Metal-based gel propellant detonation engine

Abstract

The invention belongs to the field of detonation engines, and particularly relates to a metal-based gel propellant detonation engine which comprises an air inlet channel, a rotary detonation combustion chamber and a propellant supply system. The propellant supply system comprises a gel propellant storage box arranged in the central cylinder, a gel propelling structure connected with the gel propellant storage box and an atomizing nozzle, and the atomizing nozzle is mounted on the propellant injection structure; the propellant supply system further comprises an atomized gas storage box arranged in the combustion chamber cylinder, and the atomized gas storage box is connected with the atomizing nozzle through an atomized gas conveying channel. According to the rotary detonation engine, the metal-based gel propellant is applied to the rotary detonation engine, the energy density is superior to that of an existing gas and liquid propellant rotary detonation engine, safety is high, and thrust output is controllable. And the propellant supply system does not occupy the space outside the engine at all, and the gel propellant rotary detonation engine with a good effect is achieved under the condition that the size of the engine is not additionally increased.

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 effect of high-speed oncoming airflow. It has a simple structure and low cost, and can meet the needs of high-speed and long-range aircraft. However, ramjet engines are sensitive to changes in flight conditions. When the flight speed is lower than the design point, the performance deteriorates rapidly and the working range is limited. A rotating detonation engine is a new type of engine that uses the continuous rotation of detonation waves in an annular combustion chamber to generate thrust. Due to the self-sustaining and self-pressurizing characteristics of detonation waves, it can generate greater effective work at lower pressures, greatly broadening the flight envelope of ramjet engines. In addition, the detonation combustion has a fast energy release rate and high thermal cycle efficiency, which is of great significance to the further development of the field of aircraft propulsion.

[0003] At present, most of the research on rotating detonation engines at home and abroad uses gas or liquid propellants. Due to the relatively low volume calorific value of gas or liquid propellants, their flight distance will be limited when the volume of the aircraft is limited, which restricts the further development of rotating detonation engines. Gel propellant is a new type of fuel that uses a gelling agent to gel liquid propellant and can maintain stability for a long time. It has the characteristics of controllable thrust output of gas and liquid propellants, and also has the advantages of easy storage and transportation of solid propellants. Adding metal powders such as boron, magnesium, and aluminum to gel propellants to prepare metal-based gel propellants can significantly improve the energy density, making it have broad prospects for application in detonation combustion. However, metal-based gel propellants also have the characteristics of high apparent viscosity, and are prone to agglomeration and clogging during actual use, making it difficult to achieve stable supply; at the same time, since most metal powders have an oxide layer on the surface, the ignition and combustion speed is slow, and the detonation initiation of metal-based gel propellants is still 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 complete 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 inlet 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 a ring-shaped air inlet passage;

[0007] The rotating detonation combustion chamber comprises a combustion chamber cylinder disposed in the engine casing and located 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 intake 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 for the atomizing nozzle. The inner wall of the combustion chamber cylinder is a 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 box 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 intake passage.

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

[0019] Furthermore, the combustible gas intake pipe is arranged at the rear end of the annular intake passage.

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

[0021] 1. The present invention can adopt gel propellant and proposes to apply metal-based gel propellant to a rotating detonation engine. By designing a propellant supply system, the rotating detonation engine can stably and reliably adopt metal-based gel propellant to work, providing a new way for the development of rotating detonation engines. The use of metal-based gel propellant has better energy density than existing gas and liquid propellant rotating detonation engines, and has high safety and controllable thrust output.

[0022] Second, the propellant supply part and the atomizing gas supply part in the propellant supply system are respectively arranged inside the central cylinder and the combustion chamber cylinder, and the space of the annular air intake channel and the annular rotating detonation combustion channel is completely not occupied, so as to ensure the efficiency and effect of air intake and detonation wave combustion. In addition, compared with the solid cylinder or hollow cylinder at the position of the central cylinder and the combustion chamber cylinder in conventional engines, the space utilization rate in the engine is improved, the space of the engine is reasonably utilized, and a rotating detonation engine with a gel propellant having a good effect is realized without increasing the size of the engine.

[0023] 3. The structural arrangement of the annular air inlet channel, the annular rotating detonation combustion channel and the step ring of the present invention is that the 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, so that the air and the propellant are mixed, and 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 to stay at this position, so as to continuously ignite the subsequent continuously injected propellant, and play the role of a flame stabilizer, but also can improve the mixing of air and propellant. The combined action of the two is conducive to the detonation and full combustion of the metal-based gel propellant injected subsequently. On the other hand, the propellant injection structure is directly arranged at the starting end of the annular rotating detonation combustion channel and is separated from the annular air inlet channel, which can avoid affecting the inflow of the air flow and quickly replenish fresh gel propellant for the detonation position to ensure the stability of continuous rotating detonation.

