A boron-based ramjet-propelled trans-medium aircraft

Abstract

The present invention relates to a boron-based ramjet-propelled trans-medium aircraft, comprising: a cavitation device, an auxiliary cabin, a gas generating device, a separation device, a booster cabin and a guide device; the cavitation device, the auxiliary cabin, the gas generating device, the separation device and the booster cabin are coaxially arranged; the cavitation device is connected to the head of the auxiliary cabin, the gas generating device is connected to the tail of the auxiliary cabin, the separation device is detachably connected to the tail of the gas generating device, and the booster cabin is connected to the tail of the separation device; the guide device is arranged in the cavitation device; the head of the auxiliary cabin is provided with a detachable fairing, and the cavitation device is located inside the fairing; the gas generating device is filled with boron-based solid propellant; the booster cabin is filled with propellant; when the boron-based ramjet-propelled trans-medium aircraft switches from air flight to water navigation, the separation device and the booster cabin are separated from the gas generating device.

Description

Technical Field

[0001] 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

[0002] Currently, commonly used weapons in the ocean battlefield are torpedoes and anti-ship missiles. Torpedoes, as the primary underwater offensive and defensive weapon, offer advantages such as high strike power, good concealment, high hit rate, and strong anti-interference capabilities; missiles have the advantages of long range, high speed, and high maneuverability. However, with the advancement of modern offensive and defensive technologies, conventional aircraft (missiles / torpedoes) that operate in a single medium have become increasingly difficult to effectively penetrate fleet anti-missile networks. Therefore, the concept of cross-medium aircraft has been proposed.

[0003] Compared with single-medium aircraft, cross-medium aircraft have the characteristics of fast flight speed in the air 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.

[0004] Current trans-medium aircraft primarily focus on anti-submarine missiles and rocket-assisted torpedoes. Research on trans-medium aircraft, both domestically and internationally, primarily focuses on variant structural design and trans-medium propulsion technology. Common variant structural designs include folding wings, variable-sweep wings, and bionic wings. By modifying the airfoil structure, these designs are suitable for both aerial and underwater travel, and for use in low-speed, low-altitude scenarios. Common trans-medium propulsion technologies include thermoelectric hybrid propulsion systems and ramjet propulsion systems.

[0005] Existing variable-configuration cross-medium aircraft, which adapt their wing structures to operate in both air and water, are generally used in specific operational scenarios, with limited operational capabilities, particularly at low speeds and altitudes. Furthermore, their complex structures make their destructive capabilities as weapons in the ocean battlefield very limited.

[0006] Existing trans-medium aircraft using combined thermoelectric propulsion systems have low underwater power and endurance requirements due to the limitations of battery capacity within the trans-medium aircraft's fuselage. For example, the "submersible aircraft" program proposed by the US Defense Advanced Research Projects Agency (DARPA) utilizes a turbofan engine for aerial propulsion and a propeller motor for underwater navigation.

[0007] Existing anti-submarine missiles and rocket-assisted torpedo cross-medium vehicles, which use rocket engines for propulsion and parachute entry into the water, suffer from short range, low specific impulse, slow cross-domain flight, and susceptibility to interception. Examples include Australia's Ikara anti-submarine missile and the United States' Sea Lance rocket-assisted torpedo. These vehicles use rocket engines for propulsion and parachute entry into the water to achieve cross-medium flight.

[0008] Existing research on new ramjet-based trans-medium vehicles primarily focuses on propulsion schemes, and most studies are conducted in a single operating environment. Representative examples include studies on the operating characteristics of solid ramjets and water ramjets. For example, Chen Wenwu et al. proposed a new trans-medium engine scheme using the same metal-based (magnesium-aluminum) solid propellant. In air, it operates in a solid rocket ramjet mode with air as the oxidizer, and in water, it operates in a water ramjet mode with water as the oxidizer. The theoretical performance of the engine under typical operating conditions was calculated. Shi Lei et al. proposed a combined air-water ramjet trans-medium anti-ship and anti-submarine missile. This missile uses a composite magnesium rod as fuel. In air, it generates thrust by reacting oxygen and its own liquid oxidizer with the fuel-rich gas generated by the magnesium rod. In water, it generates thrust by directly reacting water with the magnesium rod. The trans-medium ramjet engine designed by Du Quan et al. is capable of multiple water-to-air crossings, flight at Mach numbers of 0 to 4, and high-speed underwater navigation. Zhou Ling et al. 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.

[0009] [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.

[0010] [2] Du Quan, Wang Yufeng, Hu Yanxiao, Mo Jianwei, Chen Lei, Zhu Xianhao, Li Jianghan. A wide-range multi-frequency water-jump air turbine ramjet combination engine and its control method [P]. Shaanxi Province: CN114439645A, 2022-05-06.

[0011] [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.

[0012] [4] Zhou Ling. Analysis and modal conversion of cross-medium dynamic system schemes[D]. Harbin Engineering University, 2021. DOI: 10.27060 / d.cnki.ghbcu.2021.000535. Summary of the Invention

[0013] The object of the present invention is to provide a boron-based ramjet-propelled trans-medium aircraft.

[0014] To achieve the above-mentioned object of the invention, the present invention provides a boron-based ramjet propulsion cross-medium aircraft, comprising: a cavitation device, an auxiliary cabin, a gas generating device, a separation device, a booster cabin and a guide device;

[0015] 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;

[0016] The guiding device is arranged in the cavitation device;

[0017] The head of the auxiliary compartment is provided with a detachable fairing, and the cavitation device is located inside the fairing;

[0018] The gas generating device is filled with a boron-based solid propellant;

[0019] The booster compartment is filled with propellant;

[0020] When the boron-based ramjet-propelled trans-medium aircraft switches from flying in the air to sailing in the water, the separation device and the booster compartment are separated from the gas generating device.

[0021] According to one aspect of the present invention, the boron-based ramjet-propelled trans-medium aircraft comprises the following stages during its flight: a boost phase, a cruise phase, and a glide phase;

[0022] When in the boost phase, the boost compartment burns the propellant to provide power;

[0023] 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 is mixed with the air introduced into the booster compartment for secondary combustion to provide power;

[0024] When in the cruising stage, the gas generating device is shut down;

[0025] During the underwater navigation of the boron-based ramjet-propelled trans-medium aircraft, the fairing is separated from the auxiliary compartment, and the gas generator 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 generator.

[0026] According to one aspect of the present invention, the auxiliary compartment and the gas generating device are located in the same cylindrical casing;

[0027] The separation device is connected to the end of the cylindrical shell by an explosive bolt;

[0028] The separation device includes: an annular hollow body and a signal generator disposed in the hollow body;

[0029] The signal generator is connected to the explosive bolt.

