CN115263608A - Solid rocket engine - Google Patents
Solid rocket engine Download PDFInfo
- Publication number
- CN115263608A CN115263608A CN202211025500.1A CN202211025500A CN115263608A CN 115263608 A CN115263608 A CN 115263608A CN 202211025500 A CN202211025500 A CN 202211025500A CN 115263608 A CN115263608 A CN 115263608A
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- attitude control
- spray pipe
- control spray
- rocket engine
- combustion chamber
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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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/88—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using auxiliary rocket nozzles
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—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
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The present application provides a solid rocket engine comprising: an engine housing having a combustion chamber formed therein; the engine housing has a rear head; the main nozzle is arranged on the rear end socket and communicated with the combustion chamber; a plurality of attitude control nozzles; all the attitude control spray pipes are arranged on the rear end socket and are circumferentially distributed around the main spray pipe; the attitude control spray pipe is communicated with the combustion chamber; a first included angle is formed between the central axis of the attitude control spray pipe and the central axis of the main spray pipe; the posture control spray pipe is internally provided with a nozzle for controlling and the attitude control spray pipe is opened and closed. When the solid rocket engine is used, whether each attitude control spray pipe works or not and the conduction degree of each attitude control spray pipe can be controlled by controlling the state of each shut-off part, namely, the size of the cross section area conducted at the throat diameter is indirectly changed, so that the solid rocket engine has the characteristics of continuous variable thrust and 360-degree variable thrust attitude control.
Description
Technical Field
The application relates to the technical field of solid rocket engines, in particular to a solid rocket engine.
Background
Solid rocket engines (solidpropellantrinegenine) are chemical rocket engines that use solid propellants. Also known as solid propellant rocket engines. The solid propellant is ignited and then burnt in the combustion chamber, and chemical energy is converted into heat energy to generate combustion products with high temperature and high pressure. The combustion products flow through the nozzle where they expand and accelerate, and the thermal energy is converted to kinetic energy and expelled from the nozzle at high velocity to produce thrust.
The solid rocket engine consists of casing, explosive column, nozzle assembly, igniter, etc. The combustion chamber is formed in the shell, the explosive column is a hollow cylinder made of propellant and a small amount of additives, the explosive column is arranged in the combustion chamber, the ignition device is used for igniting the explosive column, and the spray pipe is positioned in the center of the tail of the shell and comprises a convergence part, a throat diameter part and an expansion part which are sequentially connected.
The thrust of the rocket engine is required to be changed when the rocket engine is used, the liquid rocket engine can be realized by adjusting the liquid flow, the throat diameter of the spray pipe is required to be adjusted when the thrust of the solid rocket engine is changed, the throat diameter is difficult to change, because the fuel in the combustion chamber generates high temperature exceeding 3000 ℃ during combustion, under the environment, the auxiliary device is required to be designed to realize the continuous adjustment of the throat diameter, and the continuous adjustment of the thrust of the solid rocket engine is hindered. To this end, the present application proposes a solid rocket engine.
Disclosure of Invention
The present application is directed to the above problems and provides a solid rocket engine.
The present application provides a solid rocket engine comprising:
an engine housing having a combustion chamber formed therein; the engine housing has a rear head;
the main nozzle is arranged on the rear seal head and communicated with the combustion chamber;
a plurality of attitude control nozzles; all the attitude control spray pipes are arranged on the rear seal head and are circumferentially distributed around the main spray pipes; the attitude control spray pipe is communicated with the combustion chamber; a first included angle is formed between the central axis of the attitude control spray pipe and the central axis of the main spray pipe; and a closing part for controlling the opening and closing of the attitude control spray pipe is arranged in the attitude control spray pipe.
According to a technical solution provided by some embodiments of the present application, the attitude control nozzle includes a nozzle housing; a convergent section, a throat diameter and an expansion section which are communicated in sequence are formed in the spray pipe shell; the expansion section is communicated with the outside; the convergent section is in communication with the combustion chamber.
