CN111749814A - Cross-medium dual-mode ramjet based on metal fuel and control method - Google Patents
Cross-medium dual-mode ramjet based on metal fuel and control method Download PDFInfo
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- CN111749814A CN111749814A CN202010542608.2A CN202010542608A CN111749814A CN 111749814 A CN111749814 A CN 111749814A CN 202010542608 A CN202010542608 A CN 202010542608A CN 111749814 A CN111749814 A CN 111749814A
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
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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
- F02K9/26—Burning control
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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
- F02K9/08—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
- F02K9/34—Casings; Combustion chambers; Liners thereof
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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)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention provides a cross-medium dual-mode ramjet engine based on metal fuel and a control method. The engine can be freely switched between two modes by adopting the air inlet channel and the water inlet pipe which comprise the valve. The preset oxidant storage tank provides oxidant for the afterburning chamber in the mode conversion stage, so that the continuous supply of thrust in the mode conversion process of the engine in the water inlet and outlet stage is ensured, the stalling of the navigation body in the medium crossing process can be effectively avoided, the high-speed water inlet and outlet process of the medium crossing navigation body is realized, and the reliability of the navigation body is greatly improved.
Description
Technical Field
The invention relates to a cross-medium bimodal ramjet based on metal fuel and a control method, and belongs to the technical field of cross-medium sailing power.
Background
In the twenty-first century, human beings are increasingly diversified in tasks and exploration activities depending on unmanned navigation bodies. The modern common unmanned navigation body comprises an aerial unmanned aircraft and an underwater unmanned underwater vehicle. However, the single navigation mode of the traditional unmanned navigation body is difficult to deal with complicated and variable natural environments.
The air-sea medium-crossing navigation body adopts a third flight mode combining full-airspace high-speed flight and underwater high-speed diving, and the coping capability of the navigation body under various complex conditions can be greatly improved by switching (for many times) between air navigation and underwater navigation. At present, in the existing air-sea medium-crossing navigation bodies, the propulsion modes of the existing air-sea medium-crossing navigation bodies generally comprise that the navigation body is boosted to a target airspace through a solid rocket engine, then the navigation body is decelerated into water by virtue of a parachute, and then the underwater propulsion system provides thrust to complete a navigation task. But the solid rocket engine has short working time, and greatly reduces the lifting space of the voyage. Meanwhile, the traditional medium-crossing navigation body is difficult to switch among different propulsion systems, and accidents are easy to happen in the unpowered deceleration water-entering process. Therefore, in order to improve the long-distance navigation capability of the high-altitude cross-medium navigation body and enhance the navigation flexibility, the design of the cross-medium power system which can enable the navigation body to keep high-speed navigation in the air and under water and has the capability of multiple water inlet and outlet has great significance.
Disclosure of Invention
Aiming at the defect that the flexibility and the maneuverability of the existing single-medium navigation body are not strong enough, the invention aims to provide the cross-medium dual-mode ramjet based on the metal fuel and the control method, which can meet the requirements of two different working modes in the air and under the water, realize the high-speed navigation of the navigation body in the air and under the water, realize the conversion of the modes of the air and the water, provide continuous thrust in the water inlet and outlet stages of the navigation body and greatly improve the reliability of a power system.
The purpose of the invention is realized as follows: the fuel gas generator is internally provided with a metal-based solid propellant, the water inlet pipeline comprises a main water inlet pipe, a water inlet pipe buffer chamber connected with the main water inlet pipe, a primary water inlet pipe and a secondary water inlet pipe connected with the water inlet pipe buffer chamber, the end parts of the primary water inlet pipe and the secondary water inlet pipe are respectively communicated with the afterburning chamber and provided with a water inlet pipe spherical valve on the pipeline, the end surface of the preset oxidant storage device is provided with a preset oxidant discharge pipe, the number of the preset oxidant discharge pipes is equal to the total number of the primary water inlet pipe and the secondary water inlet pipe, and the end part of the preset oxidant discharge pipe is connected with the corresponding primary water inlet pipe and the corresponding secondary water inlet pipe, and the joints are provided with spherical valves of the oxidant storage tanks, and the air inlet device comprises air inlet pipes symmetrically arranged on the outer surface of the afterburning chamber along the circumferential direction and air inlet channel spherical valves arranged on the air inlet pipes.
