A fuel supply structure and a solid-liquid hybrid rocket engine

Abstract

This invention belongs to the field of engines, specifically relating to a fuel supply structure and a solid-liquid hybrid rocket engine, including an oxygen-enriched propellant supply mechanism and a gel fuel supply mechanism. The oxygen-enriched propellant supply mechanism includes a coating column, which includes a coating sleeve with an opening facing the combustion chamber, and the coating sleeve is used to hold the oxygen-enriched propellant. The gel fuel supply mechanism includes a gel fuel supply device, an annular channel, and an atomizer arranged sequentially. The annular channel is arranged around the outer edge of the coating sleeve, with its downstream end protruding downstream of the coating sleeve. The atomizer is located at the end of the annular channel protruding downstream of the coating sleeve, and the annular channel and the coating sleeve together seal the upstream end of the combustion chamber. This invention's engine adopts a novel combination of gel fuel and oxygen-enriched propellant, combining some of the advantages of both to achieve the effects of increased specific impulse, adjustable thrust, and multiple starts.

Description

Technical Field

[0001] This invention belongs to the field of engines, specifically relating to a fuel supply structure and a solid-liquid hybrid rocket engine. Background Technology

[0002] Gel fuel is a chemical power source that utilizes gelling agents and additives to create a long-term stable structure and specific properties from liquid fuel. Gel fuel is produced by adding energetic solid powders to gel fuel to create a high-density, high-calorific-value suspension homogeneous mixture. Gel fuel combines the advantages of liquid fuel (high specific impulse, controllable thrust output, multiple start-ups) with solid fuel (easy storage, transportation, maintenance, and stability), making it a key area of ​​research in novel power sources for missile engines. Energetic solid fuels such as boron, aluminum, magnesium, and carbon are often used as metal additives in gel fuel to increase its bulk density, thereby enhancing the thrust and specific impulse of the power plant.

[0003] Solid rocket engines are chemical rocket engines that use solid propellants. They work by igniting the propellant to produce high-temperature, high-pressure gas, which expands and accelerates through a nozzle to generate thrust. They have a simple structure and high reliability, but their specific impulse is low and their thrust is difficult to adjust. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a fuel supply structure and a solid-gel hybrid rocket engine that uses oxygen-rich solid propellant and gel fuel, combining some of the advantages of both, to achieve the effects of increasing specific impulse, adjustable thrust, and multiple starts.

[0005] This invention provides a fuel supply structure, including an oxygen-enriched propellant supply mechanism and a gel fuel supply mechanism;

[0006] The oxygen-enriched propellant supply mechanism includes a coating column, which includes a coating sleeve with an opening facing the combustion chamber, and the oxygen-enriched propellant is disposed inside the coating sleeve.

[0007] The gel fuel supply mechanism includes a gel fuel supply device, an annular channel, and an atomizer arranged in sequence. The annular channel is arranged around the outer edge of the cover sleeve, and the downstream end of the annular channel protrudes from the downstream end of the cover sleeve. The atomizer is located at the end of the annular channel that protrudes from the downstream end of the cover sleeve, and the annular channel and the cover sleeve together block the upstream end of the combustion chamber.

[0008] Furthermore, the gel fuel supply device includes a gel fuel tank and a propulsion mechanism;

[0009] One end of the gel fuel storage tank is provided with an outlet for communication with the annular channel;

[0010] The propulsion mechanism includes a linear drive mechanism and a piston located at the output end of the linear drive mechanism. The piston is slidably disposed inside the gel fuel tank, and the space between the piston and the side wall where the outlet is located is used to accommodate the gel fuel.

[0011] Furthermore, the linear drive mechanism includes a motor, a piston drive rod connected to the output rod of the motor, an external thread on the outer wall of the piston drive rod, and a threaded hole on the piston that mates with the external thread of the piston drive rod.

[0012] Furthermore, an end face connection channel is provided at the end of the annular channel away from the combustion chamber, and the end face connection channel is used to connect the annular channel and the gel fuel supply device;

[0013] The end face connection channel covers the back of the cover sleeve at the opening end.

