A metal-based gel propellant detonation engine

Abstract

The present invention belongs to the field of detonation engines, and specifically relates to a metal-based gel propellant detonation engine, comprising an air inlet, a rotating detonation combustion chamber, and a propellant supply system; the propellant supply system comprises a gel propellant tank disposed within a central cylinder, a gel propulsion structure connected to the gel propellant tank, and an atomizing nozzle, the atomizing nozzle being mounted on the propellant injection structure; the propellant supply system also comprises an atomizing gas tank disposed within the combustion chamber cylinder, the atomizing gas tank being connected to the atomizing nozzle via an atomizing gas delivery channel. The present invention proposes the application of metal-based gel propellant to a rotating detonation engine, which has an energy density superior to that of existing gas and liquid propellant rotating detonation engines, is highly safe, and has controllable thrust output. Furthermore, the propellant supply system does not occupy any space outside the engine, achieving a highly effective gel propellant rotating detonation engine without increasing the engine size.

Description

Technical Field

[0001] The invention belongs to the field of detonation engines, and in particular relates to a metal-based gel propellant detonation engine. Background Art

[0002] A ramjet is a jet engine that relies on the deceleration and supercharging of a high-speed oncoming airflow. Its simple construction and low cost make it suitable for high-speed, long-range aircraft. However, ramjets are sensitive to changes in flight conditions. When flight speeds fall below their design point, their performance rapidly deteriorates, limiting their operating range. A rotating detonation engine, a novel engine that generates thrust by continuously rotating a detonation wave within an annular combustion chamber, generates greater effective power at lower pressures due to the detonation wave's self-sustaining and self-pressurizing properties, significantly expanding the ramjet's flight envelope. Furthermore, detonation combustion offers a rapid energy release rate and high thermal cycle efficiency, making it of great significance for the further development of aircraft propulsion.

[0003] Currently, most research on rotating detonation engines, both domestically and internationally, uses gas or liquid propellants. Due to their relatively low volumetric calorific value, these propellants limit their flight range when the vehicle is limited, hindering their further development. Gel propellants, a new type of fuel that uses a gelling agent to gel liquid propellants, can maintain long-term stability. They combine the controllable thrust output of gas and liquid propellants with the ease of storage and transportation of solid propellants. Adding metal powders, such as boron, magnesium, and aluminum, to gel propellants to create metal-based gel propellants can significantly increase their energy density, making them promising for applications in detonation combustion. However, metal-based gel propellants also have high apparent viscosity, making them prone to agglomeration and clogging during actual use, making stable supply difficult. Furthermore, due to the presence of an oxide layer on the surface of most metal powders, ignition and combustion are slow, making detonation initiation of metal-based gel propellants difficult. Therefore, metal-based gel propellants have not yet been applied to rotating detonation engines. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a metal-based gel propellant detonation engine which can achieve a high detonation success rate and sufficient combustion without increasing the size of the engine.

[0005] The present invention provides a metal-based gel propellant detonation engine, comprising an air inlet, a rotating detonation combustion chamber and a propellant supply system;

[0006] The air intake passage comprises a cylindrical engine casing and a central cylinder arranged in the engine casing, wherein the inner wall of the engine casing and the outer wall of the central cylinder enclose an annular air intake passage;

[0007] The rotating detonation combustion chamber includes a combustion chamber cylinder disposed in the engine casing and downstream of the central cylinder, wherein the inner wall of the engine casing and the outer wall of the combustion chamber cylinder enclose an annular rotating detonation combustion channel;

[0008] A step ring is provided at the connection between the central cylinder and the combustion chamber cylinder, a step is formed between the annular air inlet channel and the annular rotating detonation combustion channel, and a propellant injection structure is provided on the step ring;

[0009] The propellant supply system includes a propellant supply part and an atomizing gas supply part. The propellant supply part includes a gel propellant tank arranged in the central cylinder, a gel propulsion structure connected to the gel propellant tank, and an atomizing nozzle. The gel propulsion structure is used to propel the gel propellant in the gel propellant tank into the atomizing nozzle. The atomizing nozzle is installed on the propellant injection structure. The atomizing gas supply part includes an atomizing gas tank arranged in the combustion chamber cylinder. The atomizing gas tank is connected to the atomizing nozzle through an atomizing gas delivery channel to provide atomizing gas to the atomizing nozzle. The inner wall of the combustion chamber cylinder is part of the atomizing gas delivery channel.