The invention also includes such structural features:
1. the primary water inlet pipe and the secondary water inlet pipe are respectively provided with four water inlet pipes and are alternately arranged, and the length of the secondary water inlet pipe is larger than that of the primary water inlet pipe.
2. The fuel gas generator comprises a fuel gas generator front seal head, a fuel gas generator barrel and a fuel gas generator spray pipe which are connected in sequence, and the metal-based solid propellant is connected with the fuel gas generator front seal head through a front support piece of the explosive column; the afterburning chamber comprises an afterburning chamber front cover connected with a gas generator spray pipe and an afterburning chamber barrel connected with the afterburning chamber front cover; the tail nozzle comprises a tail nozzle convergent section connected with the afterburning chamber cylinder and a tail nozzle expansion section connected with the tail nozzle convergent section.
3. The preset oxidant storage device comprises a preset oxidant storage tank front cover, a preset oxidant storage tank cylinder body and a preset oxidant storage tank rear cover, and the preset oxidant discharge pipe is connected with an opening on the preset oxidant storage tank rear cover.
4. The number of the air inlet pipes is four.
5. A control method of a cross-medium dual-mode ramjet engine based on metal fuel comprises the following steps:
(1) an air stamping stage: the main water inlet pipe, the primary water inlet pipe, the secondary water inlet pipe and the preset oxidant storage tank do not work, and air entering the air inlet channel reacts with fuel gas generated by the fuel gas generator to generate thrust;
(2) and (3) entering water: the main water inlet pipe and the air inlet pipe do not work, and the oxidant in the preset oxidant storage tank enters the afterburning chamber through the primary water inlet pipe and the secondary water inlet pipe to react with the fuel gas generated by the fuel gas generator to generate thrust;
(3) a water stamping stage: the air inlet channel and the preset oxidant storage tank do not work, seawater enters the afterburning chamber through the water inlet pipe, the primary water inlet pipe and the secondary water inlet pipe and reacts with fuel gas generated by the fuel gas generator to generate thrust;
(4) and (3) water outlet acceleration stage: the main water inlet pipe and the air inlet channel do not work, oxidant in the preset oxidant storage tank enters the afterburning chamber through the primary water inlet pipe and the secondary water inlet pipe again to react with fuel gas generated by the fuel gas generator to generate thrust, when the navigation body accelerates to the speed required by air punching, the primary water inlet pipe, the secondary water inlet pipe and the preset oxidant storage tank stop working, the air inlet channel starts working, and the engine returns to the air punching stage again.
(5) And a return air stamping stage: the engine reenters the air ram mode; after the water outlet of the aircraft body is accelerated to reach the speed required by air ram, the water inlet pipe ball valve and the oxidant storage tank ball valve are closed, the air inlet pipe ball valve is opened, and the engine returns to the air ram mode to continuously generate thrust.
Compared with the prior art, the invention has the beneficial effects that: four different working stages related in the cross-medium dual-mode ramjet based on the metal fuel provided by the invention circulate in sequence after being started, cross-medium navigation of a navigation body can be realized, a reverse guidance system of the opposite side is avoided as much as possible, and the success rate of combat missions is greatly improved.
