CN115288878A - Variable geometry throat for semi-axis symmetric rocket-based combined engine - Google Patents
Variable geometry throat for semi-axis symmetric rocket-based combined engine Download PDFInfo
- Publication number
- CN115288878A CN115288878A CN202210871394.2A CN202210871394A CN115288878A CN 115288878 A CN115288878 A CN 115288878A CN 202210871394 A CN202210871394 A CN 202210871394A CN 115288878 A CN115288878 A CN 115288878A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- bottom plate
- semi
- throat
- top plate
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/15—Control or regulation
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a variable geometry throat for a semi-axis symmetric rocket-based combined engine, which comprises: an intake passage and a combustion chamber communicating in an axial direction, wherein: the air inlet channel and the combustion chamber are both of cavity structures surrounded by the shell; the air inlet channel comprises a shell, a first air inlet channel and a second air inlet channel, wherein the shell consists of a first bottom plate and a first top plate; the first top plate is in an upwards arched semi-trumpet shape; the combustion chamber consists of a straight line section and a bending section which have the same inner diameter and are connected in front and back; the shell of the device consists of a second bottom plate and a second top plate, the second bottom plate consists of a horizontal section and a bending section, the horizontal section is integrally connected with the front and the back of the second bottom plate, the bending section bends downwards, and the front end of the horizontal section is integrally connected with the first bottom plate; the second top plate is formed by two semi-cylindrical shells which are connected in front and back to form a row. By adopting the variable geometry throat, the thrust and specific impulse performance in wide-range work are improved, meanwhile, the efficient combustion of the combustion chamber of the RBCC engine under different modes is realized, and the matching of air flow under different incoming flow conditions is met.
Description
Technical Field
The invention belongs to the technical field of rocket-based combined cycle engine runners, and particularly relates to a variable geometry throat for a semi-axis symmetric rocket-based combined engine.
Background
The RBCC engine is a Combined propulsion system which organically integrates a Rocket engine with high thrust-weight ratio and low specific impulse and a ramjet engine with low thrust-weight ratio and high specific impulse, and integrates an injection mode, a sub-combustion mode, a super-combustion mode and a pure Rocket mode into a whole, so that the RBCC engine can be automatically started, has a very wide flight envelope and strong task adaptability, and becomes one of novel power devices with the most potential development in the future. On the premise that a plurality of modes share one flow channel, the variable structure technology of the engine is one of effective ways for ensuring the optimal working performance of the engine in the whole process.
Domestic researchers have proposed a variable structure rocket-based combined power cycle engine and a rocket-based combined power cycle engine (RBCC) variable structure combustion chamber, wherein an adjustable top plate of the combustion chamber slides back and forth along the direction of a fixed top plate of the combustion chamber to change the area of the combustion chamber, and the combustion chamber area ratio is changed by utilizing a variable profile section on the upper wall surface of the combustion chamber.
Disclosure of Invention
The invention aims to provide a variable throat for a semi-axis symmetric rocket-based combined engine, which improves the thrust and specific impulse performance of the engine in a wide working range, realizes efficient combustion of a combustion chamber of an RBCC engine in different modes and meets the matching of air flow under different incoming flow conditions.
The invention adopts the following technical scheme: a variable geometry throat for a semi-axisymmetric rocket-based compound engine, comprising: the intake duct and the combustion chamber that communicate in the axial still include the intake duct dustcoat, wherein: the air inlet channel and the combustion chamber are both of cavity structures surrounded by the shell;
the air inlet channel comprises a shell, a first air inlet channel and a second air inlet channel, wherein the shell consists of a first bottom plate and a first top plate; the first top plate is in an upwardly arched semi-trumpet shape, and an outward expanded trumpet opening is positioned at the front end; the first top plate is connected with the first bottom plate in a sliding mode;
the combustion chamber consists of a straight line section and a bending section which have the same inner diameter and are connected in front and back; the shell of the device consists of a second bottom plate and a second top plate, and corresponds to the straight line section and the bending section, the second bottom plate consists of a horizontal section and a bending section which are integrally connected in front and at the back and are bent downwards, and the front end of the horizontal section is integrally connected with the first bottom plate; the second top plate consists of two semi-cylindrical shells which are connected in front and back, and the straight line edge of each semi-cylindrical shell is parallel to the corresponding horizontal section and the corresponding bending section;
the rear end of the bending section is connected with a horizontal spray pipe;
the outer cover of the air inlet channel is in a semi-cylindrical shape, is sleeved outside the arched side of the air inlet channel, and the bottom of the outer cover is in sliding connection with the bottom plate and can move back and forth along the bottom plate;
the air inlet cover and the air inlet shell move forwards or backwards at the same time and move forwards, so that the area of an air inlet throat is reduced; and moving backwards to increase the area of the throat of the air inlet.
