CN114876673A - Low-cost ablation-resistant embedded spray pipe and machining method thereof - Google Patents
Low-cost ablation-resistant embedded spray pipe and machining method thereof Download PDFInfo
- Publication number
- CN114876673A CN114876673A CN202210378130.3A CN202210378130A CN114876673A CN 114876673 A CN114876673 A CN 114876673A CN 202210378130 A CN202210378130 A CN 202210378130A CN 114876673 A CN114876673 A CN 114876673A
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- section
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- convergence
- resistant layer
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- 238000002679 ablation Methods 0.000 title claims abstract description 106
- 239000007921 spray Substances 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims description 7
- 238000003754 machining Methods 0.000 title description 2
- 239000010410 layer Substances 0.000 claims abstract description 84
- 239000011241 protective layer Substances 0.000 claims abstract description 35
- 230000000903 blocking effect Effects 0.000 claims abstract description 13
- 239000003822 epoxy resin Substances 0.000 claims description 15
- 239000003292 glue Substances 0.000 claims description 15
- 229920000647 polyepoxide Polymers 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 11
- 229920002379 silicone rubber Polymers 0.000 claims description 7
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000005488 sandblasting Methods 0.000 claims description 3
- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 239000004945 silicone rubber Substances 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims 1
- 229910052802 copper Inorganic materials 0.000 claims 1
- 239000010949 copper Substances 0.000 claims 1
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims 1
- 229910052721 tungsten Inorganic materials 0.000 claims 1
- 239000010937 tungsten Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 239000007769 metal material Substances 0.000 abstract description 3
- 238000002485 combustion reaction Methods 0.000 description 7
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 239000002737 fuel gas Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000003672 processing method Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- SBYXRAKIOMOBFF-UHFFFAOYSA-N copper tungsten Chemical compound [Cu].[W] SBYXRAKIOMOBFF-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- -1 phenolic aldehyde Chemical class 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- 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)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a low-cost ablation-resistant embedded spray pipe which is provided with an internal spray pipe channel and comprises a rotary shell, wherein the shell is provided with a convergence section and an expansion section, the inner wall of the expansion section is provided with an expansion protective layer, one end of the expansion section, which is far away from an opening, extends to form the convergence section, the outer wall of the joint of the convergence section and the expansion section is also provided with a convergence fixing shell 15, and the inner wall of the convergence section is provided with a back lining; a convergence protective layer is arranged between one side of the convergence fixed shell 15 close to the convergence section and the outer wall of the expansion section, a first ablation-resistant layer and a second ablation-resistant layer are sequentially arranged on the back lining from outside to inside, a blocking cover is arranged between the first ablation-resistant layer and the second ablation-resistant layer, and the blocking cover completely blocks the inner nozzle channel; a method of making a low cost ablation resistant insert nozzle is also provided. The invention reduces the consumption of metal materials, reduces the weight compared with the traditional mode, improves the ablation resistance of the submerged nozzle, simplifies the processing technology difficulty of the ablation layer and saves the cost of the nozzle.
Description
Technical Field
The invention relates to the field of rocket nozzles, in particular to a low-cost ablation-resistant embedded nozzle and a processing method thereof.
Background
The jet pipe is a device for energy conversion of the solid rocket engine, and has the main functions of controlling the mass flow rate of fuel gas through the throat area of the jet pipe, keeping the pressure of the fuel gas in a combustion chamber at a preset level, ensuring normal combustion of charged fuel, expanding and accelerating combustion products of propellant, fully converting the heat energy of the propellant into the kinetic energy of the fuel gas, and obtaining reaction thrust through high-speed ejection of the fuel gas. The cost of the jet pipe accounts for 22% -26% of the total cost of the engine, the raw materials account for 13% -14%, and the working hours account for 9% -12%. Obviously, the design structure of the spray pipe is optimized, and the method has important significance for reducing the cost of the spray pipe.
In the existing submerged nozzle, a part of the nozzle is embedded into a combustion chamber, a convergent section and a throat liner are in direct contact with combustion gas in the combustion chamber, the gas can scour the convergent section and the throat liner of the nozzle, and a large amount of ablation is generated. When the jet pipe is designed, the metal throat liner is mostly adopted to reduce the ablation rate of the jet pipe (the ablation rate of the metal throat liner is lower), the area consistency of the throat part of the jet pipe is kept, and the stable thrust of the solid rocket engine is ensured, but the weight of the jet pipe is greatly increased by adopting the metal throat liner, and the jet pipe is expensive.
