CN110159456B - Rocket engine thrust chamber - Google Patents
Rocket engine thrust chamber Download PDFInfo
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- CN110159456B CN110159456B CN201910305453.8A CN201910305453A CN110159456B CN 110159456 B CN110159456 B CN 110159456B CN 201910305453 A CN201910305453 A CN 201910305453A CN 110159456 B CN110159456 B CN 110159456B
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- rotating shaft
- cooling body
- fuel
- oxidant
- body part
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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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
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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
- F02K9/44—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 invention provides a rocket engine thrust chamber, which comprises a head injector (1), a regenerative cooling body part (2), a spray pipe extension section (3), an oxidant pipeline (4), a fuel pipeline (5), a first rotating shaft (6) and a second rotating shaft (7); the head injector (1) is sequentially connected with a regenerative cooling body part (2) and a spray pipe extension section (3), a first rotating shaft (6) and a second rotating shaft (7) are arranged on the regenerative cooling body part (2), the injector (1) is connected with the second rotating shaft (7) through an oxidant pipeline (4), and the spray pipe extension section (3) is connected with the first rotating shaft (6) through a fuel pipeline (5). The invention can obviously improve the vacuum specific impulse performance of the rocket engine; the temperature of the outer wall surface of the thrust chamber is effectively reduced, and the thermal protection of the spacecraft is facilitated; the rocket engine can conveniently realize the swinging function; the capability of resisting the pollution of excess substances of the rocket engine can be improved.
Description
Technical Field
The invention relates to the technical field of spacecraft propulsion systems, in particular to a rocket engine thrust chamber.
Background
The rocket engine is the heart of a spacecraft such as a carrier rocket, a satellite and the like and provides power for the spacecraft to change orbit and adjust attitude. The thrust chamber is a core component of the rocket engine, generally comprises an injector, a combustion chamber and a nozzle, and can convert chemical energy of a propellant into propulsion of a spacecraft. The working principle of the thrust chamber is as follows, a propellant is supplied into the combustion chamber by the injector to be atomized, mixed and combusted, high-temperature and high-pressure fuel gas is generated, and finally the high-temperature fuel gas is discharged in a supersonic speed by the spray pipe to generate thrust required by the spacecraft.
The rocket engine thrust chamber has various classification methods, and can be divided into a carrying boosting stage thrust chamber, an upper stage thrust chamber, a spacecraft maneuvering orbital transfer thrust chamber and an attitude control thrust chamber according to different purposes and working environments; according to different thrust levels, the thrust chamber can be divided into a high-thrust chamber and a low-thrust chamber; according to the different kinds and quantity of the propellant, the thrust chamber can be divided into a two-component thrust chamber and a single-component thrust chamber. Throughout the technical current situation at home and abroad, the design scheme of the rocket engine thrust chamber is various and has many successful cases, and the research work of the rocket engine thrust chamber is mainly focused on the following three aspects: 1. the area ratio of the spray pipe is increased to obtain higher specific impulse; for example, "a discrete spoiler (200910123198.1) for a combustion chamber of a low thrust liquid rocket engine" uses the discrete spoiler device to improve combustion performance and improve specific impulse. 2. The low-cost, non-toxic and high-energy propellant is used, so that the development and emission cost of the engine is reduced; for example, the low-thrust monopropellant hydrogen peroxide rocket engine (201010052128.4) uses high-concentration hydrogen peroxide as a propellant of the monopropellant attitude control rocket engine, can replace the conventional toxic hydrazine monopropellant, and has the advantage of nontoxic monopropellant attitude control engines. 3. The novel material and the novel technology are adopted, the weight is reduced, and the performance is improved.
In order to realize the functions of large-angle swing, multiple starting, long-term on-orbit and the like of the rocket engine, the rocket engine thrust chamber is provided based on the invention of 'a novel connecting structure (Z L201610345885.8) of the head part and the regenerative cooling body part of the rocket engine' and 'a novel connecting structure (Z L201610345895.1) of the composite material nozzle extension section and the short nozzle thrust chamber of the rocket engine'.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a rocket engine thrust chamber.
The rocket engine thrust chamber comprises a head injector, a regenerative cooling body, a nozzle extension section, an oxidant pipeline, a fuel pipeline, a first rotating shaft and a second rotating shaft, wherein the head injector is arranged on the front end of the regenerative cooling body; the head injector is sequentially connected with the regenerative cooling body part and the spray pipe extension section, a first rotating shaft and a second rotating shaft are arranged on the regenerative cooling body part, the injector is connected with the second rotating shaft through an oxidant pipeline, and the spray pipe extension section is connected with the first rotating shaft through a fuel pipeline.