[0010] Furthermore, a portion of the atomizing gas delivery channel is arranged along the downstream end to the upstream end of the combustion chamber cylinder.

[0011] Furthermore, the atomizing gas stored in the atomizing gas storage tank is a combustible gas.

[0012] Furthermore, the propulsion structure includes a piston arranged on a side of the gel propellant tank away from the atomizing nozzle and a linear drive mechanism for driving the piston to move.

[0013] Furthermore, the propellant injection structure includes a plurality of propellant injection ports arranged in a ring array along the step ring;

[0014] A plurality of atomizing nozzles are provided, and correspond one to one with the propellant injection ports.

[0015] Furthermore, a propellant valve is provided between the gel propellant tank and the atomizing nozzle;

[0016] The atomizing gas delivery channel is provided with an atomizing gas valve and a one-way valve.

[0017] Furthermore, it also includes an auxiliary ignition system, which injects combustible gas into the annular air intake passage.

[0018] Furthermore, the auxiliary ignition system includes a combustible gas intake pipe tangentially connected to the annular intake channel.

[0019] Furthermore, the combustible gas inlet pipe is arranged at the tail end of the annular inlet channel.

[0020] The beneficial effects of the present invention are:

[0021] 1. The present invention can use gel propellant and proposes the application of metal-based gel propellant to a rotating detonation engine. By designing a propellant supply system, the rotating detonation engine can stably and reliably use metal-based gel propellant, providing a new path for the development of rotating detonation engines. The use of metal-based gel propellant has an energy density superior to that of existing gas and liquid propellant rotating detonation engines, and is highly safe and has controllable thrust output.

[0022] Second, the propellant supply system's propellant supply and atomizing gas supply are located within the central cylinder and combustion chamber cylinder, respectively, completely eliminating the need for space in the annular air intake and rotating detonation combustion channels. This ensures efficient and effective air intake and detonation combustion. Furthermore, compared to conventional engines employing solid or hollow cylinders for the central cylinder and combustion chamber, this improves engine space utilization, effectively utilizing the space within the engine and achieving a highly effective gel propellant rotating detonation engine without significantly increasing engine size.

[0023] Third, the structural arrangement of the annular air inlet channel, annular rotating detonation combustion channel, and its step ring of the present invention: air flows from the upstream of the annular air inlet channel to the downstream, and finally enters the annular rotating detonation combustion channel through the step ring. The propellant injection structure on the step ring continuously injects propellant into the annular rotating detonation combustion channel, causing the air and propellant to mix. After ignition, a continuous rotating detonation wave is formed in the annular rotating detonation combustion channel, and finally ejected from the downstream of the annular rotating detonation combustion channel to generate thrust. On the one hand, the air flow forms a vortex when passing through the step ring. The vortex not only helps to form a stable flame and stay at this location, thereby facilitating the continuous ignition of the subsequently injected propellant, acting as a flame stabilizer, but also improves the mixing of air and propellant. The combined effect of these two factors facilitates the detonation and complete combustion of the subsequently injected metal-based gel propellant. On the other hand, the propellant injection structure is directly located at the starting end of the annular rotating detonation combustion channel and separated from the annular air inlet channel. This not only avoids affecting the inflow of air flow, but also allows for the rapid replenishment of fresh gel propellant to the detonation location, ensuring the stability of the continuous rotating detonation.

[0024] Fourth, the inner wall of the combustion chamber cylinder forms part of the atomizing gas delivery channel. Specifically, the atomizing gas within the atomizing gas tank flows through the inner wall of the combustion chamber cylinder into the atomizing nozzle. Before entering the atomizing nozzle for atomization, the atomizing gas can exchange heat with the combustion chamber cylinder, cooling the high-temperature combustion chamber cylinder and thus protecting it. Furthermore, the heated atomizing gas can promote the evaporation of the kerosene in the gel propellant, achieving both better atomization and enhanced combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0026] Figure 2 Schematic diagram of the structure of the gel propellant supply system of the present invention;

[0027] Figure 3 This is a radial cross-sectional view of the auxiliary ignition system of the present invention;

[0028] Figure 4 Schematic diagram of the overall structure of the engine when storing combustible gas in the atomized gas storage tank in the embodiment of the present invention.

