CN110159456A - Thrust chamber - Google Patents
Thrust chamber Download PDFInfo
- Publication number
- CN110159456A CN110159456A CN201910305453.8A CN201910305453A CN110159456A CN 110159456 A CN110159456 A CN 110159456A CN 201910305453 A CN201910305453 A CN 201910305453A CN 110159456 A CN110159456 A CN 110159456A
- Authority
- CN
- China
- Prior art keywords
- rotating shaft
- body portion
- cooled body
- fuel
- jet pipe
- 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.)
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/54—Leakage detectors; Purging systems; Filtration systems
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- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention provides a kind of thrust chambers, including head injector (1), re-generatively cooled body portion (2), jet pipe extended segment (3), oxidant pipeline (4), fuel conduit (5), first rotating shaft (6), the second shaft (7)；The head ejector filler (1) is sequentially connected re-generatively cooled body portion (2), jet pipe extended segment (3), first rotating shaft (6), the second shaft (7) are provided in re-generatively cooled body portion (2), the ejector filler (1) passes through fuel conduit (5) connection first rotating shaft (6) by oxidant pipeline (4) connection the second shaft (7), the jet pipe extended segment (3).The present invention can significantly improve rocket engine vacuum specific impulse performance；Thrust chamber outside wall surface temperature is effectively reduced, is conducive to spacecraft thermal protection；Swing function is realized convenient for rocket engine；It is able to ascend the anti-fifth wheel pollution capacity of rocket engine.
Description
Technical field
The present invention relates to spacecraft propulsion system technical fields, more particularly to a kind of thrust chamber.
Background technique
Rocket engine is the heart of the spacecrafts such as carrier rocket, satellite, becomes rail posture adjustment for spacecraft and provides power.Thrust
Room is the core component of rocket engine, is generally made of ejector filler, combustion chamber and jet pipe, can be transformed into propellant chemistry
Spacecraft propulsion power.Thrust chamber working principle is as follows, and propellant is fed atomization in combustion chamber, mixing and combustion using ejector filler
It burns, generates high-temperature high-pressure fuel gas, finally high-temperature fuel gas supersonic speed is discharged using jet pipe, thrust needed for generating spacecraft.
Thrust chamber has a variety of classification methods, different with working environment depending on the application, can be divided into delivery and help
Push away a grade thrust chamber, Upper Stage thrust chamber and aerospace craft vehicle out-driving thrust chamber and gesture stability thrust chamber；According to thrust amount
Grade is different, can be divided into the thrust chamber of high thrust and the thrust chamber of low-thrust；It is different according to propellant number of species, double groups can be divided into
First thrust chamber and single group member thrust chamber.Technology status at home and abroad is made a general survey of, thrust chamber's design scheme is varied,
With many successful cases, thrust chamber's research work is concentrated mainly on following three aspect: 1, increasing nozzle area
Than obtaining compared with high specific impulse；Such as a kind of " discrete spoiler applied to low thrust Liquid Rocket Engine Combustion Chambers
(200910123198.1) " combustibility is improved using discrete spoiler device and improves the effect of specific impulse.2, using cheap, nothing
Poison, high-energy propellant, reduce development and the launch cost of engine；Such as " low thrust single group member peroxide rocket
(201010052128.4) " high-strength hydrogen peroxide is used as to the propellant of single group member Attitude rocket engine, it is alternative existing
Conventional toxic hydrazine monopropellant, achieves the beneficial effect of single group member attitude control engine Non-toxic.3, using green wood
Material, new technology mitigate weight, improve performance.
For realize rocket engine have the function of wide-angle wave, repeatedly starting, can be long-term in-orbit etc., based on inventing " one
The new Joining Structure (ZL201610345885.8) of kind rocket motor chain-drive section and re-generatively cooled body portion " and " rocket engine
The new Joining Structure (ZL201610345895.1) of composite material jet pipe extended segment and short nozzle thrust room ", proposes a kind of fire
Arrow motor power room.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of thrust chambers.