Preferably, the outer wall of the convergent section of the regenerative cooling body part combustion chamber is thickened and connected with a first rotating shaft and a second rotating shaft, and the first rotating shaft and the second rotating shaft are symmetrically distributed relative to the axis of the regenerative cooling body part combustion chamber.
Preferably, an internal thread interface and an external thread interface are arranged at the upper end of the head injector, the head injector is connected with the oxidant passage filter through the internal thread interface, and the head injector is connected with the oxidant pipeline through the external thread interface.
Preferably, the size of the internal thread connector is M20 × 1.5.5, the size of the external thread connector is M36 × 1.5.5, the precision of the oxidizer line filter is 400 meshes, and the drift diameter of the oxidizer line is DN 14.
Preferably, the inner side of the lower end part of the head injector is provided with a mounting groove which can position the side of a combustion chamber of the regenerative cooling body part, the head injector and the regenerative cooling body part are welded by high-energy beam to isolate high-temperature gas and fuel, the outer side of the lower end part of the head injector is provided with a step for welding a lock bottom, the step can be used for welding the large end of a connecting ring by the high-energy beam, and the small end of the connecting ring is welded and connected with the side of the combustion chamber of the regenerative cooling body part; the connection ring is capable of isolating fuel from the external environment.
Preferably, the connection ring is provided with a fuel path filter having a precision of 400 mesh.
Preferably, the spray pipe side of the regenerative cooling body part is connected with the small end of the extension section of the spray pipe by adopting a flange structure,
the flange of the spray pipe extension section expands outwards along the small end of the spray pipe extension section to form a conical opening, and the included angle between the conical opening and the axis of the spray pipe extension section is 45 degrees;
the flange of the regeneration cooling body part is in a conical shape matched with the shape of the flange of the spray pipe extension section.
Preferably, the flange of the spray pipe extension section and the flange of the regeneration cooling body part are sealed through a flexible graphite sealing ring and locked through a plurality of high-temperature alloy bolts; and a spring gasket and a clamping ring are arranged between the high-temperature alloy bolt and the flange structure.
Preferably, the flexible graphite sealing ring has an initial thickness of 2mm and a compression ratio of 25%; the thread size of the superalloy bolt is M8.
Preferably, the first rotating shaft and the second rotating shaft both comprise a rotating shaft system, and the rotating shaft system comprises a key interface, a first sealing surface, a second sealing surface, a threaded nozzle, a revolution-shaped curved surface, a shaft cover plate and a fuel/oxidant inlet;
one end of the rotating shaft system is provided with a key interface which can be connected with a motor for providing torque, the other end of the rotating shaft system is a rotary curved surface which is attached to a convergent section of a combustion chamber of the regenerative cooling body part, a shaft cover plate is arranged inside the rotary curved surface, a threaded nozzle arranged on the side surface of the rotating shaft system can be connected with an oxidant pipeline or a fuel pipeline, a first sealing surface and a second sealing surface which are connected with a fuel/oxidant conveying device are axially arranged in the middle of the rotating shaft system, one or more radial holes are arranged between the first sealing surface and the second sealing surface and are used as fuel/oxidant inlets, and fuel/oxidant flows into a cavity channel inside the rotating shaft system through the radial holes and flows out through the threaded nozzle;
the threaded nozzle on the side surface of the first rotating shaft is connected with a fuel pipeline to realize that fuel flows into a cooling channel of the regeneration cooling body part; and the threaded nozzle on the side surface of the second rotating shaft is connected with an oxidant pipeline, so that oxidant flows into the head injector.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts the extension section of the spray pipe, thereby obviously improving the vacuum specific impulse performance of the rocket engine.
2. The invention adopts the regenerative cooling body part, effectively reduces the temperature of the outer wall surface of the thrust chamber, and is beneficial to the thermal protection of the spacecraft.
3. The rotating shaft is arranged on the regenerative cooling body part, so that the rocket engine can conveniently realize the swinging function.
4. The oxidant path filter and the fuel path filter are arranged in the thrust chamber, so that the capacity of resisting the redundant substances pollution of the rocket engine can be improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of the structure of the present invention.
Fig. 2 is a partial cross-sectional view of the head injector of the present invention.
Fig. 3 is a partial cross-sectional view of the junction of the head injector and the regeneratively cooled body of the present invention.
FIG. 4 is a partial sectional view of the connection between the regenerative cooling body and the nozzle extension according to the invention.