[0029] In the figure, 1-inlet duct; 101-engine casing; 102-center body cone section; 103-center cylinder; 104-annular inlet channel; 2-propellant supply system; 201-linear drive mechanism; 202-piston; 203-gel propellant tank; 204-propellant valve; 205-atomizing nozzle; 206-one-way valve; 207-atomizing gas tank; 208-atomizing gas valve; 209-atomizing gas delivery channel; 3-auxiliary ignition system; 301-combustible gas tank; 302-combustible gas valve; 303-combustible gas inlet pipe; 4-rotating detonation combustion chamber; 401-propellant injection port; 402-combustion chamber cylinder; 403-annular rotating detonation combustion channel; 404-step ring; 5-tail nozzle; 501-plug nozzle. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In the description of the present invention, “several” means at least two, such as two, three, etc., unless otherwise clearly defined.

[0033] In the present invention, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can mean fixed connection, detachable connection, or integration; it can mean mechanical connection, electrical connection, physical connection, or wireless communication connection; it can mean direct connection or indirect connection through an intermediate medium; it can mean internal communication between two elements or interaction between two elements, unless otherwise specified. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in this field can implement it. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0035] As attached Figure 1 -Attached Figure 4 As shown, the present invention provides a metal-based gel propellant detonation engine, comprising an air inlet 1, a rotating detonation combustion chamber 4 and a propellant supply system 2;

[0036] The air intake duct 1 includes a cylindrical engine housing 101 and a central cylinder 103 disposed in the engine housing 101. The inner wall of the engine housing 101 and the outer wall of the central cylinder 103 enclose an annular air intake passage 104.

[0037] The rotating detonation combustion chamber 4 includes a combustion chamber cylinder 402 disposed in the engine housing 101 and downstream of the central cylinder 103. The inner wall of the engine housing 101 and the outer wall of the combustion chamber cylinder 402 enclose an annular rotating detonation combustion channel 403.

[0038] A step ring 404 is provided at the connection between the central cylinder 103 and the combustion chamber cylinder 402, and a step is formed between the annular air inlet channel 104 and the annular rotating detonation combustion channel 403, that is, the inner diameter of the annular air inlet channel 104 is larger than the inner diameter of the annular rotating detonation combustion channel 403, that is, the volume of the annular air inlet channel 104 is smaller than the volume of the annular rotating detonation combustion channel 403. At this time, there will be a step at the connection between the annular air inlet channel 104 and the annular rotating detonation combustion channel 403, and a step ring 404 is provided at the connection between the annular air inlet channel 104 and the annular rotating detonation combustion channel 403. The step ring 404 connects and transitions the annular air inlet channel 104 and the annular rotating detonation combustion channel 403, and a propellant injection structure is provided on the step ring 404. The propellant injection structure is used to inject propellant into the annular rotating detonation combustion channel 403 at the position of the step ring 404;

[0039] The propellant supply system 2 includes a propellant supply portion and an atomizing gas supply portion. The propellant supply portion includes a gel propellant tank 203 disposed within the central cylinder 103, a gel propulsion structure connected to the gel propellant tank 203, and an atomizing nozzle 205. The gel propulsion structure is used to propel the gel propellant within the gel propellant tank 203 into the atomizing nozzle 205. The atomizing nozzle 205 is mounted on the propellant injection structure. The gel propellant supply portion of the propellant supply system 2 is disposed within the central cylinder 103, completely eliminating space in the annular air inlet passage 104, thereby ensuring air intake efficiency and effectiveness. Furthermore, compared to a solid or hollow cylinder in the position of the center cylinder 103 in conventional engines, this improves the utilization rate of the space within the engine and effectively utilizes the space in the engine. The atomizing gas supply unit includes an atomizing gas tank 207 disposed within the combustion chamber cylinder 402. The atomizing gas tank 207 is connected to the atomizing nozzle 205 via an atomizing gas delivery channel 209, providing atomizing gas to the atomizing nozzle 205. Positioning the atomizing gas supply unit in the propellant supply system 2 within the combustion chamber cylinder 402 completely eliminates the space in the annular rotating detonation combustion channel 403, ensuring the efficiency and effectiveness of the detonation wave combustion. Similarly, compared to a solid or hollow cylinder in the position of the conventional combustion chamber cylinder 402, this improves the utilization rate of the space within the engine and effectively utilizes the space in the engine.

