CN114876673B - Low-cost ablation-resistant embedded spray pipe and processing method thereof - Google Patents
Low-cost ablation-resistant embedded spray pipe and processing method thereof Download PDFInfo
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- CN114876673B CN114876673B CN202210378130.3A CN202210378130A CN114876673B CN 114876673 B CN114876673 B CN 114876673B CN 202210378130 A CN202210378130 A CN 202210378130A CN 114876673 B CN114876673 B CN 114876673B
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- ablation
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- layer
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- 238000002679 ablation Methods 0.000 title claims abstract description 104
- 239000007921 spray Substances 0.000 title claims abstract description 29
- 238000003672 processing method Methods 0.000 title abstract description 5
- 239000010410 layer Substances 0.000 claims abstract description 91
- 239000011241 protective layer Substances 0.000 claims abstract description 26
- 230000000903 blocking effect Effects 0.000 claims abstract description 10
- 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
- 230000007704 transition Effects 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 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
- 239000000463 material Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 239000012778 molding material Substances 0.000 claims description 2
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 2
- 239000004945 silicone rubber Substances 0.000 claims description 2
- 239000011248 coating agent Substances 0.000 claims 1
- 238000000576 coating method Methods 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 3
- 239000007769 metal material Substances 0.000 abstract description 3
- 239000002737 fuel gas Substances 0.000 description 9
- 238000002485 combustion reaction Methods 0.000 description 7
- 229910052751 metal Inorganic materials 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007789 gas 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
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 239000000843 powder Substances 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
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 convergent section and an expansion section, an expansion protection layer is arranged on the inner wall of the expansion section, one end of the expansion section, which is far away from an opening, extends to form the convergent section, a convergent fixed shell is further arranged on the outer wall of the joint of the convergent section and the expansion section, and a backing is arranged on the inner wall of the convergent section; a convergence protective layer is arranged between one side of the convergence fixed shell, which is 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 channel of the internal spray pipe; also provides a processing method of the low-cost ablation-resistant embedded spray pipe. 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 an 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 converting the energy of the solid rocket engine, and has the main functions of controlling the mass flow rate of the 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 the normal combustion of the powder charge, accelerating the expansion of the combustion products of the propellant, fully converting the heat energy of the propellant into the kinetic energy of the fuel gas, and obtaining the reaction thrust through the high-speed ejection of the fuel gas. The cost of the spray pipe is about 22% -26% of the total cost of the engine, wherein the raw materials are 13% -14%, and the working time is 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.
The existing submerged nozzle is characterized in that a part of the nozzle is embedded into a combustion chamber, a convergent section and a throat liner are directly contacted with combustion chamber fuel gas, and the fuel gas can wash the convergent section and the throat liner of the nozzle and generate a large amount of ablation. When designing the jet pipe, the metal throat liner is adopted to reduce the ablation rate of the jet pipe (the metal throat liner has lower ablation rate), the consistency of the throat area of the jet pipe is maintained, the stable thrust of the solid rocket engine is ensured, but the metal throat liner greatly increases the weight of the jet pipe and the price is high.
In the patent 'a solid rocket low ablation throat liner', the throat liner is made of non-metal materials, a plurality of grooves are formed in an easily-eroded area, a metal heat dissipation ring is arranged, and heat is absorbed by utilizing high-temperature phase transition of metal to protect the throat liner body and reduce the ablation rate of the throat liner body. Although the method reduces the ablation rate of the spray pipe, the method has higher requirements on the processing technology, and the cost of the spray pipe is increased.
Disclosure of Invention
In order to overcome the defect of high spray pipe cost in the prior art, the invention provides the low-cost ablation-resistant embedded spray pipe and the processing method thereof, which are simple in manufacture and low in cost.