Fig. 5 is a schematic view of a first rotating shaft structure of the present invention.
The figures show that:
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention. In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The rocket engine thrust chamber provided by the invention comprises a head injector 1, a regenerative cooling body 2, a nozzle extension section 3, an oxidant pipeline 4, a fuel pipeline 5, a first rotating shaft 6 and a second rotating shaft 7, wherein the head injector is arranged on the outer side of the nozzle extension section; the head injector 1 is sequentially connected with a regenerative cooling body part 2 and a spray pipe extension section 3, a first rotating shaft 6 and a second rotating shaft 7 are arranged on the regenerative cooling body part 2, the injector 1 is connected with the second rotating shaft 7 through an oxidant pipeline 4, and the spray pipe extension section 3 is connected with the first rotating shaft 6 through a fuel pipeline 5. The outer wall of the convergent section of the combustion chamber of the regenerative cooling body part 2 is thickened and connected with a first rotating shaft 6 and a second rotating shaft 7, and the first rotating shaft 6 and the second rotating shaft 7 are symmetrically distributed relative to the axis of the combustion chamber of the regenerative cooling body part 2. The invention can convert the chemical energy of the propellant into the flying kinetic energy of the spacecraft, and simultaneously realizes the functions of large-angle swing, multiple starting, long-term on-orbit and the like of the rocket engine. The invention has strong expansibility, is suitable for carrying a superior rail-controlled engine, a manned spacecraft rail-controlled engine, a strategic missile final-stage rail-controlled engine and a deep space detector rail-controlled engine, and has certain reference significance for the design of a space attitude control engine.
As shown in fig. 2, an internal threaded connector 101 and an external threaded connector 102 are arranged at the upper end of the head injector 1, the head injector 1 is connected with the oxidizer line filter 8 through the internal threaded connector 101, the head injector 1 is connected with the oxidizer line 4 through the external threaded connector 102, the internal threaded connector 101 is M20 × 1.5 in size, the external threaded connector 102 is M36 × 1.5 in size, the precision of the oxidizer line filter 8 is 400 meshes, and the through diameter of the oxidizer line 4 is DN 14.
As shown in fig. 3, the inner side of the lower end of the head injector 1 is provided with a mounting groove capable of positioning the combustion chamber side of the regenerative cooling body 2, the head injector 1 and the regenerative cooling body 2 are welded by high-energy beam to isolate high-temperature gas and fuel, the outer side of the lower end of the head injector 1 is provided with a step for welding a lock bottom, the step can be used for welding the large end of a connecting ring 9 by the high-energy beam, and the small end of the connecting ring 9 is welded and connected with the combustion chamber side of the regenerative cooling body 2; the connection ring 9 is capable of isolating the fuel from the external environment. The connection ring 9 is provided with a fuel path filter 10, and the accuracy of the fuel path filter 10 is 400 meshes.
As shown in FIG. 4, the nozzle side of the regeneration cooling body part 2 is connected with the small end of the nozzle extension section 3 by a flange structure, the flange of the nozzle extension section 3 expands outwards along the small end of the nozzle extension section 3 to form a conical opening, an included angle between the conical opening and the axis of the nozzle extension section 3 is 45 degrees, the flange of the regeneration cooling body part 2 is conical matched with the flange of the nozzle extension section 3, the flange of the nozzle extension section 3 and the flange of the regeneration cooling body part 2 are sealed by a flexible graphite sealing ring 11 and locked by a plurality of high-temperature alloy bolts 12, a spring gasket 13 and a clamping ring 14 are arranged between the high-temperature alloy bolts 12 and the flange structure, the flexible graphite sealing ring 11 is 2mm in initial thickness and 25% in compression, the thread size of the high-temperature alloy bolts 12 is M8., preferably, the high-temperature alloy bolts 12 are 18 and are uniformly distributed in the circumferential direction of the flange structure, and the high-temperature alloy bolts 12 are uniformly stressed by double HA L F clamping rings (half clamping rings) 14 and are prevented from loosening by the spring gasket 13.
