CN116428916A - A boron-based ram thrust trans-media aircraft - Google Patents

Abstract

The invention relates to a boron-based ram propulsion cross-medium aircraft, comprising: cavitation device, auxiliary cabin section, gas generator, separator, boosting cabin section and guide device; the cavitation device, the auxiliary cabin section, the gas generating device, the separation device and the boosting cabin section are coaxially arranged; the cavitation device is connected to the head of the auxiliary cabin section, the gas generating device is connected to the tail of the auxiliary cabin section, the separation device is detachably connected to the tail of the gas generating device, and the boosting cabin section is connected to the tail of the separation device; the guiding device is arranged in the cavitation device; the head of the auxiliary cabin section is provided with a separable fairing, and the cavitation device is positioned in the fairing; the fuel gas generating device is filled with a boron-based solid propellant; the boosting cabin section is filled with a boosting agent; when the boron-based stamping propulsion cross-medium aircraft is transferred from air flight to underwater navigation, the separation device and the boost cabin section are separated from the gas generating device.

Description

A boron-based ramjet-propelled cross-medium aircraft

Technical Field

The present invention relates to the field of trans-medium aircraft, and in particular to a boron-based ramjet-propelled trans-medium aircraft.

Background Art

At present, the commonly used weapons in the ocean battlefield are mainly torpedoes and anti-ship missiles. As a major underwater offensive and defensive weapon, torpedoes have the advantages of strong striking power, good concealment, high hit rate, and strong anti-interference ability; missiles have the advantages of long range, high speed, and strong maneuverability. However, with the development of modern offensive and defensive technologies, conventional aircraft (missiles/torpedoes) sailing in a single medium have become increasingly difficult to efficiently break through the fleet's anti-missile network. Therefore, the concept of cross-medium aircraft has been proposed.

Compared with single-medium aircraft, cross-medium aircraft have the characteristics of fast air flight speed and good underwater concealment. They can effectively enhance the maneuverability, flexibility and evasion ability of weapons, and have the ability to launch and respond quickly. They are suitable for performing various complex tasks and have very broad application prospects.

The existing cross-medium aircraft are mainly anti-submarine missiles and rocket-assisted torpedoes. The research on cross-medium aircraft at home and abroad mainly includes two aspects: variant structure design and cross-medium propulsion technology. Common variant structure designs mainly include folding wings, variable sweep wings and bionic wings. By changing their airfoil structures, they are suitable for air and underwater navigation and are used in low-speed and low-altitude scenarios. Common cross-medium propulsion technologies include thermoelectric combined power systems and ramjet power systems.

Existing variable-configuration cross-medium aircraft are suitable for navigation in air and water by changing their wing structure. They are generally used in specific operation scenarios, have limited operation capabilities, and are suitable for low-speed and low-altitude working conditions. In addition, the aircraft structure is also relatively complex, and its destructive capability as a marine battlefield weapon is very limited.

Existing trans-medium aircraft that use a thermoelectric combined power system have low underwater power and endurance that cannot meet design requirements due to the limitation of battery capacity by the fuselage of the trans-medium aircraft. For example, the "submersible aircraft" program proposed by the US Defense Advanced Research Projects Agency uses a turbofan engine to provide air power and a propeller motor to improve the power system for underwater navigation.

Existing anti-submarine missiles and rocket-assisted torpedo cross-medium aircraft use rocket engines to boost and parachute into the water, which leads to problems such as short range, low specific impulse, slow cross-domain, and easy interception. For example, Australia's Ikara anti-submarine missile and the United States' Sea Lance rocket-assisted torpedo use rocket engines to boost and parachute into the water to achieve cross-medium flight.

The new cross-medium aircraft based on ramjet engines currently under development mainly focus on the research of power schemes, and most of them are in the research of a single working environment. The representative ones are the research on the working characteristics of solid ramjet engines and water ramjet engines. For example, Chen Wenwu et al. proposed a new cross-medium engine scheme, using the same metal-based (magnesium-aluminum) solid propellant, using air as an oxidant in the air to adopt the solid rocket ramjet engine working mode, and using water as an oxidant in the water to adopt the water ramjet engine mode, and calculated the theoretical performance of the engine under typical working conditions. Shi Lei et al. proposed an air-water ramjet combined cross-medium anti-ship and anti-submarine missile, which uses a composite magnesium rod as fuel, uses oxygen and its own liquid oxidant to react with the rich fuel gas generated by the magnesium rod in the air to generate thrust, and directly enters water to react with the magnesium rod in the water to generate thrust. The cross-medium ramjet engine designed by Du Quan et al. has the ability to cross water and air at multiple frequencies, fly at Mach numbers of 0 to 4, and sail underwater at high speed. Zhou Ling and others designed a cross-medium power system scheme based on the ramjet engine, using aluminum-based and magnesium-based metal propellants as the energy source of the cross-medium power system, and adopting a ring-nested (parallel) gas generator layout scheme in the design of the gas generator.

[1] Chen Wenwu, Huang Liya, Xia Zhixun, Li Pengfei. Analysis of theoretical performance and operating parameters of trans-medium ramjet engine[J]. Acta Aeronautica Sinica, 2020, 41(11): 202-211.

[2] Du Quan, Wang Yufeng, Hu Yanxiao, Mo Jianwei, Chen Lei, Zhu Xianhao, Li Jianghan. A wide-range multi-frequency water-jumping air turbine ramjet combined engine and its control method [P]. Shaanxi Province: CN114439645A, 2022-05-06.

[3] Shi Lei, Yang Yiyan, Jin Bingning, Xiao Bo, He Guoqiang. An air-water ramjet combined cross-medium anti-ship and anti-submarine missile[P]. Shaanxi Province: CN113108654B, 2021-11-23.

[4] Zhou Ling. Analysis of cross-medium power system scheme and research on modal conversion[D]. Harbin Engineering University, 2021. DOI: 10.27060/d.cnki.ghbcu.2021.000535.

Summary of the invention

The object of the present invention is to provide a boron-based ramjet-propelled trans-medium aircraft.

To achieve the above-mentioned invention object, the present invention provides a boron-based ramjet-propelled cross-medium aircraft, comprising: a cavitation device, an auxiliary cabin section, a gas generating device, a separation device, a booster cabin section and a guidance device;

The cavitation device, the auxiliary compartment, the gas generating device, the separation device and the booster compartment are coaxially arranged with each other; wherein the cavitation device is connected to the head of the auxiliary compartment, the gas generating device is connected to the tail of the auxiliary compartment, the separation device is detachably connected to the tail of the gas generating device, and the booster compartment is connected to the tail of the separation device;

The guiding device is arranged in the cavitation device;

The head of the auxiliary compartment is provided with a detachable fairing, and the cavitation device is located inside the fairing;

The gas generating device is filled with a boron-based solid propellant;

The booster compartment is filled with a propellant;

When the boron-based ramjet-propelled trans-medium aircraft switches from air flight to water navigation, the separation device and the booster compartment are separated from the gas generating device.

According to one aspect of the present invention, the boron-based ramjet-propelled trans-medium aircraft includes: a boost phase, a cruise phase, and a gliding phase during its flight in the air;

When in the boosting stage, the boosting compartment burns the propellant to provide power;

When in the cruise phase, the gas generating device burns part of the boron-based solid propellant to generate primary gas, and the primary gas provides power after secondary combustion of the booster compartment section mixed with the introduced air;

When in the cruising stage, the gas generating device is shut down;

During the underwater navigation of the boron-based ramjet-propelled trans-medium aircraft, the fairing is separated from the auxiliary compartment, the gas generating device burns the boron-based solid propellant to produce a primary fuel-rich gas, and the primary fuel-rich gas provides power after being mixed and reacted with the introduced water in the gas generating device.

According to one aspect of the present invention, the auxiliary compartment and the gas generating device are located in the same cylindrical casing;

The separation device is connected to the end of the cylindrical shell by an explosive bolt;

The separation device comprises: an annular hollow body and a signal generator arranged in the hollow body;

The signal generator is connected to the explosive bolt.

