CN117128107A - Dual-mode knocking thrust chamber - Google Patents
Dual-mode knocking thrust chamber Download PDFInfo
- Publication number
- CN117128107A CN117128107A CN202311132488.9A CN202311132488A CN117128107A CN 117128107 A CN117128107 A CN 117128107A CN 202311132488 A CN202311132488 A CN 202311132488A CN 117128107 A CN117128107 A CN 117128107A
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- Prior art keywords
- detonation
- inner shell
- thrust chamber
- shell
- detonation tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000005474 detonation Methods 0.000 claims abstract description 66
- 238000002485 combustion reaction Methods 0.000 claims abstract description 53
- 239000000446 fuel Substances 0.000 claims abstract description 39
- 239000007800 oxidant agent Substances 0.000 claims abstract description 31
- 230000001590 oxidative effect Effects 0.000 claims abstract description 31
- 238000001816 cooling Methods 0.000 claims abstract description 12
- 238000004880 explosion Methods 0.000 claims description 33
- 230000005284 excitation Effects 0.000 claims description 19
- 230000009977 dual effect Effects 0.000 claims description 11
- 238000002347 injection Methods 0.000 claims description 9
- 239000007924 injection Substances 0.000 claims description 9
- 239000012530 fluid Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000011084 recovery Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000005422 blasting Methods 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The application provides a dual-mode knocking thrust chamber, which belongs to the technical field of thrust chambers and comprises an inner shell and an outer shell, wherein a cooling channel is formed between the inner shell and the outer shell, a combustion chamber of the thrust chamber is formed in a head area inside the inner shell, a nozzle of the thrust chamber is formed in a tail area inside the inner shell, annular inner columns are arranged at the heads of the inner shell and the outer shell and penetrate through the inner shell and the outer shell, an oxidant nozzle is arranged at one end of the annular inner columns, which is positioned inside the inner shell, a fuel nozzle is arranged inside the inner shell, and a fuel inlet communicated with the cooling channel is arranged at the tail parts of the inner shell and the outer shell; the inner shell and the outer shell which are positioned at one side of the combustion chamber are provided with pre-detonation tubes for exciting continuous rotary detonation. By the treatment scheme, the thrust adjustment range of the rocket engine thrust chamber is improved, the combustion efficiency of the rocket engine thrust chamber under the low working condition is improved, and the specific impulse is improved.
Description
Technical Field
The application relates to the technical field of thrust chambers, in particular to a dual-mode knocking thrust chamber.
Background
The Thrust chamber (Thrust chamber) of a rocket engine is a key component in a rocket engine for generating Thrust and propelling the rocket. A thrust chamber is a device that converts high pressure and high temperature combustion products into a high velocity jet stream.
The thrust chamber is typically comprised of a combustion chamber and a nozzle. The combustion chamber is the area where fuel and oxidant mix and burn. In the combustion chamber, fuel and oxidant are injected and mixed for combustion in a proper ratio. The high temperature and pressure gases produced by such combustion release significant energy and produce high temperature and pressure combustion products, such as combustion gases and combustion residues. The nozzle is an outlet portion of the thrust chamber for ejecting the high pressure combustion products to generate thrust.
The working principle of the thrust chamber is based on newton's third law, i.e. each force has a reaction force of equal magnitude but opposite direction. The high-pressure combustion products generated in the combustion chamber are ejected out through the nozzle at a high speed, and the generated reaction force is thrust, so that the rocket is pushed to move forward.
The design and performance of the thrust chamber have important influences on parameters such as the thrust, combustion efficiency, fuel consumption rate and the like of the rocket. Thus, the design of the thrust chamber requires consideration of a number of factors, such as fuel selection, nozzle shape, cooling system, material high temperature resistance, and the like. By optimizing the design of the thrust chamber, the performance and efficiency of the rocket engine can be improved, and higher thrust and more effective carrying capacity are realized.