The combustion chamber geometric throat adjusting block is arranged on a bottom plate in the spray pipe, is axially connected, and has a tip end facing to the front end and the rear end, and the plane side of the combustion chamber geometric throat adjusting block is attached to the wall surface of the bottom plate, can move in the spray pipe above the front end or move in the rear lower end for resetting, reduces the area of the geometric throat when moving in the front upper end, and increases the area of the geometric throat when moving in the rear lower end.
Furthermore, the spray pipe is enclosed by a bottom plate body and a top plate, the direction of the bottom plate body and the plate body at the bottom of the bending section are on the same straight line, and the top plate is in an upwards arched shape and smoothly expands upwards from front to back.
Furthermore, at least two air inlet channel actuating cylinders are arranged on the outer wall of the top plate of the straight-line section and positioned close to the air inlet channel end, and the two air inlet channel actuating cylinders are arranged around the top plate at intervals;
a plurality of first actuating blocks are arranged at the rear end of a first top plate of the air inlet channel, the number of the first actuating blocks is the same as that of air inlet channel actuating cylinders, the positions of the first actuating blocks are consistent, and one first actuating block is connected with one air inlet channel actuating cylinder; each first actuating block is a block;
each air inlet channel actuating cylinder is used for pushing the first top plate to move back and forth along the first bottom plate.
Furthermore, an air inlet throat adjusting block actuating cylinder is arranged at the rear end of the air inlet housing and used for pushing the air inlet housing to move back and forth.
Furthermore, the length of the semi-cone at the front end of the combustion chamber geometric throat adjusting block is equal to that of the bending section.
Furthermore, the front end of the air inlet cover crosses over the edge of the front end of the air inlet, and the rear end of the air inlet cover is positioned at the inner contraction section of the air inlet.
Furthermore, in the air inlet, an air inlet central body is coaxially sleeved, the front end of the air inlet central body is a semi-cone with a tip, the plane side of the air inlet central body is attached to the side of the bottom plate, and a semi-annular channel is formed between the air inlet central body and the first top plate.
The beneficial effects of the invention are: 1. the air inlet channel actuator cylinder pushes the first top plate to move back and forth, the contraction ratio of the air inlet channel is changed, the contraction ratio of the air inlet channel moving in front of the first top plate is reduced, and the requirement of the air inlet channel with high Mach is met; first roof rearward movement, intake duct contraction ratio grow satisfies the intake duct demand of low mach. The intake duct throat regulating block actuator cylinder pushes the intake duct outer cover to move back and forth, the external contraction ratio of the intake duct is regulated, the intake duct outer cover moves forward, the external contraction ratio is increased, the intake duct requirement of high mach is met, the intake duct outer cover moves backward, the external contraction ratio is reduced, and the requirement of a low-mach intake duct is met. And the matching of an air inlet and exhaust system is met by adjusting the contraction ratio of the air inlet. 2. At low Mach, the geometric throat regulating block of the combustion chamber moves backwards to increase the geometric throat area of the combustion chamber, and at high Mach, the geometric throat regulating block of the combustion chamber moves forwards to reduce the geometric throat area of the combustion chamber, improve the choking capacity of the engine and generate large acting force. The combustion chamber can realize different incoming flows and fuel matching work, and stable and efficient combustion performance is realized. 3. The geometric throat of the air inlet channel and the geometric throat of the combustion chamber have only one degree of freedom, the adjusting mode is simple, and the geometry is easy to realize.
