CN109139298B - Space two-component rail-controlled engine based on double-path single-nozzle centrifugal injector - Google Patents
Space two-component rail-controlled engine based on double-path single-nozzle centrifugal injector Download PDFInfo
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- CN109139298B CN109139298B CN201810924471.XA CN201810924471A CN109139298B CN 109139298 B CN109139298 B CN 109139298B CN 201810924471 A CN201810924471 A CN 201810924471A CN 109139298 B CN109139298 B CN 109139298B
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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
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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
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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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
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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
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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
- F02K9/97—Rocket nozzles
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
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Abstract
A space two-component rail-controlled engine based on a two-way single-nozzle centrifugal injector is suitable for the task requirements of rail maneuvering, rail transfer and the like of an aerospace craft and comprises a mounting connection plate, a heating device, a control valve, a screw, a main body structure, an inner nozzle, an outer nozzle, a temperature measurement sensor, a combustion chamber and a spray pipe.
Description
Technical Field
The invention relates to a space two-component rail-controlled engine based on a two-way single-nozzle centrifugal injector and a molybdenum silicide composite coating thrust chamber, which is suitable for the task requirements of orbital maneuver, orbital transfer and the like of a space craft.
Background
The double-path single-nozzle centrifugal engine adopts a double-path centrifugal nozzle with a nested structure to realize the injection of two paths of propellants for oxygen and fuel, the propellants are sprayed out in a high-speed rotating jet flow state through the pressure drop potential energy and the rotational flow effect, and partial liquid drops are atomized and evaporated to participate in spontaneous combustion reaction under the disturbance effect of internal and external forces.
The space orbit control engine based on the centrifugal single-nozzle injection scheme has the characteristics of high performance, long service life, good combustion stability and repeated starting, can provide reliable power for spacecrafts such as large satellite platforms and in-orbit service cabins, can meet the task requirements of efficient orbit transfer, frequent in-orbit maneuvering and the like, and has good application potential.
However, unlike high chamber pressure engines, space propulsion systems can provide limited operating pressures and it is difficult to improve the injection effect of the nozzle at lower pressure drops. Especially for centrifugal engines, it is difficult to obtain the ideal injection velocity and angle under low pressure drop conditions, which affects the quality of atomization.
Furthermore, the injection pattern of the centrifugal injector and the design of the combustion chamber can have a critical influence on combustion and cooling, and there is a severe coupling relationship. If the atomization and mixing are insufficient, the performance of the engine is necessarily greatly reduced, and if the combustion temperature distribution is not reasonable or the cooling is insufficient, the local high temperature of the combustion chamber is caused, and the service life is further influenced.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the space two-component rail control engine based on the two-way single-nozzle centrifugal injector and the molybdenum silicide composite coating thrust chamber is provided.
The technical scheme of the invention is as follows: a space two-component rail control engine based on a two-way single-nozzle centrifugal injector comprises a control valve, an injector, a thrust chamber and a temperature control device; the control valve is connected with the injector and is used for respectively controlling the supply on-off of the oxidant and the combustion agent; the injector adopts a structure of an inner nozzle and an outer nozzle coaxial embedded rotational flow cavity, oxidant and combustion agent are injected into a thrust chamber connected with the injector, and a temperature control device provides temperature guarantee for the engine so as to maintain the normal state of the propellant.
Further, the injector comprises a mounting connection plate, a main body structure, an inner nozzle and an outer nozzle; the mounting connecting plate is connected with the main body structure, and the main body structure is used for providing connection interfaces of the inner nozzle, the outer nozzle and the control valve; the inner nozzle and the outer nozzle are both hollow cylinders with vortex cavities, one side of the top end of each hollow cylinder is provided with a ring of annular grooves, and a plurality of tangential holes are uniformly distributed in each annular groove; the inner nozzle and the outer nozzle are contracted at a certain angle at the bottom of the swirling flow cavity to finally form a cylindrical nozzle which is communicated with the external environment; the inner nozzle is coaxially arranged in the inner cavity of the outer nozzle and fixed to form an inner nozzle and outer nozzle assembly.