According to one aspect of the present invention, the auxiliary compartment comprises: a warhead and a power source coaxially arranged in sequence;

The gas generating device comprises: a water ram gas generator, a solid ram gas generator and a first tail nozzle which are coaxially arranged in sequence;

The first tail nozzle is provided with a first flow regulating valve;

The water ram gas generator comprises: a first hollow container, a first igniter arranged at the head of the first hollow container, and an intermediate nozzle arranged at the tail of the first hollow container;

The first hollow container is filled with a boron-based solid propellant;

The first igniter is connected to the power source;

The intermediate nozzle is provided with a second flow regulating valve;

The solid-impact gas generator comprises: a second hollow container, a second igniter, and a plurality of foldable tail wing devices arranged outside the second hollow container;

The head of the second hollow container is connected to the middle nozzle, and the tail of the second hollow container is connected to the first tail nozzle;

The second hollow container is filled with a boron-based solid propellant;

The foldable tail wing device is located at the tail end of the second hollow container and is arranged at equal intervals along the circumference of the second hollow container;

An opening is arranged on the side wall of the cylindrical shell corresponding to the foldable tail wing device.

According to one aspect of the present invention, the cavitation device comprises: a conical cavitator, a guide bowl structure coaxially connected to the conical cavitator, a flow control device connected to the guide bowl structure, and a gas-liquid transmission component connected to the flow control device;

The gas-liquid transmission component is in communication with the second hollow container;

The flow control device is located in the cylindrical outer shell, and the flow control device is arranged at the front side of the auxiliary compartment.

According to one aspect of the present invention, the conical cavitator comprises: a cone cap portion, a cone bottom portion and a middle partition;

The large diameter end of the cone cap portion is fixedly connected to the cone bottom portion;

The middle partition plate is spaced apart from the cone bottom portion and is disposed in the cone cap portion, and is used to enclose an installation cavity for installing the guide device between the middle partition plate and the cone cap portion, and to enclose a water inlet cavity between the middle partition plate and the cone bottom portion;

A plurality of water inlets for communicating with the water inlet cavity are arranged at intervals on the cone cap portion between the middle partition plate and the cone bottom portion;

A water outlet for communicating with the water inlet cavity is arranged at the center of the cone bottom portion.

According to one aspect of the present invention, the diversion bowl structure comprises: a connecting body and a plurality of bowl-shaped diversion parts;

Along the axial direction of the connecting body, a plurality of the bowl-shaped flow guiding parts are arranged at intervals;

The connecting body is provided with a water inlet channel and an air outlet cavity;

The water inlet channel is coaxially arranged with the connecting body and passes through two opposite ends thereof;

The air outlet cavity is coaxially arranged around the water inlet flow channel, and the air outlet cavity and the water inlet flow channel are isolated from each other;

An air outlet hole for communicating with the air outlet cavity is arranged on the radial outer side wall of the connecting body, and an air inlet hole for communicating with the air outlet cavity is arranged at the axial rear end of the connecting body;

The radial dimensions of the adjacent bowl-shaped flow guide parts are successively increased in a direction away from the conical cavitator, and the bowl-shaped flow guide parts and the air outlet holes are successively alternately arranged.

According to one aspect of the present invention, the flow control device comprises: a first mounting housing, a second mounting housing, a water flow control unit and a cavitation gas flow control unit;

The first mounting shell is in the shape of a hollow cone as a whole, with a connection opening at its small diameter end and an air inlet connection port and a water outlet connection port at its large diameter end;

The second mounting shell is an axisymmetric hollow structure, which is coaxially arranged in the first mounting shell with the first mounting shell, one end of which is a shell fixing end fixedly connected to the bottom of the first mounting shell, and the other end is a shell docking end;

The first installation shell and the second installation shell form a first installation cavity for installing the cavitation gas flow control unit;

The hollow portion of the second mounting shell forms a second mounting cavity for mounting the water flow control unit;

The shell docking end of the second mounting shell is provided with a water inlet docking opening, and the water inlet docking opening is provided beyond the connection opening;

The fixed end of the second installation shell is provided with a connecting channel for connecting the second installation cavity and the water outlet connection port;

The shell docking end of the second installation shell is coaxial with the connecting opening and is spaced apart, and an air outlet docking opening connected to the first installation cavity is formed between the shell docking end and the connecting opening, and the first installation cavity is connected to the air inlet connecting port.

According to one aspect of the present invention, the gas-liquid transmission assembly comprises: an air guide pipe, a water guide pipe, a heat exchanger, an air guide pipe and a water delivery pipe;

One end of the air guide pipe is connected to the air inlet connection port of the flow control device, and the other end is connected to the heat exchanger;

One end of the air bleed pipe is connected to the heat exchanger, and the other end is connected to the second hollow container of the solid-impact gas generator; wherein the position where the air bleed pipe is connected to the second hollow container is adjacent to the tail end of the second hollow container;

One end of the water guide pipe is connected to the water outlet connection port of the flow control device, and the other end is connected to the heat exchanger;

One end of the water pipe is connected to the heat exchanger, and the other end is connected to the second hollow container of the solid-impact gas generator; wherein an atomizing nozzle is provided at the end of the water pipe connected to the second hollow container.

According to one aspect of the present invention, the heat exchanger is disposed between the water ram gas generator and the solid ram gas generator;

The heat exchanger comprises: a hollow heat exchanger shell, a spiral heat exchange tube arranged in the heat exchanger shell;

The heat exchanger shell is an annular hollow structure as a whole, and its two axial ends are respectively provided with a gas collecting cavity structure for connecting the spiral heat exchange tube, and the heat exchanger water inlet and heat exchanger water outlet for connecting the hollow part of the heat exchanger shell are respectively provided at the two axial ends of the heat exchanger shell, and the heat exchanger air inlet and heat exchanger air outlet for connecting the air collecting cavity structure are respectively provided;

The water inlet of the heat exchanger is connected to the water pipe, and the water outlet of the heat exchanger is connected to the water pipe;

The air inlet of the heat exchanger is connected to the air duct, and the air outlet of the heat exchanger is connected to the air duct.

According to one aspect of the present invention, the booster compartment comprises: a booster compartment body, a plurality of air inlet structures and a plurality of tail rudder assemblies arranged on the outer side of the booster compartment body;

The booster compartment body comprises: a combustion chamber and a tail nozzle connected coaxially;

The length of the air inlet structure is consistent with the axial length of the booster compartment body.

The air intake structure is provided with an air intake for connecting the combustion chamber with the outside, and a switch mechanism corresponding to the air intake;

Along the axial direction of the booster compartment body, the air inlet is arranged adjacent to the front end of the booster compartment body;

Along the axial direction of the booster compartment body, the tail rudder assembly is arranged adjacent to the tail end of the booster compartment body.

According to one solution of the present invention, the present invention has excellent capabilities in rapid response, long-range strike, cross-domain penetration attack, etc., and provides a new idea for the development of a new generation of cross-medium aircraft.

According to one solution of the present invention, a body of revolution shape design is adopted, and the aircraft can navigate in both air and water media environments without changing its geometric configuration.

According to one solution of the present invention, a ramjet engine is adopted as the power system, which can realize supersonic flight in the air, and with the aid of a cavitation device in the water, it can realize high-speed navigation of ≮200 knots, which greatly improves its penetration performance.

According to one solution of the present invention, a water ramjet engine is used, which can use air and water in the medium environment as oxidants, thereby causing the propulsion system to have a specific impulse far higher than that of rocket engines, motors and other power devices, thereby effectively increasing the range of the aircraft.

According to one solution of the present invention, a boron-based propellant is used to achieve rapid response while having the advantages of reliable fuel ignition, stable combustion, and high energy density.

According to one solution of the present invention, designs such as fuel flow regulation, multi-stage structure, multiple water inlets, and regenerative cooling are adopted to achieve intelligent regulation of the aircraft's operating state and intelligent switching of operating modes.

According to one scheme of the present invention, the present invention also incorporates the concept of sharing throughout the entire design process, adopts a rotating body configuration design and a ramjet propulsion system to achieve cross-medium aircraft configuration and cross-medium power scheme sharing; uses an air ramjet combustion chamber to place booster charges and uses a gas generator as a water ramjet engine afterburner to achieve space sharing; and uses high-temperature combustion exhaust gas to heat water for combustion to achieve energy sharing.

According to one scheme of the present invention, the present invention combines the performance advantages of ramjet engines with the physical and chemical advantages of boron-based propellants, and at the same time utilizes the rotating body shape design, flow regulating device, supercavitation device, multi-stage structure, and multi-stage water inlet design, and has the advantages of cross-airspace attack, wide-speed range flight, long-range strike, and intelligent work, which effectively enhances the concealment, maneuverability and evasion capability of marine battlefield weapons, and greatly broadens the combat capability of marine battlefield weapons.