Drawings
FIG. 1 is a schematic diagram of a variable geometry throat for a semi-axisymmetric rocket-based compound engine;
FIG. 2 is a view of the intake ram in connection with the intake port and the combustion chamber;
FIG. 3 is a diagram of an actuating device of an inner contraction section of an air inlet passage;
FIG. 4 is a schematic structural view of a geometric throat adjusting block of a combustor;
wherein: 1. an air intake centerbody; 2. an air inlet channel; 3. an air inlet duct housing; 4. an air inlet passage throat adjusting block actuator cylinder; 5. a supporting plate rocket; 6. a fuel injection support plate; 7. a combustion chamber geometric throat adjusting block actuating cylinder; 8. a combustion chamber geometric throat adjusting block; 9. an intake duct actuator cylinder; 10. a first actuator block; 11. a second actuator block; 12. a combustion chamber; 12-1, a straight line segment; 12-2, bending a section; 13. and (4) a spray pipe.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a variable geometry throat for a semi-axis symmetric rocket-based combined engine, which comprises an air inlet 2 and a combustion chamber 12 which are axially communicated and an air inlet housing 3, as shown in figure 1, wherein: the air inlet channel 2 and the combustion chamber 12 are both cavity structures surrounded by a shell;
the air inlet 2 is provided with a shell which consists of a first bottom plate and a first top plate, wherein the first bottom plate is horizontal; the first top plate is in an upwardly arched semi-trumpet shape, and an outward expanded trumpet opening is positioned at the front end; the first top plate is connected with the first bottom plate in a sliding mode; in the air inlet 2, an air inlet central body 1 is coaxially sleeved, the front end of the air inlet central body is a semi-cone with a tip, the plane side of the air inlet central body is attached to the bottom plate side, and a semi-annular channel is formed between the air inlet central body and the first top plate.
The combustion chamber 12 consists of a straight line section 12-1 and a bending section 12-2 which have the same inner diameter and are connected in front and back; the shell of the device consists of a second bottom plate and a second top plate, and corresponds to the straight line section 12-1 and the bending section 12-2, the second bottom plate consists of a horizontal section and a bending section, the horizontal section and the bending section are integrally connected in front and at back, and the front end of the horizontal section is integrally connected with the first bottom plate; the second top plate consists of two semi-cylindrical shells which are connected in front and at the back, and the straight line edge of each semi-cylindrical shell is parallel to the corresponding horizontal section and the corresponding bending section;
the rear end of the bending section 12-2 is connected with a horizontal spray pipe 13;
the air inlet channel outer cover 3 is in a semi-cylindrical shape, is sleeved outside the arched side of the air inlet channel 2, is connected with the bottom plate in a sliding manner, and can move back and forth along the bottom plate;
the air inlet duct outer cover 3 and the air inlet duct 2 shell move forwards or backwards simultaneously and move forwards, so that the area of the throat of the air inlet duct 2 is reduced; moving backwards, the area of the throat of the inlet 2 is increased.
As shown in fig. 2, 3 and 4, the nozzle further comprises a combustion chamber geometric throat adjusting block 8, the combustion chamber geometric throat adjusting block 8 is arranged on a bottom plate in the nozzle 13, is axially connected, and has a tip facing to the front end and the rear end of the double semi-cone, and a plane side of the double semi-cone is attached to the wall surface of the bottom plate, and can move in the nozzle towards the front upper part or move backwards and downwards to reset, when moving towards the front upper part, the area of the geometric throat is reduced, and when moving towards the back lower part, the area of the geometric throat is increased.
An air inlet passage throat adjusting block actuating cylinder 4 is arranged at the rear end of the air inlet passage outer cover 3, and the air inlet passage throat adjusting block actuating cylinder 4 is used for pushing the air inlet passage outer cover 3 to move back and forth. The front end of the air inlet channel throat adjusting block actuator cylinder 4 is connected with an inner contraction section of the air inlet channel 2 through a second actuator 11, and the second actuator 11 is a cone with the radian consistent with that of the outer wall of the inner contraction or a block with the radian, and the principle of the second actuator is that the second actuator can be attached to the outer wall of the inner contraction section.