Furthermore, the mounting connecting plate is a hollow circular plate with a mounting hole, and the top end of the main body structure is inserted into the central hollow part of the mounting connecting plate and connected with the central hollow part; the main structure is a cylinder with a central hole at the top end and the bottom end respectively, and a cylindrical table with a central hole is arranged at each of the two sides; a positioning step is arranged in the center hole at the bottom end of the main body structure and outside the cylinder; an inner nozzle assembly and an outer nozzle assembly which are composed of an inner nozzle and an outer nozzle are arranged from a central hole at the bottom of the main body structure, and are tightly pressed on and fixed on a hollow positioning step of the main body structure; the cylindrical platforms with central holes at two sides of the main body structure are respectively butted and fixed with the outlets of the two control valves.
Furthermore, the top end of the main body structure is inserted into the central hollow part of the mounting connection plate and is fixed by electron beam welding; the inner nozzle assembly and the outer nozzle assembly are tightly pressed on the hollow positioning step of the main body structure and are fixed through electron beam welding.
Further, the adjustment of the injector inner path flow is controlled by the diameter of the inner nozzle tangential hole, and the adjustment of the outer path flow is controlled by the diameter of the outer nozzle tangential hole.
Further, the angle of the atomizer inner path atomization angle is controlled by the length of the inner nozzle opening, and the angle of the outer path atomization angle is controlled by the length of the outer nozzle opening.
Further, the injector adopts an all-electron beam welding structure.
Further, the thrust chamber is connected with the injector through electron beam welding, and the temperature control device is connected with the injector through laser welding.
Further, the thrust chamber comprises a combustion chamber and a nozzle; the combustion chamber is a hollow thin-wall revolving body, one end with a small diameter is a straight cylindrical cylinder with equal wall thickness, the wall thickness meets the strength design requirement, the top is provided with a step, the combustion chamber is in butt joint and sliding fit with the step outside the main structure cylinder and is connected with the step through electron beam welding, the diameter of the other end of the cylinder with the equal wall thickness is gradually reduced, the diameter of the throat position reaches the minimum, the diameter of the revolving body is gradually expanded and increased after passing through the throat, and the combustion chamber is connected with the spray pipe through the electron beam welding; the nozzle is a Laval nozzle which is a thin-wall bell-shaped revolving body, according to the design of a maximum thrust molded line, one end with a small diameter is welded and connected with one end with a large diameter of the combustion chamber through an electron beam, the wall thickness of the welding end is 1-2 mm, the wall thickness is gradually reduced along with the gradual increase of the bell-shaped diameter, and the thickness of the other end is 0.4-0.6 mm.
Furthermore, the surface of the combustion chamber is coated with a coating which is a high-temperature-resistant and oxidation-resistant molybdenum silicide coating and is prepared by adopting a vacuum ion plating and silicification pack cementation method.
Furthermore, the characteristic length of the combustion chamber is more than 900 mm.
Furthermore, the injector is made of a titanium alloy material, and the thrust chamber base material is made of a niobium-tungsten alloy material.
Furthermore, the temperature control device comprises a heating device, a cover plate and a temperature measuring sensor; the heating device and the cover plate are arranged in the central hole of the main body structure from the central hole at the top, are flush with the top of the main body structure through the top of the cover plate and are fixed through laser welding; the temperature sensor is arranged at the upper end of the step outside the main structure cylinder body and is fixed by laser welding.
Furthermore, the heating device is a circular sheet type heater with a heating wire embedded inside, and a main backup heating wire is integrated for improving reliability.
Furthermore, the control valve is an electromagnetic valve or a self-locking valve product with a proper drift diameter.
Compared with the prior art, the invention has the beneficial effects that:
(1) the space double-component rail-controlled engine provided by the invention adopts a design structure of a large-diameter swirl cavity to improve swirl influence, so as to reduce the flow coefficient, increase the tangential component and ensure that the injector can realize stable liquid flow injection and atomization in a low-pressure-drop state.