[0030] According to one aspect of the present invention, the auxiliary compartment includes: a warhead and a power supply coaxially arranged in sequence;

[0031] 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;

[0032] The first tail nozzle is provided with a first flow regulating valve;

[0033] The water ram gas generator includes: 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;

[0034] The first hollow container is filled with a boron-based solid propellant;

[0035] The first igniter is connected to the power supply;

[0036] The intermediate nozzle is provided with a second flow regulating valve;

[0037] The solid-impact gas generator includes: a second hollow container, a second igniter, and a plurality of foldable tail fin devices arranged outside the second hollow container;

[0038] 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;

[0039] The second hollow container is filled with a boron-based solid propellant;

[0040] The foldable tail 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;

[0041] An opening is provided on the side wall of the cylindrical shell corresponding to the foldable tail device.

[0042] According to one aspect of the present invention, the cavitation device includes: 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;

[0043] The gas-liquid transmission component is in communication with the second hollow container;

[0044] The flow control device is located in the cylindrical outer shell, and the flow control device is arranged on the front side of the auxiliary compartment.

[0045] According to one aspect of the present invention, the conical cavitator comprises: a cone cap portion, a cone bottom portion and a middle partition;

[0046] The large diameter end of the cone cap portion is fixedly connected to the cone bottom portion;

[0047] The middle partition is spaced apart from the cone bottom and is disposed in the cone cap portion, so as to form a mounting cavity for mounting the guide device between the middle partition and the cone cap portion, and a water inlet cavity between the middle partition and the cone bottom portion;

[0048] A plurality of water inlets for communicating with the water inlet cavity are provided at intervals on the cone cap portion between the middle partition plate and the cone bottom portion;

[0049] A water outlet for communicating with the water inlet cavity is provided at the center of the cone bottom portion.

[0050] According to one aspect of the present invention, the diversion bowl structure comprises: a connecting body and a plurality of bowl-shaped diversion parts;

[0051] Along the axial direction of the connecting body, a plurality of the bowl-shaped flow-guiding portions are arranged at intervals;

[0052] The connecting body is provided with a water inlet channel and an air outlet cavity;

[0053] The water inlet channel is coaxially arranged with the connecting body and passes through two opposite ends thereof;

[0054] 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;

[0055] An air outlet hole for communicating with the air outlet cavity is provided on the radial outer side wall of the connecting body, and an air inlet hole for communicating with the air outlet cavity is provided at the axial rear end of the connecting body;

[0056] The radial sizes of the adjacent bowl-shaped flow-guiding parts are successively increased in a direction away from the conical cavitator, and the bowl-shaped flow-guiding parts and the air outlet holes are successively alternately arranged.

[0057] 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;

[0058] The first mounting shell is in the shape of a hollow cone, with a small diameter end having a connection opening, and a large diameter end having an air inlet connection port and a water outlet connection port.

[0059] 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 fixed end fixedly connected to the bottom of the first mounting shell, and the other end is a shell docking end;

[0060] The first mounting shell and the second mounting shell form a first mounting cavity for mounting the cavitation gas flow control unit;

[0061] The hollow portion of the second mounting shell constitutes a second mounting cavity for mounting the water flow control unit;

[0062] 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;

[0063] The fixed end of the second mounting shell is provided with a connecting channel for connecting the second mounting cavity and the water outlet connection port;

[0064] The shell docking end of the second mounting shell is coaxial with the connecting opening and is spaced apart, and an air outlet docking opening communicating with the first mounting cavity is formed between the shell docking end and the connecting opening, and the first mounting cavity is communicated with the air inlet connecting port.

[0065] According to one aspect of the present invention, the gas-liquid transmission assembly includes: an air guide pipe, a water guide pipe, a heat exchanger, an air duct and a water delivery pipe;

[0066] 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;

[0067] 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;

[0068] One end of the water pipe is connected to the water outlet connection port of the flow control device, and the other end is connected to the heat exchanger;

[0069] 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.

[0070] According to one aspect of the present invention, the heat exchanger is provided between the water ram gas generator and the solid ram gas generator;

[0071] The heat exchanger comprises: a hollow heat exchanger shell, a spiral heat exchange tube arranged in the heat exchanger shell;

[0072] 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 communicating with 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 communicating with the gas collecting cavity structure are respectively provided;

[0073] 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;

[0074] 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.

[0075] 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 fin assemblies arranged on the outer side of the booster compartment body;

[0076] The booster compartment body includes: a combustion chamber and a tail nozzle connected coaxially;

[0077] The length of the air inlet structure is consistent with the axial length of the booster compartment body.

[0078] The air intake structure is provided with an air intake duct for connecting the combustion chamber with the outside, and a switch mechanism corresponding to the air intake duct;

[0079] Along the axial direction of the booster compartment body, the air inlet is arranged adjacent to the front end of the booster compartment body;

[0080] 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.

[0081] 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-media aircraft.

[0082] According to one solution of the present invention, a body of revolution design is adopted, and the aircraft can navigate in both air and water media environments without changing its geometric configuration.

[0083] According to one solution of the present invention, a ramjet engine is used as the power system, which can achieve supersonic flight in the air and is assisted by a cavitation device in the water to achieve high-speed navigation of ≮200 knots, greatly improving its penetration performance.

[0084] 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 making the propulsion system specific impulse much higher than that of power devices such as rocket engines and motors, effectively improving the range of the aircraft.

[0085] 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.

[0086] 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 status and intelligent switching of operating modes.

[0087] According to one solution of the present invention, the present invention incorporates the concept of sharing throughout the entire design process, adopts a rotating body configuration design and a ramjet propulsion system to achieve sharing of cross-medium aircraft configuration and cross-medium power solutions; utilizes an air ramjet combustion chamber to place propellant and utilizes a gas generator as a water ramjet engine afterburner to achieve space sharing; utilizes high-temperature combustion exhaust to heat water for combustion to achieve energy sharing.

[0088] 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 operation, effectively enhancing the concealment, maneuverability and evasion capability of marine battlefield weapons, and greatly broadening the combat capability of marine battlefield weapons.

[0089] According to one solution 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's damage effect.

[0090] According to one solution of the present invention, the present invention proposes to use boron-based propellant as the fuel of the water ramjet engine. Theoretical calculations show that compared with aluminum-based propellant, the water ramjet engine using boron-based propellant can achieve better working performance. Under the same charge volume, the range is increased by about one-fold. In addition, the water ramjet engine adopts a secondary water inlet structure.