[0024] Fourth, the inner wall of the combustion chamber cylinder is a part of the atomizing gas delivery channel. That is, the atomizing gas inside the atomizing gas storage box flows into the atomizing nozzle through the inner wall of the combustion chamber cylinder. At this time, before the atomizing gas enters the atomizing nozzle for atomization, it can exchange heat with the combustion chamber cylinder to cool down the high-temperature combustion chamber cylinder, thereby protecting the combustion chamber cylinder. At the same time, the heated atomizing gas can also promote the evaporation of kerosene in the gel propellant, which can achieve a better atomization effect and promote 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 This is a schematic diagram of the structure of the gel propellant supply system of the present invention;

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

[0028] Figure 4 It is a schematic diagram of the overall structure of the engine when the combustible gas is stored in the atomized gas storage tank in the embodiment of the present invention.

[0029] In the figure, 1-intake duct; 101-engine casing; 102-center body cone section; 103-center cylinder; 104-annular intake 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 intake 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 be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are 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 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 and specifically defined.

[0033] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, 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 the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such 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 inlet 1 comprises a cylindrical engine casing 101 and a central cylinder 103 disposed in the engine casing 101, wherein the inner wall of the engine casing 101 and the outer wall of the central cylinder 103 enclose an annular air inlet passage 104;

[0037] The rotating detonation combustion chamber 4 comprises a combustion chamber cylinder 402 disposed in the engine casing 101 and located downstream of the central cylinder 103, and the inner wall of the engine casing 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 passage 104 and the annular rotating detonation combustion passage 403, that is, the inner diameter of the annular air inlet passage 104 is larger than the inner diameter of the annular rotating detonation combustion passage 403, that is, the volume of the annular air inlet passage 104 is smaller than the volume of the annular rotating detonation combustion passage 403. At this time, a step will exist at the connection between the annular air inlet passage 104 and the annular rotating detonation combustion passage 403, and a step ring 404 is provided at the connection between the annular air inlet passage 104 and the annular rotating detonation combustion passage 403. The step ring 404 connects and transitions the annular air inlet passage 104 and the annular rotating detonation combustion passage 403, and a propellant injection structure is provided on the step ring 404, and the propellant injection structure is used to inject propellant into the annular rotating detonation combustion passage 403 at the position of the step ring 404;

[0039] 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 gel propellant supply part in the propellant supply system 2 is arranged in the central cylinder 103, and does not occupy the space of the annular air inlet channel 104 at all, thereby ensuring the air intake efficiency and effect. In addition, compared with the solid cylinder or hollow cylinder at the position of the center cylinder 103 in the conventional engine, the space utilization rate in the engine is improved, and the space of the engine is reasonably utilized. The atomizing gas supply part includes an atomizing gas storage tank 207 arranged in the combustion chamber cylinder 402, and the atomizing gas storage tank 207 is connected to the atomizing nozzle 205 through the atomizing gas delivery channel 209 to provide atomizing gas for the atomizing nozzle 205. The atomizing gas supply part in the propellant supply system 2 is arranged in the combustion chamber cylinder 402, and the space of the annular rotating detonation combustion channel 403 is not occupied at all, so as to ensure the combustion efficiency and effect of the detonation wave. Similarly, compared with the solid cylinder or hollow cylinder at the position of the conventional combustion chamber cylinder 402, the space utilization rate in the engine is improved, and the space of the engine is reasonably utilized.

[0040] The inner wall of the combustion chamber cylinder 402 is a part of the atomizing gas delivery channel 209. That is, the atomizing gas inside the atomizing gas storage box 207 flows into the atomizing nozzle 205 through the inner wall of the combustion chamber cylinder 402. At this time, the atomizing gas can exchange heat with the combustion chamber cylinder 402 before entering the atomizing nozzle 205 for atomization, and the temperature of the combustion chamber cylinder 402 gradually increases due to the continuously rotating detonation wave, thereby protecting the combustion chamber cylinder 402. At the same time, the heated atomizing gas can also promote the evaporation of kerosene in the gel propellant, which can achieve a better atomization effect and promote combustion.

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

[0042] 1. The present invention can adopt gel propellant and proposes to apply metal-based gel propellant to a rotating detonation engine. By designing a propellant supply system, the rotating detonation engine can stably and reliably adopt metal-based gel propellant to work, providing a new way for the development of rotating detonation engines. The use of metal-based gel propellant has better energy density than existing gas and liquid propellant rotating detonation engines, and has high safety and controllable thrust output.