According to one scheme of the present invention, the present invention utilizes the combustion exhaust gas generated by the water ramjet engine as cavitation gas and utilizes the high temperature and high pressure properties of the fuel gas to achieve complete cavitation when the aircraft is working underwater. There is no need to carry an additional high-pressure gas source, which effectively reduces the dead weight and increases the engine payload, greatly improving the weapon damage effect.

According to one solution of the present invention, the present invention proposes to use boron-based propellant as the fuel of a water ramjet engine. Theoretical calculations show that compared with aluminum-based propellants, a water ramjet engine using boron-based propellants can obtain better working performance. Under the same charge volume, the range is increased by about one time, and a secondary water inlet structure of the water ramjet engine is adopted.

According to one scheme of the present invention, the present invention also incorporates the concept of sharing throughout the entire design concept, adopts a rotating body configuration design and a ramjet propulsion system to achieve cross-medium aircraft configuration and cross-medium power solution sharing; uses an air ramjet combustion chamber to place booster charges and uses a gas generator as a water ramjet engine afterburner to achieve space sharing; uses high-temperature combustion exhaust gas to heat water for combustion to achieve energy sharing.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic structural diagram of a boron-based ramjet-propelled trans-medium aircraft flying in the air according to an embodiment of the present invention;

FIG2 is a schematic diagram showing the structure of a boron-based ramjet-propelled trans-medium aircraft sailing in water according to an embodiment of the present invention;

FIG3 is a diagram schematically showing the internal structure of a boron-based ramjet-propelled trans-medium aircraft according to an embodiment of the present invention;

FIG4 is a cross-sectional view schematically showing a boron-based ramjet-propelled trans-medium aircraft according to an embodiment of the present invention;

FIG5 is a structural diagram schematically showing a conical cavitator according to an embodiment of the present invention;

FIG6 is a cross-sectional view schematically showing a conical cavitator and a guide bowl structure assembly according to an embodiment of the present invention;

FIG7 is a structural diagram schematically showing a guide bowl structure according to an embodiment of the present invention;

FIG8 is a perspective view schematically showing a flow control device according to an embodiment of the present invention;

9 is a cross-sectional view schematically showing a flow control device according to an embodiment of the present invention;

FIG10 is a cross-sectional view schematically showing a flow control device according to an embodiment of the present invention;

Fig. 11 is a schematic cross-sectional view taken along the direction A-A in Fig. 10;

Fig. 12 is a cross-sectional view schematically showing the direction B-B in Fig. 10;

Fig. 13 is a schematic cross-sectional view taken along the C-C direction in Fig. 10;

Fig. 14 is a schematic cross-sectional view taken along the D-D direction in Fig. 10;

15 is a schematic diagram showing a connection structure of a flow control device and a gas-liquid transmission component according to an embodiment of the present invention;

FIG16 is a cross-sectional view schematically showing a heat exchanger according to an embodiment of the present invention;

FIG17 is a cross-sectional view schematically showing a heat exchanger according to an embodiment of the present invention;

FIG18 is a structural diagram schematically showing a second hollow container according to an embodiment of the present invention;

FIG19 is a schematic diagram showing the working mode of an air ramjet engine in the cruise stage of a boron-based ramjet propulsion trans-medium aircraft according to an embodiment of the present invention;

FIG20 is a schematic diagram showing the working mode of a water ramjet engine when a boron-based ramjet-propelled trans-medium aircraft is sailing underwater according to an embodiment of the present invention;

FIG21 is a diagram schematically showing the variation of specific impulse of different propellants with air-fuel ratio;

FIG22 is a diagram schematically showing the variation of specific impulse of different propellants with water-fuel ratio;

FIG23 is a diagram schematically showing the range of an aircraft under unit charge volume of different propellants;

FIG24 is a diagram schematically showing a tail flame of a boron-based ramjet propulsion cross-medium aircraft air ramjet engine test process according to an embodiment of the present invention;

FIG. 25( a ) is a diagram schematically showing a pressure-time curve of a boron-based ramjet-propelled trans-medium vehicle according to an embodiment of the present invention;

FIG. 25( b ) is a diagram schematically showing a thrust-time curve of a boron-based ramjet propulsion trans-medium vehicle according to an embodiment of the present invention;

FIG. 26( a ) is a diagram schematically showing a water ramjet test tail flame diagram of a boron-based ramjet-propelled trans-medium aircraft in a test A state according to an embodiment of the present invention;

FIG26( b ) is a diagram schematically showing a water ramjet test tail flame diagram of a boron-based ramjet-propelled trans-medium aircraft in a test state b according to an embodiment of the present invention;

FIG27 is a diagram schematically showing a pressure-time curve of a afterburner of a boron-based ramjet propulsion trans-medium vehicle according to an embodiment of the present invention;

FIG. 28 is a diagram schematically showing a step thrust-time curve of a boron-based ramjet propulsion trans-medium aircraft engine according to an embodiment of the present invention.

DETAILED DESCRIPTION

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

Combined with Figure 1. As shown in Figures 2, 3 and 4, according to an embodiment of the present invention, a boron-based ramjet-propelled cross-medium aircraft of the present invention comprises: a cavitation device 1, an auxiliary compartment 2, a gas generator 3, a separation device 4, a booster compartment 5 and a guide device 6. In this embodiment, the boron-based ramjet-propelled cross-medium aircraft of the present invention adopts a rotating body shape design as a whole, and the aircraft can sail in both air and water media environments without changing the geometric configuration. Among them, the cavitation device 1, the auxiliary compartment 2, the gas generator 3, the separation device 4 and the booster compartment 5 are coaxially arranged with each other; specifically, the cavitation device 1 is connected to the head of the auxiliary compartment 2, the gas generator 3 is connected to the tail of the auxiliary compartment 2, the separation device 4 is detachably connected to the tail of the gas generator 3, and the booster compartment 5 is connected to the tail of the separation device 4. In this embodiment, the guide device 6 is arranged in the cavitation device 1; the head of the auxiliary compartment 2 is provided with a detachable fairing 7, and the cavitation device 1 is located inside the fairing 7. In this embodiment, the gas generator 3 is filled with boron-based solid propellant; the booster cabin section 5 is filled with propellant. In this embodiment, when the boron-based ramjet-propelled trans-medium aircraft switches from air flight to water navigation, the separation device 4 and the booster cabin section 5 are separated from the gas generator 3. The separation device 4 and the booster cabin section 5 can be separated from the gas generator 3 in a combined form, or can be separated by a separate sequential separation.

In this embodiment, the guidance device 6 is a control and navigation system of the entire cross-medium aircraft, which can be implemented using existing mature products and will not be described in detail here.

Combined with Figure 1. As shown in Figures 2, 3 and 4, according to one embodiment of the present invention, the boron-based ramjet-propelled trans-medium aircraft includes the following during its flight in the air: a boost phase, a cruise phase and a gliding phase; wherein, when in the boost phase, the boost compartment 5 burns the propellant to provide power; when in the cruise phase, the gas generator 3 burns part of the boron-based solid propellant to generate primary gas, and the primary gas provides power after secondary combustion after the boost compartment 5 is mixed with the introduced air; when in the cruise phase, the gas generator 3 is shut down. In this embodiment, during the underwater navigation of the boron-based ramjet-propelled trans-medium aircraft, the fairing 7 is separated from the auxiliary compartment 2, the gas generator 3 burns the boron-based solid propellant to generate a primary fuel-rich gas, and the primary fuel-rich gas provides power after the gas generator 3 is mixed with the introduced water.

Combined with Figure 1. As shown in Figures 2, 3 and 4, according to one embodiment of the present invention, the auxiliary compartment 2 and the gas generator 3 are in the same cylindrical outer shell 8. In this embodiment, by arranging the auxiliary compartment 2 and the gas generator 3 in the same cylindrical outer shell 8 so that they form an overall streamlined shape, it is more beneficial for them to be able to navigate in the water. Specifically, the cylindrical outer shell 8 is a cylindrical hollow cylinder as a whole, and its head adopts a conical structure design. In this embodiment, the separation device 4 can be connected to the end of the cylindrical outer shell 8 by using explosive bolts; of course, in another embodiment, when the separation device 4 needs to be separated from the booster compartment 5, the separation device 4 and the booster compartment 5 can also be connected by a grab bolt, thereby achieving the effect of controlled separation.

In this embodiment, the separation device 4 includes: a ring-shaped hollow body and a signal generator disposed in the hollow body; wherein the hollow body is an integrally connected and supported structure, and setting it to be hollow can further facilitate the installation of the signal generator and the installation of explosive bolts connected to other structures. In this embodiment, the signal generator is electrically connected to the explosive bolt, thereby achieving controlled disconnection of the explosive bolt. In this embodiment, the signal generator can work autonomously without being affected by other components, and it can also be implemented using existing mature products, which will not be repeated here.