A kind of thrust chamber provided according to the present invention, including head injector, re-generatively cooled body portion, jet pipe
Extended segment, oxidant pipeline, fuel conduit, first rotating shaft, the second shaft；The head ejector filler is sequentially connected re-generatively cooled body
Portion, jet pipe extended segment are provided with first rotating shaft, the second shaft in re-generatively cooled body portion, and the ejector filler passes through oxidant
The second shaft of piping connection, the jet pipe extended segment connect first rotating shaft by fuel conduit.
Preferably, re-generatively cooled body portion combustion chamber converging portion outer wall thickeies and connects first rotating shaft, the second shaft, institute
State first rotating shaft, the second shaft is symmetric with respect to re-generatively cooled body portion burning chamber axis.
Preferably, internal thread interface, external screw joint is arranged in the head injector upper end, and the head injector is logical
Internal thread interface connection oxidant pipe filter is crossed, the head injector connects oxidant pipeline by external screw joint.
Preferably, for the internal thread interface having a size of M20 × 1.5, the external screw joint is described having a size of M36 × 1.5
The precision of oxidant pipe filter is 400 mesh, and the latus rectum of the oxidant pipeline is DN14.
Preferably, it is provided with mounting groove on the inside of the head injector lower end, the combustion in re-generatively cooled body portion can be positioned
Room side is burnt, using high energy beam current welded header ejector filler and re-generatively cooled body portion, high-temperature fuel gas and fuel, head injector is isolated
Be provided with the step at welding lock bottom on the outside of lower end, can be used in high energy beam current and be welded to connect ring big end, connection ring small end with
The weldering connection of re-generatively cooled body portion's combustion chamber side；Fuel and external environment can be isolated in the connection ring.
Preferably, fuel pipe filter is provided in the connection ring, the precision of the fuel pipe filter is 400 mesh.
Preferably, re-generatively cooled body portion jet pipe side is connect with jet pipe extended segment small end using flange arrangement,
The flange of jet pipe extended segment expands outwardly along jet pipe extended segment small end and extends to form tapered opening, and the taper is opened
Angle between mouth and jet pipe extended segment axis is 45 °；
The flange in re-generatively cooled body portion is the taper to match with the flange shape of jet pipe extended segment.
Preferably, pass through flexible graphite sealing ring between the flange of the jet pipe extended segment and the flange in re-generatively cooled body portion
Sealing, and locked by multiple high-temperature alloy bolts；Be provided between the high-temperature alloy bolt and flange arrangement spring shim,
Snap ring.
Preferably, the flexible graphite sealing ring original depth is 2mm, compression ratio 25%；The high-temperature alloy bolt
Thread size be M8.
Preferably, the first rotating shaft, the second shaft include rotating shaft system, and the rotating shaft system includes bonded mouth,
One sealing surface, secondary sealing area, screw thread ozzle, jatharapanvartanasana curved surface, shaft-cup plate, fuel/oxidant import；
One end of the rotating shaft system be provided with can connect provide torque motor bonded mouth, rotating shaft system it is another
End is shaft-cup plate, the shaft inside jatharapanvartanasana curved surface to be bonded jatharapanvartanasana curved surface with re-generatively cooled body portion combustion chamber converging portion
The screw thread ozzle being arranged on system side can connect oxidant pipeline or fuel conduit, set in axial direction in the middle part of the rotating shaft system
Be equipped with the primary sealing area connecting with fuel/oxidant conveying device, secondary sealing area, primary sealing area, secondary sealing area it
Between one or more radial holes be set be used as fuel/oxidant import, by radial hole fuel/oxidant inflow rotating shaft system
Portion's cavity, and screw thread ozzle flows out；
The screw thread ozzle of the first rotating shaft side is connect with fuel conduit, realizes that fuel flows into the cold of re-generatively cooled body portion
But conduit；The screw thread ozzle and oxidant piping connection of second shaft side realize that oxidant flows into head injector.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the present invention uses jet pipe extended segment, significantly improves rocket engine vacuum specific impulse performance.
2, the present invention uses re-generatively cooled body portion, and thrust chamber outside wall surface temperature is effectively reduced, and is conducive to spacecraft thermal protection.
3, shaft is arranged in re-generatively cooled body portion in the present invention, realizes swing function convenient for rocket engine.