[0091] According to one solution of the present invention, the present invention incorporates the concept of sharing throughout the entire design concept, adopts a rotating body configuration design and a ramjet propulsion system to achieve sharing of cross-medium aircraft configuration and cross-medium power solutions; utilizes an air ramjet combustion chamber to place propellant and utilizes a gas generator as a water ramjet engine afterburner to achieve space sharing; utilizes high-temperature combustion exhaust to heat water for combustion to achieve energy sharing. BRIEF DESCRIPTION OF THE DRAWINGS

[0092] Figure 1 is a diagram schematically showing the structure of a boron-based ramjet-propelled trans-medium aircraft flying in the air according to one embodiment of the present invention;

[0093] Figure 2 is a schematic diagram showing the structure of a boron-based ramjet-propelled trans-medium aircraft sailing in water according to one embodiment of the present invention;

[0094] Figure 3 is a diagram schematically showing the internal structure of a boron-based ramjet-propelled trans-medium aircraft according to one embodiment of the present invention;

[0095] Figure 4 is a cross-sectional view schematically showing a boron-based ramjet-propelled trans-medium aircraft according to one embodiment of the present invention;

[0096] Figure 5 is a structural diagram schematically showing a conical cavitator according to one embodiment of the present invention;

[0097] Figure 6 is a cross-sectional view schematically showing a conical cavitator and guide bowl structure combination according to one embodiment of the present invention;

[0098] Figure 7 is a structural diagram schematically showing a diversion bowl structure according to an embodiment of the present invention;

[0099] Figure 8 is a perspective view schematically showing a flow control device according to one embodiment of the present invention;

[0100] Figure 9 is a cross-sectional view schematically showing a flow control device according to one embodiment of the present invention;

[0101] Figure 10 is a cross-sectional view schematically showing a flow control device according to one embodiment of the present invention;

[0102] Figure 11 It is a schematic representation Figure 10 Cross-section view in the AA direction;

[0103] Figure 12 It is a schematic representation Figure 10 Cross-section along the mid-BB direction;

[0104] Figure 13 It is a schematic representation Figure 10 Cross-section in the CC direction;

[0105] Figure 14It is a schematic representation Figure 10 Cross-section along the mid-DD direction;

[0106] Figure 15 is a diagram schematically showing a connection structure of a flow control device and a gas-liquid transmission component according to one embodiment of the present invention;

[0107] Figure 16 is a cross-sectional view schematically showing a heat exchanger according to one embodiment of the present invention;

[0108] Figure 17 is a cross-sectional view schematically showing a heat exchanger according to one embodiment of the present invention;

[0109] Figure 18 is a structural diagram schematically showing a second hollow container according to one embodiment of the present invention;

[0110] Figure 19 1 is a diagram schematically showing the working modes of a boron-based ramjet propulsion cross-medium aircraft in the cruise phase according to one embodiment of the present invention;

[0111] Figure 20 1 is a diagram schematically showing the working mode of a water ramjet engine of a boron-based ramjet-propelled trans-medium aircraft during underwater navigation according to an embodiment of the present invention;

[0112] Figure 21 It is a diagram schematically showing the variation of specific impulse of different propellants with air-fuel ratio;

[0113] Figure 22 It is a diagram schematically showing the variation of specific impulse of different propellants with water-fuel ratio;

[0114] Figure 23 It is a diagram schematically showing the range of an aircraft under unit charge volume of different propellants;

[0115] Figure 24 1. It is a diagram schematically showing the tail flame of a boron-based ramjet propulsion cross-medium aircraft air ramjet engine test process according to one embodiment of the present invention;

[0116] FIG25( 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;

[0117] FIG25( 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;

[0118] FIG26( a ) is a diagram schematically showing a water ramjet test tail flame of a boron-based ramjet-propelled trans-medium aircraft in test state A according to an embodiment of the present invention;

[0119] FIG26( b ) is a diagram schematically showing a water ramjet test tail flame of a boron-based ramjet-propelled trans-medium aircraft in test state b according to an embodiment of the present invention;

[0120] Figure 27 1 is a diagram schematically showing a pressure-time curve of an afterburner of a boron-based ramjet propulsion trans-medium aircraft according to an embodiment of the present invention;

[0121] Figure 28 FIG. 1 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

[0122] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0123] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "transverse", "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. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to 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.

[0124] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not limited to the following embodiments.

[0125] Combine Figure 1 . Figure 2 、 Figure 3 and Figure 4As shown, according to one embodiment of the present invention, a boron-based ramjet-propelled trans-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 trans-medium aircraft of the present invention adopts a rotating body shape design as a whole, and the aircraft can navigate in both air and water media environments without changing its 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 a boron-based solid propellant, and the booster compartment 5 is filled with a propellant. In this embodiment, when the boron-based ramjet-propelled trans-medium vehicle transitions from airborne flight to underwater navigation, the separation device 4 and booster compartment 5 are separated from the gas generator 3. The separation device 4 and booster compartment 5 can be separated from the gas generator 3 as a combined unit, or individually and sequentially.

[0126] In this embodiment, the guidance device 6 is the 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.

[0127] Combine Figure 1 . Figure 2 、 Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the boron-based ramjet-propelled trans-medium aircraft includes the following flight stages during the airborne flight: a boost phase, a cruise phase, and a glide phase; wherein, during the boost phase, the booster compartment 5 burns the propellant to provide power; during the cruise phase, the gas generator 3 burns a portion of the boron-based solid propellant to produce primary gas, and the primary gas is mixed with the incoming air and then combusted to provide power; during 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, and the gas generator 3 burns the boron-based solid propellant to produce a primary fuel-rich gas, and the primary fuel-rich gas is mixed with the incoming water and then reacts to provide power.

[0128] Combine Figure 1 . Figure 2 、 Figure 3 and Figure 4As shown, 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, they form an overall streamlined shape, which makes it more beneficial for them 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 gripping bolt, thereby achieving the effect of controlled separation.

[0129] In this embodiment, the separation device 4 comprises an annular hollow body and a signal generator disposed within the hollow body. The hollow body serves as an integral connecting and supporting structure. Its hollow design further facilitates the installation of the signal generator and the explosive bolts connected to other structures. In this embodiment, the signal generator and explosive bolts are electrically connected, enabling controlled disconnection of the explosive bolts. In this embodiment, the signal generator operates autonomously, independent of other components. This can also be implemented using existing, proven products, and will not be further elaborated here.