The invention has the following advantages:
the invention provides a cross-medium dual-mode ramjet based on metal fuel, which adopts an aluminum-based or aluminum-magnesium alloy solid propellant capable of reacting with air and water simultaneously as fuel, and combines the solid air ramjet with a solid water ram engine, thereby realizing the aim of continuously supplying thrust in two working environments of air and underwater by a single propulsion system, and meeting the requirement of continuous high-speed sailing of a sailing body in air and underwater. Aiming at the problem that external air or seawater cannot be supplied to a afterburning chamber for maintaining combustion in a short time in the process of crossing media, a scheme of arranging a preset oxidant in the inner part of the sailing body is provided, and the continuous supply of thrust in the process of crossing media is ensured.
In the air ram stage, the engine enters an air ram mode to provide thrust for the navigation body. As the propellant reacts with the air in the atmosphere, the propellant does not need to carry an oxidant, thereby greatly reducing the occupation of the internal space of the navigation body and lightening the weight of the navigation body.
In the air-water mode conversion stage, air and seawater cannot enter the afterburning chamber to react with the propellant in a short time. The preset oxidant can adopt water, liquid oxygen or hydrogen peroxide and other oxidants.
In the water-ram phase, the engine enters a water-ram mode. Seawater enters the afterburning chamber through a water inlet pipeline and reacts with the propellant. Because the water stamping stage is excessive water inflow which is larger than the chemical equivalence ratio of the aluminum water reaction, the engine is easy to be flamed out by single water inflow. Aiming at the problem, the invention adopts a scheme of secondary water inflow, wherein primary water inflow is mainly used for reaction heat release, and excessive seawater absorbs heat released by reaction and is vaporized into gas while secondary water inflow continues to react, and the gas is sprayed out from a tail nozzle along with reaction products to do work to generate thrust.
And stopping external seawater injection in the water-air mode conversion stage, and restarting injecting the preset oxidant into the afterburning chamber for reaction. After the sailing body goes out of water, the preset oxidant is continuously supplied, and the sailing body enters an acceleration stage. When the flight speed of the navigation body reaches the requirement of air ram, the preset oxidant is stopped being supplied, the air inlet channel starts working, and the engine returns to the air ram mode.
Drawings
FIG. 1 is a perspective view of a metal fuel based cross-media dual-modality ramjet engine of the present invention;
FIG. 2 is a cross-sectional view of a metal fuel based cross-media dual-modality ramjet engine of the present invention;
FIG. 3 is a sectional view A-A of the pre-oxidizer tank and the gasifier;
FIG. 4 is a sectional view of afterburner B-B;
wherein, 1-a gas generator, 2-a afterburning chamber, 3-a tail nozzle, 4-a preset oxidant storage tank, 5-a main water inlet pipe, 6-a primary water inlet pipe, 7-a secondary water inlet pipe, 8-a preset oxidant discharge pipe, 9-an air inlet pipe, 10-a water inlet pipe ball valve I, 11-a metal-based solid propellant, 12-a water inlet pipe buffer chamber, 13-an oxidant storage tank ball valve, 14-an air inlet pipe ball valve, 15-a front support part of a explosive column, 16-a water inlet pipe ball valve II, 17-a preset oxidant storage tank front cover, 18-a preset oxidant storage tank barrel, 19-a preset oxidant storage tank rear cover, 20-a gas generator front end socket, 21-a gas generator barrel, 22-a gas generator nozzle, 23-a afterburning chamber front cover, 24-afterburning chamber cylinder, 25-tail nozzle convergent section and 26-tail nozzle expansion section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 and 2, the invention provides a metal fuel-based cross-medium dual-mode ramjet engine, which comprises a water inlet pipeline, a preset oxidant storage device, an air inlet device and an engine body which are sequentially arranged.