4, setting oxidant pipe filter and fuel pipe filter inside thrust chamber of the present invention, it is anti-can to promote rocket engine
Fifth wheel pollution capacity.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is schematic structural view of the invention.
Fig. 2 is head injector partial sectional view of the present invention.
Fig. 3 is head injector of the present invention and re-generatively cooled body portion junction office cross-sectional view.
Fig. 4 is re-generatively cooled body of the present invention portion and jet pipe extended segment junction office cross-sectional view.
Fig. 5 is first rotating shaft structural schematic diagram of the present invention.
It is shown in figure:
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.In the description of the present application, it is to be understood that term " on ", "lower", "front", "rear", "left", "right",
The orientation or positional relationship of the instructions such as "vertical", "horizontal", "top", "bottom", "inner", "outside" be orientation based on the figure or
Positional relationship is merely for convenience of description the application and simplifies description, rather than the device or element of indication or suggestion meaning must
There must be specific orientation, be constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
A kind of thrust chamber provided according to the present invention, as shown in Figure 1, including head injector 1, raw and cold again
But body portion 2, jet pipe extended segment 3, oxidant pipeline 4, fuel conduit 5, first rotating shaft 6, the second shaft 7；The head ejector filler 1 according to
Secondary connection re-generatively cooled body portion 2, jet pipe extended segment 3 are provided with first rotating shaft 6, the second shaft 7 in re-generatively cooled body portion 2,
The ejector filler 1 connects the second shaft 7 by oxidant pipeline 4, and the jet pipe extended segment 3 passes through the connection of fuel conduit 5 first
Shaft 6.2 combustion chamber converging portion outer wall of re-generatively cooled body portion thickeies and connects first rotating shaft 6, the second shaft 7, and described first
Shaft 6, the opposite burning of re-generatively cooled body portion 2 chamber axis of the second shaft 7 are symmetric.The present invention can be by the chemistry of propellant
The kinetic energy of spacecraft flight can be converted into, at the same realize rocket engine there is wide-angle to wave, repeatedly starting, can be long-term in-orbit
Etc. functions.Expansion of the present invention is strong, is suitable for delivery Upper Stage precise tracking, manned spaceship precise tracking, is suitable for war
Slightly guided missile final stage precise tracking, deep space probe precise tracking also have certain reference to the design of space attitude control engine
Meaning.
As shown in Fig. 2, internal thread interface 101, external screw joint 102, the head is arranged in 1 upper end of head injector
Portion's ejector filler 1 connects oxidant pipe filter 8 by internal thread interface 101, and the head injector 1 passes through external screw joint
102 connection oxidant pipelines 4.The internal thread interface 101 is having a size of M20 × 1.5, and the external screw joint 102 is having a size of M36
× 1.5, the precision of the oxidant pipe filter 8 is 400 mesh, and the latus rectum of the oxidant pipeline 4 is DN14.
As shown in figure 3, being provided with mounting groove on the inside of 1 lower end of head injector, re-generatively cooled body portion 2 can be positioned
Combustion chamber side high-temperature fuel gas and fuel, head are isolated using high energy beam current welded header ejector filler 1 and re-generatively cooled body portion 2
It is provided with the step at welding lock bottom on the outside of 1 lower end of ejector filler, can be used in high energy beam current and be welded to connect 9 big end of ring, connection
9 small end of ring and the weldering of 2 combustion chamber side of re-generatively cooled body portion connect；Fuel and external environment can be isolated in the connection ring 9.The company
It connects and is provided with fuel pipe filter 10 on ring 9, the precision of the fuel pipe filter 10 is 400 mesh.