The repeated recovery rocket technology puts higher demands on the depth variable pushing requirements of the liquid rocket engine. The repeatedly recovered rocket is a rocket which can be used for multiple times, and the cost of the space mission is reduced and the sustainability is improved through recovery and reutilization. Depth-varying pushing is critical to repeated rocket recovery. Depth rolling (Deep rolling) of liquid rocket engines refers to achieving accurate adjustment of thrust over a wide range, including real-time adjustability from maximum thrust to smaller thrust. Depth-varying thrusting is very important to rocket flexibility and application scope, but achieving depth-varying thrusting also presents some difficulties and challenges.
On the one hand, when the thrust of the liquid rocket engine is reduced, the flow rates of fuel and oxidant in the combustion chamber are reduced, which may lead to unstable combustion. Under low thrust conditions, the mixing and combustion process of the fuel and oxidant is more susceptible to disturbances such as turbulence and vibration. Thus, ensuring stability of combustion at low thrust is a challenge. On the other hand, under low working conditions, the pressure in the combustion chamber is low, and the combustion chamber and the nozzle are mainly optimized aiming at the design working conditions, so that the specific impulse of the thrust chamber is extremely low under the low working conditions.
Disclosure of Invention
In view of the above, the embodiment of the application provides a dual-mode detonation thrust chamber, which at least partially solves the problems of unstable combustion and low specific impulse of a rocket engine in the prior art.
The embodiment of the application provides a dual-mode knocking thrust chamber, which comprises an inner shell and an outer shell, wherein a cooling channel is formed between the inner shell and the outer shell, a combustion chamber of the thrust chamber is formed by a head area inside the inner shell, a nozzle of the thrust chamber is formed by a tail area inside the inner shell, annular inner columns are arranged at the heads of the inner shell and the outer shell and penetrate through the inner shell and the outer shell, an oxidant nozzle is arranged at one end of the annular inner columns, which is positioned at the inner side of the inner shell, a fuel nozzle is arranged at the inner side of the inner shell, and a fuel inlet communicated with the cooling channel is arranged at the tail parts of the inner shell and the outer shell;
the inner shell and the outer shell which are positioned at one side of the combustion chamber are provided with pre-detonation tubes for exciting continuous rotary detonation.
According to a specific implementation manner of the embodiment of the application, the pre-explosion tube is arranged to be of a hollow structure, one end of the pre-explosion tube penetrates through the outer shell and the inner shell, the hollow structure is communicated with a fluid circulation space of the combustion chamber, an ignition member is arranged at the other end of the pre-explosion tube, a pre-explosion tube fuel inlet and a pre-explosion tube oxidant inlet which are not communicated with each other are arranged at positions, close to the ignition member, on the pre-explosion tube, and an excitation step is arranged on the inner wall of the pre-explosion tube.
According to a specific implementation manner of the embodiment of the application, the pre-explosion tube fuel inlet and the pre-explosion tube oxidant inlet are oppositely arranged on the pre-explosion tube.
According to a specific implementation manner of the embodiment of the application, the excitation step is arranged below the pre-explosion tube fuel inlet and the pre-explosion tube oxidant inlet, the excitation step is arranged in a circumferential annular manner along the inner wall of the pre-explosion tube, and the excitation step is arranged into a step structure protruding towards the central axis of the pre-explosion tube along the inner wall of the pre-explosion tube.
According to a specific implementation manner of the embodiment of the application, a plurality of excitation steps are uniformly arranged along the length direction of the pre-detonation tube.
According to a specific implementation manner of the embodiment of the application, the pre-explosion tube is provided with a high-frequency pressure sensor, and the high-frequency pressure sensor is arranged at one end of the pre-explosion tube, which is close to the combustion chamber.
According to a specific implementation of an embodiment of the application, the axis of the annular inner post coincides with the axis of the inner housing.
According to a specific implementation manner of the embodiment of the application, a plurality of oxidant nozzles are uniformly arranged on the side wall of the annular inner column.
According to a specific implementation of an embodiment of the application, the injection direction of the oxidant nozzle is perpendicular to the injection direction of the fuel nozzle.