In the patent of 'a low ablation throat insert of solid rocket', the throat insert is made of non-metallic materials, a plurality of grooves are arranged in an area easy to ablate, a metal heat dissipation ring is arranged, and the high-temperature phase change of metal is utilized to absorb heat to protect the throat insert main body and reduce the ablation rate of the throat insert main body. Although the method of the patent reduces the ablation rate of the jet pipe, the requirement on the processing technology is higher, and the cost of the jet pipe is increased.
Disclosure of Invention
In order to overcome the defect of high cost of the spray pipe in the prior art, the invention provides the low-cost ablation-resistant embedded spray pipe and the processing method thereof, and the manufacture is simple and the cost is low.
The invention provides a low-cost ablation-resistant embedded spray pipe which is provided with an internal spray pipe channel and comprises a rotary shell, wherein the shell comprises a convergent section and an expansion section, the expansion section forms a horn mouth shape with an opening gradually enlarged, an expansion protective layer is arranged on the inner wall of the expansion section, one end, far away from the opening, of the expansion section extends to form the convergent section, a limiting boss is arranged at one end, close to the convergent section, of the expansion section, a convergent fixing shell is further arranged on the outer wall of the joint of the convergent section and the expansion section, and a back lining is arranged on the inner wall of the convergent section; a convergence protective layer is arranged between one side of the convergence fixed shell close to the convergence section and the outer wall of the expansion section, and the convergence protective layer and the backing lining both exceed the edge of the convergence section and are connected with each other; the anti-ablation nozzle comprises a backing and is characterized in that a first ablation-resistant layer and a second ablation-resistant layer are sequentially arranged on the backing from outside to inside, the first ablation-resistant layer, the second ablation-resistant layer and a convergence protection layer form an inner nozzle channel, a blocking cover is arranged between the first ablation-resistant layer and the second ablation-resistant layer, and the blocking cover completely blocks the inner nozzle channel.
In another aspect of the present invention, a method for processing an ablation-resistant insert nozzle at low cost is provided, which comprises the following steps:
s1, processing the shell, forming the first ablation resistant layer, the second ablation resistant layer, the blocking cover, the back lining, the convergence protective layer and the expansion protective layer, and performing sand blasting treatment on the inner surface of the shell;
s2, adhering the second ablation-resistant layer and the backing to form an adhesive assembly by using epoxy resin glue, and adhering the adhesive assembly to the inner wall of the shell convergence section by using epoxy resin glue;
s3, adhering the first ablation-resistant layer with a backing and a convergence protective layer by using epoxy resin glue, and smearing D03(L) silicon rubber at the gap between the first ablation-resistant layer and the convergence protective layer and between the first ablation-resistant layer and the second ablation-resistant layer;
s4, installing the sealing ring in the sealing groove, bonding the expansion protection layer on the inner wall of the expansion end by adopting epoxy resin glue, and smearing D03(L) silicon rubber on the gap between the expansion section and the second ablation-resistant layer; forming a to-be-processed assembly;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner profile;
s6, mounting screws;
and S7, adhering the plug cover to the interior of the spray pipe by adopting epoxy resin glue.
The invention has the advantages that the ablation resistance of the ablation resistant layer is utilized, the first ablation resistant layer and the second ablation resistant layer are adopted to ensure the smooth runner profile at the front part of the spray pipe, the stress is more concentrated and positioned on the second ablation resistant layer, the second ablation layer is positioned in the shell and is provided with the limiting boss, the stress can be better transmitted to the shell, and the phenomena of flying-out of parts and the like are not easy to generate. Meanwhile, compared with the traditional design structure adopting the metal throat insert, the consumption of metal materials is reduced, the weight is reduced compared with the traditional mode, the ablation resistance of the submerged nozzle is improved, the processing technology difficulty of an ablation layer is simplified, and the cost of the nozzle is saved.
Drawings
FIG. 1 is a schematic view of a low cost ablation resistant insert nozzle in accordance with an embodiment of the present invention;
the reference numbers are as follows:
1. a rotary housing; 2. a convergence section; 3. an expansion section; 4. expanding the protective layer; 5. a limiting boss; 6. a seal ring; 7. a convergence protection layer; 8. a backing; 9. a first ablation-resistant layer; 10. a second ablation-resistant layer; 11. an internal nozzle passage; 12. blocking the cover; 13. a screw; 14. connecting holes of bolts; 15. the housing is convergent fixed.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The following further describes embodiments of the present invention with reference to the drawings.