Combined with Figure 1. As shown in Figures 2, 3 and 4, according to one embodiment of the present invention, the auxiliary compartment 2 includes: a warhead 21 and a power supply 22 which are coaxially arranged in sequence. In this embodiment, the power supply 22 is electrically connected to the warhead 21 for controlled excitation of the warhead 21. Similarly, the power supply 22 is also connected to the gas generator 3 at the rear side for controlled excitation of the gas generator 3, which is the power energy device of the entire boron-based ramjet propulsion trans-medium aircraft.

As shown in Figure 1, Figure 2, Figure 3 and Figure 4, according to an embodiment of the present invention, the gas generating device 3 comprises: a water ram gas generator 31, a solid ram gas generator 32 and a first tail nozzle 33 which are coaxially arranged in sequence; wherein the first tail nozzle 33 is provided with a first flow regulating valve 331 for controlling the ejection flow of the gas in the working state.

In this embodiment, the water ram gas generator 31 includes: a first hollow container 311, a first igniter 312 arranged at the head of the first hollow container 311, and an intermediate nozzle 313 arranged at the tail of the first hollow container 311. In this embodiment, the first hollow container 311 is filled with boron-based solid propellant. In this embodiment, the first igniter 312 is connected to the power supply 22. In this embodiment, the intermediate nozzle 313 is provided with a second flow regulating valve 3131; wherein the intermediate nozzle 313 is used as a nozzle when the water ram gas generator 31 is working, and the second flow regulating valve 3131 is provided to control the ejection flow rate of its gas. In this embodiment, the first igniter 312 is controlled by the cross-medium aircraft control program, and can be implemented by the "on and off" control between the power supply and the existing mature products, which will not be repeated here.

In this embodiment, the solid ram gas generator 32 includes: a second hollow container 321, a second igniter 322, and a plurality of foldable tail wing devices 323 arranged outside the second hollow container 321. In this embodiment, the head of the second hollow container 321 is connected to the intermediate nozzle 313, and the tail thereof is connected to the first tail nozzle 33. In this embodiment, by setting the second hollow container 321 to be connected to the intermediate nozzle 313, when the water ram gas generator 31 is working, the hollow second hollow container 321 can be used to realize a mixing reaction of a fuel-rich gas into water to provide higher navigation power. In this embodiment, the second hollow container 321 is filled with a boron-based solid propellant; it is provided with a boron-based solid propellant to realize the operation in the cruise stage to provide power in the cruise stage. In this embodiment, the second igniter 322 is also controlled by the cross-medium aircraft control program, and can be realized by the "on and off" control between the power supply and the existing mature products, which will not be repeated here.

In this embodiment, the foldable tail device 323 is located at the tail end of the second hollow container 321 and is arranged at equal intervals along the circumference of the second hollow container 321. In this embodiment, the foldable tail device 323 includes a mounting base, a foldable tail structure and a steering gear. By setting the foldable tail device 323, the foldable tail structure is ejected when the present invention is sailing in the water, and the overall navigation direction is controlled by the control of the steering gear. When the present invention is flying in the air, the foldable tail structure is folded to avoid affecting other control structures. In this embodiment, an opening is provided on the side wall of the cylindrical shell 8 corresponding to the foldable tail device 323, and the foldable tail structure is ejected through the provided opening. In this embodiment, a corresponding sealing setting is performed at the position where the foldable tail device 323 is installed to ensure the overall sealing when sailing in the water. For example, an installation chamber is set at the opening position where the foldable tail device 323 is installed to achieve the overall sealing of the installation position, and further a sealing is set at the connection between the foldable tail and the steering gear joystick to achieve complete sealing.

As shown in combination with Figures 3 to 17, according to an embodiment of the present invention, the cavitation device 1 is used to generate supercavitation when the present invention is sailing in water to ensure the navigation speed and stability of the present invention. Specifically, the cavitation device 1 includes: a conical cavitator 11, a guide bowl structure 12 coaxially connected to the conical cavitator 11, a flow control device 13 connected to the guide bowl structure 12, and a gas-liquid transmission component 14 connected to the flow control device 13. In this embodiment, the conical cavitator 11, the guide bowl structure 12 and the flow control device 13 are all axisymmetric structures. In this embodiment, the gas-liquid transmission component 14 is connected to the second hollow container 321 to achieve air intake to the guide bowl structure 12 and water supply to the second hollow container 321 of the solid fuel gas generator 32 during navigation in water. In this embodiment, when the cavitation device 1 is working, first, the conical cavitator 11 completes partial cavitation, and then the high-temperature combustion gas in the gas generator 3 is used as the cavitation gas to replenish the gas, and finally the complete cavitation of the aircraft is achieved, thereby effectively ensuring that the supercavitation wraps the entire navigation body.

In this embodiment, the flow control device 13 is located in the cylindrical shell 8, and the flow control device 13 is arranged at the front side of the auxiliary compartment 2. In this embodiment, the guide bowl structure 12 is connected to the outer side of the head of the cylindrical shell 8, and the flow control device 13 is docked with the inner side of the head of the cylindrical shell 8. Then, by setting a water inlet transition channel for water to pass through and an outlet transition channel for cavitation gas output at the head of the cylindrical shell 8, the connection with the front conical cavitator 11 and the guide bowl structure 12 can be achieved. The structure is simple, reliable and easy to connect. In this embodiment, the flow control device 13 guides the gas into the guide bowl structure 12, and flows out through the small holes inside the guide bowl structure 12 to supplement the supercavitation gas flow. This guide bowl structure 12 can generate a stable, smooth and transparent cavitation surface, which is the most commonly used configuration and can be generated at an incoming flow velocity (10m/s) or even a lower incoming flow velocity.

As shown in combination with FIG. 5 and FIG. 6 , according to an embodiment of the present invention, the conical cavitator 11 includes: a conical cap portion 111, a conical bottom portion 112 and a middle partition 113. In this embodiment, the large diameter end of the conical cap portion 111 is fixedly connected to the conical bottom portion 112; the middle partition 113 and the conical bottom portion 112 are arranged in the conical cap portion 111 with a spacing, which is used to enclose an installation cavity for installing the guide device 6 between the middle partition 113 and the conical cap portion 111, and to enclose a water inlet cavity between the middle partition 113 and the conical bottom portion 112; a plurality of water inlets 111a for connecting to the water inlet cavity are arranged at intervals on the conical cap portion 111 between the middle partition 113 and the conical bottom portion 112. In this embodiment, a water outlet 112a for connecting to the water inlet cavity is arranged at the center position of the conical bottom portion 112. Furthermore, during the navigation process of the present invention, water is introduced into the water inlet cavity through the water inlet 111a and sent to the rear end structure through the water outlet 112a. In this embodiment, eight water inlets 111a are arranged at equal intervals.

As shown in combination with Figures 6 and 7, according to an embodiment of the present invention, the guide bowl structure 12 includes: a connecting body 121 and a plurality of bowl-shaped guide portions 122. In this embodiment, along the axial direction of the connecting body 121, a plurality of bowl-shaped guide portions 122 are arranged at intervals. In this embodiment, the connecting body 121 is provided with a water inlet channel 121a and an air outlet cavity 121b; the water inlet channel 121a is coaxially arranged with the connecting body 121 and passes through its opposite ends; wherein, one end of the water inlet channel 121a is sealed and connected to the water outlet 112a of the cone bottom portion 112 of the conical cavitator 11, and the other end thereof is sealed and connected to the water inlet transition channel provided at the head of the cylindrical shell 8.

In this embodiment, the air outlet cavity 121b is coaxially arranged around the water inlet flow channel 121a, and the air outlet cavity 121b and the water inlet flow channel 121a are isolated from each other; wherein, the air outlet cavity 121b is an annular cavity, which is coaxially arranged around the water inlet flow channel 121a. In this embodiment, an air outlet hole 121c for communicating with the air outlet cavity 121b is arranged on the radial outer side wall of the connecting body 121, and an air inlet hole 121d for communicating with the air outlet cavity 121b is arranged at the axial rear end of the connecting body 121; in this embodiment, the air inlet hole 121d arranged at the rear end of the connecting body 121 is used for sealing and docking with the air outlet transition channel arranged at the head of the cylindrical shell 8. In this embodiment, a plurality of air inlet holes 121d are provided at the rear end of the connecting body 121 and are distributed in a circular array. Correspondingly, the air outlet transition channel provided at the head of the cylindrical shell 8 corresponds one to one with the air inlet holes 121d.

