The conventional plug of the solid rocket engine designed in the past is easy to generate larger fragments and the like to spray mist when the plug is opened due to materials, installation forms and damage forms.
Disclosure of Invention
The invention aims to provide a jet pipe of a solid rocket engine without jet matters, which solves the problem that jet matters are easy to generate after a blanking cover is opened in the prior art.
In order to realize the tasks, the invention adopts the following technical scheme:
a solid rocket engine jet pipe without jet comprises a jet convergence section heat insulation layer, a jet convergence section shell, a back lining, a throat liner, a front blanking cover, a rear blanking cover, a jet diffusion section heat insulation layer and a jet diffusion section shell, wherein all parts are rotary bodies and are coaxially arranged;
the heat insulation layer of the spray pipe convergent section is molded or glued into the shell of the spray pipe convergent section, the throat liner is embedded into the back lining, the front end face and the rear end face of the throat liner are flush, and the throat liner and the back liner are simultaneously arranged at the rear end of the heat insulation layer of the spray pipe convergent section and the inside of the shell of the spray pipe convergent section, and the four parts form the spray pipe convergent section;
the front end of the heat insulation layer of the spray pipe diffusion section is molded or glued into the shell of the spray pipe diffusion section, and the front end of the heat insulation layer of the spray pipe diffusion section and the shell of the spray pipe diffusion section form the spray pipe diffusion section;
the front end cover is arranged on the rear end surfaces of the throat liner and the back lining, the rear plug cover is arranged on the rear side of the front plug cover, the spray pipe diffusion section is fixedly arranged on the rear end of the spray pipe convergence section, and the rear plug cover is tightly pressed when the spray pipe diffusion section is fixedly arranged;
the front end cover is a flat disc, is tightly adhered to the rear end surfaces of the throat liner and the back lining, and can bear the airtight inspection pressure of the engine;
the outside of back blanking cover is round annular plate, and inside is the metal casing that spray tube outlet side swelled, and the back blanking cover adopts aerospace to use metal material to make, has evenly offered prefabricated defect groove around from the middle part of the inside swelled part of back blanking cover.
Further, after the engine is ignited, high-temperature and high-pressure gas generated in the engine is impacted onto the front blanking cover through the converging section of the spray pipe, and the front blanking cover made of the film is instantaneously ablated into gas; the rear blanking cover can bear the ignition pressure of the engine, and after the preset ignition pressure is reached in the combustion chamber, high-temperature and high-pressure gas generated in the engine is flushed by the jet pipe convergent section and then is opened to the jet pipe outlet in a flowering shape along a preset defect groove to form fan-shaped petals; the fan-shaped petals are turned around the root part and attached to the heat insulation layer of the diffusion section of the spray pipe under the impact of high-temperature and high-pressure air flow, and then are ablated and gasified from the edge under the impact of high-temperature and high-pressure fuel gas.
Further, the overall axial change trend of the inner diameter of the convergent section of the spray pipe is: the front end of the heat insulation layer of the spray pipe convergent section is of a horn-shaped structure and has the largest inner diameter; the inner diameter of the middle section of the heat insulation layer of the converging section of the spray pipe is consistent, and the inner diameter of the rear end is gradually reduced.
Further, the inside of the front end of the throat liner is in smooth transition with the inside of the rear end of the heat insulation layer of the converging section of the spray pipe, and the inner diameter of the throat liner is gradually reduced along the axis and then tends to be consistent.
Further, the inner diameter of the heat insulation layer of the nozzle diffusion section is gradually enlarged along the axial direction; the nozzle diffuser housing is connected inside the rear end of the nozzle convergent section housing.
Further, the front end cover has a thickness in the range of 0.1mm to 0.5 mm; the bulge angle of the rear blanking cover is controlled to be in the range of 15-45 degrees, wherein the bulge angle is the angle formed by the tangent line of the bulge part relative to the annular plate.