According to the technical scheme provided by some embodiments of the application, the Guan Duanjian is a pintle structure; the pintle structure has a first end and a second end; the first end is positioned in the convergent section and can be inserted into the throat diameter to block the convergent section and the divergent section; the second end penetrates through one end, far away from the expansion section, of the spray pipe shell and is connected with the driving end of the linear driving device; the linear driving device is used for driving the pintle structure to reciprocate along the direction of the central axis of the attitude control spray pipe.
According to the technical solution provided by some embodiments of the present application, the first end includes a conical portion and a first cylindrical portion disposed at a large-diameter end of the conical portion; the second end includes a second cylindrical portion; the second cylindrical portion is disposed at an end of the first cylindrical portion away from the conical portion.
According to the technical scheme provided by some embodiments of the application, one end of the spray pipe shell, which is far away from the expansion section, is provided with a jack; the second cylindrical part is movably inserted in the jack; the diameter of the second cylindrical portion is smaller than the diameter of the first cylindrical portion; the diameter of the insertion hole is smaller than that of the first cylindrical portion.
According to the technical scheme provided by some embodiments of the application, a connecting pipe is further connected to the outside of the engine shell; one end of the connecting pipe is communicated with the convergent section, and the other end of the connecting pipe is communicated with the combustion chamber.
According to the technical scheme provided by some embodiments of the application, the rear end socket is provided with four attitude control spray pipes; the central angle corresponding to the two adjacent attitude control spray pipes is 90 degrees.
According to the technical solution provided by some embodiments of the present application, the angle of the first included angle is 90 °.
According to the technical scheme provided by some embodiments of the application, the switch-off piece is a solenoid valve switch.
Compared with the prior art, the beneficial effect of this application: the solid rocket engine provided by the invention has the advantages that the attitude control spray pipes are arranged on the rear end socket of the engine shell and are distributed in the circumferential direction, all the attitude control spray pipes are communicated with a combustion chamber, a first included angle is formed between the central axis of each attitude control spray pipe and the central axis of the main spray pipe, and a shutoff piece used for controlling whether the attitude control spray pipe works or not is arranged in each attitude control spray pipe; the solid rocket engine has rich use scenes, can be used for recovering and landing the aircraft, and can also be used for improving the maneuverability of the aircraft, thereby widening the use range of the solid rocket engine.
Drawings
FIG. 1 is a schematic view of a solid rocket engine provided in embodiment 1 of the present application;
fig. 2 is a schematic cross-sectional view of a solid rocket engine provided in embodiment 1 of the present application.
The text labels in the figures are represented as:
1. an engine housing; 101. a combustion chamber; 102. sealing the end; 103. a connecting pipe; 2. a main nozzle; 3. an attitude control spray pipe; 4. guan Duanjian.
Detailed Description
The following detailed description of the present application is given for the purpose of enabling those skilled in the art to better understand the technical solutions of the present application, and the description in this section is only exemplary and explanatory, and should not be taken as limiting the scope of the present application in any way.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
Example 1
Referring to fig. 1 and 2, the present embodiment provides a solid rocket engine, including:
an engine housing 1, in which a combustion chamber 101 is formed inside the engine housing 1; the engine housing 1 has a rear head 102;
the main nozzles 2 are arranged on the rear head 102 and communicated with the combustion chamber 101;
a plurality of attitude control nozzles 3; all the attitude control spray pipes 3 are arranged on the rear seal head 102 and are circumferentially distributed around the main spray pipes 2; the attitude control spray pipe 3 is communicated with the combustion chamber 101; a first included angle is formed between the central axis of the attitude control spray pipe 3 and the central axis of the main spray pipe 2; a shutoff part 4 for controlling the opening and closing of the attitude control spray pipe 3 is arranged in the attitude control spray pipe 3.