[0040] The inner wall of the combustion chamber cylinder 402 forms part of the atomizing gas delivery channel 209. Specifically, the atomizing gas within the atomizing gas storage tank 207 flows through the inner wall of the combustion chamber cylinder 402 into the atomizing nozzle 205. Before entering the atomizing nozzle 205 for atomization, the atomizing gas can exchange heat with the combustion chamber cylinder 402, cooling the combustion chamber cylinder 402 as it gradually rises in temperature due to the continuously rotating detonation wave. This protects the combustion chamber cylinder 402, and the heated atomizing gas can also promote the evaporation of kerosene in the gel propellant, thereby achieving a better atomization effect and promoting combustion.

[0041] The beneficial effects of the present invention are:

[0042] 1. The present invention can use gel propellant and proposes the application of metal-based gel propellant to a rotating detonation engine. By designing a propellant supply system, the rotating detonation engine can stably and reliably use metal-based gel propellant, providing a new path for the development of rotating detonation engines. The use of metal-based gel propellant has an energy density superior to that of existing gas and liquid propellant rotating detonation engines, and is highly safe and has controllable thrust output.

[0043] Second, the propellant supply system's propellant supply and atomizing gas supply components are located within central cylinder 103 and combustion chamber cylinder 402, respectively, completely eliminating the space in annular air intake passage 104 and annular rotating detonation combustion passage 403. This ensures efficient and effective air intake and detonation wave combustion. Furthermore, compared to conventional engines employing solid or hollow cylinders within central cylinder 103 and combustion chamber cylinder 402, this improves engine space utilization and effectively utilizes engine space, achieving a highly effective gel propellant rotating detonation engine without significantly increasing engine size.

[0044] 3. The structural arrangement of the annular air inlet channel 104, the annular rotating detonation combustion channel 403, and its step ring 404 of the present invention: air flows from the upstream of the annular air inlet channel 104 to the downstream, and finally enters the annular rotating detonation combustion channel 403 through the step ring 404. The propellant injection structure on the step ring 404 continuously injects propellant into the annular rotating detonation combustion channel 403, causing the air and propellant to mix. After ignition, a continuous rotating detonation wave is formed within the annular rotating detonation combustion channel 403, and finally ejected from the downstream of the annular rotating detonation combustion channel 403 to generate thrust. On the one hand, the air flow forms a vortex when passing through the step ring 404. The vortex not only helps form a stable flame that resides at this location, thereby facilitating the continuous ignition of subsequently injected propellant and acting as a flame stabilizer, but also improves the mixing of air and propellant. The combined effect of these two factors facilitates the detonation and complete combustion of the subsequently injected metal-based gel propellant. On the other hand, the propellant injection structure is directly arranged at the starting end of the annular rotating detonation combustion channel 403 and is separated from the annular air inlet channel 104. This can not only avoid affecting the inflow of air flow, but also quickly replenish fresh gel propellant to the detonation position to ensure the stability of continuous rotating detonation.

[0045] Fourth, the inner wall of the combustion chamber cylinder forms part of the atomizing gas delivery channel. Specifically, the atomizing gas within the atomizing gas tank flows through the inner wall of the combustion chamber cylinder into the atomizing nozzle. Before entering the atomizing nozzle for atomization, the atomizing gas can exchange heat with the combustion chamber cylinder, cooling the high-temperature combustion chamber cylinder and thus protecting it. Furthermore, the heated atomizing gas can promote the evaporation of the kerosene in the gel propellant, achieving both better atomization and enhanced combustion.

[0046] In one embodiment, the atomizing gas delivery channel 209 is led out from the end of the atomizing gas storage tank 207 facing away from the central cylinder 103 and splits. It is then arranged from downstream to upstream of the combustion chamber cylinder 402, forming a countercurrent heat exchange structure that can improve the cooling effect on the central cylinder 103 and the heating effect on the atomizing gas. Furthermore, after the atomizing gas delivery channel 209 is split, multiple atomizing gas delivery channels 209 can be provided, and the number of atomizing gas delivery channels 209 matches and corresponds to the number of atomizing nozzles 205. Furthermore, multiple atomizing gas delivery channels 209 are arranged in close contact with the inner wall of the combustion chamber cylinder 402.