[0043] Second, the propellant supply part and the atomizing gas supply part in the propellant supply system are respectively arranged inside the central cylinder 103 and the combustion chamber cylinder 402, and the space of the annular air intake channel 104 and the annular rotating detonation combustion channel 403 is completely not occupied, so as to ensure the efficiency and effect of air intake and detonation wave combustion. In addition, compared with the solid cylinder or hollow cylinder at the position of the central cylinder 103 and the combustion chamber cylinder 402 in conventional engines, the space utilization rate in the engine is improved, the space of the engine is reasonably utilized, and a rotating detonation engine with a gel propellant having a good effect is realized without increasing the size of the engine.

[0044] 3. The structural arrangement of the annular air inlet channel 104, the annular rotating detonation combustion channel 403 and the step ring 404 of the present invention is that the 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, so that the air and the propellant are mixed, and after ignition, a continuous rotating detonation wave is formed in 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 is helpful to form a stable flame to stay at this position, so as to continuously ignite the subsequent continuously injected propellant, play the role of a flame stabilizer, and can also improve the mixing of air and propellant. The combined effect of the two is conducive to the detonation and full combustion of the metal-based gel propellant injected subsequently. 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, which 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 is a part of the atomizing gas delivery channel. That is, the atomizing gas inside the atomizing gas storage box flows into the atomizing nozzle through the inner wall of the combustion chamber cylinder. At this time, before the atomizing gas enters the atomizing nozzle for atomization, it can exchange heat with the combustion chamber cylinder to cool down the high-temperature combustion chamber cylinder, thereby protecting the combustion chamber cylinder. At the same time, the heated atomizing gas can also promote the evaporation of kerosene in the gel propellant, which can achieve a better atomization effect and promote combustion.

[0046] In one embodiment, the atomizing gas delivery channel 209 is led out from the end of the atomizing gas storage tank 207 away from the central cylinder 103 and split, and arranged from the downstream direction to the upstream direction of the combustion chamber cylinder 402, forming a counter-current heat exchange structure, which can improve the cooling effect of the central cylinder 103 and the heating effect of the atomizing gas. Moreover, the atomizing gas delivery channel 209 can be provided with multiple atomizing gas delivery channels 209 after splitting, and the number of atomizing gas delivery channels 209 is consistent with the number of atomizing nozzles 205 and corresponds one to one. And 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 can exchange heat with the entire axial direction of the combustion chamber cylinder 402 to improve 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 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. The linear drive mechanism 201 can be a linear motor, a cylinder or a hydraulic cylinder. With such a configuration, the linear drive mechanism 201 can accurately control the movement of the piston 202 in view of the high surface viscosity of the metal-based gel propellant, thereby adjusting the supply of gel propellant and regulating the engine thrust.

[0050] In one embodiment, the propellant injection structure includes a plurality of propellant injection ports 401 arranged in an annular array along the step ring 404; a plurality of atomizing nozzles 205 are provided, and correspond one to one with the propellant injection ports 401. In this embodiment, the atomizing nozzle 205 is embedded in the propellant injection port 401, so that the atomizing nozzle 205 directly acts on the annular rotating detonation combustion channel 403. The use of a plurality of atomizing nozzles 205 arranged in an annular array can ensure that the propellant is fully injected into the annular rotating detonation combustion channel 403 and the injection is uniform.

[0051] In one embodiment, a propellant valve 204 is provided between the gel propellant tank 203 and the atomizing nozzle 205, so as to 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 one atomizing gas valve 208 to open and close the atomizing gas storage box 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. In addition, the combustible gas atomization gas in the initial stage can be triggered by the spark plug to start the engine ignition, thereby achieving stable atomization and efficient detonation of the metal-based gel propellant. With such a configuration, the combustion gas can enter the annular air inlet passage 104 and mix with the incoming air, and then the combustible gas and the incoming air are fully mixed in front of the annular rotating detonation combustion passage 403, and then ignited to release huge energy, detonating the metal-based gel propellant, thereby solving the problem of difficult ignition and combustion of the metal-based gel propellant.

[0054] The combustible gas is preferably hydrogen. In one preferred embodiment, the auxiliary ignition system 3 comprises a combustible gas storage tank 301 and a combustible gas intake pipe 303 , and a combustible gas valve 302 is arranged on the combustible gas intake 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 of the embodiments, the combustible gas intake pipe 303 is disposed at the tail end of the annular intake passage 104, so that the ignition position has a higher concentration of combustible gas, ensuring the enhancement of combustion by the auxiliary ignition system.