Specifically, the engine housing 1 is an approximately cylindrical housing structure, the inner wall of the engine housing is provided with a heat insulation layer, the engine housing 1 comprises a front head, a rear head 102 and a plurality of middle sections connected between the front head and the rear head 102, and the front head, the rear head 102 and the middle sections jointly enclose to form the combustion chamber 101; a grain is placed in the combustion chamber 101; the main nozzle 2 is mounted on the rear head 102 through a bolt, the central axis of the main nozzle 2 coincides with the central axis of the engine shell 1, and the main nozzle 2 is communicated with the combustion chamber 101; the specific structure of the main nozzle 2 is prior art and will not be described in detail here, and the main nozzle 2 is used to provide main thrust.
The rear end enclosure 102 is also provided with a plurality of attitude control spray pipes 3, and in the embodiment, a total of four attitude control spray pipes 3 are arranged; the four attitude control spray pipes 3 have the same structure; the four attitude control nozzles 3 are uniformly distributed around the main nozzles 2, and the four attitude control nozzles 3 are distributed on a circle; the four attitude control spray pipes 3 and the main spray pipes 2 share one combustion chamber 101; the central angle corresponding to two adjacent attitude control spray pipes 3 is 90 degrees; the external contour of the attitude control spray pipe 3 is a cylindrical contour, a first included angle is formed between the central axis of the attitude control spray pipe and the central axis of the main spray pipe 2, and the opening direction of the first included angle faces the direction departing from the rear end enclosure 102; preferably, the angle of the first included angle is 90 °, that is, the central axis of the attitude control nozzle 3 is perpendicular to the central axis of the engine housing 1, and the spraying end of the attitude control nozzle 3 is located at one end far away from the main nozzle 2; each attitude control nozzle 3 is internally provided with a shut-off part 4 which can control the opening and closing of the corresponding attitude control nozzle 3.
Further, the attitude control nozzle 3 comprises a nozzle shell; a convergent section, a throat diameter and an expansion section which are communicated in sequence are formed in the spray pipe shell; the expansion section is communicated with the outside; the convergent section communicates with the combustion chamber 101.
Specifically, the spray pipe shell is of a hollow cylindrical structure, one end of the spray pipe shell is of an open structure, and the other end of the spray pipe shell is of a closed structure; a convergent section, a throat diameter and an expansion section which are connected in sequence are formed in the spray pipe shell, wherein the small-diameter end of the convergent section is close to the small-diameter end of the expansion section, the large-diameter end of the convergent section is close to the closed end of the spray pipe shell, and the large-diameter end of the expansion section is close to the open end of the spray pipe shell; the junction of the convergent section and the divergent section forms a throat diameter, and the cross-sectional area of the throat diameter is the minimum area in the whole cavity.
Further, a connecting pipe 103 is connected to the outside of the engine housing 1; one end of the connecting pipe 103 is communicated with the convergent section, and the other end is communicated with the combustion chamber 101.
Specifically, the connecting pipe 103 is fixedly connected to the engine housing 1 through a bolt, a cavity inside the connecting pipe 103 communicates the combustion chamber 101 and a convergent section of the attitude control nozzle 3, and in this embodiment, the connecting pipe 103 is connected to a side wall of the convergent section.
Further, the shut-off member 4 is of a pintle structure; the pintle structure has a first end and a second end; the first end is positioned in the convergent section and can be inserted into the throat diameter to block the convergent section and the divergent section; the second end penetrates through one end, far away from the expansion section, of the spray pipe shell and is connected with the driving end of the linear driving device; the linear driving device is used for driving the pintle structure to reciprocate along the direction of the central axis of the attitude control spray pipe 3.
Specifically, a linear driving device is arranged outside the spray pipe shell, and the linear driving device can be an electric push rod; the linear driving device can be fixed on the rear seal head 102, or fixed on the outer wall of the main spray pipe 2, or fixed on the outer wall of the attitude control spray pipe 3; the linear driving device is connected with the controller; the driving end of the linear driving device is connected with a pintle structure; the pintle structure is a shutoff piece for controlling the posture control spray pipe to be opened and closed; the pintle structure is provided with a first end and a second end which are connected, the first end of the pintle structure is positioned in the convergent section, and the second end of the pintle structure extends out of the closed end of the spray pipe shell and is connected with the driving end of the linear driving device.