According to a first aspect of the invention, a low-cost ablation-resistant embedded nozzle is provided, and the low-cost ablation-resistant embedded nozzle is provided with an internal nozzle channel, and comprises a rotary shell, wherein the shell comprises a convergent section and an expansion section, the expansion section forms a bell mouth shape with an opening gradually enlarged, an expansion protection layer is arranged on the inner wall of the expansion section, one end of the expansion section far away from the opening extends to form the convergent section, a limit boss is arranged on one end of the expansion section close to the convergent section, a convergent fixed shell is further arranged on the outer wall of the joint of the convergent section and the expansion section, and a backing is arranged on the inner wall of the convergent section; a convergence protection layer is arranged between one side of the convergence fixing shell, which is close to the convergence section, and the outer wall of the expansion section, and the convergence protection layer and the backing are both beyond the edge of the convergence section and are connected with each other; the backing is provided with a first ablation resistant layer and a second ablation resistant layer from outside to inside in sequence, the first ablation resistant layer, the second ablation resistant layer and the convergence protective layer form an internal spray pipe 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 internal spray pipe channel.
In another aspect of the invention, a method for processing a low-cost ablation-resistant embedded nozzle is provided, comprising the following steps:
s1, processing a shell, forming a first ablation-resistant layer, a second ablation-resistant layer, a blanking cover, a backing, a convergence protective layer and an expansion protective layer, and carrying out sand blasting treatment on the inner surface of the shell;
s2, bonding the second ablation resistant layer and the back lining by using epoxy resin glue to form a bonding assembly, and bonding the bonding assembly to the inner wall of the converging section of the shell by using epoxy resin glue;
s3, bonding the first ablation-resistant layer with the backing and the convergence protective layer by using epoxy resin glue, and smearing D03 (L) silicon rubber at gaps among the first ablation-resistant layer, the convergence protective layer and the first ablation-resistant layer and the second ablation-resistant layer;
s4, mounting the sealing ring to the sealing groove, bonding the expansion protective layer on the inner wall of the expansion end by adopting epoxy resin glue, and smearing D03 (L) silicon rubber at the gap between the expansion section and the second ablation resistant layer; forming an assembly to be processed;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner surface;
s6, installing a screw;
and S7, adhering the blocking cover to the inside of the spray pipe by using epoxy resin glue.
The invention has the advantages that the ablation-resistant characteristic 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 concentrated 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 well transmitted to the shell, and the phenomena of part flying and the like are not easy to occur. Meanwhile, compared with the traditional design structure adopting the metal throat liner, the metal throat liner 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 an ablation layer, and saves the cost of the nozzle.
Drawings
FIG. 1 is a schematic diagram of a low cost ablation resistant embedded nozzle in accordance with an embodiment of the present invention;
the reference numerals are as follows:
1. a rotary housing; 2. a convergence section; 3. an expansion section; 4. expanding the protective layer; 5. a limit 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. a blanking cover; 13. a screw; 14. a bolt connection hole; 15. the housing is fixed in a converging manner.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The following describes the embodiments of the present invention further with reference to the drawings.
As shown in fig. 1, a 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 protection layer 4 is arranged on the inner wall of the expansion section 3, one end of the expansion section 3 far away from the opening extends to form the convergent section 2, a limit boss 5 is arranged on one end of the expansion section 3 close to the convergent section 2, the outer wall of the joint of the convergent section 2 and the expansion section 3 also comprises a convergent fixed shell 15, and the convergent fixed shell 15 is also a part of the rotary shell 1; a backing 8 is arranged on the inner wall of the convergence section 2, and one end of the backing 8 is abutted against the limit boss 5; a convergence protection layer 7 is arranged between one side of the convergence fixing shell 15, which is close to the convergence section 2, and the outer wall of the expansion section 3, and the convergence protection layer 7 and the backing 8 are both beyond the edge of the convergence section 2 and are connected with each other, so that the convergence section 2 is completely coated; the backing 8 is sequentially provided with a first ablation resistant layer 9 and a second ablation resistant layer 10 from outside to inside, the first ablation resistant layer 9, the second ablation resistant layer 10 and the expansion protective layer 4 form an inner spray pipe channel 11, a blocking cover 12 is arranged between the first ablation resistant layer 9 and the second ablation resistant layer 10, and the inner spray pipe channel 11 is completely blocked by the blocking cover 12.