In this embodiment, the radial dimensions of adjacent bowl-shaped flow guide portions 122 are successively increased in the direction away from the conical cavitator 11. In this embodiment, two bowl-shaped flow guide portions 122 are provided, wherein the radial maximum dimension of the bowl-shaped flow guide portion 122 at the front end is smaller than the radial maximum dimension of the bowl-shaped flow guide portion 122 at the rear end. In this embodiment, the front side surface of the bowl-shaped flow guide portion 122 at the front end and the front side surface of the bowl-shaped flow guide portion 122 at the rear end are arranged in different shapes, wherein the front side surface of the bowl-shaped flow guide portion 122 at the front end is a straight-edged conical surface, and the front side surface of the bowl-shaped flow guide portion 122 at the rear end is an arc-edged conical surface.

In this embodiment, the bowl-shaped flow guide portion 122 and the air outlet 121c are arranged alternately in a direction away from the conical cavitator 11. In this embodiment, a plurality of air outlets 121c are arranged at equal intervals along the circumference of the connecting body 121. It should be noted that the number of air outlets 121c on the connecting body 121 can be set according to actual needs, for example, the number of circumferentially arranged or the number of axially arranged.

In combination with Figures 3, 4, 8 to 15, according to an embodiment of the present invention, the function of the flow control device 13 is to regulate the flow of cavitation gas and the flow of water in real time according to the navigation conditions. Specifically, the flow control device 13 includes: a first mounting shell 131, a second mounting shell 132, a water flow control unit 133 and a cavitation gas flow control unit 134. In this embodiment, the first mounting shell 131 is a hollow cone as a whole, and its small diameter end has a connecting opening 131a, and its large diameter end is provided with an air inlet connection port 131b and a water outlet connection port 131c. In this embodiment, the second mounting shell 132 is an axisymmetric hollow structure, which is coaxially arranged in the first mounting shell 131 with the first mounting shell 131, one end of which is a shell fixed end fixedly connected to the bottom of the first mounting shell 131, and the other end is a shell docking end. In this embodiment, the first installation shell 131 and the second installation shell 132 enclose a first installation cavity for installing the cavitation gas flow control unit 134; the hollow portion of the second installation shell 132 constitutes a second installation cavity for installing the water flow control unit 133. In this embodiment, the shell docking end of the second installation shell 132 is provided with a water inlet docking opening 132a, and it is arranged beyond the connection opening 131a; the shell fixed end of the second installation shell 132 is provided with a connecting channel for connecting the second installation cavity and the water outlet connection port 131c. In this embodiment, the shell docking end of the second installation shell 132 is coaxial with the connection opening 131a and has a spacing setting, and an air outlet docking port connected to the first installation cavity is formed between the shell docking end and the connection opening 131a, and the first installation cavity is connected to the air inlet connection port 131b.

In this embodiment, the second mounting shell 132 includes: a conical shell portion and a cylindrical shell portion arranged coaxially, wherein the shell docking end of the second mounting shell 132 is arranged at the small diameter end of the conical shell portion, and one end of the cylindrical shell portion away from the conical shell portion constitutes the shell fixing end of the second mounting shell 132. In this embodiment, the radial dimension of the large diameter end of the conical shell portion is greater than the radial dimension of the cylindrical shell portion. In this embodiment, the water flow control unit 133 is coaxially arranged on the inner side of the cylindrical shell portion with the cylindrical shell portion, and the cavitation gas flow control unit 134 is coaxially arranged on the outer side of the cylindrical shell portion with the cylindrical shell portion.

Through the above-mentioned arrangement, the second mounting shell 132 in the present invention effectively increases the volume of the water inlet side of the second mounting shell 132 by setting a conical shell part at the front end, so that the input water can be stored more advantageously. This can effectively ensure that there is sufficient water on the water inlet side of the water flow control unit 133 to be transported to the rear side, thereby ensuring the working stability of the present invention.

In addition, by setting a conical shell portion, the outer side surface of the conical shell portion is matched with the first mounting shell 131, so that an annular gas transmission channel with a certain length in the axial direction is formed between the conical shell portion and the first mounting shell 131, and the gas transmission channel from the first mounting cavity to the outside is gradually reduced in the radial direction, which effectively ensures the stability of the airflow and facilitates the accurate control of the gas flow.

In this embodiment, the water flow regulator 133 is a cylindrical structure as a whole, and a water passage is provided at its center. In this embodiment, the water flow regulator 133 is used to adjust the water inlet flow and pressurize the water flow to ensure that the water flow can enter the afterburning chamber. Specifically, the corresponding water flow and water flow pressure can be controlled by controlling the cross-sectional opening size of the water passage. For example, at least one blade with adjustable position can be provided in the water passage to adjust the cross-sectional opening size. Of course, other structures can also be used to achieve the function of adjusting the cross-sectional opening size, which will not be repeated here.

In this embodiment, the cavitation gas flow control unit 134 is annular in structure as a whole, and a plurality of air passages are arranged at intervals along its circumference. In this embodiment, the corresponding water flow and water flow pressure can be controlled by controlling the cross-sectional opening size of the air passage. For example, at least one blade with adjustable position can be arranged in the air passage to adjust the cross-sectional opening size. Of course, other structures can also be used to adjust the cross-sectional opening size, which will not be described in detail here.

4, 8 and 9, according to an embodiment of the present invention, two air inlet connection ports 131b and two water outlet connection ports 131c are respectively provided, and are arranged at equal intervals from each other, wherein, along the radial direction of the first shell 131, the two air inlet connection ports 131b are arranged opposite to each other, and the two water outlet connection ports 131c are arranged opposite to each other.

As shown in FIG. 9 to FIG. 14 , according to an embodiment of the present invention, a flow diversion structure 1311 is provided in the first shell 131; wherein the flow diversion structure 1311 includes: a baffle 1311a and a side plate 1311b. In this embodiment, the baffle 1311a is an annular plate, which is sleeved on the outer surface of the cylindrical shell part through a hollow portion, and its radial outer side surface is connected to the inner side wall of the first shell 131. In this embodiment, the side plate 1311b is located between the baffle 1311a and the bottom plate of the large diameter end of the first shell 131, and is used to divide the rear liquid accumulation chamber a connecting the second installation chamber and the water outlet connection port 131c and the rear gas collection chamber b connecting the first installation chamber and the air inlet connection port 131b. In this embodiment, the rear liquid accumulation chamber a is arranged in a one-to-one correspondence with the water outlet connection port 131c, and the rear gas collection chamber b is arranged in a one-to-one correspondence with the air inlet connection port 131b.

In this embodiment, an opening is provided at a position of the baffle 1311a corresponding to the rear gas collecting cavity b.

As shown in FIG. 9 to FIG. 14 , according to an embodiment of the present invention, the side plate 1311b is a long strip-shaped plate. In the axial direction of the first shell 131, the opposite ends of the side plate 1311b are respectively connected to the baffle 1311a and the bottom plate of the large diameter end of the first shell 131; in the embodiment, in the radial direction of the first shell 131, the opposite ends of the side plate 1311b are respectively connected to the outer wall of the cylindrical shell part and the inner wall of the first shell 131; in the direction away from the cylindrical shell part, the thickness of the side plate 1311b gradually increases. In the embodiment, along the circumference of the first shell 131, a plurality of side plates 1311b are arranged at equal intervals; in the embodiment, four side plates 1311b are arranged at equal intervals, thereby realizing the four-equal division of the space between the baffle 1311a and the bottom plate, thereby forming the required rear liquid accumulation chamber a and rear gas collection chamber b.

It should be noted that the air inlet connection port 131b and the water outlet connection port 131c in this solution can also be set to other numbers, for example, 3, 4, etc. Accordingly, the side plates 1311b are added to the diversion structure 1311 to divide the corresponding rear liquid accumulating chambers a and rear gas collecting chambers b in corresponding numbers.