(2) The injector of the spatial bipropellant rail-controlled engine provided by the invention is mainly used for realizing throttling by the tangential holes and the nozzles, and controlling the two paths of propellants of the oxidant and the combustion agent to be injected at reasonable speed and angle respectively through the lengths of the tangential holes and the nozzles, so that on one hand, the injection speed is adjusted, the momentum distribution of the sprayed liquid drops is controlled, the reasonable distribution ratio of cooling and combustion is realized, on the other hand, the injection angle is adjusted, the collision wall and the position of secondary mixing after the collision wall are determined, the combustion flame is close to the injection panel, and the thermal load of the throat is reduced. The hydraulic characteristics of the injector can be adjusted and controlled by a method of finishing the tangential holes, so that the injector can obtain better consistency and uniformity.
(3) According to the space double-component rail-controlled engine provided by the invention, the atomization angle of the injector can be controlled through the length of the nozzle, the length of the nozzle does not influence the flow pressure drop characteristic of the injector, and the atomization angle can be adjusted. The reduction of the length of the nozzle can improve the atomization angle, and the increase of the length of the nozzle can reduce the atomization angle.
(4) The space two-component rail-controlled engine provided by the invention only consists of one injection unit, namely one inner nozzle and one outer nozzle, which are of a coaxial embedded structure, so that the problem of combustion oscillation coupling of a plurality of injection units is solved, and the space two-component rail-controlled engine has good ignition stability.
(5) The space double-component rail-controlled engine provided by the invention adopts a large combustion space design, the length of a combustion chamber is increased, a part of space is reserved for wall collision, secondary atomization and diffusion mixing of liquid drops, and fuel gas has enough residence time to realize sufficient combustion.
(6) According to the space bipropellant rail-controlled engine provided by the invention, the surface of the combustion chamber is coated with the coating which is a high-temperature-resistant and oxidation-resistant molybdenum silicide coating, and the coating is prepared by adopting a vacuum ion plating and silicification pack infiltration method, so that the surface is compact and high in smoothness, secondary atomization and spreading of a cooling liquid film can be facilitated, the matching performance with a large-flow one-way centrifugal nozzle is better, and the secondary mixing effect after two kinds of propellant liquid drops collide with the wall is more ideal. The molybdenum silicide coating is applied to the combustion chamber of the high-temperature section, so that the temperature resistance of the material can be improved, and the allowable working temperature of the material is improved by over 100 ℃ compared with that of the traditional coating. In addition, the thrust chamber with the molybdenum silicide composite coating can provide a relatively smooth wall surface condition, avoids the phenomenon that the liquid drops are broken and burnt close to the wall after colliding with the wall, causes local high temperature of the combustion chamber, and has higher temperature resistance.
(7) The thermal control device of the space bipropellant rail control engine provided by the invention adopts an integrated and modularized design, the heating device is a disc heater with a heating wire embedded inside, and the main and standby heating wires are integrated, so that the temperature guarantee can be provided for the engine in a deep space environment, and the propellant is prevented from freezing. .