According to a specific implementation of an embodiment of the application, the ignition member is provided as a spark plug.
Advantageous effects
According to the dual-mode detonation thrust chamber provided by the embodiment of the application, the pre-detonation tube is arranged, when the thrust chamber works under a low working condition, an excitation instruction can be sent to the pre-detonation tube, and continuous rotary detonation combustion is generated in the excitation thrust chamber, so that the thrust regulation range of the rocket engine thrust chamber is improved, the combustion efficiency of the rocket engine thrust chamber under the low working condition is improved, and the specific impulse can be improved due to the self-pressurization effect of the continuous rotary detonation combustion.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a dual mode detonation thrust chamber according to an embodiment of the present application;
FIG. 2 is an enlarged view of a combustion chamber of a dual mode detonation thrust chamber according to an embodiment of the present application.
In the figure: 1. an inner housing; 2. an outer housing; 3. pre-bursting tube; 31. a pre-detonation tube fuel inlet; 32. a spark plug; 33. pre-detonation tube oxidant inlet; 34. exciting the step; 35. a high frequency pressure sensor; 4. a cooling channel; 5. a detonation combustion zone; 6. an annular inner column; 7. an oxidant nozzle; 8. a fuel nozzle; 9. a fuel inlet.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
Embodiments of the present application provide a dual mode detonation thrust chamber, described in detail below with reference to fig. 1 and 2.
In this embodiment, the dual-mode detonation thrust chamber includes an inner casing 1 and an outer casing 2, a cooling channel 4 is formed between the inner casing 1 and the outer casing 2, a head area inside the inner casing 1 forms a combustion chamber of the thrust chamber, a tail area inside the inner casing 1 forms a nozzle of the thrust chamber, the heads of the inner casing 1 and the outer casing 2 are provided with annular inner columns 6, the annular inner columns 6 penetrate through the inner casing 1 and the outer casing 2, one end of the annular inner columns 6 located inside the inner casing 1 is provided with an oxidant nozzle 7, the inside of the inner casing 1 is provided with a fuel nozzle 8, and the tail parts of the inner casing 1 and the outer casing 2 are provided with a fuel inlet 9 communicated with the cooling channel 4; the inner shell 1 and the outer shell 2 positioned at one side of the combustion chamber are provided with pre-explosion tubes 3 for exciting continuous rotary knocking.
In specific implementation, the detonation combustion zone 5 is formed by the inner shell 1, the annular inner column 6 and the part formed between the connection part of the pre-detonation tube 3 and the combustion chamber, fuel enters from the fuel inlet at the tail part and flows through the cooling channel 4 to the fuel nozzle 8 at the head part for ejection, and the fuel can have a cooling effect on the inner shell 1 of the thrust chamber.
In practice, the shape and design of the nozzle has a significant impact on rocket engine performance. The nozzles are typically tapered or flared, known as nozzles (nozzles), and in this embodiment the nozzles are in the form of cornell nozzles (conversion-conversion nozzles). The structure of the kanell nozzle consists of a converging section and a diverging section. The converging section accelerates the gas flow and increases the pressure of the gas, while the diverging section continues to expand and accelerate the gas flow to increase the injection velocity and produce more thrust.
In one embodiment, the pre-explosion tube 3 is provided with a hollow structure, one end of the pre-explosion tube 3 penetrates through the outer shell 2 and the inner shell 1, the hollow structure is communicated with the fluid circulation space of the combustion chamber, the other end of the pre-explosion tube 3 is provided with an ignition member, a pre-explosion tube fuel inlet 31 and a pre-explosion tube oxidant inlet 33 which are not communicated with each other are arranged on the pre-explosion tube 3 at positions close to the ignition member, and an excitation step 34 is arranged on the inner wall of the pre-explosion tube 3.