Furthermore, the inside of the rear blanking cover can not bulge, and a flat plate structure is adopted; when the configuration is adopted, the preset defect grooves are uniformly formed in the periphery of the rear blanking cover from the center of the rear blanking cover.
Further, the rear blanking cover can be made of aluminum, rubber and composite materials, aluminum powder is doped when the rubber and the composite materials are selected, and electromagnetic shielding effect of the blanking cover is improved.
Further, the number of preset defect grooves is not less than 3 and not more than 12, the preset defect grooves are required to be uniformly distributed, the 4 preset defect grooves are in a cross shape, and the 8 preset defect grooves are uniformly distributed in a rice shape.
Further, the wall thickness of the rear blanking cover is controlled within the range of 0.1mm to 0.5mm, the groove depth of the prefabricated defect groove is controlled within the range of 0.2 to 0.5 times of the wall thickness of the rear blanking cover, the cross section of the preset defect groove is rectangular or triangular, the maximum width of the preset defect groove is controlled to be not more than 5mm, and the groove length of the preset defect groove is controlled within the range of 0.75 to 1.0 times of the minimum inner diameter of the nozzle throat liner.
Compared with the prior art, the invention has the following technical characteristics:
1. the invention adopts a film material front blanking cover and a 'Jin' shaped metal shell back blanking cover double-layer blanking cover structure which bulges towards the outlet side of the spray pipe, the film material front blanking cover is tightly adhered to the convergent section of the spray pipe and has good air tightness, the air tightness in the combustion chamber of the engine can not be influenced when the spray pipe is disassembled and assembled, after the engine is ignited, high-temperature and high-pressure gas generated in the engine is impacted to the front blanking cover through the convergent section of the spray pipe, the film front blanking cover is instantaneously ablated into gas, and the jet matters which endanger the safety of a carrier can not be generated; when the spray pipe diffusion section is detached, the 'Jin' -shaped metal shell body back blanking cover bulged towards the spray pipe outlet side can be removed, the integral structure condition of the front blanking cover can be observed, after the spray pipe diffusion section is installed, the back blanking cover can bear the ignition pressure of an engine, when the engine ignites, after the preset ignition pressure is reached in a combustion chamber of the engine, high-temperature high-pressure gas generated in the engine flushes the back blanking cover through the spray pipe convergence section, each fan-shaped area of the back blanking cover is opened towards the spray pipe outlet in a 'flowering' shape along a preset defect groove, fan-shaped petals are formed, the fan-shaped petals are overturned around the root part and are attached to a heat insulation layer of the spray pipe diffusion section under the impact of high-temperature high-pressure gas, and then the fan-shaped petals are ablated and gasified from the edge until the part exposed in a gas channel is completely gasified under the impact of the high-temperature high-pressure gas.
2. In the process of opening the front blanking cover and the rear blanking cover of the spray pipe, the front blanking cover is gasified, the rear blanking cover is gradually gasified after being opened according to a preset defect groove, and the whole process can not generate a spray.
Drawings
FIG. 1 is a schematic view of a solid rocket engine nozzle without jet (with the cover unopened);
FIG. 2 is a schematic view of a nozzle convergent section;
FIG. 3 is a schematic view of a nozzle diffuser section;
FIG. 4 is a schematic view of the front closure in an unopened condition;
FIG. 5 is a schematic view of the back cover in an unopened state;
FIG. 6 is a schematic view of a solid rocket engine nozzle without jet (with the cover open);
FIG. 7 is a schematic view of the front closure in an open condition;
fig. 8 is a schematic view of the back cover in an open state.
The reference numerals in the figures illustrate: 1 spray pipe convergent section heat insulation layer, 2 spray pipe convergent section shell, 3 back lining, 4 throat lining, 5 front blanking cover, 6 back blanking cover, 7 spray pipe divergent section heat insulation layer, 8 spray pipe divergent section shell, 9 prefabricated defect groove.