Drawings
FIG. 1 is a schematic structural diagram of a spatial two-component rail-controlled engine;
FIG. 2 is a schematic diagram of a two-way single-nozzle centrifugal injector;
FIG. 3 is a schematic view of a control valve mounting arrangement;
FIG. 4 is a schematic view of an oxidant flow channel configuration;
FIG. 5 is a schematic view of a combustion agent flow path configuration;
FIG. 6 is a schematic view of a thrust chamber;
FIG. 7 is a schematic view of a thermal control device mounting structure;
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
As shown in figure 1, the invention provides a space two-component rail control engine based on a two-way single-nozzle centrifugal injector and a molybdenum silicide composite coating thrust chamber, which comprises a mounting connection plate 1, a main body structure 2, an inner nozzle 3 and an outer nozzle 4, wherein the thrust chamber part comprises a combustion chamber 5, a spray pipe 6, a heating device 7, a cover plate 8, a temperature measuring sensor 9, a control valve 10 and a screw 11;
as shown in fig. 2, the mounting connection plate 1 is a hollow circular plate with a mounting hole, and the top end of the main structure 2 is inserted into the central hollow part of the mounting connection plate 1 and is fixedly connected with the mounting connection plate 1 through electron beam welding; the main structure 2 is a cylinder with a central hole at the top end and the bottom end respectively, and two sides of the main structure are respectively provided with a cylindrical table with a central hole; a positioning step is arranged in the center hole at the bottom end of the main body structure 2 and outside the cylinder; the inner nozzle 3 and the outer nozzle 4 are both hollow cylinders with vortex cavities, one side of the top end of each hollow cylinder is provided with a ring of annular grooves, and a plurality of tangential holes are uniformly distributed in each annular groove; the inner nozzle 3 and the outer nozzle 4 contract at a certain angle at the bottom of the rotational flow cavity to finally form a cylindrical nozzle communicated with the external environment; the outer cylinder of the inner nozzle 3 is provided with a positioning inner step, the positioning inner step is arranged from the top of the outer nozzle 4, the positioning step compresses the top end of the outer nozzle 4 and is fixed by electron beam welding to form an inner nozzle and outer nozzle assembly; an inner nozzle assembly and an outer nozzle assembly which are composed of an inner nozzle 3 and an outer nozzle 4 are installed from a central hole at the bottom of the main structure 2, are tightly pressed on a hollow positioning step of the main structure 2, and are fixed through electron beam welding.
As shown in fig. 3, a cylindrical table with a central hole is extended from each of the left and right sides of the main structure 2, and is respectively abutted with the outlets of two control valves 10, and is fixed by a plurality of screws 11, so that the control valves 10 are tightly connected with the main structure 2; the oxygen path and the fuel path control valves respectively control the on-off of the supply of the oxidant and the combustion agent, and once the valves are opened, the oxidant and the combustion agent enter the injector and the combustion chamber to perform mixed combustion and ignition operation. Wherein, the left oxygen passage control valve is communicated with the outer nozzle flow passage, and the right fuel passage control valve is communicated with the outer nozzle flow passage.
As shown in fig. 4, the oxidant enters the left central hole of the main structure 2 from the left control valve 10, passes through the annular channel of the outer nozzle 4, enters the uniformly distributed tangential holes in the annular groove to generate high-speed tangential velocity, enters the swirling cavity of the outer nozzle 4, and is finally ejected from the cylindrical nozzle consisting of the outer nozzle 4 and the inner nozzle 3.
As shown in fig. 5, the combustion agent enters the left central hole of the main structure 2 from the right control valve 10, passes through the annular groove flow channel of the inner nozzle 3, enters the uniformly distributed tangential holes in the annular groove to generate high-speed tangential velocity, enters the swirling flow cavity of the outer nozzle 3, and is finally ejected from the cylindrical nozzle of the inner nozzle 3.
As shown in fig. 6, the combustion chamber 5 is a revolving body with a hollow cavity, and the oxidant and the combustion agent sprayed from the injector enter a central control cavity of the combustion chamber to be atomized, mixed and combusted, so as to form high-temperature fuel gas. The small-diameter end of the combustion chamber 5 is a hollow straight-barrel-shaped cylinder with equal wall thickness, the wall thickness meets the strength design requirement, the top of the combustion chamber is provided with a positioning step, the combustion chamber is in butt joint and sliding fit with the lower edge of the positioning step outside the cylinder of the main structure 2, and the combustion chamber is connected with the cylinder of the main structure by electron beam welding. The diameter of the other end of the cylinder with the equal wall thickness is gradually reduced, the diameter of the cylinder reaches the minimum at the throat position, the diameter of the revolving body gradually expands and increases after passing through the throat, and the cylinder is connected with the spray pipe through electron beam welding; the spray pipe (6) is a Laval spray pipe, is a thin-wall bell-shaped revolving body, and is designed according to the maximum thrust profile, one end with a small diameter is welded and connected with one end with a large diameter of the combustion chamber (5) through an electron beam, the wall thickness of a welding end is relatively thick and can reach 1-2 mm, the wall thickness is gradually reduced along with the gradual increase of the bell-shaped diameter, and the thickness at the other end can reach 0.4-0.6 mm.