When the attitude control nozzle is required to be closed, the controller controls the linear driving device to extend out, so that the first end of the pintle structure is abutted against the throat diameter, and the convergent section and the divergent section of the attitude control nozzle are blocked; when the attitude control spray pipe needs to be opened, the controller controls the linear driving device to retract, so that the first end of the pintle structure is gradually separated from the throat diameter, and the convergence section and the expansion section of the attitude control spray pipe are communicated; the more the pintle structure moves towards the direction far away from the throat diameter, the larger the conduction area of the convergent section and the expansion section of the attitude control spray pipe is, and conversely, the smaller the conduction area of the convergent section and the expansion section of the attitude control spray pipe is, namely, the size of the conduction cross-sectional area at the throat diameter is indirectly changed by changing the position of the pintle structure.
Further, the first end comprises a conical part and a first cylindrical part arranged at the large-diameter end of the conical part; the second end includes a second cylindrical portion; the second cylindrical part is arranged at one end, far away from the conical part, of the first cylindrical part.
Specifically, the pintle structure comprises three parts, namely a conical part, a first cylindrical part and a second cylindrical part, which are coaxially and sequentially connected, the first cylindrical part is connected with the large-diameter end of the conical part, and the second cylindrical part movably extends out of the closed end of the spray pipe shell.
Furthermore, one end of the spray pipe shell, which is far away from the expansion section, is provided with a jack; the second cylindrical part is movably inserted in the jack; the diameter of the second cylindrical portion is smaller than the diameter of the first cylindrical portion; the diameter of the insertion hole is smaller than that of the first cylindrical portion.
Specifically, a jack is formed in the center of the closed end of the spray pipe shell; the second cylindrical portion movably penetrates through the insertion hole, the diameter of the second cylindrical portion is smaller than that of the first cylindrical portion, and the diameter of the insertion hole is smaller than that of the first cylindrical portion, so that a limiting blocking portion is formed at the end portion of the first cylindrical portion, and the pintle structure can be placed to be completely separated from the insertion hole.
When the solid rocket engine provided by the embodiment is used, the following three working modes are provided:
first, common solid rocket engine mode:
the mode control method is that the positions of the four pintle structures are controlled to enable the four attitude control spray pipes to be in a closed state at the same time, and at the moment, the effect of a common fixed spray pipe solid rocket engine is reflected.
Second, 360-degree variable thrust attitude control and continuous variable thrust solid rocket engine modes:
the control method of the modality comprises the following steps: controlling any one of the four attitude control spray pipes to work, and keeping the other three in a closed state; or two attitude control spray pipes in opposite positions among the four attitude control spray pipes are controlled to work, and the positions of pintle structures in the four attitude control spray pipes are different; or controlling any one of the four attitude control spray pipes to be closed, wherein the other three attitude control spray pipes are all in a working state, and the positions of pintle structures in two attitude control spray pipes in opposite positions in the three attitude control spray pipes are the same; or controlling all four attitude control spray pipes to work, wherein the positions of the pintle structures in only one group of attitude control spray pipes in the relative positions are the same; the four conditions show the attitude control capability of changing the thrust along four directions, and the main thrust of the engine is adjusted.
The control method of the modality further includes: any two adjacent attitude control spray pipes in the four attitude control spray pipes are controlled to work, and the other two attitude control spray pipes do not work; or any three of the four attitude control spray pipes are controlled to work, the other one does not work, and the positions of the pintle structures in the two attitude control spray pipes which are in opposite positions in the three working attitude control spray pipes are different; or the four attitude control spray pipes are controlled to work, and the positions of the pintle structures in the four attitude control spray pipes are different from each other, so that the attitude control capability of changing the direction and the thrust is embodied under the three conditions, and the main thrust of the engine is adjusted.