As shown in fig. 5, the first and second shafts 6, 7 each comprise a shaft system comprising a key interface 61, a first sealing surface 62, a second sealing surface 63, a threaded nozzle 64, a toroidal curved surface 65, a shaft cover plate 66, a fuel/oxidant inlet 67; a key joint 61 capable of being connected with a motor for providing torque is arranged at one end of the rotating shaft system, a rotary curved surface 65 is attached to a convergent section of a combustion chamber of the regenerative cooling body part 2 and is welded with the regenerative cooling body part 2 at the other end of the rotating shaft system, a shaft cover plate 66 is arranged inside the rotary curved surface 65, a threaded nozzle 64 arranged on the side surface of the rotating shaft system can be connected with an oxidant pipeline 4 or a fuel pipeline 5, a first sealing surface 62 and a second sealing surface 63 connected with a fuel/oxidant conveying device are axially arranged in the middle of the rotating shaft system, one or more radial holes are arranged between the first sealing surface 62 and the second sealing surface 63 and are used as fuel/oxidant inlets 67, fuel/oxidant flows into a cavity in the rotating shaft system through the radial holes and flows out from the threaded nozzle 64, and preferably, the radial holes are radial unthreaded holes; the threaded nozzle 64 on the side surface of the first rotating shaft 6 is connected with the fuel pipeline 5, so that fuel flows into the cooling channel of the regenerative cooling body 2; the threaded nozzle 64 on the side of the second rotating shaft 7 is connected with the oxidant pipeline 4 to realize the oxidant flow into the head injector 1.
The working principle of the invention is as follows:
the fuel firstly enters the inner cavity channel of the rotating shaft through the radial hole on the first rotating shaft 6; fuel flows out of the threaded nozzle 64 on the first rotor shaft 6 and into the fuel line 5; the fuel flows out of the fuel pipeline 5 into the cooling channel of the regenerative cooling body 2; the fuel flows out from the cooling channel of the regenerative cooling body 2, passes through the connecting ring 9 and the fuel path filter 10 and enters the head injector 1; the fuel is sprayed from the head injector 1 and enters a thrust chamber combustion chamber of the regenerative cooling body part 2;
the oxidant firstly enters the cavity channel inside the rotating shaft through the radial hole on the second rotating shaft 7; the oxidant flows out of the threaded nozzle 64 on the second rotating shaft 7 and enters the oxidant pipeline 4; the oxidant flows out of the oxidant pipeline 4, passes through the oxidant pipeline filter 8 and enters the head injector 1; the oxidant is sprayed from the head injector 1 and enters a thrust chamber combustion chamber of the regenerative cooling body part 2;
the oxidant and the fuel are atomized, mixed and combusted in the thrust chamber combustion chamber to form high-temperature and high-pressure fuel gas, and thrust is generated through the thrust chamber spray pipe;
the motor is connected with the first rotating shaft 6 or the second rotating shaft 7, and outputs torque required by the swinging of the engine, so that the swinging function of the engine is realized.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. A rocket engine thrust chamber is characterized by comprising a head injector (1), a regenerative cooling body part (2), a spray pipe extension section (3), an oxidant pipeline (4), a fuel pipeline (5), a first rotating shaft (6) and a second rotating shaft (7); the head injector (1) is sequentially connected with a regenerative cooling body part (2) and a spray pipe extension section (3), a first rotating shaft (6) and a second rotating shaft (7) are arranged on the regenerative cooling body part (2), the injector (1) is connected with the second rotating shaft (7) through an oxidant pipeline (4), and the spray pipe extension section (3) is connected with the first rotating shaft (6) through a fuel pipeline (5);
the outer wall of the convergent section of the combustion chamber of the regenerative cooling body part (2) is thickened and connected with a first rotating shaft (6) and a second rotating shaft (7), and the first rotating shaft (6) and the second rotating shaft (7) are symmetrically distributed relative to the axis of the combustion chamber of the regenerative cooling body part (2);
the upper end of the head injector (1) is provided with an internal thread interface (101) and an external thread interface (102), the head injector (1) is connected with an oxidant pipeline filter (8) through the internal thread interface (101), and the head injector (1) is connected with an oxidant pipeline (4) through the external thread interface (102);
the size of the internal thread connector (101) is M20 × 1.5.5, the size of the external thread connector (102) is M36 × 1.5.5, the precision of the oxidant passage filter (8) is 400 meshes, and the drift diameter of the oxidant pipeline (4) is DN 14;
the inner side of the lower end part of the head injector (1) is provided with a mounting groove which can position the side of a combustion chamber of the regenerative cooling body part (2), the head injector (1) and the regenerative cooling body part (2) are welded by high-energy beam to isolate high-temperature gas and fuel, the outer side of the lower end part of the head injector (1) is provided with a step for welding a lock bottom, the step can be used for welding the large end of a connecting ring (9) by the high-energy beam, and the small end of the connecting ring (9) is welded and connected with the side of the combustion chamber of the regenerative cooling body part (2; the connection ring (9) is capable of isolating the fuel from the external environment;
the connecting ring (9) is provided with a fuel path filter (10), and the precision of the fuel path filter (10) is 400 meshes.