[0130] Combine Figure 1 . Figure 2 、 Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the auxiliary compartment 2 includes a coaxially arranged warhead 21 and a power supply 22. In this embodiment, the power supply 22 is electrically connected to the warhead 21 for controlled activation. Similarly, the power supply 22 is also connected to the rear-side gas generator 3 for controlled activation. This power supply 22 serves as the electrical energy source for the entire boron-based ramjet-propelled trans-medium vehicle.

[0131] Combine Figure 1 . Figure 2 、 Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the gas generating device 3 includes: a water ram gas generator 31, a solid ram gas generator 32 and a first tail nozzle 33 arranged coaxially 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.

[0132] In this embodiment, the water ram gas generator 31 comprises a first hollow vessel 311, a first igniter 312 disposed at the head of the first hollow vessel 311, and an intermediate nozzle 313 disposed at the tail of the first hollow vessel 311. In this embodiment, the first hollow vessel 311 is filled with boron-based solid propellant. In this embodiment, the first igniter 312 is connected to the power source 22. In this embodiment, the intermediate nozzle 313 is equipped with a second flow control valve 3131. The intermediate nozzle 313 serves as the nozzle for the water ram gas generator 31 during operation, and the second flow control valve 3131 controls the flow rate of the gas ejected from the intermediate nozzle 313. In this embodiment, the first igniter 312 is controlled by the trans-medium aircraft control program and is switched on and off by the power source. This can be implemented using existing mature products and will not be further described here.

[0133] In this embodiment, the solid ram gas generator 32 comprises a second hollow container 321, a second igniter 322, and multiple foldable tail fins 323 disposed 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 its tail is connected to the first tail nozzle 33. In this embodiment, the connection between the second hollow container 321 and the intermediate nozzle 313 enables the hollow second hollow container 321 to be used to achieve a primary fuel-rich gas-water mixing reaction during operation of the water ram gas generator 31, providing increased propulsion. In this embodiment, the second hollow container 321 is filled with a boron-based solid propellant; this boron-based solid propellant enables operation during the cruise phase, providing propulsion during the cruise phase. In this embodiment, the second igniter 322 is also controlled by the trans-medium vehicle control program through on / off control with a power supply. This can be implemented using existing mature products and will not be further described here.

[0134] In this embodiment, the foldable tail device 323 is located at the rear end of the second hollow container 321 and is evenly spaced along the circumference of the second hollow container 321. In this embodiment, the foldable tail device 323 comprises a mounting base, a foldable tail structure, and a steering gear. The foldable tail device 323 allows the foldable tail structure to be deployed during underwater navigation, allowing the steering gear to control the overall navigation direction. When the present invention is airborne, the foldable tail structure is retracted to avoid interfering with other control mechanisms. In this embodiment, an opening is provided on the sidewall of the cylindrical housing 8 corresponding to the foldable tail device 323, through which the foldable tail structure can be deployed. In this embodiment, appropriate sealing arrangements are implemented at the location where the foldable tail device 323 is mounted to ensure complete sealing during underwater navigation. For example, a mounting chamber is provided at the opening where the foldable tail device 323 is mounted to ensure complete sealing at the mounting location. Furthermore, a seal is provided at the connection between the foldable tail device and the steering gear lever to achieve complete sealing.

[0135] Combine Figures 3 to 17 As shown, according to one embodiment of the present invention, a cavitation device 1 is used to generate supercavitation during underwater navigation, thereby ensuring the navigation speed and stability of the present invention. Specifically, the cavitation device 1 comprises 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 assembly 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 assembly 14 is connected to the second hollow container 321 to enable air to be drawn into the guide bowl structure 12 and water to be supplied to the second hollow container 321 of the solid fuel gas generator 32 during underwater navigation. In this embodiment, when the cavitation device 1 is in operation, the conical cavitator 11 first performs partial cavitation. Then, high-temperature fuel gas from the fuel gas generator 3 is used as cavitating gas to provide additional fuel, ultimately achieving complete cavitation of the aircraft, effectively ensuring that the supercavitation envelops the entire vehicle.

[0136] In this embodiment, the flow control device 13 is located inside the cylindrical shell 8, and the flow control device 13 is set at the front side of the auxiliary compartment 2. In this embodiment, the guide bowl structure 12 is connected to the outside of the head of the cylindrical shell 8, and the flow control device 13 is docked with the inside of the head of the cylindrical shell 8. Furthermore, by setting a water inlet transition channel for water to pass through and an air outlet transition channel for cavitation gas output at the head of the cylindrical shell 8, it is possible to achieve communication with the front conical cavitator 11 and the guide bowl structure 12. Its 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, thereby supplementing the supercavitation flow rate. 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 lower.

[0137] Combine Figure 5 and Figure 6 As shown, according to one 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 gap, 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 provided at the center position of the conical bottom portion 112. Furthermore, during navigation in the water, the present invention introduces water into the water inlet cavity through the water inlet 111a and sends it to the rear end structure through the water outlet 112a. In this embodiment, eight water inlets 111 a are arranged at equal intervals.

[0138] Combine Figure 6 and Figure 7 As shown, according to one 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 part 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.

[0139] In this embodiment, the air outlet cavity 121b is coaxially disposed around the water inlet channel 121a, and the air outlet cavity 121b and the water inlet channel 121a are isolated from each other. The air outlet cavity 121b is an annular cavity, coaxially disposed around the water inlet channel 121a. In this embodiment, an air outlet hole 121c is disposed on the radially outer side wall of the connecting body 121 for communicating with the air outlet cavity 121b, and an air inlet hole 121d is disposed at the axial rear end of the connecting body 121 for communicating with the air outlet cavity 121b. In this embodiment, the air inlet hole 121d disposed at the rear end of the connecting body 121 is used to seal and connect with the air outlet transition channel disposed at the head of the cylindrical shell 8. In this embodiment, there are multiple air inlet holes 121d set at the rear end of the connecting body 121, and they are distributed in a circular array. Correspondingly, the air outlet transition channel set at the head of the cylindrical shell 8 is set in a one-to-one correspondence with the air inlet holes 121d.

[0140] In this embodiment, the radial dimensions of adjacent bowl-shaped flow guide portions 122 are arranged to increase in sequence as they move 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, while the front side surface of the bowl-shaped flow guide portion 122 at the rear end is a curved-edged conical surface.

[0141] In this embodiment, the bowl-shaped flow guide portion 122 and the air outlet holes 121c are arranged alternately in a direction away from the conical cavitator 11. In this embodiment, multiple air outlet holes 121c are arranged at equal intervals along the circumference of the connecting body 121. It should be noted that the number of air outlet holes 121c provided on the connecting body 121 can be set according to actual needs, for example, the number provided along the circumference or the number arranged axially.