As shown in fig. 1, the low-cost ablation-resistant embedded nozzle is provided with an internal nozzle channel 11, and comprises a rotary shell 1, wherein the rotary shell 1 comprises a convergent section 2 and an expansion section 3, the expansion section 3 forms a bell mouth shape with an opening gradually enlarged, an expansion protective layer 4 is arranged on the inner wall of the expansion section 3, one end of the expansion section 3, which is far away from the opening, extends to form the convergent section 2, one end of the expansion section 3, which is close to the convergent section 2, is provided with a limiting boss 5, the outer wall of the joint of the convergent section 2 and the expansion section 3 further comprises a convergent fixing shell 15, and the convergent fixing shell 15 is also a part of the rotary shell 1; a back lining 8 is arranged on the inner wall of the convergent section 2, and one end of the back lining 8 is abutted against the limiting boss 5; a convergence protective layer 7 is arranged between one side of the convergence fixed shell 15 close to the convergence section 2 and the outer wall of the expansion section 3, and the convergence protective layer 7 and the backing 8 both exceed the edge of the convergence section 2 and are connected with each other, so that the convergence section 2 is completely coated; the first ablation resistant layer 9 and the second ablation resistant layer 10 are sequentially arranged on the backing 8 from outside to inside, the first ablation resistant layer 9, the second ablation resistant layer 10 and the expansion protection layer 4 form an inner nozzle channel 11, a blocking cover 12 is arranged between the first ablation resistant layer 9 and the second ablation resistant layer 10, and the blocking cover 12 completely blocks the inner nozzle channel 11.
When the engine works, the first ablation resistant layer 9 and the second ablation resistant layer 10 resist the scouring of high-temperature gas, and the consistency of the throat area of the molded surface of the spray pipe is kept; the convergence section 2, the back lining 8 and the expansion section 3 play a role in heat insulation and heat insulation for the rotary shell 1, so that the strength of the rotary shell 1 is ensured, high-temperature gas of the engine can be converted into low-temperature high-speed airflow, and larger thrust is generated.
In a preferred embodiment of the present invention, the convergent securing means 15 is inclined toward the divergent section 3, so that the force of the second ablation-resistant layer 10 does not vertically act on the convergent securing means 15, thereby increasing the service life, and the convergent securing means 15 is provided at the outer side thereof with a bolt coupling hole 14, typically a flange hole, for coupling with a rocket motor.
In a preferred embodiment of the invention, the first ablation-resistant layer 9 is arc-shaped, wraps the end part of the convergence section 2, extends outwards to the convergence protective layer 7, is respectively connected with the back lining 8 and the convergence protective layer 7, and is used for resisting ablation when fuel gas passes through a combustion throat diameter, keeping the area consistency of the throat diameter and ensuring the stability of the thrust of an engine; a second ablation-resistant layer 10 is arranged on the inner wall of the backing 8 positioned in the convergence section 2, the second ablation-resistant layer 10 is bonded with the first ablation-resistant layer 9, the backing 8 and the convergence protective layer 7, and the first ablation-resistant layer 9 and the second ablation-resistant layer 10 are made of tungsten copper infiltrated materials generally and used for resisting ablation of a combustion chamber on the rotary shell 1 of the nozzle at high temperature and high pressure; the blanking cover 12 is located at the end of the convergent section 2 away from the divergent section 3, and is generally made of aluminum alloy, and is used for sealing and preventing moisture, quickly establishing ignition pressure and shortening ignition delay time to improve ignition reliability.
In a preferred embodiment of the present invention, the second ablation resistant layer 10 extends toward the expansion segment 3 and partially covers the expansion segment 3, forming a smooth transition between the second ablation resistant layer 10 and the expansion protection layer 4.
In a preferred embodiment of the invention, the rotary shell 1 adopts 30CrMnSiA, and the inner wall is respectively provided with a convergence protective layer 7, a back lining 8 and an expansion protective layer 4 for ensuring the strength of the spray pipe and preventing the high-pressure gas from damaging the spray pipe; the back lining 8, the convergence protective layer 7 and the expansion protective layer 4 are made of carbon fiber/phenolic aldehyde mould pressing materials and are used for protecting the rotary shell 1, preventing high temperature from being conducted to the rotary shell 1 and ensuring that the rotary shell 1 fails in high-temperature strength.
In a preferred embodiment of the present invention, the expansion section 3 is provided with a screw 13 for fixing the expansion fixing layer, and a pin may be used to insert the expansion section 3 through the rotary casing 1 for reinforcing the connection between the expansion section 3 and the rotary casing 1.
In a preferred embodiment of the present invention, a sealing groove is disposed on one side of the limiting boss 5 close to the expanding section 3, and a sealing ring 6 is disposed in the sealing groove.