As shown in Figures 3, 4, 6, 8, 9, 15 to 17, according to an embodiment of the present invention, the gas-liquid transmission component 14 includes: an air guide pipe 141, a water guide pipe 142, a heat exchanger 143, an air bleed pipe 144 and a water delivery pipe 145. In this embodiment, one end of the air guide pipe 141 is connected to the air inlet connection port 131b of the flow control device 13, and the other end is connected to the heat exchanger 143; one end of the air bleed pipe 144 is connected to the heat exchanger 143, and the other end is connected to the second hollow container 321 of the solid-fuel gas generator 32; wherein, the position where the air bleed pipe 144 is connected to the second hollow container 321 is adjacent to the tail end of the second hollow container 321. In this embodiment, one end of the water pipe 142 is connected to the water outlet connection port 131c of the flow control device 13, and the other end is connected to the heat exchanger 143; one end of the water pipe 145 is connected to the heat exchanger 143, and the other end is connected to the second hollow container 321 of the solid-fuel gas generator 32; wherein, an atomizing nozzle is provided at the end of the water pipe 145 connected to the second hollow container 321.

In this embodiment, at least two pipelines connected to the second hollow container 321 are arranged at intervals on the same water delivery pipe 145, and both have corresponding atomizing nozzles. Through the above arrangement, the distribution range of water in the afterburning chamber is increased, further promoting the mixed combustion in the afterburning chamber.

As shown in FIG. 16, FIG. 17 and FIG. 18, according to an embodiment of the present invention, the heat exchanger 143 is arranged between the water ram gas generator 31 and the solid ram gas generator 32. In this embodiment, the heat exchanger 143 includes: a hollow heat exchanger shell 1431, and a spiral heat exchange tube 1432 arranged in the heat exchanger shell 1431; the heat exchanger shell 1431 is an annular hollow structure as a whole, and the two axial ends thereof are respectively provided with a gas collecting cavity structure for connecting the spiral heat exchange tube 1432. And, the heat exchanger water inlet 143a and the heat exchanger water outlet 143b for connecting the hollow part of the heat exchanger shell 1431, and the heat exchanger air inlet 143c and the heat exchanger air outlet 143d for connecting the air collecting cavity structure are respectively provided at the two axial ends of the heat exchanger shell 1431. In this embodiment, the heat exchanger water inlet 143a is connected to the water pipe 142, and the heat exchanger water outlet 143b is connected to the water pipe 145; the heat exchanger air inlet 143c is connected to the air duct 144, and the heat exchanger air outlet 143d is connected to the air duct 141. The heat of the high-temperature gas is used to heat the water through the heat exchanger 143, so as to realize the regeneration of the heat of the high-temperature gas.

In this embodiment, a plurality of spiral heat exchange tubes 1432 are provided, wherein the spiral heat exchange tubes 1432 undergo a 90° deflection during the process of passing through the interior of the heat exchanger housing 1431, so the heat exchanger air inlet 143c/heat exchanger water inlet 143a and the heat exchanger air outlet 143d/heat exchanger water outlet 143b also rotate 90° after passing through the heat exchanger. Through the above arrangement, the heat exchange distance and heat exchange time between low-temperature water and high-temperature gas are effectively increased to improve the heat exchange effect.

In the present embodiment, the gas collecting cavity structure adopts an arc-shaped plate body, and its radial width is consistent with the radial width of the hollow part of the heat exchanger shell 1431, and then the gas collecting cavity structure is fixedly connected to the inside of the heat exchanger shell 1431 to form an arc-shaped gas collecting cavity. In the present embodiment, the length of the gas collecting cavity structure is five-sixths of the circumferential length of the heat exchanger shell 1431. In the present embodiment, baffles are used at both ends of the circumference of the gas collecting cavity structure to ensure that the gas collecting cavity is isolated from the remaining hollow part of the heat exchanger shell 1431. In the present embodiment, the ends of the spiral heat exchange tubes 1432 are connected in an array on the gas collecting cavity structure to achieve simultaneous communication between multiple spiral heat exchange tubes 1432 and the gas collecting cavity.

In this embodiment, two air pipes 141, two water pipes 142, two air ducts 144 and two water delivery pipes 145 are respectively provided, and are symmetrically arranged on both sides of the auxiliary compartment 2 and the gas generating device 3 combination.

Since the cavitation gas is taken from the end of the afterburner of the water ramjet engine, thermal calculations show that the gas temperature at the end of the afterburner reaches 2500K. For the cavitation gas, its work does not require such a high temperature, and such a high temperature, after being transmitted through the pipeline, poses a great threat to the safety of the entire navigation body. At the same time, the temperature of seawater obtained from the outside is about 280K. Experiments show that the lower the water temperature, the less conducive it is to the operation of the water ramjet engine. If the temperature of the water entering the afterburner can be increased, it will help improve the engine's operating performance. Therefore, the present invention proposes a heat exchanger. Before the seawater enters the afterburner, it first passes through the heat exchanger, and the heat in the high-temperature gas is used to heat the seawater, thereby realizing heat regeneration.

As shown in FIG. 3 and FIG. 4 , according to an embodiment of the present invention, the booster compartment 5 includes: a booster compartment body 51, a plurality of air inlet structures 52 and a plurality of tail rudder assemblies 53 arranged on the outer side of the booster compartment body 51. The booster compartment body 51 includes: a combustion chamber 511 and a tail nozzle 512 connected coaxially. In this embodiment, the combustion chamber 511 is filled with propellant to realize the boosting stage flight of the present invention after being launched. In this embodiment, the length of the air inlet structure 52 is set to be consistent with the axial length of the booster compartment body 51; wherein, the air inlet structure 52 is provided with an air inlet 521 for connecting the combustion chamber 511 with the outside, and a switch mechanism corresponding to the air inlet 521. In this embodiment, an igniter is also provided in the combustion chamber 511 for realizing controlled ignition of the propellant. In this embodiment, the igniter can be implemented by using an existing mature product, which will not be described in detail here.

In this embodiment, the air inlet 521 is arranged adjacent to the front end of the booster module body 51 along the axial direction of the booster module body 51; wherein the air inlet 521 is arranged to extend obliquely relative to the axial direction of the booster module body 51, and a first opening is formed on the outer side of the air inlet structure 52, and a second opening is formed on the side wall of the combustion chamber 511. The first opening is located in front of the second opening along the axial direction of the booster module body 51. In this embodiment, four air inlet structures 52 are arranged at equal intervals along the circumference of the booster module body 51.

In this embodiment, along the axial direction of the booster compartment body 51, the tail rudder assembly 53 is arranged adjacent to the tail end of the booster compartment body 51. In this embodiment, the tail rudder assembly 53 includes: a connection base, a tail wing component connected to the connection base, and a steering engine for controlling the tail wing component. In this embodiment, along the circumference of the booster compartment body 51, four tail rudder assemblies 53 are arranged at equal intervals, and the tail rudder assembly 53 is staggered with the air inlet structure 52.

Through the above arrangement, the tail rudder assembly 53 adopts an X-shaped arrangement, which effectively meets the high maneuverability requirements, and the air inlet structure 52 adopts an X-shaped arrangement, which effectively maintains the efficient operation of the propulsion system.

To further illustrate this scheme, the flight process is further described in conjunction with Figures 1, 3, 4, 18 and 19.

Boosting stage

After launch, the aircraft first enters the rocket mode. At this time, the air inlet 521 of the booster compartment 5 is closed, and the solid propellant grains in the combustion chamber 511 burn rapidly, generating a large thrust to propel the aircraft to climb and accelerate to the ramjet engine starting speed and cruising altitude.

Cruise segment

Entering the ramjet mode, the switch mechanism of the air inlet 521 of the booster compartment 5 is opened, and the supersonic incoming flow enters the combustion chamber 511, and is mixed with the primary gas generated by the ignition and combustion of the solid ramjet gas generator 32 to undergo secondary combustion to release heat and generate high-temperature gas. The high-temperature gas is expanded through the tail nozzle 512 and then ejected to generate thrust to maintain the cruising flight of the aircraft. In this embodiment, the first flow regulating valve 331 provided on the first tail nozzle 33 can affect the mass flow of the fuel-rich gas, thereby changing the heat release distribution in the afterburner, and thus achieving better performance of the engine under different flight conditions, see Figure 19.

Gliding section

After the cruise phase, the solid fuel gas generator 32 is shut down, and the aircraft uses its own kinetic energy and potential energy to continue gliding at a certain angle of attack under the control of the tail rudder assembly 53 to increase the range and reduce the water entry speed, reduce the impact load, and improve the controllability of water entry.

Interstage separation section

When the aircraft flies close to the predetermined sea area by gliding, the explosive bolt receives a separation signal, the separation device 4 is disconnected from the front end structure, the separation device 4 and the booster compartment 5 are jettisoned, and the fuel-depleted solid ram gas generator 32 is retained to be used as a refueling chamber for the water ram gas generator 31.