When the engine works, the first ablation-resistant layer 9 and the second ablation-resistant layer 10 resist the scouring of high-temperature fuel gas, and the consistency of the throat area of the molded surface of the spray pipe is maintained; the convergence section 2, the backing 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, and high-temperature fuel gas of an engine can be converted into low-temperature high-speed air flow to generate larger thrust.
In a preferred embodiment of the invention, the convergent fixed shell 15 is inclined towards the divergent section 3, which is configured so that the force of the second ablation resistant layer 10 does not act vertically on the convergent fixed shell 15, increasing the service life, and the convergent fixed shell 15 is provided on its outside with bolting holes 14, typically flanged holes, for connection with rocket engines.
In a preferred embodiment of the invention, the first ablation-resistant layer 9 is arc-shaped and wraps the end part of the convergence section 2, and extends outwards to the convergence protection layer 7, and is respectively connected with the back lining 8 and the convergence protection layer 7, so as to resist ablation when fuel gas passes through the combustion throat, keep the uniformity of the throat area and ensure the stability of the thrust of the engine; the inner wall of the backing 8 positioned in the convergent section 2 is provided with a second ablation resistant layer 10, the second ablation resistant layer 10 is adhered to the first ablation resistant layer 9, the backing 8 and the convergent protection layer 7, and the first ablation resistant layer 9 and the second ablation resistant layer 10 are made of tungsten-copper-infiltrated materials and are used for resisting the ablation of the combustion chamber high temperature and high pressure on the jet pipe rotary shell 1; the end of the converging section 2 far from the diverging section 3 is covered by a plug 12, typically made of aluminum alloy, for sealing against moisture, for rapidly establishing ignition pressure and for shortening ignition delay time to improve ignition reliability.
In a preferred embodiment of the invention, the second ablation-resistant layer 10 extends towards the expansion section 3 and partially covers the expansion section 3, and a smooth transition is formed 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, so as to ensure the strength of the spray pipe and prevent 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 molding materials and are used for protecting the rotary shell 1, preventing high temperature from being conducted to the rotary shell 1 and ensuring the high temperature strength failure of the rotary shell 1.
In a preferred embodiment of the invention, the expansion section 3 is provided with screws 13 for fixing the expansion cover 4, or pins can be used, which are inserted into the expansion section 3 through the swivel housing 1 for reinforcing the connection between the expansion section 3 and the swivel housing 1.
In a preferred embodiment of the invention, a sealing groove is arranged on one side of the limiting boss 5, which is close to the expansion section 3, and a sealing ring 6 is arranged in the sealing groove.
In a preferred embodiment of the present invention, all the seam gaps on the inner nozzle passage 11 are coated with D03 (L) silicone rubber, specifically including the seam between the first ablation resistant layer 9 and the second ablation resistant layer 10, the seam between the second ablation resistant layer 10 and the expansion protective layer 4, to improve the ablation resistance.
In a preferred embodiment of the present invention, the inner wall of the internal nozzle channel 11 is a smoothly transitioned flow path profile to reduce the internal nozzle drag.
In a preferred embodiment of the present invention, there is also provided a method of manufacturing a low cost ablation resistant insert nozzle, comprising the steps of:
s1, processing a rotary shell 1, a first ablation resistant layer 9, a second ablation resistant layer 10, a blanking cover 12, a backing 8, a convergence protective layer 7 and an expansion protective layer 4, and performing sand blasting treatment on the inner surface of the rotary shell 1;
s2, bonding the second ablation resistant layer 10 and the back lining 8 into an adhesive assembly by using epoxy resin glue, and then bonding the adhesive assembly to the inner wall of the convergence section 2 by using the epoxy resin glue;
s3, bonding the first ablation-resistant layer 9 with the backing 8 and the convergence protective layer 7 by using epoxy resin glue, and smearing D03 (L) silicon rubber at the gaps 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, mounting the sealing ring 6 to 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 at the gap between the expansion section 3 and the second ablation resistant layer 10; forming an assembly to be processed;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner surface;
s6, installing a screw 13;
and S7, adhering the blanking cover 12 to the inside of the spray pipe by using epoxy resin glue.