In order to fully mix the fuel and the oxidant for blasting, the pre-squib fuel inlet 31 and the pre-squib oxidant inlet 33 are arranged opposite to each other on the pre-squib 3. Specifically, the length direction of the pre-detonation tube 3 is perpendicular to the axis direction of the combustion chamber, the ignition member is located at the top end of the pre-detonation tube 3, and the pre-detonation tube fuel inlet 31 and the pre-detonation tube oxidant inlet 33 are located below the ignition member and are located on both sides in the width direction of the pre-detonation tube 3, respectively.
Preferably, the excitation step 34 is disposed below the pre-detonation tube fuel inlet 31 and the pre-detonation tube oxidant inlet 33, the excitation step 34 is disposed in a circumferential annular manner along the inner wall of the pre-detonation tube 3, and the excitation step 34 is disposed in a step structure protruding toward the central axis of the pre-detonation tube 3 along the inner wall of the pre-detonation tube 3.
Further, the excitation steps 34 are uniformly arranged along the length direction of the pre-explosion tube 3.
The principle of exciting the step 34 is: when continuous rotary knocking needs to be excited, a small amount of oxidant and fuel enter the pre-detonation tube 3, and after being ignited by the ignition component, pulse detonation waves are generated under the action of the excitation step 34 of the pre-detonation tube 3, so that the continuous rotary knocking in the combustion chamber is excited.
Further, a high-frequency pressure sensor 35 is arranged on the pre-explosion tube 3, and the high-frequency pressure sensor 35 is arranged at one end of the pre-explosion tube 3 close to the combustion chamber. In specific implementation, the pre-explosion tube 3 and the high-frequency pressure sensor 35 are respectively connected with a control system, the high-frequency pressure sensor 35 is used for monitoring the stability of continuous rotary knocking in the combustion chamber, and when the combustion chamber is in explosion, the control system excites the rotary knocking again through the pre-explosion tube 3, so that the combustion chamber can burn stably.
In one embodiment, the axis of the annular inner post 6 coincides with the axis of the inner housing 1. In this embodiment, the annular inner column 6 has a cavity structure with one end open, the open side faces the outside, the side opposite to the opening is located inside the combustion chamber, the oxidant nozzles 7 are located on the side wall of the annular inner column 6, and the oxidant nozzles 7 are uniformly provided in plurality. In this embodiment, the injection direction of the oxidant nozzle 7 is perpendicular to the central axis of the annular inner column 6.
Further, the injection direction of the oxidant nozzle 7 is perpendicular to the injection direction of the fuel nozzle 8, in this embodiment, the fuel nozzle 8 is located on the head side of the inner housing 1, and the injection direction of the fuel nozzle 8 is parallel to the central axis of the annular inner post 6.
In the above embodiment, the ignition member is provided as the ignition plug 32, and the oxidant and fuel used for the thrust chamber may be liquid and gaseous.
The thrust chamber has two modes, namely ordinary combustion is adopted when the thrust chamber works under higher working conditions and design working conditions (preferably, the thrust percentage is 40% -110%), namely, the pre-detonation tube 3 is not required to work at the moment. And in the second mode, knocking combustion is performed, when the thrust chamber works under a low working condition (preferably, the thrust percentage is less than 40%), the control system sends an excitation instruction to the pre-explosion tube 3, and continuous rotary knocking combustion is generated in the thrust chamber.
According to the embodiment provided by the application, the pre-detonation tube 3 is arranged at the combustion chamber part, and the pre-detonation tube 3 is controlled to excite rotary detonation under the low working condition of the thrust chamber, so that continuous rotary detonation combustion is generated in the thrust chamber, and the adjustment capability of depth variable pushing is realized; under the low working condition, the specific impulse can be improved due to the self-pressurization effect of continuous rotary detonation combustion.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (10)
1. The dual-mode knocking thrust chamber is characterized by comprising an inner shell (1) and an outer shell (2), wherein a cooling channel (4) is formed between the inner shell (1) and the outer shell (2), a combustion chamber of the thrust chamber is formed by a head area inside the inner shell (1), a nozzle of the thrust chamber is formed by a tail area inside the inner shell (1), annular inner columns (6) are arranged at the heads of the inner shell (1) and the outer shell (2), the annular inner columns (6) penetrate through the inner shell (1) and the outer shell (2), an oxidant nozzle (7) is arranged at one end, located inside the inner shell (1), of the inner shell (1), a fuel nozzle (8) is arranged at the inner side of the inner shell (1), and a fuel inlet (9) communicated with the cooling channel (4) is arranged at the tail parts of the inner shell (1) and the outer shell (2);
the inner shell (1) and the outer shell (2) which are positioned at one side of the combustion chamber are provided with pre-explosion pipes (3) for exciting continuous rotary knocking.