[0047] In one embodiment, a portion of the atomizing gas delivery channel 209 is arranged along the downstream end to the upstream end of the combustion chamber cylinder 402. On the one hand, the atomizing gas delivery channel 209 enables heat exchange to the entire axial direction of the combustion chamber cylinder 402, thereby improving the heat exchange effect. On the other hand, a countercurrent heat exchange structure can also be formed to improve the cooling effect on the central cylinder 103 and the heating effect on the atomizing gas.

[0048] The atomizing gas stored in the atomizing gas storage tank 207 may be air, which is only used to atomize the gel propellant. In a preferred embodiment, the atomizing gas stored in the atomizing gas storage tank 207 is a combustible gas, such as hydrogen. The combustible gas can be used to atomize the gel propellant and increase the combustion effect of the gel propellant.

[0049] In one embodiment, the propulsion structure includes a piston 202 disposed on the side of the gel propellant tank 203 facing away from the atomizing nozzle 205, and a linear drive mechanism 201 for driving the piston 202. The linear drive mechanism 201 can be a linear motor, a pneumatic cylinder, or a hydraulic cylinder. This configuration allows the linear drive mechanism 201 to precisely control the movement of the piston 202, thereby adjusting the gel propellant supply and regulating the engine thrust, taking into account the high surface viscosity of the metal-based gel propellant.

[0050] In one embodiment, the propellant injection structure includes a plurality of propellant injection ports 401 arranged in an annular array along a step ring 404; a plurality of atomizing nozzles 205 are provided, each corresponding one-to-one with the propellant injection ports 401. In this embodiment, the atomizing nozzles 205 are embedded in the propellant injection ports 401, allowing the atomizing nozzles 205 to directly act on the annular rotating detonation combustion channel 403. The use of a plurality of atomizing nozzles 205 arranged in an annular array ensures sufficient and uniform injection of propellant into the annular rotating detonation combustion channel 403.

[0051] In one embodiment, a propellant valve 204 is provided between the gel propellant tank 203 and the atomizing nozzle 205 to thereby realize opening and closing of the gel propellant tank 203 and the atomizing nozzle 205;

[0052] The atomizing gas delivery channel 209 is provided with an atomizing gas valve 208 and a one-way valve 206. Preferably, the atomizing gas valve 208 is provided at the position before the atomizing gas delivery channel 209 is split, and then all pipelines after the split are controlled by a single atomizing gas valve 208 to open and close the atomizing gas storage tank 207; a one-way valve 206 can be provided on each atomizing gas delivery channel 209 after the split to prevent the atomizing gas from flowing back and ensure the atomization effect.

[0053] In one embodiment, the present invention further includes an auxiliary ignition system 3, which injects combustible gas into the annular air inlet passage 104. Furthermore, the initial atomized combustible gas can be activated by a spark plug to trigger engine ignition, achieving stable atomization and efficient detonation of the metal-based gel propellant. This arrangement allows combustion gas to enter the annular air inlet passage 104 and mix with the incoming air. This mixing then occurs in front of the annular rotating detonation combustion passage 403, where it ignites, releasing significant energy and detonating the metal-based gel propellant. This resolves the difficulty in igniting and burning the metal-based gel propellant.

[0054] In one preferred embodiment, the auxiliary ignition system 3 comprises a combustible gas storage tank 301 and a combustible gas inlet pipe 303 , wherein a combustible gas valve 302 is provided on the combustible gas inlet pipe 303 .

[0055] In one embodiment, the auxiliary ignition system 3 includes a combustible gas intake pipe 303 tangentially connected to the annular intake channel 104. In this embodiment, the combustion gas enters the annular intake channel 104 tangentially, which can improve the mixing effect with the incoming air on the one hand, and on the other hand, it can also improve the rotation effect of the incoming air, which helps the rotation of the detonation wave.

[0056] In one embodiment, the combustible gas inlet pipe 303 is arranged at the tail end of the annular inlet channel 104, so that the ignition position has a higher combustible gas concentration, ensuring that the auxiliary ignition system improves combustion.