The spray pipe 13 is enclosed by a bottom plate body and a top plate, the direction of the bottom plate body is on the same straight line with the plate body at the bottom of the bending section 12-2, and the top plate is in an upward arched shape and smoothly expands outwards from front to back.
At least two air inlet channel actuating cylinders 9 are arranged on the outer wall of a top plate of the straight line section 12-1 and positioned close to the end of the air inlet channel 2, and the two air inlet channel actuating cylinders 9 are arranged at intervals around the top plate;
the rear end of the top plate of the air inlet channel 2 is provided with a plurality of actuating blocks 10, the number of the actuating blocks 10 is the same as that of the air inlet channel actuating cylinders 9, the positions of the actuating blocks are consistent, and one actuating block 10 is connected with one air inlet channel actuating cylinder 9; each actuator block 10 is a one-piece, e.g. cubic, body, which serves as a connection.
Each inlet ram 9 is adapted to move the first head plate back and forth along the first base plate.
The length of the front half cone of the combustion chamber geometrical throat adjusting block 8 is equal to that of the bending section 12-2.
The air inlet 2, the air inlet outer cover 3 and the combustion chamber geometric throat adjusting block 8 are all in sliding connection with the bottom plate, if the air inlet is connected with a slide way arranged on the bottom plate, and dynamic sealing is adopted.
The actuating cylinder in the embodiment is an existing device, can be selected from various types, and for example, the actuating cylinder can adopt the following structure and comprises an outer cylinder, a piston rod is coaxially arranged in the outer cylinder, and pushing or pulling is realized in a hydraulic control mode.
To validate a variable geometry throat for a semi-axisymmetric rocket-based compound engine of the present invention, simulation experiments were conducted as follows:
when the engine is operated at Ma2, the air inlet housing 3 and the combustion chamber geometric throat adjusting block 8 are in initial positions, namely: the geometric throat adjusting block 8 of the combustion chamber of the air inlet cover 3 is completely positioned in the spray pipe 13, the capture area of the air inlet is 1, the throat area of the air inlet is 0.2855, the maximum sectional area of the combustion chamber is 0.67, and the geometric throat area of the combustion chamber is 0.0625. In order to ensure the normal operation of the air inlet, the overflow flow of the air inlet is larger at the moment, and the throat area of the air inlet is also larger.
When the engine works at Ma3, the air inlet outer cover 3 moves forwards by 95mm, the combustion chamber geometric throat adjusting block 8 moves forwards by 20mm, the area of the air inlet throat is changed to 0.2665 at the moment, the area of the combustion chamber geometric throat and the maximum sectional area of the combustion chamber 12 are kept unchanged, the air inlet capture flow is guaranteed, the requirement on the starting performance of the air inlet can be met at the moment, and the throat of the combustion chamber is adjusted to keep the working state when Ma3 comes.
In the conversion process from Ma3 to Ma6, in order to adapt to the drastic change of incoming flow and ensure that an engine does not stall, namely, the starting performance of the air inlet channel needs to be ensured, on the basis of the Ma3 configuration, the inner contraction section of the air inlet channel moves forwards by 42.5mm to reduce the throat area, the outer cover 3 of the air inlet channel moves forwards by 65mm to ensure the starting characteristic of the air inlet channel, the throat area of the air inlet channel becomes 0.1590, and the capture area of the air inlet channel 2 and the maximum sectional area of the combustion chamber 12 are kept unchanged. Meanwhile, the geometric throat adjusting block 8 of the combustion chamber moves forwards by 310mm along the spray pipe to the inside of the bending section 12-2, the area of the geometric throat is reduced, the choking degree of the engine is increased, the combustion heat release in the combustion chamber 12 is enhanced, the pressure of the combustion chamber 12 can be increased, and the thrust specific impulse performance of the engine is improved. The geometric throat area of the combustor becomes 0.2850 as the throat size of the combustor is reduced to meet the combustion requirement of the combustor fuel. And the throat adjustment keeps the working state of Ma3 during incoming flow. In the invention, the matching work of different incoming flows and oil injection states of the combustion chamber 12 can be realized by adjusting the position of the geometric throat and the contraction ratio of the air inlet.