As shown in fig. 7, the heating device 7, the cover plate 8 are fitted into the central hole of the body structure 2 from the top central hole; the heating device 7 is a circular sheet type heater with a built-in heating wire, integrates a main backup heating wire, can provide temperature guarantee for the engine in a deep space environment, and prevents the propellant from freezing; the top of the cover plate 8 is flush with the top of the main body structure 2 and is fixed by laser welding, so that the deformation of other parts of the injector caused by welding heat can be avoided; the temperature measuring sensors 9 are installed on two sides of the upper end of the step outside the cylinder body of the main body structure 2, are fixed through laser welding, and can be used as a master part and a backup part respectively for detecting the heating effect of the heater and monitoring the ignition state of the engine.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (13)
1. A space two-component rail control engine based on a two-way single-nozzle centrifugal injector is characterized in that: the engine comprises a control valve, an injector, a thrust chamber and a temperature control device; the control valve is connected with the injector and is used for respectively controlling the supply on-off of the oxidant and the combustion agent; the injector adopts a structure of an inner nozzle and an outer nozzle coaxial embedded rotational flow cavity, an oxidant and a combustion agent are injected into a thrust chamber connected with the injector, and a temperature control device provides temperature guarantee for the engine so as to maintain the normal state of a propellant;
the injector comprises a mounting connection plate (1), a main body structure (2), an inner nozzle (3) and an outer nozzle (4); the mounting connection plate (1) is connected with the main body structure (2), and the main body structure (2) is used for providing connection interfaces of the inner nozzle (3), the outer nozzle (4) and the control valve; the inner nozzle (3) and the outer nozzle (4) are both hollow cylinders with vortex cavities, one side of the top end of each hollow cylinder is provided with a ring of annular grooves, and a plurality of tangential holes are uniformly distributed in the annular grooves; the inner nozzle (3) and the outer nozzle (4) contract at a certain angle at the bottom of the rotational flow cavity to finally form a cylindrical nozzle communicated with the external environment; the inner nozzle (3) is coaxially arranged in the inner cavity of the outer nozzle (4) and fixed to form an inner nozzle assembly and an outer nozzle assembly; the mounting connecting plate (1) is a hollow circular plate with a mounting hole, and the top end of the main body structure (2) is inserted into the central hollow part of the mounting connecting plate (1) and connected with the central hollow part; the main structure (2) is a cylinder with a central hole at the top end and the bottom end respectively, and a cylindrical table with a central hole is arranged at each of the two sides; a positioning step is arranged in the center hole at the bottom end of the main body structure (2) and outside the cylinder; an inner nozzle assembly and an outer nozzle assembly which are composed of an inner nozzle (3) and an outer nozzle (4) are installed from a central hole at the bottom of the main structure (2), and are tightly pressed on a hollow positioning step of the main structure (2) and fixed; the cylindrical platforms with central holes on the two sides of the main body structure (2) are respectively butted and fixed with the outlets of the two control valves.
2. The engine of claim 1, wherein: the top end of the main body structure (2) is inserted into the central hollow part of the mounting connection plate (1) and is fixed by electron beam welding; the inner nozzle assembly and the outer nozzle assembly are tightly pressed on the hollow positioning step of the main body structure (2) and are fixed through electron beam welding.
3. The engine of claim 1, wherein: the adjustment of the flow of the inner path of the injector is controlled by the diameter of the tangential hole of the inner nozzle (3), and the adjustment of the flow of the outer path is controlled by the diameter of the tangential hole of the outer nozzle (4).
4. The engine of claim 1, wherein: the angle of the inner path atomizing angle of the injector is controlled by the length of the nozzle of the inner nozzle (3), and the angle of the outer path atomizing angle is controlled by the length of the nozzle of the outer nozzle (4).