Detailed Description
Referring to the drawings, the invention discloses a jet-free solid rocket engine jet pipe, which comprises a jet pipe convergent section heat insulation layer 1, a jet pipe convergent section shell 2, a back lining 3, a throat liner 4, a front blanking cover 5, a rear blanking cover 6, a jet pipe divergent section heat insulation layer 7 and a jet pipe divergent section shell 8, wherein all the parts are revolution bodies and are coaxial.
The heat insulation layer 1 of the spray pipe convergent section is molded or glued into the shell 2 of the spray pipe convergent section, the throat liner 4 is inlaid into the back lining 3, the front end surface and the rear end surface of the throat liner are flush, and the throat liner and the back lining are simultaneously arranged at the rear end of the heat insulation layer 1 of the spray pipe convergent section and the inside of the shell 2 of the spray pipe convergent section, so that the spray pipe convergent section is formed; the integral axial change trend of the inner diameter of the spray pipe convergent section is as follows: the front end of the heat insulation layer 1 of the spray pipe convergent section is of a horn-shaped structure and has the largest inner diameter; the inner diameter of the middle section of the spray pipe convergent section heat insulation layer 1 is consistent, and the inner diameter of the rear end is gradually reduced; the inside of the front end of the throat liner 4 is in smooth transition with the inside of the rear end of the nozzle convergent section heat insulation layer 1, and the inner diameter of the throat liner 4 is gradually reduced along the axis and then tends to be consistent.
The front end of the spray pipe diffusion section heat insulation layer 7 is molded or glued into the spray pipe diffusion section shell 8, and the spray pipe diffusion section is formed by the front end and the spray pipe diffusion section heat insulation layer; the inner diameter of the nozzle diffusion section heat insulation layer 7 is gradually enlarged along the axial direction; the nozzle divergent casing 8 is connected to the inside of the rear end of the nozzle convergent section casing 2.
The front end cover 5 is arranged on the rear end surfaces of the throat liner 4 and the back lining 3, the rear blanking cover 6 is arranged on the rear side of the front blanking cover 5, and the spray pipe diffusion section is arranged on the rear end of the spray pipe convergence section through threads; when screwing up the nozzle diffuser, the rear blanking cover 6 is pressed.
The front end cover 5 is a flat plate-shaped wafer and is made of a film with good barrier property and puncture resistance, and the thickness of the film is controlled to be in the range of 0.1mm to 0.5mm, for example, 0.3mm; the film is tightly adhered to the rear end surfaces of the throat liner 4 and the back lining 3, and can bear the airtight inspection pressure of the engine.
The outer part of the rear blanking cover 6 is a circle of annular plate, the inner part is a 'Jin' shaped metal shell with a bulged spray pipe outlet side, and the bulged angle of the rear blanking cover 6 is generally controlled to be in the range of 15-45 degrees, for example 30 degrees; wherein the bulge angle is the angle formed by the tangent to the bulge portion relative to the loop plate. The inner part 6 of the rear blanking cover can not bulge, and adopts a flat plate structure; the rear blanking cover 6 is made of a conventional aerospace metal material which is easy to machine and punch, aluminum, rubber, composite materials and the like can be selected, and proper aluminum powder can be doped when the rubber and the composite materials are selected, so that the electromagnetic shielding effect of the blanking cover is improved; the front end cover 5 can be made of rubber film; the prefabricated defect grooves 9 are uniformly formed from the middle part of the bulge part in the rear blanking cover 6 to the periphery, and the number of the preset defect grooves 9 is not less than 3 and not more than 12, for example, 8; the preset defect grooves are required to be uniformly distributed, namely 4 preset defect grooves are in a cross shape, and 8 preset defect grooves are uniformly distributed in a rice shape;
the wall thickness of the rear blanking cover 6 is controlled within the range of 0.1mm to 0.5mm, preferably 0.3mm; the depth of the preformed defect groove 9 is controlled to be in the range of 0.2 to 0.5 times the thickness of the wall thickness of the rear blanking cover 6, for example, 0.1mm; the wall thickness of the rear blanking cover 6 and the groove depth of the preset defect groove 9 are required to be adaptively adjusted according to the ignition pressure and the working pressure of the engine; the cross section of the preset defect groove 9 can be rectangular or triangular, and the maximum width of the preset defect groove 9 is controlled to be not more than 5mm, preferably 2mm; the groove length (the furthest distance between the two ends) of the defect groove 9 should be controlled to be in the range of 0.75 to 1.0 times, preferably 1 time, the minimum inner diameter of the nozzle throat insert 4.