Third, a continuous variable thrust solid rocket engine mode:
the control method of the modality comprises the following steps: controlling two attitude control spray pipes in opposite positions to work in the four attitude control spray pipes, wherein the positions of pintle structures in the two attitude control spray pipes are the same; or the four attitude control spray pipes are controlled to work completely, and the positions of the pintle structures in the two attitude control spray pipes which are positioned in opposite positions in the four attitude control spray pipes are the same, so that the adjustment of the main thrust of the engine is reflected in the two conditions.
When the attitude control jet pipe is used, the corresponding control mode of the attitude control jet pipe can be selected according to actual needs, and the engine is set in one or more working modes.
Example 2
The present embodiment provides another solid rocket engine, and the same parts of the solid rocket engine provided in the present embodiment and the solid rocket engine in embodiment 1 are not repeated, and the differences are only that: the switch-off part 4 is a solenoid valve switch; the electromagnetic valve switch is arranged at the throat diameter and is connected with the controller.
When the solid rocket engine provided by the embodiment is used, the following three working modes are provided:
first, common solid rocket engine mode:
the mode control method is that four electromagnetic valve switches are controlled to enable the four attitude control spray pipes to be in a closed state at the same time, and at the moment, the effect of the common fixed spray pipe solid rocket engine is reflected.
Second, 8 direction attitude control, three-stage variable thrust solid rocket engine modes:
the control method of the modality comprises the following steps: controlling any one of the four attitude control spray pipes to work, and keeping the other three in a closed state; or controlling any one of the four attitude control spray pipes to be closed, and controlling the other three spray pipes to be in a working state; in the two situations, the attitude control capability along four directions is reflected, and the main thrust of the engine is adjusted.
The control method of the modality further includes: any two adjacent attitude control spray pipes in the four attitude control spray pipes are controlled to work, and the other two do not work; at the moment, the attitude control capability in the 45-degree direction is embodied, and the main thrust of the engine is adjusted.
Third and second stage variable thrust solid rocket engine modes:
the control method of the modality comprises the following steps: controlling two attitude control spray pipes in opposite positions of the four attitude control spray pipes to work; or the four attitude control spray pipes are controlled to work completely, and the main thrust of the engine is adjusted under the two conditions.
It should be noted that, in the present application, the two nozzles in opposite positions refer to two attitude control nozzles that are not adjacent to each other, the two attitude control nozzles are symmetrically arranged with respect to the main nozzle, and a connection line of the two attitude control nozzles passes through the main nozzle.
When the attitude control jet pipe is used, the corresponding control mode of the attitude control jet pipe can be selected according to actual needs, and the engine is set in one or more working modes.
The application provides a solid rocket engine, through set up a plurality of attitude control spray pipes that are distributed in the circumference at the back head of engine housing, each attitude control spray pipe all is linked together with the combustion chamber, the central axis of each attitude control spray pipe forms first contained angle with the central axis of main spray pipe, and each attitude control spray pipe is equipped with the shutoff piece that is used for controlling whether this attitude control spray pipe works in, when using, can control whether the work of each attitude control spray pipe is in order to control through the state of controlling each shutoff piece, and the conduction degree of each attitude control spray pipe, the size of the cross-sectional area that has been switched on in throat department has been changed indirectly, make this solid rocket engine have the characteristics of continuous variable thrust and 360 degrees variable thrust attitude control.
The solid rocket engine provided by the application has rich use scenes, can be used for recovering and landing the aircraft, and can also be used for improving the maneuvering capability of the aircraft, thereby widening the use range of the solid rocket engine.
The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are no specific structures which are objectively limitless due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes can be made without departing from the principle of the present invention, and the technical features mentioned above can be combined in a suitable manner; such modifications, decorations, variations or combinations, or direct application of the inventive concepts and solutions to other applications without modification, are intended to be within the scope of the present application.