[0057] In one embodiment, a center cone section 102 is provided at the upper end of the center cylinder 103, and the upstream end of the engine casing 101 is also provided with a trumpet structure corresponding to the center cone section 102. A tail nozzle 5 is provided downstream of the rotating detonation combustion chamber 4 and consists of the engine casing 101 and a plug nozzle 501.

[0058] The present invention provides three specific embodiments:

[0059] Example 1, refer to the attached Figure 1 The atomized gas tank 207 in the metal-based gel propellant detonation engine stores air and is equipped with an auxiliary ignition system 3

[0060] The specific working process of Example 1 is:

[0061] S1. Before the metal-based gel propellant rotating detonation engine operates, gel propellant tank 203 stores metal-based gel propellant, atomizing gas tank 207 stores air, and combustible gas tank 301 stores hydrogen. Propellant valve 204, atomizing gas valve 208, and combustible gas valve 302 are all closed.

[0062] S2. When the metal-based gel propellant rotating detonation engine is started, air enters annular inlet passage 104 through intake duct 1. Atomizing gas valve 208 opens to begin supplying atomizing gas. Propellant valve 204 opens, and linear drive mechanism 201 activates, pushing piston 202 to begin supplying metal-based gel propellant. Atomizing gas impacts the metal-based gel propellant within atomizing nozzle 205. The atomized gel propellant is then sprayed through step ring 404 into annular rotating detonation combustion passage 403.

[0063] S3. When the metal-based gel propellant rotating detonation engine begins ignition, the combustible gas valve 302 opens, and hydrogen is injected tangentially into the annular inlet passage 104 to mix with the incoming air. The mixed hydrogen and air enter the annular rotating detonation combustion passage 403 and are ignited by a spark plug. The hydrogen explosion generates enormous energy, detonating the atomized metal-based gel propellant. The metal-based gel propellant at the detonation location is consumed, and the detonation wave moves along the wall of the rotating detonation combustion chamber 4 to the next propellant injection port 401, which is arranged along the stepped ring 404. Fresh gel propellant is then rapidly replenished at the detonation location, resulting in continuous rotating detonation.

[0064] S4. During the operation of the metal-based gel propellant rotating detonation engine, the detonation wave continuously rotates along the outer wall of the combustion chamber cylinder 402. After the energy in the metal-based gel propellant is fully released, the high-temperature and high-pressure combustion gas is ejected through the tail nozzle 5 to generate thrust.

[0065] During the continuous propulsion process, the continuously rotating detonation wave will gradually increase the temperature of the combustion chamber cylinder 402. At this time, the atomized gas supplied close to the inner wall of the combustion chamber cylinder 402 can take away some of the heat and protect the combustion chamber cylinder 402. At the same time, the heated atomized gas is more conducive to atomizing the metal-based gel propellant and promoting combustion.

[0066] A step ring 404 is provided between the annular air inlet channel 104 and the annular rotating detonation combustion channel 403. After the external air enters the annular rotating detonation combustion channel 403 through the annular air inlet channel 104, a vortex is formed at the step. The step acts as a flame stabilizer, which is beneficial to the detonation and full combustion of the subsequently injected metal-based gel propellant.

[0067] Example 2, refer to the attached Figure 4 The atomized gas tank 207 in the metal-based gel propellant detonation engine stores combustible gas and is not equipped with an auxiliary ignition system 3;

[0068] The specific working process of this embodiment is basically the same as that of the first embodiment, except that:

[0069] Atomizing gas tank 207 stores hydrogen, and no auxiliary ignition system is provided. When the metal-based gel propellant rotating detonation engine begins operation, air enters the annular inlet passage 104 through the inlet duct 1. Atomizing gas valve 208 opens to begin hydrogen supply. Propellant valve 204 opens, and linear drive mechanism 201 activates, pushing piston 202 to begin supplying metal-based gel propellant. Hydrogen impacts and shears the metal-based gel propellant within atomizing nozzle 205. The atomized gel propellant is then sprayed into the annular rotating detonation combustion passage 403. Spark plug ignition initiates the detonation, and the detonation wave moves to the next propellant injection port 401, arranged along the stepped rotational path. Fresh gel propellant is rapidly replenished at the original detonation location, resulting in continuous rotating detonation. Finally, high-temperature, high-pressure combustion gas is ejected through tail nozzle 5 to generate thrust.

