CN113217227A - Cross-medium dual-mode ramjet based on metal fuel and control method thereof - Google Patents
Cross-medium dual-mode ramjet based on metal fuel and control method thereof Download PDFInfo
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- CN113217227A CN113217227A CN202110710427.0A CN202110710427A CN113217227A CN 113217227 A CN113217227 A CN 113217227A CN 202110710427 A CN202110710427 A CN 202110710427A CN 113217227 A CN113217227 A CN 113217227A
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- 239000000446 fuel Substances 0.000 title claims abstract description 20
- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000002184 metal Substances 0.000 title claims abstract description 18
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 103
- 239000002737 fuel gas Substances 0.000 claims abstract description 35
- 239000007800 oxidant agent Substances 0.000 claims description 49
- 230000001590 oxidative effect Effects 0.000 claims description 49
- 239000002360 explosive Substances 0.000 claims description 44
- 238000003860 storage Methods 0.000 claims description 35
- 239000004449 solid propellant Substances 0.000 claims description 7
- 239000007789 gas Substances 0.000 claims description 5
- 238000004080 punching Methods 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 2
- 239000013535 sea water Substances 0.000 claims description 2
- 238000004880 explosion Methods 0.000 abstract description 76
- 238000007789 sealing Methods 0.000 abstract description 19
- 238000010892 electric spark Methods 0.000 abstract description 2
- 239000000843 powder Substances 0.000 description 19
- 239000003721 gunpowder Substances 0.000 description 7
- 238000000926 separation method Methods 0.000 description 6
- 239000000565 sealant Substances 0.000 description 5
- 238000003466 welding Methods 0.000 description 5
- 230000002902 bimodal effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000009189 diving Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
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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
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Abstract
The invention provides a cross-medium dual-mode ramjet based on metal fuel and a control method thereof. In the air cruise stage, air enters the engine afterburning chamber through the ram air inlet channel to further react with rich fuel gas, so that thrust is provided for the navigation body. Before the navigation body enters water, the valve of the air inlet channel is closed, so that the whole navigation body is kept sealed, the explosion bolt is ignited by electric sparks to explode, and the air inlet channel is separated from the engine shell. After the air inlet channel is separated, the resistance of the navigation body in the water entering stage and the underwater navigation stage can be greatly reduced, and the reliability is improved. The invention solves the problem of integral sealing of the navigation body after the air inlet channel is separated, improves the stability of the cross-medium ramjet engine when crossing an air-water interface in the working process, reduces the resistance in underwater navigation and greatly improves the comprehensive performance of the engine.
Description
Technical Field
The invention relates to a cross-medium bimodal ramjet based on metal fuel and a control method thereof, belonging to the technical field of cross-medium sailing power systems.
Background
The high-speed medium-crossing navigation body can keep supersonic flight in the air and can keep high-speed navigation underwater after entering water. The working mode can greatly improve the maneuverability and evasion of the navigation body, enhance the adaptability of the navigation body to complex working environments, and has wide application prospect in the future cross-medium aircrafts. The cross-medium power system is the key point for realizing cross-medium navigation. Therefore, the research on the novel medium-crossing power system integrating the aerial and underwater power devices has important significance on the development of medium-crossing navigation in the future.
The high-speed medium-crossing navigation body is a new concept navigation body integrating the characteristics of high-speed navigation in the air and high-speed navigation under water. Compared with the traditional navigation body in a single medium, the flexibility and the maneuverability of the navigation body are obviously enhanced, and the navigation body is suitable for executing complex tasks under various conditions. By adopting the cross-medium dual-mode ramjet engine based on metal fuel, the power devices in the air and under water can be integrated, the continuous supply of thrust in the navigation process can be ensured, the defects that the traditional cross-medium navigation body is difficult to switch between a hollow power system and an underwater power system and is easy to intercept and destabilize in the low-speed water inlet process can be overcome, and the comprehensive performance of the cross-medium navigation body is greatly improved.