When the incoming flow Mach numbers are 2, 3 and 6, the geometric throat adjusting block 8 of the combustion chamber is respectively positioned at the positions of 0mm, 0mm and 310mm, and is specifically defined as follows: when the geometric throat adjusting block 8 of the combustion chamber is completely positioned in the jet 13, defining the position of the rear end of the geometric throat adjusting block 8 of the combustion chamber as a point 0; as it slides toward the forward bend section 12-2, its rear end is forward away from point 0 by a positive number. The geometric throat adjusting block 8 of the combustion chamber moves forwards, the area of the geometric throat is reduced, the choking degree of the combustion chamber 12 is increased, namely, the efficient work of the engine under different inflow conditions is realized, the actuation of the geometric throat adjusting block 8 is realized only by the actuating device 7, and the actuation mode is simple.
Claims (8)
1. A variable geometry throat for a semi-axisymmetric rocket-based compound engine, comprising: the air inlet (2) and the combustion chamber (12) which are communicated in the axial direction further comprise an air inlet housing (3), wherein: the air inlet channel (2) and the combustion chamber (12) are both of cavity structures surrounded by the shell;
the shell of the air inlet channel (2) consists of a first bottom plate and a first top plate, wherein the first bottom plate is horizontal; the first top plate is in an upward arched semi-horn shape, and an outward expanded horn mouth is positioned at the front end; the first top plate is connected with the first bottom plate in a sliding mode;
the combustion chamber (12) consists of a straight line section (12-1) and a bending section (12-2) which have the same inner diameter and are connected in front and back; the shell of the device consists of a second bottom plate and a second top plate, the second bottom plate corresponds to the straight line section (12-1) and the bending section (12-2), the second bottom plate consists of a horizontal section and a bending section, the horizontal section and the bending section are integrally connected in front and at back, and the front end of the horizontal section is integrally connected with the first bottom plate; the second top plate consists of two semi-cylindrical shells which are connected in front and at the back, and the straight line edge of each semi-cylindrical shell is parallel to the corresponding horizontal section and the corresponding bending section;
the rear end of the bending section (12-2) is connected with a horizontal spray pipe (13);
the air inlet channel outer cover (3) is in a semi-cylindrical shape, is sleeved outside the arched side of the air inlet channel (2), is connected with the bottom plate in a sliding mode, and can move back and forth along the bottom plate;
the air inlet cover (3) and the air inlet (2) shell move forwards or backwards at the same time, and move forwards, so that the area of the throat of the air inlet (2) is reduced; moving backwards, and increasing the area of the throat of the air inlet (2).
2. The variable geometry throat for a semi-axisymmetric rocket-based combined engine of claim 1, further comprising a combustion chamber geometry throat adjusting block (8), wherein said combustion chamber geometry throat adjusting block (8) is disposed on the bottom plate in said nozzle (13), is a double half cone connected in the axial direction, and has a tip facing to the front and rear ends, and a plane side thereof is attached to the wall surface of the bottom plate, and can move forward and upward in the nozzle or move backward and downward for restoration, when moving forward and upward, the area of the geometry throat is reduced, and when moving backward and downward, the area of the geometry throat is increased.
3. A variable geometry throat for a semi-axisymmetric rocket-based compound engine, as set forth in claim 2, characterized in that said nozzle (13) is defined by a bottom plate and a top plate, said bottom plate is oriented in the same line as the plate at the bottom of said bending section (12-2), and said top plate is in the shape of an upwardly arched dome smoothly expanding upward from front to back.
4. A variable geometry throat for a semi-axisymmetric rocket-based compound engine, as set forth in claim 3, characterized in that at least two inlet rams (9) are provided on the outer wall of the top plate of said straight line segment (12-1) at the end near the inlet (2), and two of said inlet rams (9) are spaced around the top plate;
a plurality of first actuating blocks (10) are arranged at the rear end of a first top plate of the air inlet channel (2), the number of the first actuating blocks (10) is the same as that of the air inlet channel actuating cylinders (9), the positions of the first actuating blocks are consistent, and one first actuating block (10) is connected with one air inlet channel actuating cylinder (9); each first actuating block (10) is a block body;
and each air inlet channel actuating cylinder (9) is used for pushing the first top plate to move back and forth along the first bottom plate.