The water inlet pipeline comprises a main water inlet pipe 5, a water inlet pipe buffer chamber 12, a primary water inlet pipe 6, a secondary water inlet pipe 7, a water inlet pipe ball valve I10, a water inlet pipe ball valve II 16 and an oxidant storage tank ball valve 13. One side of the main inlet pipe 5 is connected to an opening in the center of the inlet pipe buffer chamber 12. One ends of the four primary water inlet pipes 6 and the four secondary water inlet pipes 7 are connected with eight openings on the side surface of the water inlet pipe buffer chamber 12, and the other ends of the four primary water inlet pipes and the four secondary water inlet pipes are connected with eight openings on the side surface of the afterburning chamber 2. The preset oxidant discharge pipe 8 connects the preset oxidant storage tank with the primary water inlet pipe 6 and the secondary water inlet pipe 7, and the joints are provided with oxidant storage tank ball valves 13 for switching pipelines. All parts of the water inlet pipeline are connected by screw threads.
The preset oxidant storage device comprises a preset oxidant storage tank 4 and a preset oxidant discharge pipe 8; the front cover 17 of the preset oxidant storage tank, the cylinder 18 of the preset oxidant storage tank and the rear cover 19 of the preset oxidant storage tank are sequentially connected and combined to form the preset oxidant storage tank 4. The connections between all parts of the pre-oxidizer tank 4 are flange connections. Namely a front cover (17) of the preset oxidant storage tank, a rear cover (19) of the preset oxidant storage tank and a cylinder body (18) of the preset oxidant storage tank are connected by flanges; the rear cover (19) of the preset oxidant storage tank is provided with eight openings which are annularly arranged along the central axis, and eight preset oxidant discharge pipes (8) are connected with the rear cover (19) of the preset oxidant storage tank at the openings through threads;
the air intake device comprises an air intake duct 9 and an air intake duct globe valve 14, which are mainly used for collecting air in the atmosphere during the air ram phase.
The engine main body comprises a fuel gas generator 1, a metal-based solid propellant 11, a front support piece 15 of a grain, a afterburning chamber 2 and a tail nozzle 3.
The gasifier 1 is formed by sequentially combining a gasifier front head 20, a gasifier barrel 21 and a gasifier nozzle 22. The afterburning chamber front cover 23 and the afterburning chamber barrel 24 are sequentially combined to form the afterburning chamber 2. All the parts of the gas generator 1 and the afterburner 2 are connected by flanges. The metal-based solid propellant 11 is embedded in the gas generator barrel 21 and is connected to the gas generator front head 20 by the charge front support 15. One end of a afterburning chamber front cover (23) is in threaded connection with a gas generator spray pipe (22), and the other end of the afterburning chamber front cover is in flange connection with a afterburning chamber barrel (24); the air inlet channel (9) is connected with the side surface of the afterburning chamber cylinder body (24) through a flange.
The jet nozzle convergent section 25 and the jet nozzle divergent section 26 are combined in sequence to form the jet nozzle 3. Wherein, one end of the tail nozzle convergent section 25 is connected with the afterburning chamber cylinder 24 through a flange, and the other end is connected with the tail nozzle expansion section 26 through threads.
Referring to fig. 4, the preset oxidizer tank back cover 19 has eight openings arranged in a ring shape along the central axis, and eight preset oxidizer outlet pipes 8 are connected to the preset oxidizer tank back cover 19 at the openings by screws.
The invention adopts the scheme of secondary combustion, and after the self-sustained combustion in the fuel gas generator, the high-temperature metal liquid drops enter the afterburning chamber and then react with the oxidant, thereby greatly improving the combustion efficiency of the propellant. When the water/air supply is stopped in the water inlet/outlet transition stage, the method of providing the preset oxidant is adopted, the engine is ensured to provide continuous thrust, and the continuous high-speed sailing of the aircraft is realized. In the water inlet/outlet transition stage, the preset oxidant provided is water, liquid oxygen or hydrogen peroxide and other oxidants. The afterburning chamber adopts a method of feeding water twice, so that aluminum particles in high-temperature gas of the propellant are fully mixed and combusted with seawater.