Claims (9)
1. A solid rocket engine, comprising:
an engine case (1) in which a combustion chamber (101) is formed inside the engine case (1); the engine housing (1) has a rear head (102);
the main nozzle (2) is arranged on the rear seal head (102) and communicated with the combustion chamber (101);
a plurality of attitude control spray pipes (3); all the attitude control spray pipes (3) are arranged on the rear seal head (102) and are circumferentially distributed around the main spray pipe (2); the attitude control spray pipe (3) is communicated with the combustion chamber (101); a first included angle is formed between the central axis of the attitude control spray pipe (3) and the central axis of the main spray pipe (2); and a Guan Duanjian (4) used for controlling the opening and closing of the attitude control spray pipe (3) is arranged in the attitude control spray pipe (3).
2. A solid-rocket engine according to claim 1, wherein said attitude control nozzle (3) comprises a nozzle housing; a convergent section, a throat diameter and an expansion section which are communicated in sequence are formed in the spray pipe shell; the expansion section is communicated with the outside; the convergent section communicates with the combustion chamber (101).
3. The solid-rocket engine of claim 2, wherein the Guan Duanjian (4) is a pintle structure; the pintle structure has a first end and a second end; the first end is positioned in the convergent section and can be inserted into the throat diameter to block the convergent section and the divergent section; the second end penetrates through one end, far away from the expansion section, of the spray pipe shell and is connected with the driving end of the linear driving device; the linear driving device is used for driving the pintle structure to reciprocate along the direction of the central axis of the attitude control spray pipe (3).
4. A solid-rocket engine as recited in claim 3, wherein said first end includes a conical portion and a first cylindrical portion disposed at a larger diameter end of said conical portion; the second end includes a second cylindrical portion; the second cylindrical part is arranged at one end, far away from the conical part, of the first cylindrical part.
5. A solid rocket engine as recited in claim 4, wherein an end of said nozzle housing remote from said diverging section defines a socket; the second cylindrical part is movably inserted in the jack; the diameter of the second cylindrical portion is smaller than the diameter of the first cylindrical portion; the diameter of the insertion hole is smaller than that of the first cylindrical portion.
6. A solid rocket engine according to claim 2, characterized in that a connecting pipe (103) is further connected to the outside of the engine case (1); one end of the connecting pipe (103) is communicated with the convergent section, and the other end of the connecting pipe is communicated with the combustion chamber (101).
7. A solid-rocket engine according to claim 1, characterized in that said rear head (102) is provided with a total of four attitude control nozzles (3); the central angle corresponding to the two adjacent attitude control spray pipes (3) is 90 degrees.
8. A solid rocket engine as recited in claim 1, wherein said first included angle is 90 °.
9. The solid-rocket engine of claim 1, wherein the Guan Duanjian (4) is a solenoid valve switch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211025500.1A CN115263608A (en) | 2022-08-25 | 2022-08-25 | Solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211025500.1A CN115263608A (en) | 2022-08-25 | 2022-08-25 | Solid rocket engine |
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| Publication Number | Publication Date |
|---|---|
| CN115263608A true CN115263608A (en) | 2022-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211025500.1A Pending CN115263608A (en) | 2022-08-25 | 2022-08-25 | Solid rocket engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116220952A (en) * | 2023-05-06 | 2023-06-06 | 北京星河动力装备科技有限公司 | Nozzle, rocket engine and carrier rocket |
-
2022
- 2022-08-25 CN CN202211025500.1A patent/CN115263608A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116220952A (en) * | 2023-05-06 | 2023-06-06 | 北京星河动力装备科技有限公司 | Nozzle, rocket engine and carrier rocket |
| CN116220952B (en) * | 2023-05-06 | 2023-09-05 | 北京星河动力装备科技有限公司 | Nozzle, rocket engine and carrier rocket |
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