Underwater navigation section.

After entering the water, the foldable tail device 323 opens and jettisons the fairing 7. Subsequently, the water inlet channel of the cavitation device 1 opens, and water is sprayed into the second hollow container 321 of the solid ram gas generator 32 after being atomized by the nozzle to mix and react with the primary fuel-rich gas generated by the water ram gas generator 31. The generated high-temperature gas is used to provide thrust, preheat the incoming water, and generate supercavitation that covers the navigation body, see Figure 20.

To further illustrate the present solution, theoretical calculations and ground direct connection tests were conducted on the working performance and feasibility of the present invention.

(1) Working performance

Performance Analysis of Boron-Based Propellants

The ramjet propulsion system used in the cross-medium aircraft of the present invention uses boron-based solid propellants when working in the air and in water. In order to illustrate the performance advantages of using boron-based propellants, the more commonly used aluminum-based solid propellants are selected here for performance comparison. The main components of the boron-based solid propellants and aluminum-based solid propellants used are shown in Tables 1 and 2.

Table 1 Main components of boron-based propellants

Table 2 Main components of aluminum-based propellants

The engine specific impulse of the two propellants in the high-altitude cruise stage and the underwater cruise stage are calculated respectively. The basic operating parameters of the ramjet engine in the high-altitude cruise stage and the underwater cruise stage are shown in Table 3. Figures 21 and 22 are the curves of the engine specific impulse changing with the air-fuel ratio and the water-fuel ratio under air ramjet conditions and water ramjet conditions, respectively.

Table 3 Basic operating parameters

As can be seen from Figures 21 and 22, when flying in the air, due to the large oxygen consumption of boron particles, the specific impulse of boron-based propellants is lower than that of aluminum-based propellants at low air-fuel ratios. When the air-fuel ratio is greater than 6, the theoretical performance of boron-based propellants is significantly better than that of aluminum-based solid propellants. When sailing in water, at any water-fuel ratio, the theoretical performance of boron-based propellants is completely better than that of aluminum-based propellants, and boron-based rich fuel has greater performance advantages under water ramjet working conditions than under air ramjet conditions. The above calculations show that compared with the aluminum-based propellants currently used, the boron-based propellants used by the trans-medium aircraft proposed in the present invention when working in the air and in water can enable the trans-medium ramjet engine to have greater performance advantages under both air ramjet and water ramjet conditions, and have higher theoretical performance.

Figure 23 shows the range of the aircraft in the air and underwater when using the boron-based ramjet, aluminum-based ramjet, and rocket-assisted propulsion systems, respectively, under unit charge volume. By comparison, it is found that when the boron-based ramjet propulsion system proposed in this article is used, the range is doubled compared to the aluminum-based ramjet propulsion system, and the range is increased by about 6 times compared to the rocket-assisted propulsion system. Therefore, it further illustrates the superiority of the performance of the cross-medium aircraft proposed in this invention when the boron-based ramjet propulsion system is used.

(2) Air ramjet engine demonstration test (i.e., cascade test of solid ramjet gas generator 32 and booster compartment 5)

A ground direct connection test was carried out based on the air ramjet engine proposed in the present invention. The test system was provided by the Hypersonic Key Laboratory of the National University of Defense Technology. The test simulated flight conditions of 10km and 3Ma, and the test parameters are shown in Table 4.

Table 4 Air ramjet direct-connection test condition parameter settings

The engine tail flame during the test is shown in Figure 24. It can be seen that the test ramjet engine can achieve ignition and combustion. The primary combustion gas produced by the combustion of the boron-based propellant can burn in the afterburner and burn more fully, forming a bright tail flame. The tail flame is bright yellow-white.

The pressure data and step thrust data collected during the test are shown in Figure 25(a) and Figure 25(b). It can be seen that the engine works stably, the gas generator pressure increases, the afterburner pressure is relatively stable, and the thrust curve increases slightly during the test. This once again shows that the test ramjet engine has stable combustion and reliable operation.

The engine performance is calculated based on the test data, and the calculation results are shown in Table 5. The average thrust of the engine reaches 2179.43N, the temperature rise combustion efficiency is 95.64%, and the thrust gain specific impulse of the ground direct test reaches 1029s. In summary, the test shows that the ramjet engine used in this report can achieve stable combustion, and the engine performance is high, basically meeting the engineering application indicators.

Table 5 Air ramjet direct connection test performance

(3) Water ramjet engine demonstration test (i.e., test of water ramjet gas generator 31 and solid ramjet gas generator 32 connected in series)

A ground direct connection test was carried out based on the water ramjet engine proposed in the present invention. The test system was provided by the Hypersonic Key Laboratory of the National University of Defense Technology. The test used a boron-based propellant with a boron content of 33%, and used a water heater to preheat the water. The test parameters are shown in Table 6.

Table 6 Air ramjet engine direct connection test condition parameter settings

After two tests, the water inlet structures were different in the two tests, where test A was a two-time water inlet structure and test B was a one-time water inlet structure. The engine tail flame during the test is shown in Figure 26 (a) and Figure 26 (b). It can be seen that the test water ramjet engine was able to achieve ignition during the two tests, and the primary gas generated by the combustion of the boron-based propellant was able to be mixed and burned with water in the afterburner. Obvious green light can be seen from the edge of the tail flame, indicating that the primary gas was not fully burned in the afterburner, and the brightness of the tail flame under the two configurations was not much different.

The data collected during the test were further used to analyze the engine performance. The combustion chamber pressure data and step thrust number during the test are shown in Figures 27 and 28 respectively. The test data show that the water ramjet engine works stably, and the afterburner pressure and engine thrust are relatively stable, indicating that the test water ramjet engine has stable combustion and reliable operation. In addition, it can be clearly seen that the afterburner pressure and bench thrust of test A are significantly better than those of test B, indicating that compared with one water inlet, two water inlets are more conducive to the organization of one gas combustion.

The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims (10)

1. A boron-based ram propulsion cross-media aircraft, comprising: the device comprises a cavitation device (1), an auxiliary cabin section (2), a gas generating device (3), a separation device (4), a boosting cabin section (5) and a guiding device (6);

the cavitation device (1), the auxiliary cabin section (2), the gas generating device (3), the separation device (4) and the boosting cabin section (5) are coaxially arranged; the cavitation device (1) is connected to the head of the auxiliary cabin section (2), the gas generation device (3) is connected to the tail of the auxiliary cabin section (2), the separation device (4) is detachably connected to the tail of the gas generation device (3), and the boosting cabin section (5) is connected to the tail of the separation device (4);

The guide device (6) is arranged in the cavitation device (1);

the head of the auxiliary cabin section (2) is provided with a separable fairing (7), and the cavitation device (1) is positioned inside the fairing (7);

the fuel gas generating device (3) is filled with a boron-based solid propellant;

the boosting cabin section (5) is filled with a boosting agent;

when the boron-based ram propulsion cross-medium aircraft is transferred from air flight to underwater navigation, the separation device (4) and the boost cabin section (5) are separated from the gas generating device (3).

2. The boron-based ram propulsion cross-media aircraft of claim 1, wherein the boron-based ram propulsion cross-media aircraft comprises during an air flight: a boosting phase, a cruising phase and a gliding phase;

when in the boosting stage, the boosting cabin section (5) burns the boosting agent to provide power;

when in the cruising stage, the fuel gas generating device (3) burns part of the boron-based solid propellant to generate primary fuel gas, and the primary fuel gas provides power after secondary combustion of the boost cabin section (5) and the introduced air;

when in the cruising phase, the gas generating device (3) is shut down;

In the underwater navigation process of the boron-based stamping propulsion cross-medium aircraft, the fairing (7) is separated from the auxiliary cabin section (2), the fuel gas generating device (3) combusts the boron-based solid propellant to generate primary fuel-rich fuel gas, and the primary fuel-rich fuel gas provides power after the fuel gas generating device (3) is mixed with introduced water for reaction.

3. The boron-based ram propulsion cross-medium aircraft of claim 2, wherein the auxiliary cabin section (2) and the gas generating device (3) are within the same cylindrical housing (8);

the separation device (4) is connected with the end part of the cylindrical shell (8) by adopting an explosion bolt;

the separation device (4) comprises: an annular hollow body and a signal generator disposed in the hollow body;

the signal generator is connected with the explosion bolt.