A method of controlling a metal fuel based cross-media dual-modality ramjet engine, comprising:
1. in the air stamping stage, the engine is in an air stamping mode; the metal-based solid propellant 11 in the gas generator 1 is continuously combusted to generate high-temperature and high-pressure gas carrying a large amount of unburned aluminum particles, and the high-temperature and high-pressure gas enters the afterburning chamber 2 through a gas generator spray pipe 22; the inlet pipe ball valve I10, the inlet pipe ball valve II 16 and the oxidizer storage tank ball valve 13 are closed, and the inlet pipeline does not work; the air inlet spherical valve 14 is opened, and the air inlet is in a working state; air enters the afterburning chamber through the air inlet channel in a stamping manner, and reacts with fuel gas entering the afterburning chamber through the fuel gas generator nozzle 22, and the fuel gas generated by combustion is discharged outwards through the tail nozzle expansion section 26 to generate driving force.
2. In the water inlet stage, the engine is in an air-water mode conversion stage; the fuel gas which has continuous high temperature and high pressure and carries a large amount of unburned aluminum particles is generated in the fuel gas generator 1, and enters the afterburning chamber 2 through a fuel gas generator spray pipe 22; the air inlet spherical valve 14 is closed, and the air inlet stops working; the water inlet pipe ball valve II 16 keeps a closed state; the inlet pipe ball valve I10 and the oxidizer tank ball valve 13 are opened; the preset oxidant enters the afterburning chamber 2 through a pressurized water inlet pipeline and reacts with the fuel gas entering the afterburning chamber through the fuel gas generator nozzle 22, and the fuel gas generated by combustion is discharged outwards through the tail nozzle expansion section 26 to continuously generate driving force.
3. In the water stamping stage, the engine is in a water stamping mode; the gas generator 1 continuously generates high-temperature and high-pressure gas carrying a large amount of unburned aluminum particles, and the gas enters the afterburning chamber 2 through a gas generator spray pipe 22; the inlet ball valve 14 remains closed and the inlet does not operate; the spherical valve 13 of the oxidant storage tank is closed, and the preset oxidant stops supplying; opening a water inlet pipe ball valve I10 and a water inlet pipe ball valve II 16; seawater enters a front-end main water inlet pipe 5 through stamping, enters an afterburning chamber 2 through four primary water inlet pipes 6 and four secondary water inlet pipes 7, reacts with fuel gas entering the afterburning chamber through a fuel gas generator spray pipe 22, and the fuel gas generated by combustion is discharged outwards through a tail spray pipe expansion section 26 to continuously generate driving force.
4. In the water outlet acceleration stage, the engine is in a water-empty mode conversion stage; the gas generator 1 continuously generates high-temperature and high-pressure gas carrying a large amount of unburned aluminum particles, and the gas enters the afterburning chamber 2 through a gas generator spray pipe 22; the inlet ball valve 14 remains closed and the inlet does not operate; the water inlet pipe ball valve II 16 keeps a closed state; the inlet pipe ball valve I10 and the oxidizer tank ball valve 13 are opened; the preset oxidant enters the afterburning chamber 2 through the water inlet pipeline by pressurization again, reacts with the fuel gas entering the afterburning chamber through the fuel gas generator nozzle 22, and the fuel gas generated by combustion is discharged outwards through the tail nozzle expansion section 26 to continuously generate driving force to push the navigation body to discharge water and accelerate.
5. Returning to the air ram stage, and enabling the engine to enter an air ram mode again; after the water outlet of the aircraft is accelerated to reach the speed required by air ram, the water inlet pipe ball valve I10, the water inlet pipe ball valve II 16 and the oxidizer storage tank ball valve 13 are closed, the air inlet pipe ball valve 14 is opened, and the engine returns to the air ram mode to continuously generate thrust.