[0070] In the third embodiment, the atomized gas tank 207 in the metal-based gel propellant detonation engine stores combustible gas and is equipped with an auxiliary ignition system 3;

[0071] The specific working process of this embodiment is basically the same as that of the first embodiment, except that:

[0072] The atomizing gas storage tank 207 stores hydrogen, so the atomizing propellant sprayed from the atomizing nozzle 205 contains hydrogen, which can improve the combustion effect.

[0073] The above description is merely an embodiment and does not limit the present invention in any way. Any person skilled in the art can, without departing from the scope of the technical solution of the present invention, make many possible changes, modifications, or modifications to the technical solution of the present invention into equivalent embodiments with equivalent changes using the technical content disclosed above. Therefore, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the scope of protection of the technical solution of the present invention.

Claims

1. A metal-based gel propellant detonation engine, characterized in that: It includes an air inlet (1), a rotating detonation combustion chamber (4) and a propellant supply system (2); The air intake duct (1) comprises a cylindrical engine housing (101) and a central cylinder (103) arranged in the engine housing (101), wherein the inner wall of the engine housing (101) and the outer wall of the central cylinder (103) enclose an annular air intake passage (104); The rotating detonation combustion chamber (4) includes a combustion chamber cylinder (402) disposed in the engine housing (101) and located downstream of the central cylinder (103), wherein the inner wall of the engine housing (101) and the outer wall of the combustion chamber cylinder (402) enclose an annular rotating detonation combustion channel (403); A step ring (404) is provided at the connection between the central cylinder (103) and the combustion chamber cylinder (402), a step is formed between the annular air inlet channel (104) and the annular rotating detonation combustion channel (403), and a propellant injection structure is provided on the step ring (404); The propellant supply system (2) includes a propellant supply part and an atomizing gas supply part. The propellant supply part includes a gel propellant tank (203) arranged in the central cylinder (103), a gel propulsion structure connected to the gel propellant tank (203), and an atomizing nozzle (205). The gel propulsion structure is used to propel the gel propellant in the gel propellant tank (203) into the atomizing nozzle (205). The atomizing nozzle (205) is installed on the propellant injection structure. The atomizing gas supply part includes an atomizing gas tank (207) arranged in the combustion chamber cylinder (402). The atomizing gas tank (207) is connected to the atomizing nozzle (205) through an atomizing gas delivery channel (209) to provide atomizing gas to the atomizing nozzle (205). The inner wall of the combustion chamber cylinder (402) is part of the atomizing gas delivery channel (209).

2. The metal-based gel propellant detonation engine according to claim 1, wherein: A portion of the atomizing gas delivery channel (209) is arranged along the downstream end to the upstream end of the combustion chamber cylinder (402).

3. The metal-based gel propellant detonation engine according to claim 1, wherein: The atomizing gas stored in the atomizing gas storage box (207) is a combustible gas.

4. The metal-based gel propellant detonation engine according to claim 1, wherein: The propulsion structure comprises a piston (202) arranged on a side of the gel propellant tank (203) away from the atomizing nozzle (205) and a linear drive mechanism (201) for driving the piston (202) to move.

5. The metal-based gel propellant detonation engine according to claim 1, wherein: The propellant injection structure comprises a plurality of propellant injection ports (401) arranged in a ring array along a step ring (404); A plurality of atomizing nozzles (205) are provided, and correspond one-to-one with the propellant injection ports (401).

6. The metal-based gel propellant detonation engine according to claim 1, wherein: A propellant valve (204) is provided between the gel propellant tank (203) and the atomizing nozzle (205); The atomizing gas delivery channel (209) is provided with an atomizing gas valve (208) and a one-way valve (206).

7. The metal-based gel propellant detonation engine according to any one of claims 1 to 6, characterized in that: It also includes an auxiliary ignition system (3), which injects combustible gas into the annular air inlet passage (104).

8. The metal-based gel propellant detonation engine according to claim 7, wherein: The auxiliary ignition system (3) comprises a combustible gas intake pipe (303) tangentially connected to the annular intake channel (104).

9. The metal-based gel propellant detonation engine according to claim 8, characterized in that: The combustible gas inlet pipe (303) is arranged at the tail end of the annular inlet channel (104).

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