4. A boron-based ram propulsion cross-medium aircraft according to claim 3, wherein the auxiliary cabin segment (2) comprises: a fighter part (21) and a power supply (22) which are coaxially arranged in sequence;

the gas generating device (3) comprises: the water stamping gas generator (31), the solid stamping gas generator (32) and the first tail nozzle (33) are coaxially arranged in sequence;

A first flow regulating valve (331) is arranged on the first tail nozzle (33);

the water stamping gas generator (31) comprises: a first hollow container (311), a first igniter (312) arranged at the head part of the first hollow container (311), and a middle spray pipe (313) arranged at the tail part of the first hollow container (311);

the first hollow container (311) is filled with a boron-based solid propellant;

the first igniter (312) is connected to the power source (22);

the intermediate nozzle (313) is provided with a second flow regulating valve (3131);

the solid-state gas generator (32) comprises: a second hollow container (321), a second igniter (322), a plurality of foldable tail units (323) arranged outside the second hollow container (321);

the head of the second hollow container (321) is communicated with the middle spray pipe (313), and the tail of the second hollow container is communicated with the first tail spray pipe (33);

the second hollow container (321) is filled with a boron-based solid propellant;

the foldable tail wing device (323) is positioned at the tail end of the second hollow container (321) and is arranged at equal intervals along the circumferential direction of the second hollow container (321);

an opening is formed in the side wall of the cylindrical shell (8) corresponding to the foldable tail wing device (323).

5. The boron-based ram propulsion cross-medium aircraft of claim 4, wherein the cavitation device (1) comprises: a cone cavitation device (11), a guide bowl structure (12) coaxially connected with the cone cavitation device (11), a flow control device (13) connected with the guide bowl structure (12), and a gas-liquid transmission assembly (14) connected with the flow control device (13);

the gas-liquid transmission assembly (14) is communicated with the second hollow container (321);

the flow control device (13) is located within the cylindrical housing (8), and the flow control device (13) is disposed on the front side of the auxiliary compartment (2).

6. The boron-based ram propulsion cross-medium aircraft of claim 5, wherein the cone cavitation (11) comprises: a cone cap portion (111), a cone bottom portion (112) and an intermediate baffle (113);

the large-diameter end of the cone cap part (111) is fixedly connected with the cone bottom part (112);

the middle partition plate (113) and the cone bottom part (112) are arranged in the cone cap part (111) at intervals, a mounting cavity for mounting the guide device (6) is formed between the middle partition plate (113) and the cone cap part (111), and a water inlet cavity is formed between the middle partition plate (113) and the cone bottom part (112);

A plurality of water inlets (111 a) for communicating the water inlet cavity are arranged on the cone cap part (111) between the middle partition plate (113) and the cone bottom part (112) at intervals;

the center of the cone bottom part (112) is provided with a water outlet (112 a) which is used for communicating the water inlet cavity.

7. The boron-based ram propulsion cross-media aircraft of claim 6, wherein the guide bowl structure (12) comprises: a connecting body (121) and a plurality of bowl-shaped flow guiding portions (122);

-a plurality of bowl-shaped deflector portions (122) arranged at intervals along the axial direction of the connecting body (121);

the connecting body (121) is provided with a water inlet flow channel (121 a) and an air outlet cavity (121 b);

the water inlet flow channel (121 a) and the connecting main body (121) are coaxially arranged and penetrate through two opposite ends of the connecting main body;

the air outlet cavity (121 b) and the water inlet flow channel (121 a) are coaxially arranged around the water inlet flow channel (121 a), and the air outlet cavity (121 b) and the water inlet flow channel (121 a) are mutually isolated;

an air outlet hole (121 c) for communicating the air outlet cavity (121 b) is formed in the radial outer side wall of the connecting main body (121), and an air inlet hole (121 d) for communicating the air outlet cavity (121 b) is formed in the axial rear end of the connecting main body (121);

The radial sizes of the bowl-shaped flow guide parts (122) which are adjacent to each other along the direction away from the conical cavitation device (11) are sequentially increased, and the bowl-shaped flow guide parts (122) and the air outlet holes (121 c) are sequentially alternately arranged.

8. The boron-based ram propulsion cross-medium aircraft of claim 7, wherein the flow control device (13) comprises: a first installation housing (131), a second installation housing (132), a water flow control unit (133) and a cavitation air flow control unit (134);

the first installation shell (131) is a hollow cone body as a whole, the small-diameter end of the first installation shell is provided with a connecting opening (131 a), and the large-diameter end of the first installation shell is provided with an air inlet connecting port (131 b) and a water outlet connecting port (131 c);

the second installation shell (132) is of an axisymmetric hollow structure, is coaxially arranged in the first installation shell (131) with the first installation shell (131), and has one end which is a shell fixed end fixedly connected with the bottom of the first installation shell (131) and the other end which is a shell butt joint end;

the first mounting shell (131) and the second mounting shell (132) enclose a first mounting cavity for mounting the cavitation air flow control unit (134);

the hollow part of the second installation shell (132) forms a second installation cavity for installing the water flow control unit (133);

The shell butt end of the second installation shell (132) is provided with a water inlet butt opening, and the water inlet butt opening is arranged beyond the connecting opening (131 a);

the shell fixed end of the second installation shell (132) is provided with a connecting channel for communicating the second installation cavity with the water outlet connecting port (131 c);

the shell butt joint end of the second installation shell (132) is coaxial with the connecting opening (131 a) and is provided with an interval, an air outlet butt joint opening communicated with the first installation cavity is formed between the shell butt joint end and the connecting opening (131 a), and the first installation cavity is communicated with the air inlet connecting opening (131 b).

9. The boron-based ram propulsion cross-media aircraft of claim 8, wherein the gas-liquid transport assembly (14) comprises: the air guide pipe (141), the water guide pipe (142), the heat exchanger (143), the air guide pipe (144) and the water guide pipe (145);

one end of the air duct (141) is connected with an air inlet connection port (131 b) of the flow control device (13), and the other end of the air duct is connected with the heat exchanger (143);

one end of the air entraining pipe (144) is connected with the heat exchanger (143), and the other end of the air entraining pipe is connected with a second hollow container (321) of the solid-gas generator (32); wherein the position where the bleed air pipe (144) is connected with the second hollow container (321) is adjacent to the tail end of the second hollow container (321);

One end of the water guide pipe (142) is connected with a water outlet connection port (131 c) of the flow control device (13), and the other end of the water guide pipe is connected with the heat exchanger (143);

one end of the water pipe (145) is connected with the heat exchanger (143), and the other end is connected with the second hollow container (321) of the solid-gas generator (32); wherein, the end of the water pipe (145) connected with the second hollow container (321) is provided with an atomizing nozzle.

10. The boron-based ram propulsion cross-medium aircraft of claim 9, wherein the heat exchanger (143) is disposed between the water ram gas generator (31) and the solid ram gas generator (32);

the heat exchanger (143) includes: a hollow heat exchanger housing (1431), a spiral heat exchange tube (1432) disposed within the heat exchanger housing (1431);

the heat exchanger shell (1431) is integrally of an annular hollow structure, two axial ends of the heat exchanger shell are respectively provided with an air collecting cavity structure for connecting the spiral heat exchange tubes (1432), and two axial ends of the heat exchanger shell (1431) are respectively provided with a heat exchanger water inlet (143 a) and a heat exchanger water outlet (143 b) for communicating the hollow part of the heat exchanger shell (1431) and a heat exchanger air inlet (143 c) and a heat exchanger air outlet (143 d) for communicating the air collecting cavity structure;

The water inlet (143 a) of the heat exchanger is connected with the water guide pipe (142), and the water outlet (143 b) of the heat exchanger is connected with the water guide pipe (145);

the heat exchanger air inlet (143 c) is connected with the air entraining pipe (144), and the heat exchanger air outlet (143 d) is connected with the air duct (141);

the boost tank section (5) comprises: a boost cabin section main body (51), a plurality of air inlet channel structures (52) and a plurality of tail vane components (53) arranged on the outer side surface of the boost cabin section main body (51);

the boost tank section body (51) comprises: a combustion chamber (511) and a tail pipe (512) coaxially connected;

the length of the air inlet channel structure (52) is consistent with the axial length of the boost cabin section main body (51)

The air inlet structure (52) is provided with an air inlet (521) for communicating the combustion chamber (511) with the outside, and a switch mechanism arranged corresponding to the air inlet (521);

along the axial direction of the boost tank section main body (51), the air inlet channel (521) is arranged adjacent to the front end of the boost tank section main body (51);

along the axial direction of the boost cabin section main body (51), the tail vane assembly (53) is arranged adjacent to the tail end of the boost cabin section main body (51).

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