In summary, the present invention relates to a metal fuel based cross-media dual-modality ramjet engine. A metal-based solid propellant capable of reacting with air and water is adopted to combine a solid air ramjet engine and a solid water ramjet engine, so as to design a dual-mode ramjet engine. The engine can be freely switched between two modes by adopting the air inlet channel and the water inlet pipe which comprise the valve. The preset oxidant storage tank provides oxidant for the afterburning chamber in the mode conversion stage, so that the continuous supply of thrust in the mode conversion process of the engine in the water inlet and outlet stage is ensured, the stalling of the navigation body in the medium crossing process can be effectively avoided, the high-speed water inlet and outlet process of the medium crossing navigation body is realized, and the reliability of the navigation body is greatly improved.
Claims (10)
1. A metal fuel based cross-media dual-modality ramjet engine characterized by: the fuel gas generator is internally provided with a metal-based solid propellant, the water inlet pipeline comprises a main water inlet pipe, a water inlet pipe buffer chamber connected with the main water inlet pipe, a primary water inlet pipe and a secondary water inlet pipe connected with the water inlet pipe buffer chamber, the end parts of the primary water inlet pipe and the secondary water inlet pipe are respectively communicated with the afterburning chamber and provided with a water inlet pipe spherical valve on the pipeline, the end surface of the preset oxidant storage device is provided with a preset oxidant discharge pipe, the number of the preset oxidant discharge pipes is equal to the total number of the primary water inlet pipe and the secondary water inlet pipe, and the end part of the preset oxidant discharge pipe is connected with the corresponding primary water inlet pipe and the corresponding secondary water inlet pipe, and the joints are provided with spherical valves of the oxidant storage tanks, and the air inlet device comprises air inlet pipes symmetrically arranged on the outer surface of the afterburning chamber along the circumferential direction and air inlet channel spherical valves arranged on the air inlet pipes.
2. The metal-fuel based cross-media dual-modality ramjet engine of claim 1, characterized in that: the primary water inlet pipe and the secondary water inlet pipe are respectively provided with four water inlet pipes and are alternately arranged, and the length of the secondary water inlet pipe is larger than that of the primary water inlet pipe.
3. A metal fuel based cross-media dual-modality ramjet engine according to claim 1 or 2, characterized in that: the fuel gas generator comprises a fuel gas generator front seal head, a fuel gas generator barrel and a fuel gas generator spray pipe which are connected in sequence, and the metal-based solid propellant is connected with the fuel gas generator front seal head through a front support piece of the explosive column; the afterburning chamber comprises an afterburning chamber front cover connected with a gas generator spray pipe and an afterburning chamber barrel connected with the afterburning chamber front cover; the tail nozzle comprises a tail nozzle convergent section connected with the afterburning chamber cylinder and a tail nozzle expansion section connected with the tail nozzle convergent section.
4. A metal fuel based cross-media dual-modality ramjet engine according to claim 1 or 2, characterized in that: the preset oxidant storage device comprises a preset oxidant storage tank front cover, a preset oxidant storage tank cylinder body and a preset oxidant storage tank rear cover, and the preset oxidant discharge pipe is connected with an opening on the preset oxidant storage tank rear cover.
5. A metal-fuel based cross-media dual-modality ramjet engine according to claim 3, characterized in that: the preset oxidant storage device comprises a preset oxidant storage tank front cover, a preset oxidant storage tank cylinder body and a preset oxidant storage tank rear cover, and the preset oxidant discharge pipe is connected with an opening on the preset oxidant storage tank rear cover.
6. A metal fuel based cross-media dual-modality ramjet engine according to claim 1 or 2, characterized in that: the number of the air inlet pipes is four.
7. A metal-fuel based cross-media dual-modality ramjet engine according to claim 3, characterized in that: the number of the air inlet pipes is four.
8. The metal-fuel based cross-media dual-modality ramjet engine of claim 4, characterized in that: the number of the air inlet pipes is four.
9. The metal-fuel based cross-media dual-modality ramjet engine of claim 5, characterized in that: the number of the air inlet pipes is four.