2. The rocket engine thrust chamber according to claim 1, wherein the nozzle side of the regenerative cooling body (2) is connected with the small end of the nozzle extension section (3) by a flange structure,
the flange of the spray pipe extension section (3) expands outwards along the small end of the spray pipe extension section (3) to form a conical opening, and an included angle between the conical opening and the axis of the spray pipe extension section (3) is 45 degrees;
the flange of the regeneration cooling body part (2) is in a conical shape matched with the shape of the flange of the spray pipe extension section (3).
3. The rocket engine thrust chamber according to claim 2, characterized in that the flange of the nozzle extension (3) and the flange of the regenerative cooling body (2) are sealed by flexible graphite sealing rings (11) and locked by a plurality of high temperature alloy bolts (12); and a spring gasket (13) and a snap ring (14) are arranged between the high-temperature alloy bolt (12) and the flange structure.
4. A rocket engine thrust chamber as claimed in claim 3, wherein said flexible graphite sealing ring (11) has an initial thickness of 2mm and a compression ratio of 25%; the thread size of the high-temperature alloy bolt (12) is M8.
5. A rocket engine thrust chamber according to claim 1, wherein said first and second rotary shafts (6, 7) each comprise a rotary shaft system comprising a key interface (61), a first sealing surface (62), a second sealing surface (63), a threaded nozzle (64), a toroidal curved surface (65), a shaft cover plate (66), a fuel/oxidant inlet (67);
one end of the rotating shaft system is provided with a key interface (61) which can be connected with a motor for providing torque, the other end of the rotating shaft system is a rotary curved surface (65) which is attached to a convergent section of a combustion chamber of the regenerative cooling body part (2), a shaft cover plate (66) is arranged inside the rotary curved surface (65), a threaded nozzle (64) arranged on the side surface of the rotating shaft system can be connected with an oxidant pipeline (4) or a fuel pipeline (5), a first sealing surface (62) and a second sealing surface (63) which are connected with a fuel/oxidant conveying device are axially arranged in the middle of the rotating shaft system, one or more radial holes are arranged between the first sealing surface (62) and the second sealing surface (63) and serve as fuel/oxidant inlets (67), fuel/oxidant flows into a cavity channel in the rotating shaft system through the radial holes, and the threaded nozzle (64;
the threaded nozzle (64) on the side surface of the first rotating shaft (6) is connected with the fuel pipeline (5) to realize the fuel flow into the cooling channel of the regenerative cooling body part (2); and a threaded nozzle (64) on the side surface of the second rotating shaft (7) is connected with an oxidant pipeline (4) to realize the flow of oxidant into the head injector (1).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910305453.8A CN110159456B (en) | 2019-04-16 | 2019-04-16 | Rocket engine thrust chamber |
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| CN201910305453.8A CN110159456B (en) | 2019-04-16 | 2019-04-16 | Rocket engine thrust chamber |
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| CN110159456B true CN110159456B (en) | 2020-07-14 |
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| CN112412662B (en) * | 2020-11-17 | 2021-11-09 | 哈尔滨工程大学 | Combined thrust vectoring nozzle system and projectile body with same |
| CN114439652B (en) * | 2021-12-29 | 2023-03-10 | 北京航天动力研究所 | Thermal protection enhancement mode 3D prints spray tube extension |
Family Cites Families (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 |
| RU2158838C2 (en) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Liquid-propellant rocket engine |
| DE19927734C2 (en) * | 1999-06-17 | 2002-04-11 | Astrium Gmbh | Thrust chamber of a propulsion engine for satellites and transport devices for space applications |
| JP2002195151A (en) * | 2000-12-26 | 2002-07-10 | Ishikawajima Harima Heavy Ind Co Ltd | Plasma gas propulsion device |
| CN106050474B (en) * | 2016-05-23 | 2017-12-15 | 上海空间推进研究所 | A kind of new Joining Structure in rocket motor chain-drive section and re-generatively cooled body portion |
| CN105888885B (en) * | 2016-05-23 | 2017-10-27 | 上海空间推进研究所 | The new Joining Structure of rocket engine composite jet pipe extension and short nozzle thrust room |
| CN109162830B (en) * | 2018-07-13 | 2020-07-28 | 上海空间推进研究所 | Novel rotating shaft structure of rocket engine capable of swinging |
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