5. The engine of claim 1, wherein: the injector adopts an all-electronic beam welding structure.
6. The engine of claim 1, wherein: the thrust chamber is connected with the injector through electron beam welding, and the temperature control device is connected with the injector through laser welding.
7. The engine of claim 1, wherein: the thrust chamber comprises a combustion chamber (5) and a spray pipe (6);
the combustion chamber (5) is a hollow thin-wall revolving body, one end with a small diameter is a straight cylindrical cylinder with equal wall thickness, the wall thickness meets the strength design requirement, the top is provided with a step, the combustion chamber is in butt joint and sliding fit with the step outside the cylinder of the main body structure (2) and is connected with the step through electron beam welding, the diameter of the other end of the cylinder with the equal wall thickness is gradually reduced, the diameter of the throat position reaches the minimum, the diameter of the revolving body is gradually expanded and increased after passing through the throat, and the combustion chamber is connected with the spray pipe through electron; the nozzle (6) is a Laval nozzle which is a thin-wall bell-shaped revolving body, according to the design of a maximum thrust profile, one end with a small diameter is welded and connected with one end with a large diameter of the combustion chamber (5) through an electron beam, the wall thickness of a welding end is 1-2 mm, the wall thickness is gradually reduced along with the gradual increase of the diameter of the bell shape, and the thickness of the other end is 0.4-0.6 mm.
8. The engine according to claim 1 or 7, characterized in that: the surface of the combustion chamber (5) is coated with a coating which is a high-temperature-resistant and oxidation-resistant molybdenum silicide coating and is prepared by adopting a vacuum ion plating and silicification pack cementation method.
9. The engine according to claim 1 or 7, characterized in that: the characteristic length of the combustion chamber (5) is more than 900 mm.
10. The engine of claim 1, wherein: the injector is made of titanium alloy material, and the thrust chamber base material is made of niobium-tungsten alloy material.
11. The engine of claim 1, wherein: the temperature control device comprises a heating device (7), a cover plate (8) and a temperature measuring sensor (9);
the heating device (7) and the cover plate (8) are arranged in the center hole of the main body structure (2) from the center hole at the top, are flush with the top of the main body structure (2) through the top of the cover plate (8), and are fixed through laser welding; the temperature sensor (9) is arranged at the upper end of the step outside the cylinder body of the main body structure (2) and is fixed by laser welding.
12. The engine of claim 11, wherein: the heating device (7) is a circular sheet type heater with a heating wire embedded therein, and the main backup heating wire is integrated.
13. The engine according to claim 11 or 12, characterized in that: the control valve (10) is an electromagnetic valve or a self-locking valve product.
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| CN110259604B (en) * | 2019-06-17 | 2020-09-01 | 中国人民解放军国防科技大学 | Pintle injector |
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| CN110594044B (en) * | 2019-10-17 | 2022-03-18 | 哈尔滨工程大学 | Flexible extension spray tube with self-adaptive height |
| CN112177804B (en) * | 2020-09-16 | 2021-10-29 | 上海空间推进研究所 | Low-temperature engine suitable for space device |
| CN112196700B (en) * | 2020-09-16 | 2021-09-14 | 西安航天动力研究所 | Inner bottom structure for improving gas temperature uniformity of gas generator |
| CN113006969B (en) * | 2021-04-16 | 2021-11-23 | 西安航天动力研究所 | Gas-liquid injector for depth variable thrust rocket engine |
| CN113107710B (en) * | 2021-05-10 | 2023-10-20 | 苏州旗磐科技有限公司 | Low-thrust double-component attitude control engine |
| CN113740047B (en) * | 2021-09-22 | 2024-04-19 | 西安航天动力研究所 | Universal liquid flow test device suitable for outer nozzle in central nozzle assembly |
| CN114810420B (en) * | 2022-03-31 | 2023-09-26 | 中国人民解放军战略支援部队航天工程大学 | Central gas-liquid coaxial rotational flow model injector capable of measuring gas core pressure oscillation |
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