As shown in figure 4,2 jet pipe side of re-generatively cooled body portion is connect with 3 small end of jet pipe extended segment using flange arrangement, spray
The flange of pipe extended segment 3 expands outwardly along 3 small end of jet pipe extended segment and extends to form tapered opening, the tapered opening and jet pipe
Angle between 3 axis of extended segment is 45 °；The flange in re-generatively cooled body portion 2 is to match with the flange shape of jet pipe extended segment 3
Taper.It is close by flexible graphite sealing ring 11 between the flange of the jet pipe extended segment 3 and the flange in re-generatively cooled body portion 2
Envelope, and locked by multiple high-temperature alloy bolts 12；Spring pad is provided between the high-temperature alloy bolt 12 and flange arrangement
Piece 13, snap ring 14.11 original depth of flexible graphite sealing ring is 2mm, compression ratio 25%；The high-temperature alloy bolt 12
Thread size be M8.Preferably, the high-temperature alloy bolt 12 is 18 and is uniformly distributed in flange arrangement circumferential direction；It is described
High-temperature alloy bolt 12 is evenly distributed with stress using double HALF snap rings (half snap ring) 14, is carried out using spring shim 13 locking.
As shown in figure 5, the first rotating shaft 6, the second shaft 7 include rotating shaft system, the rotating shaft system includes bonded
Mouthfuls 61, primary sealing area 62, secondary sealing area 63, screw thread ozzle 64, jatharapanvartanasana curved surface 65, shaft-cup plate 66, fuel/oxidant into
Mouth 67；One end of the rotating shaft system be provided with can connect provide torque motor bonded mouth 61, rotating shaft system it is another
End is to be bonded jatharapanvartanasana curved surface 65 with 2 combustion chamber converging portion of re-generatively cooled body portion and be welded to connect re-generatively cooled body portion 2, jatharapanvartanasana
Be shaft-cup plate 66 inside curved surface 65, the screw thread ozzle 64 being arranged on the rotating shaft system side can connect oxidant pipeline 4 or
Fuel conduit 5 is provided with the primary sealing area connecting with fuel/oxidant conveying device in axial direction in the middle part of the rotating shaft system
62, one or more radial holes are arranged as fuel/oxygen in secondary sealing area 63 between primary sealing area 62, secondary sealing area 63
Agent import 67 flows into rotating shaft system internal passage by radial hole fuel/oxidant, and screw thread ozzle 64 flows out, it is preferable that
The radial hole is radial unthreaded hole；The screw thread ozzle 64 of 6 side of first rotating shaft is connect with fuel conduit 5, realizes fuel stream
Enter the cooling channels in re-generatively cooled body portion 2；The screw thread ozzle 64 of second shaft, 7 side is connect with oxidant pipeline 4, is realized
Oxidant flows into head injector 1.
Working principle of the present invention is as follows:
The radial hole that fuel first passes through in first rotating shaft 6 enters shaft internal passage；Fuel is from the screw thread in first rotating shaft 6
Ozzle 64 flows out into fuel conduit 5；Fuel enters the cooling channels in re-generatively cooled body portion 2 from the outflow of fuel conduit 5；Fuel
It is flowed out from the cooling channels in re-generatively cooled body portion 2, by connection ring 9 and fuel pipe filter 10, into head injector 1；Combustion
Material is sprayed from head injector 1, into the thrust chamber combustion chamber in re-generatively cooled body portion 2；
The radial hole that oxidant first passes through in the second shaft 7 enters shaft internal passage；Oxidant is from the second shaft 7
Screw thread ozzle 64 flows out into oxidant pipeline 4；Oxidant is flowed out from oxidant pipeline 4, by oxidant pipe filter 8,
Into head injector 1；Oxidant is sprayed from head injector 1, into the thrust chamber combustion chamber in re-generatively cooled body portion 2；
Oxidant and fuel form high-temperature high-pressure fuel gas, pass through thrust thrust chamber combustion chamber is atomization, mixing, burning
Room jet pipe generates thrust；
Motor is connect with first rotating shaft 6 or the second shaft 7, and output engine waves required torque, and then realizes and start
Machine swing function.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of thrust chamber, which is characterized in that including head injector (1), re-generatively cooled body portion (2), jet pipe
Extended segment (3), oxidant pipeline (4), fuel conduit (5), first rotating shaft (6), the second shaft (7)；The head ejector filler (1) according to
Secondary connection re-generatively cooled body portion (2), jet pipe extended segment (3) are provided with first rotating shaft (6), in re-generatively cooled body portion (2)
Two shafts (7), the ejector filler (1) are passed through by oxidant pipeline (4) connection the second shaft (7), the jet pipe extended segment (3)
Fuel conduit (5) connects first rotating shaft (6).