[0142] Combine Figure 3 、 Figure 4 、 Figures 8 to 15As shown, according to one embodiment of the present invention, the flow control device 13 functions to regulate the cavitation and water flow rates in real time based on navigation conditions. Specifically, the flow control device 13 comprises a first mounting housing 131, a second mounting housing 132, a water flow control unit 133, and a cavitation flow control unit 134. In this embodiment, the first mounting housing 131 is a hollow conical body with a connection opening 131a at its smaller diameter end and an air inlet connection port 131b and a water outlet connection port 131c at its larger diameter end. In this embodiment, the second mounting housing 132 is an axisymmetric hollow structure, coaxially disposed within the first mounting housing 131. One end of the second mounting housing 132 is a fixed end fixedly connected to the bottom of the first mounting housing 131, and the other end is a docking end. In this embodiment, the first mounting housing 131 and the second mounting housing 132 define a first mounting cavity for mounting the cavitation flow control unit 134. The hollow portion of the second mounting housing 132 forms a second mounting cavity for mounting the water flow control unit 133. In this embodiment, the docking end of the second mounting housing 132 is provided with a water inlet docking opening 132a, which extends beyond the connection opening 131a. A connecting channel is provided at the fixed end of the second mounting housing 132, connecting the second mounting cavity and the water outlet connection opening 131c. In this embodiment, the docking end of the second mounting housing 132 is coaxial with the connection opening 131a, but spaced apart. An air outlet docking port for communication with the first mounting cavity is formed between the docking end and the connection opening 131a. The first mounting cavity is connected to the air inlet connection opening 131b.

[0143] In this embodiment, the second mounting housing 132 comprises a coaxially arranged conical housing portion and a cylindrical housing portion. The butting end of the second mounting housing 132 is located at the smaller diameter end of the conical housing portion, while the end of the cylindrical housing portion distal from the conical housing portion constitutes the fixed end of the second mounting housing 132. In this embodiment, the radial dimension of the larger diameter end of the conical housing portion is greater than that of the cylindrical housing portion. In this embodiment, the water flow control unit 133 is coaxially arranged on the inner side of the cylindrical housing portion, while the cavitation gas flow control unit 134 is coaxially arranged on the outer side of the cylindrical housing portion.

[0144] 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, thereby being able to more advantageously store the input water. 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.

[0145] In addition, by providing 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.

[0146] In this embodiment, the water flow controller 133 is an overall cylindrical structure with a water passage disposed at its center. In this embodiment, the water flow controller 133 is used to regulate the incoming water flow and simultaneously increase the water pressure to ensure that the water can enter the afterburner. Specifically, the water flow rate and pressure can be controlled by controlling the cross-sectional opening size of the water passage. For example, at least one adjustable blade can be provided in the water passage to adjust the cross-sectional opening size. Of course, other structures can also be used to achieve this cross-sectional opening size adjustment function, which will not be detailed here.

[0147] In this embodiment, the cavitation gas flow control unit 134 is annular in structure, with multiple air passages spaced apart along its circumference. In this embodiment, the water flow rate and pressure can be controlled by controlling the cross-sectional opening size of the air passages. For example, at least one adjustable vane can be provided in the air passage to adjust the cross-sectional opening size. Of course, other structures can also be used to achieve this cross-sectional opening size adjustment, which will not be discussed further here.

[0148] Combine Figure 4 、 Figure 8 and Figure 9 As shown, according to one embodiment of the present invention, there are two air inlet connection ports 131b and two water outlet connection ports 131c respectively, and they 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.

[0149] Combine Figures 9 to 14As shown, according to one embodiment of the present invention, a diversion structure 1311 is provided in the first shell 131; the diversion structure 1311 includes a baffle 1311a and a side plate 1311b. In this embodiment, the baffle 1311a is an annular plate that is sleeved onto the outer surface of the cylindrical shell portion through a hollow portion, and its radial outer surface is connected to the inner sidewall of the first shell 131. In this embodiment, the side plate 1311b is located between the baffle 1311a and the bottom plate at the large diameter end of the first shell 131, and is used to divide the rear liquid accumulation chamber a that connects the second installation chamber and the water outlet connection port 131c, and the rear gas collection chamber b that connects the first installation chamber and the air inlet connection port 131b. In this embodiment, the rear liquid accumulation chamber a is provided in a one-to-one correspondence with the water outlet connection port 131c, and the rear gas collection chamber b is provided in a one-to-one correspondence with the air inlet connection port 131b.

[0150] In this embodiment, an opening is provided at a position of the baffle 1311 a corresponding to the rear gas collecting cavity b.

[0151] Combine Figures 9 to 14 As shown, according to one embodiment of the present invention, the side plate 1311b is a long strip-shaped plate. Along 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 at the large diameter end of the first shell 131; in this embodiment, along 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 portion and the inner wall of the first shell 131; wherein the thickness of the side plate 1311b gradually increases in the direction away from the cylindrical shell portion. In this embodiment, a plurality of side plates 1311b are arranged at equal intervals along the circumference of the first shell 131; wherein, four side plates 1311b are arranged at equal intervals, thereby achieving the purpose of dividing the space between the baffle 1311a and the bottom plate into four equal parts, thereby forming the required rear effusion chamber a and rear gas collection chamber b.

[0152] 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 or 4 respectively. Accordingly, the side plates 1311b are added to the diversion structure 1311 to divide the corresponding number of rear liquid effusion chambers a and rear gas collection chambers b.

[0153] Combine Figure 3 、 Figure 4 、 Figure 6 、 Figure 8 、 Figure 9 、 Figures 15 to 17As shown, according to one embodiment of the present invention, the gas-liquid transmission assembly 14 includes: an air conduit 141, a water conduit 142, a heat exchanger 143, an air bleed pipe 144, and a water delivery pipe 145. In this embodiment, one end of the air conduit 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. The air bleed pipe 144 is connected to the heat exchanger 143 at one end, and to the second hollow container 321 of the solid-fuel gas generator 32 at the other end. The connection between the air bleed pipe 144 and the second hollow container 321 is adjacent to the rear 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-injection gas generator 32; wherein, the end of the water pipe 145 connected to the second hollow container 321 is provided with an atomizing nozzle.

[0154] In this embodiment, at least two pipes connected to the second hollow container 321 are spaced apart on the same water pipe 145, and each pipe has a corresponding atomizing nozzle. This arrangement increases the distribution range of water in the afterburner, further promoting mixed combustion in the afterburner.