In a preferred embodiment of the present invention, all the joint gaps on the inner nozzle passage 11 are coated with D03(L) silicone rubber, specifically including the joints between the first ablation-resistant layer 9 and the second ablation-resistant layer 10, and the joints between the second ablation-resistant layer 10 and the expansion protection layer 4, to improve the ablation resistance.
In a preferred embodiment of the invention, the inner wall of the inner nozzle channel 11 is a smoothly transitioning flow path profile to reduce the internal resistance of the nozzle.
In a preferred embodiment of the present invention, there is also provided a method for manufacturing a low-cost ablation-resistant insert nozzle, including the steps of:
s1, processing the rotary shell 1, the first ablation resistant layer 9, the second ablation resistant layer 10, the blocking cover 12, the back lining 8, the convergence protective layer 7 and the expansion protective layer 4, molding, and performing sand blasting treatment on the inner surface of the rotary shell 1;
s2, bonding the second ablation-resistant layer 10 and the backing 8 into a bonding assembly by using epoxy resin glue, and then bonding the bonding assembly to the inner wall of the convergence section 2 by using the epoxy resin glue;
s3, adhering the first ablation-resistant layer 9 with a backing 8 and a convergence protective layer 7 by using epoxy resin glue, and smearing D03(L) silicon rubber at the gap between the first ablation-resistant layer 9 and the convergence protective layer 7 and between the first ablation-resistant layer 9 and the second ablation-resistant layer 10;
s4, installing the sealing ring 6 in the sealing groove, bonding the expansion protection layer 4 on the inner wall of the expansion end by adopting epoxy resin glue, and smearing D03(L) silicon rubber on the gap between the expansion section 3 and the second ablation-resistant layer 10; forming a to-be-processed assembly;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner profile;
s6, mounting screws 13;
and S7, adhering the plug cover 12 to the interior of the spray pipe by using epoxy resin glue.
And connecting the assembled and bonded spray pipe to an engine by adopting a bolt.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A low-cost ablation-resistant embedded spray pipe is provided with an internal spray pipe channel and is characterized by comprising a rotary shell, wherein the rotary shell comprises a convergent section and an expansion section, the expansion section is in a horn mouth shape with a gradually enlarged opening, an expansion protective layer is arranged on the inner wall of the expansion section, one end, far away from the opening, of the expansion section extends to form the convergent section, a limiting boss is arranged at one end, close to the convergent section, of the expansion section, a convergent fixing shell is further arranged on the outer wall of the joint of the convergent section and the expansion section, and a back lining is arranged on the inner wall of the convergent section; a convergence protective layer is arranged between one side of the convergence fixed shell close to the convergence section and the outer wall of the expansion section, and the convergence protective layer and the backing lining both exceed the edge of the convergence section and are connected with each other; the inner nozzle comprises a backing, and is characterized in that a first ablation-resistant layer and a second ablation-resistant layer are sequentially arranged on the backing from outside to inside, the first ablation-resistant layer, the second ablation-resistant layer and a convergence protection layer form an inner nozzle channel, a blocking cover is arranged between the first ablation-resistant layer and the second ablation-resistant layer, and the blocking cover completely blocks the inner nozzle channel.
2. The low-cost ablation-resistant pilot nozzle of claim 1, wherein the convergent securing means is inclined toward the divergent section and has bolt-fastening holes formed on the outside.
3. The low-cost ablation-resistant insert nozzle of claim 1, wherein the first ablation-resistant layer is wrapped around the end of the convergent section in a circular arc shape and extends outward to the convergent protective layer; and a second ablation-resistant layer is arranged on the inner wall of the back lining positioned in the convergent section, and the blocking cover is positioned at the end part of the convergent section far away from the divergent section.
4. The low cost, ablation-resistant in-line nozzle of claim 3, wherein said second ablation-resistant layer extends toward and partially covers said expanded section, said second ablation-resistant layer forming a smooth transition with said expanded protective layer.
5. The low cost, ablation-resistant insert nozzle of claim 1, wherein the housing comprises 30CrMnSiA, the backing, the converging protective layer, and the diverging protective layer comprise carbon fiber/phenolic molded material, the first and second ablation resistant layers comprise tungsten impregnated copper material, and the cap comprises aluminum alloy.
6. The low-cost ablation-resistant insert nozzle of claim 1, wherein the expanded section is provided with a screw for fixing the expanded fixing layer.
7. The low-cost ablation-resistant embedded nozzle according to claim 1, wherein a sealing groove is formed in one side, close to the expansion section, of the limiting boss, and a sealing ring is arranged in the sealing groove.
8. The low cost, ablation-resistant in-line nozzle of claim 1 wherein all joint gaps on the inner nozzle passageway are coated with D03(L) silicone rubber.