2. thrust chamber according to claim 1, which is characterized in that re-generatively cooled body portion (2) burning
Room converging portion outer wall thickeies and connects first rotating shaft (6), the second shaft (7), and the first rotating shaft (6), the second shaft (7) are opposite
Re-generatively cooled body portion (2) burning chamber axis is symmetric.
3. thrust chamber according to claim 1, which is characterized in that head injector (1) upper end
Internal thread interface (101), external screw joint (102) are set, and the head injector (1) is connected by internal thread interface (101)
Oxidant pipe filter (8), the head injector (1) pass through external screw joint (102) connection oxidant pipeline (4).
4. thrust chamber according to claim 3, which is characterized in that internal thread interface (101) size
For M20 × 1.5, the external screw joint (102) is 400 having a size of M36 × 1.5, the precision of the oxidant pipe filter (8)
Mesh, the latus rectum of the oxidant pipeline (4) are DN14.
5. thrust chamber according to claim 1, which is characterized in that head injector (1) lower end
Inside is provided with mounting groove, can position the combustion chamber side in re-generatively cooled body portion (2), using high energy beam current welded header ejector filler
(1) and re-generatively cooled body portion (2), isolation high-temperature fuel gas and fuel, head injector (1) lower end outside are provided with welding lock bottom
Step can be used in high energy beam current and be welded to connect ring (9) big end, and connection ring (9) small end and re-generatively cooled body portion (2) burn
The weldering connection of room side；Fuel and external environment can be isolated in the connection ring (9).
6. thrust chamber according to claim 5, which is characterized in that be provided with combustion on the connection ring (9)
Material tube filter (10), the precision of the fuel pipe filter (10) are 400 mesh.
7. thrust chamber according to claim 1, which is characterized in that re-generatively cooled body portion (2) jet pipe
Side is connect with jet pipe extended segment (3) small end using flange arrangement,
The flange of jet pipe extended segment (3) expands outwardly along jet pipe extended segment (3) small end and extends to form tapered opening, the taper
Angle between opening and jet pipe extended segment (3) axis is 45 °；
The flange in re-generatively cooled body portion (2) is the taper to match with the flange shape of jet pipe extended segment (3).
8. thrust chamber according to claim 7, which is characterized in that the flange of the jet pipe extended segment (3)
It is sealed between the flange in re-generatively cooled body portion (2) by flexible graphite sealing ring (11), and passes through multiple high-temperature alloy bolts
(12) it locks；Spring shim (13), snap ring (14) are provided between the high-temperature alloy bolt (12) and flange arrangement.
9. thrust chamber according to claim 8, which is characterized in that the flexible graphite sealing ring (11) is just
Begin with a thickness of 2mm, compression ratio 25%；The thread size of the high-temperature alloy bolt (12) is M8.