2. The dual-mode detonation thrust chamber as claimed in claim 1, wherein the pre-detonation tube (3) is provided with a hollow structure, one end of the pre-detonation tube (3) penetrates through the outer shell (2) and the inner shell (1), the hollow structure is communicated with a fluid circulation space of the combustion chamber, an ignition member is arranged at the other end of the pre-detonation tube (3), a pre-detonation tube fuel inlet (31) and a pre-detonation tube oxidant inlet (33) which are not communicated with each other are arranged on the pre-detonation tube (3) at positions close to the ignition member, and an excitation step (34) is arranged on the inner wall of the pre-detonation tube (3).
3. The dual mode detonation thrust chamber of claim 2 wherein said pre-detonation tube fuel inlet (31) and said pre-detonation tube oxidant inlet (33) are oppositely disposed on said pre-detonation tube (3).
4. The dual mode detonation thrust chamber of claim 2 wherein said excitation step (34) is disposed below said pre-detonation tube fuel inlet (31) and said pre-detonation tube oxidant inlet (33), said excitation step (34) being circumferentially disposed annularly along an inner wall of said pre-detonation tube (3), said excitation step (34) being disposed as a stepped structure protruding along an inner wall of said pre-detonation tube (3) toward a central axis of said pre-detonation tube (3).
5. The dual mode detonation thrust chamber according to claim 4, wherein said excitation steps (34) are uniformly provided in plurality along the length direction of said pre-detonation tube (3).
6. The dual mode detonation thrust chamber of claim 1 wherein a high frequency pressure sensor (35) is provided on said pre-detonation tube (3), said high frequency pressure sensor (35) being disposed at an end of said pre-detonation tube (3) proximate to said combustion chamber.
7. The dual mode detonation thrust chamber according to claim 1, characterized in that the axis of the annular inner post (6) coincides with the axis of the inner housing (1).
8. The dual mode detonation thrust chamber according to claim 1, wherein said oxidant nozzles (7) are uniformly provided in plurality on the side wall of said annular inner column (6).
9. The dual mode detonation thrust chamber of claim 8 wherein the injection direction of the oxidant nozzle (7) and the injection direction of the fuel nozzle (8) are perpendicular.
10. The dual mode detonation thrust chamber of any of claims 2-5 wherein said ignition member is provided as a spark plug (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311132488.9A CN117128107A (en) | 2023-09-04 | 2023-09-04 | Dual-mode knocking thrust chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311132488.9A CN117128107A (en) | 2023-09-04 | 2023-09-04 | Dual-mode knocking thrust chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117128107A true CN117128107A (en) | 2023-11-28 |
Family
ID=88852517
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311132488.9A Pending CN117128107A (en) | 2023-09-04 | 2023-09-04 | Dual-mode knocking thrust chamber |
Country Status (1)
| Country | Link |
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| CN (1) | CN117128107A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117846819A (en) * | 2024-03-05 | 2024-04-09 | 北京大学 | Pre-detonation tube device of continuous detonation engine and control method thereof |
-
2023
- 2023-09-04 CN CN202311132488.9A patent/CN117128107A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117846819A (en) * | 2024-03-05 | 2024-04-09 | 北京大学 | Pre-detonation tube device of continuous detonation engine and control method thereof |
| CN117846819B (en) * | 2024-03-05 | 2024-05-31 | 北京大学 | Pre-detonation tube device of continuous detonation engine and control method thereof |
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