And connecting the assembled and bonded spray pipe to an engine by adopting bolts.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (8)
1. The 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 forms a bell mouth shape with an opening gradually enlarged, an expansion protection layer is arranged on the inner wall of the expansion section, one end of the expansion section far away from the opening extends to form the convergent section, a limit boss is arranged at one end of the expansion section close to the convergent section, a convergent fixed shell is further arranged on the outer wall of the joint of the convergent section and the expansion section, and a backing is arranged on the inner wall of the convergent section; a convergence protection layer is arranged between one side of the convergence fixing shell, which is close to the convergence section, and the outer wall of the expansion section, and the convergence protection layer and the backing are both beyond the edge of the convergence section and are connected with each other; a first ablation resistant layer and a second ablation resistant layer are sequentially arranged on the back lining from outside to inside, the first ablation resistant layer, the second ablation resistant layer and the convergence protective layer form the inner spray pipe channel, a blocking cover is arranged between the first ablation resistant layer and the second ablation resistant layer, the inner spray pipe channel is completely blocked by the blocking cover, and the first ablation resistant layer is wrapped at the end part of the convergence section in a circular arc shape and extends outwards to the convergence protective layer; the backing is located the inside inner wall of convergence section is provided with the second and resists the ablative layer, the blanking cover is located the convergence section and keeps away from the tip of expansion section, the fixed casing of convergence to expansion section slope sets up, and the outside is provided with the bolted connection hole.
2. The low cost ablation resistant insert nozzle of claim 1, wherein a smooth transition is formed between said second ablation resistant layer and said expansion protective layer.
3. The low-cost ablation-resistant embedded nozzle of claim 1, wherein the shell is 30CrMnSiA, the backing, the convergence protection layer and the expansion protection layer are all made of carbon fiber/phenolic molding materials, the first ablation-resistant layer and the second ablation-resistant layer are both made of tungsten-copper-infiltrated materials, and the plug cover is made of aluminum alloy.
4. The low cost ablation resistant insert nozzle of claim 1, wherein said expansion section is provided with screws for securing said expansion cover.
5. The low-cost ablation-resistant embedded nozzle of claim 1, wherein a sealing groove is formed in one side of the limiting boss, which is close to the expansion section, and a sealing ring is arranged in the sealing groove.
6. The low cost ablation resistant insert nozzle of claim 1, wherein all joint gaps in said interior nozzle channel are coated with D03 (L) silicone rubber.
7. A low cost ablation resistant insert nozzle as claimed in claim 1, wherein said inner nozzle channel inner wall is a smooth transition runner profile.
8. The method of manufacturing a low cost ablation resistant insert nozzle of claim 1, comprising the steps of:
s1, processing a shell, forming a first ablation-resistant layer, a second ablation-resistant layer, a blanking cover, a backing, a convergence protective layer and an expansion protective layer, and carrying out sand blasting treatment on the inner surface of the shell;
s2, bonding the second ablation resistant layer and the back lining by using epoxy resin glue to form a bonding assembly, and bonding the bonding assembly to the inner wall of the converging section of the shell by using epoxy resin glue;
s3, bonding the first ablation-resistant layer with the backing and the convergence protective layer by using epoxy resin glue, and coating silicon rubber at gaps among the first ablation-resistant layer, the convergence protective layer and the first ablation-resistant layer and the second ablation-resistant layer;
s4, bonding the expansion protective layer on the inner wall of the expansion end by adopting epoxy resin glue to form an assembly to be processed;
s5, finishing the assembly to be processed in the S4 on a lathe to form a smooth inner surface;
s6, adhering the blocking cover to the inside of the spray pipe by using 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 |
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| Publication Number | Publication Date |
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| CN114876673A CN114876673A (en) | 2022-08-09 |
| CN114876673B true CN114876673B (en) | 2024-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210378130.3A Active CN114876673B (en) | 2022-04-12 | 2022-04-12 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
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Families Citing this family (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 |
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| 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 |
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| Publication number | Publication date |
|---|---|
| CN114876673A (en) | 2022-08-09 |
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