10. thrust chamber according to claim 1, which is characterized in that the first rotating shaft (6), second turn
Axis (7) include rotating shaft system, the rotating shaft system include bonded mouth (61), primary sealing area (62), secondary sealing area (63),
Screw thread ozzle (64), jatharapanvartanasana curved surface (65), shaft-cup plate (66), fuel/oxidant import (67)；
One end of the rotating shaft system be provided with can connect provide torque motor bonded mouth (61), rotating shaft system it is another
End is shaft-cup inside jatharapanvartanasana curved surface (65) to be bonded jatharapanvartanasana curved surface (65) with re-generatively cooled body portion (2) combustion chamber converging portion
Plate (66), the screw thread ozzle (64) being arranged on the rotating shaft system side can connect oxidant pipeline (4) or fuel conduit
(5), the primary sealing area (62) connecting with fuel/oxidant conveying device, the are provided in the middle part of the rotating shaft system in axial direction
One or more radial holes are arranged as fuel/oxygen in two sealing surfaces (63) between primary sealing area (62), secondary sealing area (63)
Agent import (67) flows into rotating shaft system internal passage by radial hole fuel/oxidant, and screw thread ozzle (64) flows out；
The screw thread ozzle (64) of first rotating shaft (6) side is connect with fuel conduit (5), realizes that fuel flows into re-generatively cooled body
The cooling channels in portion (2)；The screw thread ozzle (64) of second shaft (7) side is connect with oxidant pipeline (4), realizes oxidation
Agent flows into head injector (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910305453.8A CN110159456B (en) | 2019-04-16 | 2019-04-16 | Rocket engine thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910305453.8A CN110159456B (en) | 2019-04-16 | 2019-04-16 | Rocket engine thrust chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110159456A true CN110159456A (en) | 2019-08-23 |
| CN110159456B CN110159456B (en) | 2020-07-14 |
Family
ID=67639633
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910305453.8A Active CN110159456B (en) | 2019-04-16 | 2019-04-16 | Rocket engine thrust chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110159456B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412662A (en) * | 2020-11-17 | 2021-02-26 | 哈尔滨工程大学 | Combined thrust vectoring nozzle system and projectile body with same |
| CN114439652A (en) * | 2021-12-29 | 2022-05-06 | 北京航天动力研究所 | Thermal protection enhancement mode 3D prints spray tube extension |
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|---|---|---|---|---|
| US2443186A (en) * | 1944-01-03 | 1948-06-15 | Foulks Edwin David | Jet propulsion fuel feeding and exhaust control device |
| US6170258B1 (en) * | 1999-01-21 | 2001-01-09 | Otkrytoe Aktsionernoe Obschestvo “Nauchno” Proizvodstvennoe Obiedinenie Energomash Imeni Akademika V.P. Glushko | Liquid-propellant rocket engine |
| JP2002195151A (en) * | 2000-12-26 | 2002-07-10 | Ishikawajima Harima Heavy Ind Co Ltd | Plasma gas propulsion device |
| US6705076B1 (en) * | 1999-06-17 | 2004-03-16 | Astrium Gmbh | Rocket thrust chamber |
| CN105888885A (en) * | 2016-05-23 | 2016-08-24 | 上海空间推进研究所 | Novel connecting structure for composite-material spray pipe extending section and short spray pipe thrust chamber of rocket engine |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN109162830A (en) * | 2018-07-13 | 2019-01-08 | 上海空间推进研究所 | It is a kind of can gimbaled rocket engine novel rotating shaft structure |
-
2019
- 2019-04-16 CN CN201910305453.8A patent/CN110159456B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2443186A (en) * | 1944-01-03 | 1948-06-15 | Foulks Edwin David | Jet propulsion fuel feeding and exhaust control device |
| US6170258B1 (en) * | 1999-01-21 | 2001-01-09 | Otkrytoe Aktsionernoe Obschestvo “Nauchno” Proizvodstvennoe Obiedinenie Energomash Imeni Akademika V.P. Glushko | Liquid-propellant rocket engine |
| US6705076B1 (en) * | 1999-06-17 | 2004-03-16 | Astrium Gmbh | Rocket thrust chamber |
| JP2002195151A (en) * | 2000-12-26 | 2002-07-10 | Ishikawajima Harima Heavy Ind Co Ltd | Plasma gas propulsion device |
| CN105888885A (en) * | 2016-05-23 | 2016-08-24 | 上海空间推进研究所 | Novel connecting structure for composite-material spray pipe extending section and short spray pipe thrust chamber of rocket engine |
| CN106050474A (en) * | 2016-05-23 | 2016-10-26 | 上海空间推进研究所 | Novel connecting structure for head and regenerative cooling body of rocket engine |
| CN109162830A (en) * | 2018-07-13 | 2019-01-08 | 上海空间推进研究所 | It is a kind of can gimbaled rocket engine novel rotating shaft structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112412662A (en) * | 2020-11-17 | 2021-02-26 | 哈尔滨工程大学 | Combined thrust vectoring nozzle system and projectile body with same |
| CN114439652A (en) * | 2021-12-29 | 2022-05-06 | 北京航天动力研究所 | Thermal protection enhancement mode 3D prints spray tube extension |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110159456B (en) | 2020-07-14 |
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