During the operation of the cross-medium ramjet, the physical properties of air and water are greatly different, so the appearance structure of the cross-medium navigation body needs to be changed in the process of entering water so as to adapt to underwater navigation. In the deformation process, if the four lateral external pressure type air inlet channels are reserved, on one hand, when the navigation body crosses the interface of air and water in the water inlet stage, the water inlet impact on the air inlet channels can reduce the stability and controllability of the whole navigation body. On the other hand, in the diving stage, the existence of the air inlet channel can bring huge resistance and vibration excitation to the navigation body, and the reliability of the navigation body is greatly reduced. Therefore, the air inlet channel of the throwable ramjet engine is designed, and the air inlet channel is controlled to be actively separated from the navigation body before entering water, so that the method has important significance for improving the overall performance of the medium-crossing navigation body.
Disclosure of Invention
The invention provides a cross-medium dual-mode ramjet engine based on metal fuel and a control method thereof, aiming at the problem that the reliability of a navigation body in a water entering stage and an underwater navigation stage can be greatly reduced due to the existence of a side four-external-pressure type air inlet channel in the deformation process of a cross-medium power system. The stability and controllability of the cross-interface can be improved, the resistance and vibration excitation in the submerging stage can be reduced, and the comprehensive performance of the cross-medium navigation body can be improved to a great extent.
A cross-medium dual-mode ramjet engine based on metal fuel comprises a water inlet pipeline, a preset oxidant storage device, an air inlet device and an engine main body, wherein the engine main body comprises a fuel gas generator, a afterburning chamber communicated with the fuel gas generator and a tail nozzle arranged at the end part of the afterburning chamber, a metal-based solid propellant is arranged in the fuel gas generator, 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, a water inlet pipe spherical valve is arranged on the pipeline, preset oxidant discharge pipes are arranged on the end surface of the preset oxidant storage device, 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 parts of the preset oxidant discharge pipes are connected with the corresponding primary water inlet pipe and 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 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.
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;
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;
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;
the number of the air inlet pipes is four.
A control method of a cross-medium dual-mode ramjet based on metal fuel comprises the following steps:
(1) an air stamping stage: the air entering from the air inlet channel reacts with the 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 passage are closed, 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 are closed, 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 are closed, the oxidant in the preset oxidant storage tank enters the afterburning chamber again through the primary water inlet pipe and the secondary water inlet pipe to react with rich fuel gas generated by the fuel gas generator, 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: the invention provides a throwable air inlet of a cross-medium ramjet engine. Aiming at the problem that the reliability of a navigation body can be greatly reduced by an air inlet channel arranged beside a medium-crossing power system in the deformation process, an explosion separation device is additionally arranged on a supersonic speed air inlet channel, and the air inlet channel is designed to be disposable. The design of the disposable air inlet channel enhances the stability of the navigation body when crossing the air-water interface and reduces the resistance after entering water. And a foundation is laid for improving the overall performance of the navigation body.
The invention has the following advantages:
the bottom of the supersonic inlet channel is consistent with the curvature of the curved surface of the outer shell of the engine, so that the sealing property between the inlet channel and the shell can be well ensured. The explosion bolt protection box is additionally arranged at the ignition end of the head part of an explosion bolt, the protection box is formed by welding two symmetrical half blocks, meanwhile, the protection box is fixedly connected with the air inlet channel connecting pipe through a bolt, and the space between the explosion bolt and the protection box is filled with sealant. On the one hand, the existence of the protection box avoids the potential accidents which can be caused by the fact that the remaining half of the explosive bolt falls into the interior of the navigation body after the explosive bolt is broken. On the other hand, the protection box can ensure that the rest half explosive bolts still remain in the original positions of the bolt holes after the explosive bolts are broken, and the sealing glue is filled between the protection box and the explosive bolts, so that the sealing state of the navigation body after the navigation body enters water is further ensured. In addition, the protection box is divided into two parts, so that the assembly of parts in the manufacturing process is facilitated. Moreover, the protection box is fixed with the bolt in a double mode through welding, firmness of the whole structure is improved, and the whole structure can bear impact when the explosive bolt is broken.
The explosion bolt ignites the ignition powder through the ignition cable, and then the explosion powder is ignited through the heat conduction released by the ignition powder combustion to realize the explosion breaking. In order to prevent explosive powder from rushing out of the interior of the bolt through the opening end of the explosive bolt to cause the situation of incapability of breaking, the explosive bolt adopts a triple protection mode of 'powder baffle → explosive bolt sealing cover bolt' to ensure that the explosive powder sealing plug achieves the due sealing effect.
After the jettisonable air inlet channel is subjected to explosive separation, the pneumatic layout of the navigation body is optimized, and the reliability of the navigation body crossing a gas-water interface and navigating underwater is improved.
Drawings
FIG. 1 is a perspective view of a throwable inlet for a cross-media ramjet engine according to the present disclosure;
FIG. 2 is a cross-sectional view of a throwable inlet of a cross-media ramjet engine of the present disclosure;
FIG. 3 is a cross-sectional view of an explosive separation and protection device
FIG. 4 is a cross-sectional view of a jettisonable air scoop A-A
FIG. 5 is a perspective view of a supersonic inlet
FIG. 6 is a perspective view of an explosive bolt protection cartridge (half)
FIG. 7 is a perspective view of an inlet duct connecting pipe
FIG. 8 is a plan view of an intake duct connecting pipe
FIG. 9 is a sectional view of an intake duct connecting pipe
FIG. 10 is a perspective view of an explosive bolt
FIG. 11 is a cross-sectional view of an explosive bolt
Wherein, 1-gas generator, 2-solid propellant, 3-afterburner housing, 4-tail nozzle, 5-supersonic air inlet, 6-water inlet pipe, 7-rear housing section, 8-middle housing section, 9-front housing section, 10-explosion bolt, 11-explosion bolt protection box, 12-air inlet connecting pipe, 13-sealant, 14-explosion bolt nut, 15-air inlet valve, 16-air inlet connecting pipe housing, 17-protection box fixing bolt, 18-explosion bolt cover bolt, 19-explosion bolt cover, 20-ignition cable, 21 gunpowder baffle, 22-ignition powder, 23-explosion sealing plug, 24-explosion gunpowder and 25-explosion bolt housing.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
A cross-medium dual-mode ramjet based on metal fuel comprises a fuel gas generator, a afterburning chamber, a tail nozzle and a jettisonable supersonic air inlet, wherein the jettisonable supersonic air inlet comprises a supersonic air inlet, an explosion bolt nut, an explosion bolt protection box and a protection box fixing bolt. The supersonic inlet and inlet connecting pipe is fixed on the outer shell by explosion bolts and explosion bolt nuts. The head of the explosive bolt is protected by an explosive bolt protection box, an explosive bolt ignition cable extends out of a small hole in the protection box, and sealing glue is filled between the protection box and the explosive bolt. The protection box divide into two, connects through the welding mode, and two half protection box sides are respectively fixed in on the intake duct connecting pipe by two protection box fixing bolt.
The invention also includes such structural features:
1. the number of the jettisonable supersonic speed air inlet channels is four, the jettisonable supersonic speed air inlet channels are uniformly distributed along the circumferential direction, and the air inlet channels are matched with the outer shell and are independent from other parts of the outer shell.
2. Each jettisonable supersonic air inlet is fixed on the outer shell by six explosion bolts and explosion bolt nuts which are uniformly distributed in the circumferential direction, the tail nut end of each explosion bolt is arranged outside the outer shell, the head ignition end of each explosion bolt is arranged in the outer shell, and an ignition cable for ignition penetrates through a small hole in the explosion bolt protection box to be connected with the electric control system.
3. The explosion bolt protection box is formed by welding two symmetrical half blocks, and is fixed on the air inlet channel connecting pipe through the protection box fixing bolt on each side face.
4. The air inlet connecting pipe is connected with the afterburning chamber shell through a flange containing eight circumferentially evenly distributed bolts.
5. The explosion bolt consists of an explosion bolt shell, explosion gunpowder, an explosion gunpowder sealing plug, ignition powder, a gunpowder baffle, an ignition cable and an explosion bolt sealing cover, wherein the explosion bolt sealing cover is fixed on the explosion bolt shell by six explosion bolt sealing cover bolts.
6. The space between the explosive bolt and the explosive bolt protection box is filled with sealant.
A method for controlling a throwable air inlet of a cross-medium ramjet engine specifically comprises the following steps:
(1) an air cruising stage: the supersonic air inlet is connected with the outer shell through an explosion bolt, an ignition end of the explosion bolt is arranged in the protection box, the ignition cable penetrates through a small hole in the bottom surface of the explosion bolt protection box to be connected with the electric control system, the ignition cable is not electrified, and the explosion bolt is in an unignition state. And opening the ball valve, and allowing the airflow to enter the afterburning chamber for the next reaction after the airflow is subjected to deceleration and diffusion through the air inlet channel.
(2) And (3) explosion separation stage: the ball valve is closed to seal the outer shell and the afterburning chamber. The electric control system is used for electrifying the ignition cable, the ignition cable ignites the ignition powder, and the heat of the ignition powder is transferred to the explosive powder through the explosive bolt explosive powder sealing plug. The explosive powder is heated and then burns and explodes, the explosive bolt is broken from the groove, the supersonic air inlet channel is separated from the outer shell, and the ignition end of the head of the explosive bolt falls into the protection box.
Referring to fig. 1 and 2, the throwable air inlet of the cross-media ramjet provided by the invention comprises a water inlet cross-media ramjet main body, a shell and a throwable air inlet which are connected in sequence.
The engine casing comprises a casing rear section 7, a casing middle section 8 and a casing front section 9. The three sections of outer shells are connected through flanges.
The engine main body comprises a fuel gas generator 1, a solid propellant 2, a afterburning chamber shell 3, a tail nozzle 4 and a water inlet pipe 6. The gas generator 1, the afterburning chamber shell 3 and the tail nozzle 4 are connected in sequence from front to back through threads. The solid propellant 2 is stuck in the gas generator by an adhesive, and the water inlet pipe 6 is connected to the casing of the afterburner by a screw thread.
Referring to fig. 3 and 4, the throwable inlet includes a supersonic inlet 5, an explosion bolt 10, an explosion bolt protection case 11, an inlet connection pipe 12, a sealant 13, an explosion bolt nut 14, and an explosion bolt protection case 15. The supersonic inlet 5 is fixed on the middle section 8 of the outer shell through an explosion bolt 11 and an explosion bolt nut 14. The explosion bolt protection box 11 is formed by welding two half blocks in the middle, and the explosion bolt protection box 11 and the air inlet connecting pipe 12 are fixedly connected through bolts. The empty space between the explosive bolt 10 and the explosive bolt protection box 11 is filled with sealant 13.
Referring to fig. 5, the bottom surface of supersonic inlet 5 conforms to the curvature of the outer surface of the outer casing of the engine.
Referring to fig. 6, the top surface of the side of the explosion bolt protection box 11 is exactly matched with the inner surface of the middle section 8 of the outer shell, two bolt holes for fixing bolts are arranged on the side of the half of the explosion bolt protection box 11, and a small hole for connecting an ignition cable of the explosion bolt with an electric control system inside the navigation body is arranged on the bottom surface.
Referring to fig. 7, 8 and 9, the inlet connection pipe 12 is composed of an inlet connection pipe housing 16 and an inlet valve 15. The air inlet valve 15 is positioned in the spherical cavity inside the air inlet connecting pipe shell 16, and the small holes on the two sides of the middle part of the rotating shaft air inlet connecting pipe shell 16 of the air inlet valve 15 extend out to be connected with other servo mechanisms. The upper surface of the air inlet connecting pipe 12 is a curved surface, and the curvature of the curved surface is consistent with that of the inner surface of the middle section 8 of the outer shell. Six explosion bolt holes which are uniformly distributed in the circumferential direction are formed in the upper surface of the umbrella-shaped area at the head part of the explosive bolt protection box, and two bolt holes are formed in two sides of the umbrella-shaped area and used for fixing the explosion bolt protection box 11.
Referring to fig. 10 and 11, the explosion bolt 10 is composed of an explosion bolt cover bolt 18, an explosion bolt cover 19, an ignition cable 20, a gunpowder retainer 21, an ignition charge 22, an explosion charge sealing plug 23, an explosion charge 24, and an explosion bolt housing 25. The explosive charge 24 is placed in the cavity in the middle of the explosive bolt housing 25, the open end of the cavity being sealed by an explosive charge sealing plug 23. The powder guard 21 is threadedly attached to the inner surface of the explosive bolt housing 25 and abuts the explosive charge seal 23 at the opening of the cavity in the middle of the explosive bolt housing 25. An ignition charge 22 is located in the cavity between the charge retainer 21 and the explosive charge sealing plug 23, and the ignition cable 20 is inserted into the ignition charge 22. The explosion bolt cover 19 is connected with the inner surface of the explosion bolt shell 25 through threads, the inner part of the explosion bolt cover is propped against the gunpowder baffle 21, and the head part of the explosion bolt 10 is reinforced and fixed by eight explosion bolt cover bolts 18 which are uniformly distributed in the circumferential direction.
A control scheme for controlling a cross-media ramjet jettisonable inlet, comprising:
(1) an air cruising stage: the ignition cable is not energized and the explosive bolt is not ignited. The supersonic air inlet and the air inlet connecting pipe are fixed on the middle section of the outer shell through an explosion bolt and an explosion bolt nut. And the inlet valve is opened, and the incoming air is decelerated and pressurized through the supersonic inlet and enters the afterburning chamber through the inlet connecting pipe.
(2) And (3) explosion separation stage: the ball valve is closed to seal the outer shell and the afterburning chamber. The electric control system is used for electrifying the ignition cable to ignite the ignition powder, the heat of the ignition powder is transferred to the explosion powder through the explosion bolt explosion powder sealing plug with good heat conductivity to induce the explosion powder to burn and explode, the explosion bolt is broken from the groove, the supersonic air inlet channel is separated from the outer shell, and the ignition end at the head part of the explosion bolt is lifted by the explosion bolt protection box and still stays at the original position.
(3) And (3) underwater navigation stage after entering water: the water inlet pipe starts to feed water, and the water and the fuel sprayed in the fuel gas generator continue to react and combust in the afterburning chamber. The remaining half sections of the explosive bolts and the explosive bolt protection boxes jointly seal the whole navigation body, and the navigation body enters an underwater navigation stage.
In summary, according to the throwable air inlet of the cross-medium ramjet and the control method thereof, the air inlet channel is connected to the outer shell through the explosive bolt, and the throwable air inlet of the cross-medium ramjet is designed. And in the air cruising stage, the explosion bolt does not ignite, and the air inlet channel is fixed on the outer shell. The air inlet channel compresses incoming air and introduces the air into the afterburning chamber for combustion. Before entering water, the valve of the air inlet channel is closed, the shell and the afterburning chamber are sealed, the explosion bolt is ignited and broken, the supersonic air inlet channel is separated, and the appearance structure of the navigation body is optimized after the air inlet channel is separated, so that the navigation body can better adapt to navigation in water and underwater stages. The invention designs a throwable air inlet of a cross-medium ramjet engine and provides a control method matched with the throwable air inlet, thereby reducing the resistance of underwater sailing, improving the stability of the engine during bimodal working and modal conversion and greatly improving the reliability of a cross-medium sailing body.