[0057] In one embodiment, a center body 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 body cone section 102. A tail nozzle 5 is provided downstream of the rotating detonation combustion chamber 4, which is composed of the engine casing 101 and the plug nozzle 501.

[0058] The present invention provides three specific embodiments:

[0059] Embodiment 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 the first embodiment is:

[0061] S1. Before the metal-based gel propellant rotating detonation engine works, the metal-based gel propellant is stored in the gel propellant tank 203, the air is stored in the atomizing gas tank 207, and the hydrogen is stored in the combustible gas tank 301. The propellant valve 204, the atomizing gas valve 208 and the combustible gas valve 302 are all in a closed state.

[0062] S2. When the metal-based gel propellant rotating detonation engine is started, air enters the annular air intake channel 104 through the air intake duct 1, the atomizing gas valve 208 opens to start supplying atomizing gas, the propellant valve 204 opens, the linear drive mechanism 201 starts, and the piston 202 is pushed to start supplying metal-based gel propellant. The atomizing gas impacts the metal-based gel propellant in the atomizing nozzle 205, and the atomized gel propellant is sprayed into the annular rotating detonation combustion channel 403 through the step ring 404.

[0063] S3. When the metal-based gel propellant rotary detonation engine starts to ignite, the combustible gas valve 302 is opened, and hydrogen is tangentially sprayed into the annular air inlet channel 104 to mix with the incoming air. The mixed hydrogen and air enter the annular rotary detonation combustion channel 403, and are ignited by a spark plug. The hydrogen explosion generates huge energy, which detonates the metal-based gel propellant sprayed in after atomization. The metal-based gel propellant at the detonation position is consumed, and the detonation wave moves along the wall of the rotary detonation combustion chamber 4 to the next propellant injection port 401 arranged in rotation along the step ring 404, and then the detonation position is quickly replenished with fresh gel propellant to form a continuous rotary 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 part 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 arranged between the annular air inlet channel 104 and the annular rotating detonation combustion channel 403. After the outside 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] Embodiment 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] The atomizing gas storage tank 207 stores hydrogen, and no auxiliary ignition system is provided. At this time, when the metal-based gel propellant rotary detonation engine starts to work, air enters the annular air inlet channel 104 through the air inlet duct 1, the atomizing gas valve 208 opens to start supplying hydrogen, the propellant valve 204 opens, the linear drive mechanism 201 starts, and the piston 202 is pushed to start supplying metal-based gel propellant. Hydrogen impacts and shears the metal-based gel propellant in the atomizing nozzle 205, and the atomized gel propellant is sprayed into the annular rotary detonation combustion channel 403. The spark plug is used for ignition and detonation, and the detonation wave moves to the next propellant injection port 401 arranged in rotation along the step. Fresh gel propellant is quickly added to the original detonation position to form a continuous rotary detonation, and finally the high-temperature and high-pressure gas is sprayed through the tail nozzle 5 to generate thrust.

[0070] Embodiment 3: The atomized gas storage 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 is only an embodiment and does not limit the present invention in any way. Any person skilled in the art can use the above disclosed technical contents to make many possible changes, modifications or modifications to the technical solutions of the present invention into equivalent embodiments of equivalent changes without departing from the scope of the technical solutions of the present invention. Therefore, any simple modification, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A metal-based gel propellant detonation engine, characterized in that: It comprises an air inlet (1), a rotating detonation combustion chamber (4) and a propellant supply system (2); The air intake passage (1) comprises a cylindrical engine casing (101) and a central cylinder (103) arranged in the engine casing (101), wherein the inner wall of the engine casing (101) and the outer wall of the central cylinder (103) enclose an annular air intake passage (104); The rotating detonation combustion chamber (4) comprises a combustion chamber cylinder (402) arranged in the engine casing (101) and located downstream of the central cylinder (103), wherein the inner wall of the engine casing (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 intake 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) comprises a propellant supply part and an atomizing gas supply part. The propellant supply part comprises 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 comprises 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 for the atomizing nozzle (205). The inner wall of the combustion chamber cylinder (402) is a part of the atomizing gas delivery channel (209).

2. The metal-based gel propellant detonation engine according to claim 1, characterized in that: 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, characterized in that: 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, characterized in that: The propulsion structure comprises a piston (202) arranged on a side of a 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, characterized in that: 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, characterized in that: 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), wherein the auxiliary ignition system (3) injects combustible gas into the annular air intake passage (104).

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

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

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