5. The variable geometry throat for a semi-axisymmetric rocket-based compound engine of claim 4, characterized in that an intake throat adjusting block ram (4) is provided at the rear end of said intake housing (3), said intake throat adjusting block ram (4) being used to push said intake housing (3) back and forth.
6. A variable geometry throat for a semi-axisymmetric rocket-based compound engine, as defined in claim 5, characterized in that said combustion chamber geometry throat adjusting block (8) has a length of its front end half cone equal to the length of said bending section (12-2).
7. A variable geometry throat for a semi-axisymmetric rocket-based compound engine, as defined in claim 6, characterized in that said inlet cowling (3) has a front end that passes over the front edge of the inlet (2) and a rear end that is located at the inner throat of the inlet.
8. The variable geometry throat for a semi-axisymmetric rocket-based compound engine, according to claim 7, characterized in that, inside said intake duct (2), coaxially fitted is an intake duct central body (1), which is a semi-cone with a tip at its front end and its planar side is attached to the bottom plate side, forming a semi-circular passage with the first head plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210871394.2A CN115288878A (en) | 2022-07-22 | 2022-07-22 | Variable geometry throat for semi-axis symmetric rocket-based combined engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210871394.2A CN115288878A (en) | 2022-07-22 | 2022-07-22 | Variable geometry throat for semi-axis symmetric rocket-based combined engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115288878A true CN115288878A (en) | 2022-11-04 |
Family
ID=83825046
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210871394.2A Pending CN115288878A (en) | 2022-07-22 | 2022-07-22 | Variable geometry throat for semi-axis symmetric rocket-based combined engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115288878A (en) |
-
2022
- 2022-07-22 CN CN202210871394.2A patent/CN115288878A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110284994B (en) | Parallel thrust vector exhaust system based on throat offset type pneumatic vector spray pipe | |
| US6668542B2 (en) | Pulse detonation bypass engine propulsion pod | |
| CN113915027B (en) | Circular-square binary vector spray pipe with yawing function | |
| CN204476593U (en) | A kind of mechanism realizing binary plug nozzle airflow direction and control | |
| CN208718799U (en) | The adjustable convergence diffusivity jet pipe of one kind | |
| CN113374594B (en) | Control mechanism for expansion section of binary spray pipe | |
| CN105240160B (en) | A kind of rocket based combined cycle engine structure changes combustion chamber | |
| CN108757215A (en) | The adjustable convergence diffusivity jet pipe of one kind | |
| CN211258815U (en) | Ma0-5+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet | |
| CN110645100A (en) | Ma0-6+ wide-range precooling + stamping combined engine axisymmetric adjustable air inlet | |
| CN112610333A (en) | Three-channel axisymmetric adjustable air inlet channel of wide-range combined engine | |
| CN115288878A (en) | Variable geometry throat for semi-axis symmetric rocket-based combined engine | |
| CN115434823A (en) | Rocket stamping combined engine with parallel compressor runners | |
| CN114109645A (en) | Axial symmetry contraction and expansion spray pipe movement mechanism | |
| CN111692013A (en) | Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method | |
| CN112360645A (en) | Tandem turbine/double-mode stamping combined engine mode conversion device | |
| CN106121865B (en) | A kind of solid rocket ramjet gas flow self-checking device | |
| CN112211753A (en) | Novel rocket engine tail nozzle throat structure | |
| CN114753930A (en) | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics | |
| CN110645099B (en) | Ma 0-5+wide-range precooling and stamping combined engine axisymmetric adjustable air inlet passage | |
| CN214533288U (en) | Long tail nozzle structure of segmentation of solid rocket engine | |
| CN210564806U (en) | Runner and storage tank integrated rocket stamping combined power system | |
| CN212318176U (en) | Four-channel combined engine shared tail nozzle based on multilateral expansion nozzle | |
| CN115585060B (en) | Secondary flow regulating mechanism of jet nozzle of multi-duct engine | |
| CN113700561B (en) | Supporting plate lifting adjustable type lower jaw type supersonic air inlet channel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |