CN113879052B - Cross-medium water stamping power system and aircraft - Google Patents
Cross-medium water stamping power system and aircraft Download PDFInfo
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- CN113879052B CN113879052B CN202111233328.4A CN202111233328A CN113879052B CN 113879052 B CN113879052 B CN 113879052B CN 202111233328 A CN202111233328 A CN 202111233328A CN 113879052 B CN113879052 B CN 113879052B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/08—Propulsion
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Abstract
The invention relates to the field of cross-medium aircrafts, in particular to a cross-medium water stamping power system, which comprises: the water flushing engine is communicated with the water inlet channel, and the water inlet channel is also communicated with the outside; the water storage device is used for storing water; and the power device can drive water in the water storage device to enter the water ramjet engine. The cross-medium water stamping power system provided by the invention enables the water stamping engine to maintain the working state after the aircraft is discharged with water, and can complete the air attitude adjustment of the aircraft. The invention also provides an aircraft.
Description
Technical Field
The invention relates to the field of cross-medium aircrafts, in particular to a cross-medium water stamping power system and an aircraft.
Background
At present, a submarine serving as a mature underwater operation platform has obvious development lag of the air attack capability, and cannot launch an air vehicle in a missile mode on sea and land targets, so that a weapon platform launching water under water has certain practical significance. Modern naval protection systems already have systematic and mature detection and defense schemes for navigation bodies in the form of torpedoes and missiles, however, radar-and sonar-based detection systems and various defense means cannot effectively attack navigation bodies which can frequently enter and exit water.
The current underwater power system mainly comprises conventional thermal power and electric power, and the conventional thermal power and the conventional electric power are used by combining propellers, so that the sailing speed is limited, and the penetration capability is limited. The water-jet engine adopts surrounding seawater as an oxidant, can realize higher navigation speed by matching with a jet propulsion mode, has the advantages of high navigation speed and high sudden defense capability, and is the first choice of an underwater high-speed power scheme. However, the water pressure engine is used as an oxidant, and the existing cross-medium aircraft is difficult to solve the working problem of the water pressure engine after water is discharged from the cross-medium aircraft by using the water pressure engine.
Disclosure of Invention
The invention aims to provide a cross-medium water ram power system and an aircraft, which are used for solving the problems in the prior art, and the water ram engine can maintain the working state after the aircraft is discharged with water and can complete the air attitude adjustment of the aircraft.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a cross-medium water stamping power system, which comprises: the water flushing engine is communicated with the water inlet channel, and the water inlet channel is also communicated with the outside; the water storage device is used for storing water; and the power device can drive water in the water storage device to enter the water stamping engine.
Preferably, a first one-way valve is arranged in the water inlet channel, a second one-way valve is arranged on the water impact engine, and the water storage device is communicated with the water inlet channel; when the aircraft navigates underwater, water in the navigation area can sequentially pass through the first one-way valve and the second one-way valve to enter the water pressure engine, and meanwhile, water in the navigation area can enter the water storage device through the first one-way valve; when the aircraft sails in the air, the power device can drive water in the water storage device to enter the water pressure engine through the second one-way valve.
Preferably, the water storage device is arranged as an annular water storage tank, and the annular water storage tank is fixedly sleeved at the tail part of the water-flushing engine; one end of the annular water storage tank is communicated with the water inlet channel, and the power device is used for enabling water in the annular water storage tank to enter the water ram engine through the second one-way valve.
Preferably, the power plant comprises: the fuel gas generator is used for generating fuel gas at the tail part in the annular water storage tank and is electrically connected with a control system; the annular piston is arranged in the annular water storage tank and is coaxial with the annular water storage tank, and the peripheral surface of the annular piston is in close contact with the inner wall surface of the annular water storage tank; the pressure relief valve is arranged on the rear wall surface of the annular water storage tank and is electrically connected with the control system, and the pressure relief valve is used for discharging the fuel gas generated by the fuel gas generator to the outside; when the aircraft sails in the air, the control system is used for controlling the fuel gas generator to generate fuel gas and pushing the annular piston to move axially in the annular water storage tank, so that water in the annular water storage tank enters the water pressure engine through the second one-way valve.
Preferably, the gas generator comprises: the cross section of the shell is set to be circular, the shell is provided with a cylindrical cavity with one side opened, and the side wall of the shell opposite to the opening side of the cavity is fixedly connected with the rear wall of the annular water storage tank; the fuel gas grain is positioned in the cavity; the ignition component is electrically connected with the control system through an ignition wire and is used for igniting the fuel gas grain; the gland with a circular section is arranged on the opening side of the cavity and is in threaded connection with the shell to seal the cavity; a plurality of uniformly distributed air outlet holes are formed in the gland, and the air outlet holes are sealed through aluminum foil; the control system is used for controlling the ignition part to ignite the fuel gas grain to generate fuel gas, and the fuel gas can break through the aluminum foil and push the annular piston to move.
Preferably, the gas grain is arranged in a circular column shape, and the outer peripheral surface of the gas grain and the inner wall surface of the shell are closely arranged in a clearance; the ignition part is a steel igniter, the steel igniter and the fuel gas grain are coaxially arranged, a wiring end of the steel igniter sequentially penetrates through the side wall of the shell, away from the gland, and the rear wall of the annular water storage tank to be electrically connected with the control system, and an ignition end of the steel igniter is positioned in a cylindrical hole in the fuel gas grain; and the steel igniter and the side wall of the shell far away from the gland and the rear wall of the annular water storage tank are fixedly connected.
Preferably, the gas grain is arranged in a cylinder shape, and the peripheral surface of the gas grain is closely attached to the inner wall surface of the shell; the ignition part is set to be an ignition explosive package, the ignition explosive package is arranged on the side face, facing the gland, of the fuel gas explosive column, a first round hole and a second round hole which are opposite to each other are respectively arranged on the side wall, away from the gland, of the shell and the rear wall of the annular water storage tank, a groove used for embedding the ignition wire is formed in the shell, one end of the ignition wire is connected with the ignition explosive package, and the other end of the ignition wire sequentially penetrates through the first round hole and the second round hole to be connected with the control system.
Preferably, the first round hole and the second round hole are coaxially arranged, and the diameter of the first round hole is larger than that of the second round hole; the fuel gas generator also comprises a steel blocking piece with a circular section, the steel blocking piece is provided with a large-diameter section and a small-diameter section along the axial direction, the large-diameter section is fixedly connected with the first round hole, and the small-diameter section is fixedly connected with the second round hole; and the steel plug sheet is provided with a through hole for the ignition wire to pass through along the axis.
Preferably, the number of the gas generators is multiple, the gas generators are uniformly arranged in the annular water storage tank along the circumferential direction of the annular water storage tank, and the peripheral surface of each gas generator is provided with a heat insulation coating.
The invention also provides an aircraft comprising a body having a water intake channel; and the cross-medium water stamping power system.
Compared with the prior art, the invention has the following technical effects:
the invention provides a cross-medium water stamping power system, when an aircraft navigates underwater, water in a navigation area can enter a water stamping engine through a water inlet channel, so that the water stamping engine provides power required by the aircraft to fly; when the aircraft sails from underwater to air across the medium, because no water source is provided in the air sailing area, the water ram engine is likely to stop working, so that the aircraft loses power, therefore, water in the water storage device can enter the water ram engine through the power device, the water ram engine is enabled to maintain the working state, and power required by the aircraft flying and changing the air posture is continuously provided.
The invention also provides an aircraft which has enough power to maintain the flight state and change the air attitude after crossing the medium.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic sectional view of a gasifier provided in accordance with a first embodiment;
FIG. 2 is a left side elevational view of the gasifier as provided in FIG. 1;
FIG. 3 is a schematic sectional view of a gasifier provided in accordance with a second embodiment;
FIG. 4 is a left side view of the gasifier as provided in FIG. 3;
figure 5 is a cutaway schematic view of a vehicle provided in a third embodiment;
FIG. 6 is an enlarged schematic view at A in bitmap 5;
fig. 7 is a right side view of the aircraft of fig. 5.
Icon: 1-an aircraft; 11-water ram engine; 12-a water inlet channel; 13-a water storage device; 14-a power plant; 141-a gas generator; 1411-a housing; 14111-grooves; 1412-a cavity; 1413, a fuel gas grain; 1414-an ignition component; 1415-an ignition wire; 1416-gland; 1417-air outlet holes; 1418-steel blanking pieces; 142-a ring-shaped piston; 143-relief valve; 15-a first one-way valve; 16-a second one-way valve; 17-a control system; 18-a cavitator; 19-battle sector.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a cross-medium water ram power system and an aircraft, which are used for solving the problems in the prior art, and the water ram engine can maintain the working state after the aircraft is discharged with water and can complete the air attitude adjustment of the aircraft.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example one
The invention provides a cross-medium water stamping power system, please refer to fig. 5, comprising: the water pressure engine 11, the water pressure engine 11 is communicated with the water inlet channel 12, and the water inlet channel 12 is also communicated with the outside; the water storage device 13 is used for storing water in the water storage device 13; and a power device 14, wherein the power device 14 is used for enabling the water in the water storage device 13 to enter the water ramjet engine 11.
When the aircraft 1 navigates underwater, water in the navigation area can enter the water ram engine 11 through the water inlet channel 12, so that the water ram engine 11 provides power required by the aircraft 1 for flying; after the aircraft 1 sails across the medium from water to air, because no water source is provided in the air sailing area, the water ram engine 11 is likely to stop working, so that the aircraft 1 loses power, and therefore, the water in the water storage device 13 can enter the water ram engine 11 through the power device 14, the water ram engine 11 is enabled to maintain a working state, and power required by the aircraft 1 to fly and change the air posture is continuously provided.
In an alternative of this embodiment, please refer to fig. 6, preferably, a first check valve 15 is disposed in the water inlet channel 12, a second check valve 16 is disposed on the water-flushing engine 11, and the water storage device 13 is communicated with the water inlet channel 12; according to the arrangement, when the aircraft 1 is positioned under water for navigation, water enters the water ramjet engine 11 through the first check valve 15 and the second check valve 16, so that the water ramjet engine 11 works to provide power required by the aircraft 1 for flying; meanwhile, water in the navigation area enters the water storage device 13 through the first one-way valve 15 to finish water storage in the water storage device 13, so that the water storage device 13 provides water for flushing the engine 11 with water when the aircraft 1 navigates in the air; when the aircraft 1 is in air for navigation, the power device 14 is used for enabling water in the water storage device 13 to enter the water ramjet engine 11 through the second one-way valve 16, so that the water ramjet engine 11 can maintain a working state in the air section, and at the moment, the first one-way valve 15 is closed, so that the water in the water storage device 13 is prevented from flowing out of the aircraft 1 from the water inlet channel 12; the provision of the first check valve 15 and the second check valve 16 ensures the flow direction of the water inside the aircraft 1.
It should be noted that the number of the first check valve 15 and the second check valve 16 may be determined according to actual situations.
In an alternative of this embodiment, please refer to fig. 5, preferably, the water storage device 13 is configured as an annular water storage tank, and the annular water storage tank is fixedly sleeved at the tail of the water-jet engine 11; the long tail nozzle of the water ramjet engine 11 is generally thin in diameter, so that the water storage capacity can be increased by arranging the long tail nozzle into an annular water storage tank; meanwhile, the water storage device 13 can also play a role in cooling the long tail nozzle of the water-jet engine 11; one end of the annular water storage tank is communicated with the water inlet channel 11, and the power device 14 is used for enabling water in the annular water storage tank to enter the water ramjet engine 11 through the second one-way valve 16 when the aircraft 1 is in the air-intermediate section.
In an alternative aspect of the present embodiment, preferably, referring to fig. 5, 6 and 7, the power device 14 includes: the fuel gas generator 141 is used for generating fuel gas at the tail part in the annular water storage tank, and the fuel gas generator 141 is electrically connected with the control system 17; the annular piston 142 is arranged in the annular water storage tank and is coaxial with the annular water storage tank, and the peripheral surface of the annular piston 142 is tightly contacted with the inner wall surface of the annular water storage tank, so that the sealing performance of the annular piston 142 in the annular water storage tank is ensured; and the pressure relief valve 143 is arranged on the rear wall surface of the annular water storage tank and is electrically connected with the control system 17, and the pressure relief valve 143 is used for discharging the fuel gas generated by the fuel gas generator 141 to the outside.
When the aircraft 1 sails in the air and the water storage device 13 is required to provide water for the water ram engine 11, the control system 17 controls the fuel gas generator 141 to generate enough fuel gas in the tail part of the annular water storage tank and pushes the annular piston 142 to move in the annular water storage tank along the axial direction, the annular piston 142 pushes the water in the annular water storage tank into the water ram engine 11 through the second one-way valve 16, and in the process, the control system 17 can adjust the opening degree of the pressure release valve 143 to adjust the movement speed of the annular piston 142 in the annular water storage tank, so that the water inflow of the water ram engine is controlled; when the vehicle 1 is going to go back into underwater navigation, the water in the navigation area enters the annular storage tank through the first one-way valve 15 and pushes the annular piston 142 back to the rear of the annular storage tank and close to the gas generator 141, during which the control system 17 controls the relief valve 143 to open to purge the gas generated by the gas generator 141, allowing the annular piston 143 to be fully retracted to complete the preparation of the next air navigation of the vehicle 1.
In an alternative to this embodiment, and preferably with reference to fig. 1 and 2, the gasifier 141 includes: the cross section of the shell 1411 is circular, the shell 1411 is provided with a cylindrical cavity 1412 with one side open, and the side wall of the shell 1411 opposite to the open side of the cavity 1412 is fixedly connected with the rear wall of the annular water storage tank; the gas explosive column 1413 is positioned in the cavity 1412; the ignition component 1414 is electrically connected with the control system 17 through an ignition wire 1415, and the ignition component 1414 is used for igniting the fuel gas charge 1413; and a gland 1416 with a circular cross section, which is arranged on the opening side of the cavity 1412, wherein the gland 1416 is fixedly connected with the housing 1411 for closing the cavity 1412, the gland 1416 also has the function of fixing the gas cartridge 1413, and preferably, the gland 1416 is in threaded connection with the housing 1411; the gland 1416 is provided with a plurality of uniformly distributed air outlet holes 1417, the air outlet holes 1417 are sealed by aluminum foil, and the aluminum foil can prevent the gas grain 1413 from being affected with damp when the gas generator 141 does not work.
The sections of all parts of the gas generator 141 are circular, so that the gas generator is convenient to assemble and integrally arranged and installed in the annular water storage tank; when the aircraft 1 is located in the vacant center and water needs to be supplied to the water ram engine 11 by the water storage device 13, the control system 17 is used for controlling the ignition component 1414 to ignite the gas grain 1413 to generate gas, and the gas can break through the aluminum foil and push the annular piston 142 to move, so that water is supplied to the water ram engine 11.
In the alternative of this embodiment, please refer to fig. 1, preferably, the gas cartridge 1413 is configured to be a circular column, and the outer peripheral surface of the gas cartridge 1413 is disposed in a gap with the inner wall surface of the housing 1411; at this time, the column hole space of the gas grain 1413 is communicated with the space between the outer peripheral surface of the gas grain 1413 and the inner wall surface of the housing 1411; the ignition component 1414 is a steel igniter, the steel igniter and the fuel gas grain 1413 are coaxially arranged, a terminal of the steel igniter sequentially penetrates through the side wall of the shell 1411 far away from the gland 1416 and the rear wall of the annular water storage tank to be electrically connected with the control system 17, an ignition end of the steel igniter is located in a cylindrical hole in the fuel gas grain 1413, and the control system 17 controls the steel igniter to ignite; the side wall of the housing 1411 far away from the gland 1416 and the rear wall of the annular water storage tank are fixedly connected, preferably, the side wall of the housing 1411 far away from the gland 1416 and the rear wall of the annular water storage tank are in threaded connection, and the housing 1411 can be fixedly connected with the rear wall of the annular water storage tank by the steel igniter, so that the gas generator 141 is prevented from moving; in addition, the rear wall of the annular water storage tank is provided with the wire hole for the ignition wire to pass through, so that the strength of the rear wall of the annular water storage tank is reduced, and when a large amount of fuel gas is generated by the fuel gas generator 141, the pressure difference between the inside and the outside of the annular water storage tank is large, so that the problem that the strength of the rear wall of the annular water storage tank is not enough due to the hole is solved by fixedly connecting the steel igniter with the rear wall of the annular water storage tank.
Further, referring to fig. 1, the outer diameter of the gland 1416 is larger than the outer diameter of the housing 1411, the end surface of the gland 1416 is provided with internal threads, and the circumferential surface of the housing 1411 is provided with external threads; the gland 1416 can plug the cavity 1412 and fix the position of the gas grain 1413, and the gas grain 1413 is arranged in such a way that the space of the hole of the gas grain 1413 is communicated with the space between the outer peripheral surface of the gas grain 1413 and the inner wall surface of the shell 1411, when the steel igniter ignites the inner peripheral surface of the hole of the gas grain 1413, the outer peripheral surface of the gas grain 1413 is ignited at the same time, namely the inner and outer peripheral surfaces of the gas grain 1413 are ignited at the same time to generate gas, the area of the inner peripheral surface is increasingly larger, the area of the outer peripheral surface is increasingly smaller, so that the gas generation amount of the gas grain 1413 is kept stable, and the combustion time of the gas grain 1413 is determined by the distance between the inner peripheral surface and the outer peripheral surface; and the gas grain 1413 is suitable for the condition that the diameter of the long tail nozzle of the water-jet engine 11 is smaller, in this case, the radial space of the annular water storage tank is large, the radial size of the gas generator 141 is large, and the adjustable range of the distance between the inner and outer peripheral surfaces of the gas grain 1413 is large, so that the combustion time of the gas grain 1413 can be controlled.
In the alternative of this embodiment, it is preferable that the number of the gas generators 141 is multiple, and the multiple gas generators 141 are uniformly arranged in the annular water storage tank along the circumferential direction of the annular water storage tank; the firing block 1414 of each gas generator 141 is connected to a control system, the arrangement of a plurality of gas generators 141 being such as to increase the number of times the aircraft 1 crosses the medium, the control system 17 being such as to control the number of gas generators 141 activated at each time; the outer circumference of each gas generator 141 is provided with a thermal insulation coating to prevent interference between adjacent gas generators 141.
Example two
The present embodiment provides another cross-medium water ram power system, which is different from the first embodiment only in the structure of the gas generator 141.
In an alternative of this embodiment, preferably, referring to fig. 3, the gas cartridge 1413 is configured to be a cylindrical shape, and a circumferential surface of the gas cartridge 1413 is closely attached to an inner wall surface of the housing 1411; the ignition component 1414 is provided with an ignition explosive charge, the ignition explosive charge is arranged on the side surface of the fuel gas explosive column 1413 facing the gland 1416, the side wall of the shell 1411 far away from the gland 1416 and the rear wall of the annular water storage tank are respectively provided with a first round hole and a second round hole which are opposite, a groove 14111 for embedding an ignition wire 1415 is arranged in the shell 1411, one end of the ignition wire 1415 is connected with the ignition explosive charge, and the other end of the ignition wire 1415 sequentially penetrates through the first round hole and the second round hole to be connected with the control system 17; the groove 14111 serves to protect the ignition wire 1415 from burning.
Further, referring to fig. 3, the outer diameter of the gland 1416 is smaller than the outer diameter of the housing 1411, the end surface of the gland 1416 is provided with external threads, and the circumferential surface of the housing 1411 is provided with internal threads; the gland 1416 can fix the position of the gas grain 1413; the combustion surface of the gas grain 1413 is the side surface where the ignition explosive bag is located, namely the combustion time of the gas grain 1413 is determined by the axial length of the gas grain itself; and the gas grain 1413 is suitable for the condition that the diameter of a long tail nozzle of the water-jet engine 11 is larger, in this case, the radial space of the annular water storage tank is small, the radial size of the gas generator 141 is small, and the adjustable range of the radial size of the gas grain 1413 is small, so that the combustion time of the gas grain 1413 is controlled by controlling the axial space occupied by the gas generator 141 and the gas grain 1413.
In the alternative of this embodiment, it is preferable that the first circular hole and the second circular hole are coaxially disposed, and the diameter of the first circular hole is larger than that of the second circular hole; referring to fig. 3, the gasifier 141 further includes a steel blocking piece 1418 with a circular cross section, the steel blocking piece 1418 has a large diameter section and a small diameter section along an axial direction, the large diameter section is fixedly connected to the first circular hole, the small diameter section is fixedly connected to the second circular hole, the steel blocking piece 1418 is used for fixedly connecting the housing 1411 to the rear wall of the annular water storage tank, preferably, the large diameter section is in threaded connection with the first circular hole, and the small diameter section is in threaded connection with the second circular hole; and the steel blanking tab 1418 is provided with a through hole along the axis for the ignition wire 1415 to pass through; because the back wall of annular storage water tank is provided with the second round hole that is used for ignition wire 1415 to pass through, can make the back wall intensity of annular storage water tank reduce, and after gas generator 141 produced a large amount of gas, the annular storage water tank internal and external pressure differential is very big, consequently set up the back wall fixed connection of steel closure plate 1418 and annular storage water tank, can alleviate the annular storage water tank back wall and lead to the not enough problem of intensity because of the trompil, and the big footpath section that steel closure plate 1418 set up can play the effect of further ensuring intensity around annular storage water tank back wall second round hole.
EXAMPLE III
The present embodiment also provides an aircraft, please refer to fig. 5, which includes a main body having a water inlet channel 12, wherein the main body includes a cavitator 18, a control system 17, a warhead 19 and the cross-medium water ram power system provided in the first embodiment.
Wherein the cross-medium water ram power system provided by the first embodiment is further replaced by the cross-medium water ram power system provided by the second embodiment.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (10)
1. A cross-medium water stamping power system is characterized in that: the method comprises the following steps:
the water pressure jetting engine (11), the water pressure jetting engine (11) is communicated with the water inlet channel (12), and the water inlet channel (12) is also communicated with the outside;
the water storage device (13) is used for storing water, the water storage device (13) is arranged to be an annular water storage tank, and one end of the annular water storage tank is communicated with the water inlet channel (12); and
a power plant (14), said power plant (14) comprising a gas generator (141) and an annular piston (142), said gas generator (141) being adapted to generate gas at the rear of said annular reservoir, said annular piston (142) being arranged inside said annular reservoir;
when the aircraft (1) sails in the air, the fuel gas generator (141) generates fuel gas and pushes the annular piston (142) to move axially in the annular water storage tank, so that water in the annular water storage tank enters the water ram engine (11).
2. The cross-media water ram power system of claim 1, wherein: a first one-way valve (15) is arranged in the water inlet channel (12), a second one-way valve (16) is arranged on the water-pressure engine (11), and the water storage device (13) is communicated with the water inlet channel (12);
when the aircraft (1) navigates underwater, water in an navigation area can enter the water ram engine (11) through the first one-way valve (15) and the second one-way valve (16) in sequence, and meanwhile, water in the navigation area can enter the water storage device (13) through the first one-way valve (15);
when the aircraft (1) sails in the air, the power device (14) can drive water in the water storage device (13) to enter the water ram engine (11) through the second one-way valve (16).
3. The cross-media water ram power system of claim 2, wherein: the annular water storage tank is fixedly sleeved at the tail part of the water flushing engine (11);
the power device (14) is used for enabling water in the annular water storage tank to enter the water-flushing engine (11) through the second one-way valve (16).
4. The cross-media water ram power system of claim 3, wherein: the power plant (14) further comprises a pressure relief valve (143): the gas generator (141) is electrically connected with a control system (17); the annular piston (142) and the annular water storage tank are coaxially arranged, and the peripheral surface of the annular piston (142) is in close contact with the inner wall surface of the annular water storage tank; the pressure relief valve (143) is arranged on the rear wall surface of the annular water storage tank and is electrically connected with the control system (17), and the pressure relief valve (143) is used for discharging gas generated by the gas generator (141) to the outside;
when the aircraft (1) sails in the air, the control system (17) is used for controlling the fuel gas generator (141) to generate fuel gas and pushing the annular piston (142) to move axially in the annular water storage tank, so that water in the annular water storage tank enters the water ram engine (11) through the second one-way valve (16).
5. The cross-media water ram power system of claim 4, wherein: the gas generator (141) comprises:
the cross section of the shell (1411) is set to be circular, the shell (1411) is provided with a cylindrical cavity (1412) with one side opened, the shell (1411) is positioned in the annular water storage tank, and the side wall of the shell (1411) opposite to the opening side of the cavity (1412) is fixedly connected with the rear wall of the annular water storage tank;
a gas plume (1413), the gas plume (1413) being located within the cavity (1412);
an ignition component (1414), the ignition component (1414) being electrically connected with the control system (17) by an ignition wire (1415), the ignition component (1414) being for igniting the gas grain (1413); and
a gland (1416) with a circular cross section and arranged on the opening side of the cavity (1412), wherein the gland (1416) is fixedly connected with the shell (1411) and used for closing the cavity (1412); a plurality of air outlet holes (1417) which are uniformly distributed are formed in the gland (1416), and the air outlet holes (1417) are sealed through aluminum foil;
the control system (17) is used for controlling the ignition part (1414) to ignite the fuel gas grain (1413) to generate fuel gas which can break through the aluminum foil and push the annular piston (142) to move.
6. The cross-media water ram power system of claim 5, wherein: the gas explosive column (1413) is arranged in a circular column shape, and the outer peripheral surface of the gas explosive column (1413) and the inner wall surface of the shell (1411) are arranged in a clearance manner;
the ignition component (1414) is arranged into a steel ignition tool, the steel ignition tool and the gas explosive column (1413) are coaxially arranged, a wiring terminal of the steel ignition tool sequentially penetrates through the side wall of the shell (1411) far away from the gland (1416) and the rear wall of the annular water storage tank to be electrically connected with the control system (17), and an ignition end of the steel ignition tool is positioned in a column hole in the gas explosive column (1413); and the steel igniter is fixedly connected with the side wall of the shell (1411) far away from the gland (1416) and the rear wall of the annular water storage tank.
7. The cross-media water ram power system of claim 5, wherein: the gas explosive column (1413) is cylindrical, and the peripheral surface of the gas explosive column (1413) is tightly attached to the inner wall surface of the shell (1411);
the ignition component (1414) is arranged to be an ignition explosive bag, the ignition explosive bag is arranged on the side face, facing the gland (1416), of the fuel gas explosive column (1413), a first round hole and a second round hole which are opposite to each other are respectively formed in the side wall, away from the gland (1416), of the shell (1411) and the rear wall of the annular water storage tank, a groove (14111) used for embedding the ignition wire (1415) is formed in the shell (1411), one end of the ignition wire (1415) is connected with the ignition explosive bag, and the other end of the ignition wire (1415) sequentially penetrates through the first round hole and the second round hole to be connected with the control system (17).
8. The cross-media water ram power system of claim 7, wherein: the first round hole and the second round hole are coaxially arranged, and the diameter of the first round hole is larger than that of the second round hole;
the fuel gas generator (141) further comprises a steel blocking piece (1418) with a circular section, the steel blocking piece (1418) is provided with a large-diameter section and a small-diameter section along the axial direction, the large-diameter section is fixedly connected with the first round hole, and the small-diameter section is fixedly connected with the second round hole; and the steel plug piece (1418) is provided with a through hole along the axis for the ignition wire (1415) to pass through.
9. The cross-media water ram power system of claim 5 or 7, wherein: the number of the fuel gas generators (141) is multiple, the fuel gas generators (141) are uniformly arranged in the annular water storage tank along the circumferential direction of the annular water storage tank, and the peripheral surface of each fuel gas generator (141) is provided with a heat insulation coating.
10. An aircraft, characterized by: the method comprises the following steps:
a body having a water inlet passage (12); and
the cross-media water ram power system of any one of claims 1-9.
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| CN201849273U (en) * | 2010-11-16 | 2011-06-01 | 沈东明 | Four-function jet-propelled helicopter-type diving airship |
| CN102606342B (en) * | 2011-01-19 | 2017-08-15 | 徐清华 | A kind of application method of metal-powder powder column connection |
| CN109098891B (en) * | 2018-10-11 | 2019-11-01 | 中国人民解放军国防科技大学 | Cross-medium ramjet based on solid propulsion |
| CN110107426B (en) * | 2019-05-08 | 2020-08-14 | 中国航空发动机研究院 | Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing |
| CN110239712B (en) * | 2019-07-10 | 2021-01-12 | 中国科学院自动化研究所 | Water-air amphibious cross-medium bionic robot flying fish |
| CN112141268B (en) * | 2020-09-14 | 2021-09-28 | 大连理工大学 | Power type fish-thunder anchor based on bionics and installation method thereof |
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