9. The low cost, ablation-resistant insert nozzle of claim 1 wherein the inner nozzle channel wall is a smooth-transitioning flow path profile.
10. The method of claim 1, comprising the steps of:
s1, processing the shell, forming the first ablation resistant layer, the second ablation resistant layer, the blocking cover, the back lining, the convergence protective layer and the expansion protective layer, and performing sand blasting treatment on the inner surface of the shell;
s2, adhering the second ablation-resistant layer and the backing to form an adhesive assembly by using epoxy resin glue, and adhering the adhesive assembly to the inner wall of the shell convergence section by using epoxy resin glue;
s3, adhering the first ablation-resistant layer with the backing and the convergence protective layer by using epoxy resin glue, and smearing silicon rubber on gaps among the first ablation-resistant layer, the convergence protective layer and the first ablation-resistant layer and the second ablation-resistant layer;
s4, adhering the expansion protection layer to the inner wall of the expansion end by using epoxy resin glue to form a to-be-processed assembly;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner profile;
and S6, adhering the plug cover to the interior of the spray pipe by adopting epoxy resin glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210378130.3A CN114876673B (en) | 2022-04-12 | 2022-04-12 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210378130.3A CN114876673B (en) | 2022-04-12 | 2022-04-12 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114876673A true CN114876673A (en) | 2022-08-09 |
| CN114876673B CN114876673B (en) | 2024-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210378130.3A Active CN114876673B (en) | 2022-04-12 | 2022-04-12 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN114876673B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115573829A (en) * | 2022-10-28 | 2023-01-06 | 西安长峰机电研究所 | Ablation-resistant structure of expansion section outlet |
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|---|---|---|---|---|
| US4384454A (en) * | 1979-11-30 | 1983-05-24 | Messerschmitt-Bolkow-Blohm | Thrust nozzle for rocket engine with ablating lining |
| US4477024A (en) * | 1983-04-05 | 1984-10-16 | The United States Of America As Represented By The Secretary Of The Air Force | Carbon/carbon rocket motor exit cone reinforcement |
| CN106762230A (en) * | 2016-11-22 | 2017-05-31 | 湖北三江航天江北机械工程有限公司 | The non-insert nozzle of solid propellant rocket and manufacture method |
| CN106979095A (en) * | 2017-05-08 | 2017-07-25 | 湖北航天技术研究院总体设计所 | The integrated jet pipe and its manufacture method of a kind of global formation |
| CN109139301A (en) * | 2018-09-07 | 2019-01-04 | 西安航天化学动力厂 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN110594043A (en) * | 2019-10-12 | 2019-12-20 | 内蒙动力机械研究所 | Gradual change type gap structure beneficial to swinging of full-axis swinging spray pipe |
| CN210714882U (en) * | 2019-08-16 | 2020-06-09 | 重庆零壹空间科技集团有限公司 | Rocket engine jet pipe |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
-
2022
- 2022-04-12 CN CN202210378130.3A patent/CN114876673B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4384454A (en) * | 1979-11-30 | 1983-05-24 | Messerschmitt-Bolkow-Blohm | Thrust nozzle for rocket engine with ablating lining |
| US4477024A (en) * | 1983-04-05 | 1984-10-16 | The United States Of America As Represented By The Secretary Of The Air Force | Carbon/carbon rocket motor exit cone reinforcement |
| CN106762230A (en) * | 2016-11-22 | 2017-05-31 | 湖北三江航天江北机械工程有限公司 | The non-insert nozzle of solid propellant rocket and manufacture method |
| CN106979095A (en) * | 2017-05-08 | 2017-07-25 | 湖北航天技术研究院总体设计所 | The integrated jet pipe and its manufacture method of a kind of global formation |
| CN109139301A (en) * | 2018-09-07 | 2019-01-04 | 西安航天化学动力厂 | A kind of integrated solid rocket motor nozzle of thermal protection structure |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN210714882U (en) * | 2019-08-16 | 2020-06-09 | 重庆零壹空间科技集团有限公司 | Rocket engine jet pipe |
| CN110594043A (en) * | 2019-10-12 | 2019-12-20 | 内蒙动力机械研究所 | Gradual change type gap structure beneficial to swinging of full-axis swinging spray pipe |
| CN114198223A (en) * | 2021-11-29 | 2022-03-18 | 湖北航泰科技有限公司 | One-step curing molding full-composite engine spray pipe |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115573829A (en) * | 2022-10-28 | 2023-01-06 | 西安长峰机电研究所 | Ablation-resistant structure of expansion section outlet |
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| Publication number | Publication date |
|---|---|
| CN114876673B (en) | 2024-03-29 |
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