[0155] Combine Figure 16 、 Figure 17 and Figure 18 As shown, according to one embodiment of the present invention, a heat exchanger 143 is disposed between the water ram gas generator 31 and the solid ram gas generator 32. In this embodiment, the heat exchanger 143 comprises a hollow heat exchanger shell 1431 and a spiral heat exchange tube 1432 disposed within the heat exchanger shell 1431. The heat exchanger shell 1431 is an annular hollow structure, with a gas manifold structure for connecting the spiral heat exchange tube 1432 disposed at each axial end. Furthermore, a heat exchanger water inlet 143a and a heat exchanger water outlet 143b are disposed at each axial end of the heat exchanger shell 1431, respectively, for communicating with the hollow portion of the heat exchanger shell 1431, and a heat exchanger air inlet 143c and a heat exchanger air outlet 143d are disposed for communicating with the air manifold structure. In this embodiment, heat exchanger water inlet 143a is connected to water pipe 142, and heat exchanger water outlet 143b is connected to water pipe 145. Heat exchanger air inlet 143c is connected to air duct 144, and heat exchanger air outlet 143d is connected to air duct 141. Heat exchanger 143 utilizes the heat of the high-temperature gas to heat the water, thereby regenerating the heat from the high-temperature gas.

[0156] In this embodiment, multiple spiral heat exchange tubes 1432 are provided. Each spiral heat exchange tube 1432 undergoes a 90° deflection as it passes through the interior of the heat exchanger housing 1431. Consequently, 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. This arrangement effectively increases the heat exchange distance and time between the low-temperature water and the high-temperature gas, thereby enhancing the heat exchange effect.

[0157] In this embodiment, the gas collecting cavity structure adopts an arc-shaped plate body, whose 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 this embodiment, the length of the gas collecting cavity structure is five-sixths of the circumferential length of the heat exchanger shell 1431. In this embodiment, baffles are used to close the gas collecting cavity structure at both ends of the circumference to ensure that the gas collecting cavity is isolated from the rest of the hollow part of the heat exchanger shell 1431. In this 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.

[0158] In this embodiment, two air pipes 141, two water pipes 142, two air bleed pipes 144 and two water delivery pipes 145 are respectively provided, and are symmetrically arranged on both sides of the combination of the auxiliary compartment 2 and the gas generating device 3.

[0159] Because cavitation gas is drawn from the end of the water ramjet's afterburner, thermal calculations show that the gas temperature there reaches 2500K. Such high temperatures are not necessary for cavitation gas to function, and such high temperatures, when transmitted through pipelines, pose a significant threat to the safety of the entire vehicle. Meanwhile, the temperature of seawater obtained from an external source is approximately 280K. Experimental studies have shown that lower water temperatures hinder the operation of the water ramjet. Raising the temperature of the water entering the afterburner would improve engine performance. Therefore, the present invention proposes a heat exchanger. Before the seawater enters the afterburner, it passes through the heat exchanger, where the heat from the high-temperature gas is used to heat the seawater, thereby achieving heat recovery.

[0160] Combine Figure 3 and Figure 4As shown, according to one embodiment of the present invention, a booster module 5 comprises a booster module body 51, multiple air intake structures 52 disposed on the outer side of the booster module body 51, and multiple tail fin assemblies 53. The booster module body 51 comprises a coaxially connected combustion chamber 511 and a tail nozzle 512. In this embodiment, the combustion chamber 511 is filled with propellant to enable the boost phase flight of the present invention after launch. In this embodiment, the air intake structure 52 is configured to have a length consistent with the axial length of the booster module body 51. The air intake structure 52 is provided with an air intake duct 521 connecting the combustion chamber 511 with the outside world, and a switch mechanism corresponding to the air intake duct 521. In this embodiment, an igniter is also provided in the combustion chamber 511 for controlled ignition of the propellant. In this embodiment, the igniter can be implemented using an existing mature product and will not be described in detail here.

[0161] In this embodiment, the air inlet 521 is disposed adjacent to the front end of the booster module body 51 along the axial direction of the booster module body 51. The air inlet 521 extends at an angle relative to the axial direction of the booster module body 51, with a first opening formed on the outer side of the air inlet structure 52 and a second opening formed on the sidewall of the combustion chamber 511. The first opening is located forward of the second opening along the axial direction of the booster module body 51. In this embodiment, four air inlet structures 52 are disposed at equal intervals along the circumference of the booster module body 51.

[0162] In this embodiment, a tail rudder assembly 53 is positioned adjacent to the aft end of the booster module body 51 along the axial direction of the booster module body 51. In this embodiment, the tail rudder assembly 53 comprises a connection base, a tail fin component connected to the connection base, and a steering gear that controls the tail fin component. In this embodiment, four tail rudder assemblies 53 are evenly spaced along the circumference of the booster module body 51, and are staggered relative to the air inlet structure 52.

[0163] 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.

[0164] To further illustrate this solution, Figure 1 、 Figure 3 、 Figure 4 、 Figure 18 and Figure 19 The flight process is further explained.

[0165] boost phase

[0166] 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.

[0167] Cruise segment

[0168] Entering the ramjet mode, the switch mechanism of the booster compartment 5's air inlet duct 521 opens, allowing supersonic airflow to enter the combustion chamber 511. It mixes with the primary gas generated by the ignition and combustion of the solid ramjet gas generator 32, undergoing secondary combustion to release heat and produce high-temperature gas. The high-temperature gas expands through the tail nozzle 512 and is ejected at an accelerated rate to generate thrust to maintain the aircraft's cruising flight. In this embodiment, the first flow control 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 within the afterburner, thereby achieving optimal engine performance under different flight conditions. Figure 19 .

[0169] Gliding segment

[0170] After the cruise phase, the solid rocket 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 water entry controllability.

[0171] Interstage separation section

[0172] 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 reburning chamber for the water ram gas generator 31.

[0173] Underwater navigation section.

[0174] After entering the water, the foldable tail device 323 opens and the fairing 7 is jettisoned. Subsequently, the water inlet channel of the cavitation device 1 opens, and water is atomized by the nozzle and sprayed into the second hollow container 321 of the solid ram gas generator 32 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 envelops the vehicle. Figure 20 .

[0175] 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.

[0176] (1) Working performance

[0177] Performance Analysis of Boron-Based Propellants

[0178] The ramjet propulsion system employed in the trans-medium aircraft of the present invention utilizes boron-based solid propellants for both airborne and underwater operation. To illustrate the performance advantages of boron-based propellants, a more commonly used aluminum-based solid propellant is used for performance comparison. The main components of the boron-based and aluminum-based solid propellants used are shown in Tables 1 and 2.