In the air cruise stage, air enters the engine afterburning chamber through the ram air inlet channel to further react with rich fuel gas, so that thrust is provided for the navigation body. Before the navigation body enters water, the valve of the air inlet channel is closed, so that the whole navigation body is kept sealed, the explosion bolt is ignited by electric sparks to explode, and the air inlet channel is separated from the engine shell. After the air inlet channel is separated, the resistance of the navigation body in the water entering stage and the underwater navigation stage can be greatly reduced, and the reliability is improved. The invention improves an air inlet channel of a cross-medium ramjet, designs a throwable air inlet device of the cross-medium ramjet, provides a set of separation schemes of the air inlet channel before water enters the cross-medium ramjet, and solves the problem of integral sealing of a navigation body after the air inlet channel is separated. The stability of the cross-medium ramjet engine in the process of working across the air-water interface is improved, the resistance in underwater navigation is reduced, and the comprehensive performance of the engine 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 which are 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 air entering from the air inlet channel reacts with the 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 passage are closed, 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 are closed, 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 are closed, the oxidant in the preset oxidant storage tank enters the afterburning chamber again through the primary water inlet pipe and the secondary water inlet pipe to react with rich fuel gas generated by the fuel gas generator, 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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110710427.0A CN113217227A (en) | 2021-06-25 | 2021-06-25 | Cross-medium dual-mode ramjet based on metal fuel and control method thereof |
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| CN202110710427.0A CN113217227A (en) | 2021-06-25 | 2021-06-25 | Cross-medium dual-mode ramjet based on metal fuel and control method thereof |
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Cited By (7)
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| CN113756986A (en) * | 2021-09-14 | 2021-12-07 | 中南大学 | Multi-mode cross-domain combined power system |
| CN113882965A (en) * | 2021-09-29 | 2022-01-04 | 中国人民解放军战略支援部队航天工程大学 | Metal hydrogen storage powder water-flushing engine |
| CN114017206A (en) * | 2021-10-22 | 2022-02-08 | 哈尔滨工程大学 | Submarine missile engine |
| CN114408145A (en) * | 2021-12-09 | 2022-04-29 | 哈尔滨工程大学 | Preheating type water inlet ramjet engine structure and control method |
| CN114562384A (en) * | 2022-03-21 | 2022-05-31 | 西北工业大学 | Multipurpose aeroengine |
| CN114562367A (en) * | 2022-01-27 | 2022-05-31 | 南京航空航天大学 | Mixing combustion device of ramjet engine and mixing combustion verification method thereof |
| CN115479508A (en) * | 2022-09-01 | 2022-12-16 | 华中科技大学 | Self-starting turbine water flushing combined engine based on fuel gas generator driving |
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| CN111734550A (en) * | 2020-06-15 | 2020-10-02 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
| CN111749814A (en) * | 2020-06-15 | 2020-10-09 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method |
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| CN111734551A (en) * | 2020-06-15 | 2020-10-02 | 哈尔滨工程大学 | Separated multi-stage thrust underwater power system and control method thereof |
| CN111734550A (en) * | 2020-06-15 | 2020-10-02 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113756986A (en) * | 2021-09-14 | 2021-12-07 | 中南大学 | Multi-mode cross-domain combined power system |
| CN113882965A (en) * | 2021-09-29 | 2022-01-04 | 中国人民解放军战略支援部队航天工程大学 | Metal hydrogen storage powder water-flushing engine |
| CN113882965B (en) * | 2021-09-29 | 2023-12-29 | 中国人民解放军战略支援部队航天工程大学 | Metal hydrogen storage powder water ramjet engine |
| CN114017206A (en) * | 2021-10-22 | 2022-02-08 | 哈尔滨工程大学 | Submarine missile engine |
| CN114408145A (en) * | 2021-12-09 | 2022-04-29 | 哈尔滨工程大学 | Preheating type water inlet ramjet engine structure and control method |
| CN114562367A (en) * | 2022-01-27 | 2022-05-31 | 南京航空航天大学 | Mixing combustion device of ramjet engine and mixing combustion verification method thereof |
| CN114562384A (en) * | 2022-03-21 | 2022-05-31 | 西北工业大学 | Multipurpose aeroengine |
| CN114562384B (en) * | 2022-03-21 | 2023-04-25 | 西北工业大学 | Multipurpose aeroengine |
| CN115479508A (en) * | 2022-09-01 | 2022-12-16 | 华中科技大学 | Self-starting turbine water flushing combined engine based on fuel gas generator driving |
| CN115479508B (en) * | 2022-09-01 | 2023-09-01 | 华中科技大学 | Self-starting turbine water stamping combined engine based on gas generator driving |
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