After the engine is ignited, high-temperature and high-pressure gas generated in the engine is impacted onto the front blanking cover 5 through the converging section of the spray pipe, and the front blanking cover 5 made of a film is instantaneously ablated into gas, so that a jet object which is harmful to the safety of a carrier is not generated; the rear blanking cover 6 can bear the ignition pressure of the engine, when the engine ignites, after the preset ignition pressure is reached in the combustion chamber, high-temperature and high-pressure gas generated in the engine is flushed by the jet pipe convergent section, and the rear blanking cover 6 is opened to the jet pipe outlet in a flowering shape along the preset defect groove 9 to form sector petals; the fan-shaped petals are turned around the root part and are attached to the heat insulation layer 7 of the nozzle diffusion section under the impact of high-temperature and high-pressure air flow, and then are ablated and gasified from the edge under the impact of high-temperature and high-pressure fuel gas until the part exposed in the nozzle diffusion section is completely gasified.
The above embodiments are only for illustrating the technical solution of the present application, and are not limiting thereof; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced equally; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application, and are intended to be included in the scope of the present application.
Claims (10)
1. The jet pipe of the solid rocket engine without the jet matters is characterized by comprising a jet pipe convergence section heat insulation layer (1), a jet pipe convergence section shell (2), a back lining (3), a throat liner (4), a front blanking cover (5), a rear blanking cover (6), a jet pipe diffusion section heat insulation layer (7) and a jet pipe diffusion section shell (8), wherein all the parts are revolution bodies and are coaxially arranged;
the heat insulation layer (1) of the spray pipe convergent section is molded or glued into the shell (2) of the spray pipe convergent section, the throat liner (4) is inlaid into the back lining (3), the front end face and the rear end face of the throat liner are flush, and the throat liner and the back lining are simultaneously arranged at the rear end of the heat insulation layer (1) of the spray pipe convergent section and the inside of the shell (2) of the spray pipe convergent section, and the four parts form the spray pipe convergent section;
the front end of the spray pipe diffusion section heat insulation layer (7) is molded or glued into the spray pipe diffusion section shell (8), and the front end form the spray pipe diffusion section;
the front end cover (5) is arranged on the rear end surfaces of the throat liner (4) and the back lining (3), the rear blanking cover (6) is arranged on the rear side of the front blanking cover (5), the spray pipe diffusion section is fixedly arranged on the rear end of the spray pipe convergence section, and the rear blanking cover (6) is tightly pressed when the spray pipe diffusion section is fixedly arranged;
the front end cover (5) is a flat plate-shaped wafer, the front end cover (5) is tightly adhered to the rear end surfaces of the throat liner (4) and the back lining (3), and can bear the airtight inspection pressure of the engine;
the outside of back blanking cover (6) is round annular plate, and inside is the metal casing that spray tube outlet side swelled, and back blanking cover (6) adopts aerospace to use metal material to make, has evenly offered prefabricated defect groove (9) around from the middle part of back blanking cover (6) inside swelled part.