[0179] Table 1 Main components of boron-based propellants

[0180]

[0181] Table 2 Main components of aluminum-based propellants

[0182]

[0183] The engine specific impulses of the two propellants in the high-altitude cruise segment and the underwater cruise segment are calculated respectively. The basic operating parameters of the ramjet engine in the high-altitude cruise segment and the underwater cruise segment are shown in Table 3. Figure 21 、 Figure 22 These are the curves of the engine specific impulse changing with the air-fuel ratio and water-fuel ratio under air ram pressure conditions and water ram pressure conditions respectively.

[0184] Table 3 Basic operating parameters

[0185]

[0186] Depend on Figure 21 、 Figure 22 It can be seen that during aerial flight, due to the high 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. At an air-fuel ratio greater than 6, the theoretical performance of boron-based propellants is significantly superior to that of aluminum-based solid propellants. During underwater navigation, at any water-fuel ratio, the theoretical performance of boron-based propellants is significantly superior to that of aluminum-based propellants, and boron-based fuel-rich propellants offer even greater performance advantages under water ramjet conditions compared to air ramjet conditions. The above calculations demonstrate that, compared to currently used aluminum-based propellants, the boron-based propellant employed by the trans-medium aircraft of the present invention, both in air and underwater, enables trans-medium ramjet engines to achieve greater performance advantages under both air and water ramjet conditions, resulting in higher theoretical performance.

[0187] Figure 23 The air and underwater ranges of the aircraft per unit charge volume are given for each of the following propulsion systems: boron-based ramjet, aluminum-based ramjet, and rocket-assisted propulsion. A comparison reveals that the proposed boron-based ramjet system doubles the range of the aluminum-based ramjet system and increases approximately sixfold compared to the rocket-assisted propulsion system. This further demonstrates the superior performance of the proposed trans-medium aircraft when using a boron-based ramjet system.

[0188] (2) Air ramjet engine demonstration test (i.e., test of the solid ramjet gas generator 32 and the booster compartment 5 in series)

[0189] A ground-based direct-connect test of the proposed ramjet was conducted using a test system provided by the National University of Defense Technology's Hypersonic Laboratory. The test simulated a flight profile of 10 km at 3 Ma. The test parameters are shown in Table 4.

[0190] Table 4 Parameter settings for the air ramjet direct-connection test condition

[0191]

[0192] During the test, the engine tail flame Figure 24 As shown, it can be seen that the test ramjet engine can achieve ignition and combustion, and the primary combustion gas produced by the combustion of the boron-based propellant can burn in the afterburning chamber and burn more fully, forming a bright tail flame, which is bright yellow-white.

[0193] The pressure and step thrust data collected during the test are shown in Figures 25(a) and 25(b). It can be seen that the engine operated stably, the gas generator pressure increased slightly, the afterburner pressure was relatively stable, and the thrust curve increased slightly during the test. This further demonstrates that the test ramjet engine had stable combustion and reliable operation.

[0194] Engine performance was calculated based on the test data, with the results shown in Table 5. The engine achieved an average thrust of 2179.43 N, a temperature-rise combustion efficiency of 95.64%, and a thrust gain-specific impulse of 1029 s in direct-ground tests. In summary, the tests demonstrate that the ramjet engine used in this report achieves stable combustion and high engine performance, essentially meeting engineering application specifications.

[0195] Table 5 Air ramjet direct connection test performance

[0196]

[0197]

[0198] (3) Water ramjet engine demonstration test (i.e., test of water ramjet gas generator 31 and solid ramjet gas generator 32 in series)

[0199] A ground-based direct-connection test of the proposed water ramjet was conducted using a test system provided by the National University of Defense Technology's Hypersonic Key Laboratory. The test used a boron-based propellant with a boron content of 33%, and preheated water using a water heater. The test parameters are shown in Table 6.

[0200] Table 6 Air ramjet direct-connection test condition parameter settings

[0201]

[0202] Two tests were conducted, each with different water inlet configurations: Test A used a double water inlet configuration, and Test B used a single water inlet configuration. The engine tail flames during the tests are shown in Figures 26(a) and 26(b). It can be seen that the test water ramjet was able to ignite in both tests. The primary gas produced by the combustion of the boron-based propellant was able to mix and burn with water in the afterburner. A distinct green glow was visible at the edge of the tail flame, indicating that the primary gas was not fully burned in the afterburner. The tail flame brightness was also similar in the two configurations.

[0203] The data collected during the test are further used to analyze the engine performance. During the test, the combustion chamber pressure data and step thrust numbers are as follows: Figure 27 、 Figure 28 The test data shows that the water ramjet operated stably, with both the afterburner pressure and engine thrust remaining relatively stable, indicating stable combustion and reliable operation. Furthermore, it is evident that the afterburner pressure and bench thrust of Test A were significantly better than those of Test B, indicating that double water injection is more conducive to primary combustion than single water injection.

[0204] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail, it should be understood that they can be implemented by adopting general devices and methods available in the art.

[0205] The above description is merely one embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A boron-based ramjet-propelled trans-medium aircraft, characterized in that: include: Cavitation device (1), auxiliary compartment (2), gas generating device (3), separation device (4), booster compartment (5) and guidance device (6); The cavitation device (1), the auxiliary compartment (2), the gas generating device (3), the separation device (4) and the booster compartment (5) are coaxially arranged with each other; wherein the cavitation device (1) is connected to the head of the auxiliary compartment (2), the gas generating device (3) is connected to the tail of the auxiliary compartment (2), the separation device (4) is detachably connected to the tail of the gas generating device (3), and the booster compartment (5) is connected to the tail of the separation device (4); The guiding 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); The auxiliary compartment (2) and the gas generating device (3) are located in the same cylindrical outer shell (8); The gas generating device (3) is filled with a boron-based solid propellant; The booster compartment (5) is filled with a propellant; When the boron-based ramjet-propelled trans-medium aircraft switches from air flight to water navigation, the separation device (4) and the booster compartment (5) are separated from the gas generating device (3); The gas generating device (3) comprises: a water-ramming gas generator (31), a solid-ramming gas generator (32), and a first tail nozzle (33) which are coaxially arranged in sequence; The solid-fuel gas generator (32) comprises: a second hollow container (321) for filling the boron-based solid propellant; The cavitation device (1) comprises: a conical cavitator (11), a flow guide bowl structure (12) coaxially connected to the conical cavitator (11), a flow control device (13) connected to the flow guide bowl structure (12), and a gas-liquid transmission component (14) connected to the flow control device (13); The gas-liquid transmission component (14) is in communication with the second hollow container (321); The flow control device (13) is located in the cylindrical housing (8), and the flow control device (13) is provided on the front side of the auxiliary compartment (2); The conical cavitator (11) comprises: a cone cap portion (111), a cone bottom portion (112) and a middle partition (113); The large diameter end of the cone cap portion (111) is fixedly connected to the cone bottom portion (112); The middle partition (113) and the cone bottom portion (112) are arranged in the cone cap portion (111) with a gap therebetween, and are used to enclose a mounting cavity for mounting the guide device (6) between the middle partition (113) and the cone cap portion (111), and to enclose a water inlet cavity between the middle partition (113) and the cone bottom portion (112); A plurality of water inlets (111a) for communicating with the water inlet cavity are provided at intervals on the cone cap portion (111) between the middle partition (113) and the cone bottom portion (112); A water outlet (112a) for communicating with the water inlet cavity is provided at the center of the cone bottom portion (112).