10. A control method of a cross-medium dual-mode ramjet engine based on metal fuel is characterized by comprising the following steps: the cross-medium dual-mode ramjet engine comprises the following control processes:
(1) an air stamping stage: the main water inlet pipe, the primary water inlet pipe, the secondary water inlet pipe and the preset oxidant storage tank do not work, and air entering the air inlet channel reacts with fuel gas generated by the fuel gas generator to generate thrust;
(2) and (3) entering water: the main water inlet pipe and the air inlet pipe do not work, and the oxidant in the preset oxidant storage tank enters the afterburning chamber through the primary water inlet pipe and the secondary water inlet pipe to react with the fuel gas generated by the fuel gas generator to generate thrust;
(3) a water stamping stage: the air inlet channel and the preset oxidant storage tank do not work, seawater enters the afterburning chamber through the water inlet pipe, the primary water inlet pipe and the secondary water inlet pipe and reacts with fuel gas generated by the fuel gas generator to generate thrust;
(4) and (3) water outlet acceleration stage: the main water inlet pipe and the air inlet channel do not work, oxidant in the preset oxidant storage tank enters the afterburning chamber through the primary water inlet pipe and the secondary water inlet pipe again to react with fuel gas generated by the fuel gas generator to generate thrust, when the navigation body accelerates to the speed required by air punching, the primary water inlet pipe, the secondary water inlet pipe and the preset oxidant storage tank stop working, the air inlet channel starts working, and the engine returns to the air punching stage again.
(5) And a return air stamping stage: the engine reenters the air ram mode; after the water outlet of the aircraft body is accelerated to reach the speed required by air ram, the water inlet pipe ball valve and the oxidant storage tank ball valve are closed, the air inlet pipe ball valve is opened, and the engine returns to the air ram mode to continuously generate thrust.
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| CN202010542608.2A CN111749814B (en) | 2020-06-15 | 2020-06-15 | Cross-medium dual-mode ramjet based on metal fuel and control method |
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| CN113217227A (en) * | 2021-06-25 | 2021-08-06 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method thereof |
| CN114017206A (en) * | 2021-10-22 | 2022-02-08 | 哈尔滨工程大学 | Submarine missile engine |
| CN114352436A (en) * | 2021-12-15 | 2022-04-15 | 西安航天动力研究所 | Metal powder fuel air-water cross-medium engine and control method thereof |
| CN114562384A (en) * | 2022-03-21 | 2022-05-31 | 西北工业大学 | Multipurpose aeroengine |
| CN114810425A (en) * | 2022-04-26 | 2022-07-29 | 中国人民解放军国防科技大学 | Variable-thrust underwater ultrahigh-speed navigation body |
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| CN114352436A (en) * | 2021-12-15 | 2022-04-15 | 西安航天动力研究所 | Metal powder fuel air-water cross-medium engine and control method thereof |
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| CN114810425A (en) * | 2022-04-26 | 2022-07-29 | 中国人民解放军国防科技大学 | Variable-thrust underwater ultrahigh-speed navigation body |
| CN114810425B (en) * | 2022-04-26 | 2023-07-18 | 中国人民解放军国防科技大学 | Variable-thrust underwater ultra-high-speed navigation body |
| RU2783054C1 (en) * | 2022-06-02 | 2022-11-08 | Акционерное общество "Машиностроительное конструкторское бюро "Искра" имени Ивана Ивановича Картукова" (АО "МКБ "Искра") | Dual-mode solid propellant rocket engine |
| CN115107968A (en) * | 2022-06-13 | 2022-09-27 | 南昌航空大学 | Low-navigation-speed underwater ramjet engine and design method thereof |
| CN115107968B (en) * | 2022-06-13 | 2023-04-18 | 南昌航空大学 | Low-navigational-speed underwater ramjet engine and design method thereof |
| CN116357478A (en) * | 2023-03-17 | 2023-06-30 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
| CN116357478B (en) * | 2023-03-17 | 2024-05-17 | 哈尔滨工程大学 | Combustion surface following type water stamping water supply method |
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