2. The jet pipe of the solid rocket engine without jet matters according to claim 1, wherein after the engine is ignited, high-temperature and high-pressure gas generated in the engine is impacted onto the front blanking cover (5) through a jet pipe converging section, and the front blanking cover (5) made of a film is instantaneously ablated into gas; the rear blanking cover (6) can bear the ignition pressure of the engine, when the engine ignites, after the preset ignition pressure is reached in the combustion chamber, high-temperature and high-pressure gas generated in the engine flushes the rear blanking cover (6) through the converging section of the spray pipe, so that the rear blanking cover (6) is opened towards the outlet of the spray pipe in a flowering shape along the preset defect groove (9) to form fan-shaped petals; the fan-shaped petals are turned around the root part and attached to the heat insulation layer (7) of the nozzle diffusion section under the impact of high-temperature and high-pressure airflow, and then are ablated and gasified from the edge under the impact of high-temperature and high-pressure fuel gas.
3. The solid rocket engine nozzle without jets of claim 1 wherein the overall axial trend of the inner diameter of the nozzle convergent section is: the front end of the spray pipe convergent section heat insulation layer (1) is of a horn-shaped structure and has the largest inner diameter; the inner diameter of the middle section of the spray pipe convergent section heat insulation layer (1) is consistent, and the inner diameter of the rear end is gradually reduced.
4. The solid rocket engine nozzle without jet according to claim 1, wherein the inside of the front end of the throat liner (4) is in smooth transition with the inside of the rear end of the nozzle convergent section heat insulation layer (1), and the inside diameter of the throat liner (4) gradually decreases along the axis and then tends to be uniform.
5. The solid rocket engine nozzle without jet according to claim 1, wherein the inner diameter of the nozzle diffuser insulation layer (7) is gradually enlarged along the axial direction; the nozzle diffuser housing (8) is connected to the rear end interior of the nozzle convergent section housing (2).
6. The solid rocket engine nozzle without jet according to claim 1, characterized in that the front end cap (5) has a thickness in the range of 0.1mm to 0.5 mm; the bulge angle of the rear blanking cover (6) is controlled to be in the range of 15-45 degrees, wherein the bulge angle is the angle formed by the tangent line of the bulge part relative to the annular plate.
7. The solid rocket engine nozzle without jet according to claim 1, wherein the rear cover (6) can be of flat plate structure without bulge; when the configuration is adopted, the preset defect grooves (9) are uniformly formed in the periphery of the rear blanking cover (6) from the center of the rear blanking cover (6).
8. The solid rocket engine nozzle without the ejectors according to claim 1, wherein the rear blanking cover (6) can be made of aluminum, rubber or composite material, aluminum powder is doped when the rubber or the composite material is selected, and the electromagnetic shielding effect of the blanking cover is improved.
9. The solid rocket engine nozzle without the ejectors according to claim 1, wherein the number of the preset defect grooves (9) is not less than 3 and not more than 12, the preset defect grooves (9) are required to be uniformly distributed, 4 preset defect grooves (9) are in a cross shape, and 8 preset defect grooves (9) are uniformly distributed in a rice shape.
10. The jet pipe of the solid rocket engine without jet matters according to claim 1, wherein the wall thickness of the rear blanking cover (6) is controlled to be in the range of 0.1mm to 0.5mm, the groove depth of the pre-defect groove (9) is controlled to be in the range of 0.2 to 0.5 times the wall thickness of the rear blanking cover (6), the cross section of the pre-defect groove (9) is rectangular or triangular, the maximum width of the pre-defect groove (9) is controlled to be not more than 5mm, and the groove length of the pre-defect groove (9) is controlled to be in the range of 0.75 to 1.0 times the minimum inner diameter of the jet pipe throat lining (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311364746.6A CN117514526A (en) | 2023-10-20 | 2023-10-20 | Jet pipe of solid rocket engine without jet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311364746.6A CN117514526A (en) | 2023-10-20 | 2023-10-20 | Jet pipe of solid rocket engine without jet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117514526A true CN117514526A (en) | 2024-02-06 |
Family
ID=89765307
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311364746.6A Pending CN117514526A (en) | 2023-10-20 | 2023-10-20 | Jet pipe of solid rocket engine without jet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117514526A (en) |
-
2023
- 2023-10-20 CN CN202311364746.6A patent/CN117514526A/en active Pending
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