2. The boron-based ramjet-propelled trans-medium aircraft according to claim 1, characterized in that: The boron-based ramjet-propelled trans-medium aircraft includes the following stages during its flight: a boost phase, a cruise phase, and a glide phase. When in the boosting stage, the boosting compartment (5) burns the propellant to provide power; When in the cruise phase, the gas generating device (3) burns part of the boron-based solid propellant to generate primary gas, and the primary gas is mixed with the air introduced into the booster compartment (5) and then provides power after secondary combustion; When in the cruising stage, the gas generating device (3) is shut down; During 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 is mixed with the introduced water in the gas generator (3) to react and provide power.

3. The boron-based ramjet-propelled trans-medium aircraft according to claim 2, characterized in that: The separation device (4) is connected to the end of the cylindrical shell (8) using an explosive bolt; The separation device (4) comprises: an annular hollow body and a signal generator arranged in the hollow body; The signal generator is connected to the explosive bolt.

4. The boron-based ramjet-propelled trans-medium aircraft according to claim 3, characterized in that: The auxiliary compartment (2) comprises: a warhead (21) and a power supply (22) coaxially arranged in sequence; The first tail nozzle (33) is provided with a first flow regulating valve (331); The water ram gas generator (31) comprises: 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); 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-impact gas generator (32) further includes: a second igniter (322), a plurality of foldable tail wing devices (323) arranged outside the second hollow container (321); The head of the second hollow container (321) is connected to the middle nozzle (313), and the tail of the second hollow container (321) is connected to the first tail nozzle (33); The foldable tail wing 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); An opening is provided on the side wall of the cylindrical shell (8) corresponding to the foldable tail wing device (323).

5. The boron-based ramjet-propelled trans-medium aircraft according to claim 4, characterized in that: The diversion bowl structure (12) comprises: a connecting body (121) and a plurality of bowl-shaped diversion parts (122); Along the axial direction of the connecting body (121), a plurality of the bowl-shaped flow-guiding portions (122) are arranged at intervals; 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 two opposite ends thereof; The air outlet cavity (121b) and the water inlet flow channel (121a) are 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; An air outlet hole (121c) for communicating with the air outlet cavity (121b) is provided 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 provided at the axial rear end of the connecting body (121); The radial dimensions of the adjacent bowl-shaped flow guide portions (122) are arranged to increase in sequence in a direction away from the conical cavitator (11), and the bowl-shaped flow guide portions (122) and the air outlet holes (121c) are arranged alternately in sequence.

6. The boron-based ramjet-propelled trans-medium aircraft according to claim 5, characterized in that: The flow control device (13) comprises: a first mounting housing (131), a second mounting housing (132), a water flow control unit (133) and a cavitation gas flow control unit (134); The first mounting shell (131) is in the form of a hollow cone as a whole, with a small diameter end having a connection opening (131a), and a large diameter end being provided with an air inlet connection port (131b) and a water outlet connection port (131c); The second mounting shell (132) is an axisymmetric hollow structure, and is coaxially arranged with the first mounting shell (131) inside the first mounting shell (131), with one end being a shell fixed end fixedly connected to the bottom of the first mounting shell (131), and the other end being a shell docking end; The first mounting shell (131) and the second mounting shell (132) enclose a first mounting cavity for mounting the cavitation gas flow control unit (134); The hollow portion of the second mounting shell (132) forms a second mounting cavity for mounting the water flow control unit (133); The shell docking end of the second mounting shell (132) is provided with a water inlet docking opening, and the water inlet docking opening is provided beyond the connection opening (131a); The fixed end of the second installation shell (132) is provided with a connection channel for connecting the second installation cavity and the water outlet connection port (131c); The shell docking end of the second mounting shell (132) is coaxial with the connecting opening (131a) and is spaced apart, and an air outlet docking opening communicating with the first mounting cavity is formed between the shell docking end and the connecting opening (131a), and the first mounting cavity is communicated with the air inlet connecting port (131b).

7. The boron-based ramjet-propelled trans-medium aircraft according to claim 6, characterized in that: The gas-liquid transmission assembly (14) comprises: an air guide pipe (141), a water guide pipe (142), a heat exchanger (143), an air guide pipe (144), and a water delivery pipe (145); 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-impact 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); 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-impact gas generator (32); wherein an atomizing nozzle is provided at the end of the water pipe (145) connected to the second hollow container (321).

8. The boron-based ramjet-propelled trans-medium aircraft according to claim 7, characterized in that: The heat exchanger (143) is provided between the water ramming gas generator (31) and the solid ramming gas generator (32); The heat exchanger (143) comprises: 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 is provided with a gas collecting cavity structure for connecting the spiral heat exchange tube (1432) at both axial ends thereof, and a heat exchanger water inlet (143a) and a heat exchanger water outlet (143b) for communicating with the hollow portion of the heat exchanger shell (1431) are provided at both axial ends of the heat exchanger shell (1431), as well as a heat exchanger air inlet (143c) and a heat exchanger air outlet (143d) for communicating with the gas collecting cavity structure. The water inlet (143a) of the heat exchanger is connected to the water pipe (142), and the water outlet (143b) of the heat exchanger 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 booster compartment (5) comprises: a booster compartment body (51), a plurality of air inlet structures (52) and a plurality of tail fin assemblies (53) arranged on the outer side of the booster compartment body (51); The booster compartment body (51) comprises a coaxially connected combustion chamber (511) and a tail nozzle (512); The length of the air inlet structure (52) is consistent with the axial length of the booster compartment body (51). The air intake duct structure (52) is provided with an air intake duct (521) for connecting the combustion chamber (511) with the outside, and a switch mechanism provided corresponding to the air intake duct (521); Along the axial direction of the booster compartment body (51), the air inlet (521) is arranged adjacent to the front end of the booster compartment body (51); 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).

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