[0014] Furthermore, the annular channel has a circular structure, and the covering sleeve has a cylindrical structure.

[0015] Furthermore, the atomizers are arranged in a ring array with several units at the end of the ring channel.

[0016] Furthermore, the atomizing nozzle of the atomizer is positioned facing the axis of the combustion chamber.

[0017] The present invention also provides a solid-liquid hybrid rocket engine, comprising the above-mentioned fuel supply structure, combustion chamber and tail nozzle arranged in sequence.

[0018] Furthermore, this solid-liquid hybrid rocket engine also includes an outer shell, which is hollow inside and open at one end, forming the tail nozzle of the tail nozzle.

[0019] The fuel supply structure is located on the upstream side inside the hollow outer shell. The annular channel and the cladding sleeve are combined to seal the middle of the outer shell. The outer shell is located on the downstream side of the annular channel and the cladding sleeve, forming the combustion chamber and the tail nozzle in sequence.

[0020] Furthermore, this solid-liquid hybrid rocket engine also includes an ignition device;

[0021] The ignition device includes an igniter fixedly mounted on an oxygen-enriched propellant column inside the casing and a wire connecting the igniter, with the wire connected to the outside of the casing.

[0022] The fuel supply structure provided by this invention has the following beneficial effects:

[0023] 1. A combined rocket engine using gel fuel and oxygen-enriched propellant is proposed. This engine employs a novel combination of gel fuel and oxygen-enriched propellant. The gel fuel and oxygen-enriched high-temperature gas are mixed and combusted in the combustion chamber, and the resulting high-temperature, high-pressure gas is discharged from the combustion chamber through the tail nozzle, generating thrust. When the gel fuel supply device can control the gel fuel flow rate, this engine utilizes the adjustable flow rate of the gel fuel to solve the problem of difficult thrust control in traditional solid rocket engines; it also solves the problem of difficult repeated starts in traditional solid rocket engines by opening and closing the gel fuel supply device; and by selecting gel fuel with a higher calorific value, the specific impulse and energy density of the fuel are increased, solving the problem of low calorific value in traditional solid propellant, thereby improving engine performance.

[0024] 2. In this fuel supply structure, both the gel fuel and the oxygen-enriched propellant burn incursions occur within the combustion chamber. The combustion process involves the gel droplets, atomized by the atomizer, mixing with the high-temperature, oxygen-enriched fuel gas generated by the propellant in the combustion chamber, where they ignite. The resulting high-temperature, high-pressure gas is then expelled from the combustion chamber through the exhaust nozzle, generating thrust. The coupled combustion of the gel fuel and the oxygen-enriched propellant within the combustion chamber, with the atomized gel droplets directly mixing with the high-temperature fuel gas, improves mixing uniformity and ensures more complete combustion. In this structure, the annular channel is flush with the engine casing, allowing for a one-piece casting design that integrates the piping with the casing, reducing the need for independent supports and connectors and lowering the overall engine weight.

[0025] 3. The annular channels are distributed around the oxygen-enriched propellant column and the combustion chamber. They preheat the gel fuel by absorbing the heat transferred to the outer shell during combustion, thereby improving the rheological properties of the gel fuel to facilitate its transport. At the same time, the atomization characteristics of the heated gel fuel are also improved, which is beneficial to the mixing and combustion of gel droplets, improving fuel combustion characteristics, reducing the overall heat loss of the engine, and improving energy efficiency. Attached Figure Description

[0026] Appendix Figure 1 This is a schematic diagram of the solid-liquid hybrid rocket engine in this invention;

[0027] Appendix Figure 2 This is a schematic diagram of the fuel supply structure in this invention;

[0028] Appendix Figure 3 This is a schematic diagram of the structure of the coated column in this invention.

[0029] In the diagram, 1-outer shell; 2-gel fuel supply device; 201-motor; 202-piston; 203-piston drive rod; 204-gel fuel storage tank; 2041-outlet; 205-gel fuel; 206-annular channel; 207-end face connection channel; 3-combustion chamber; 4-coating column; 401-coating sleeve; 402-oxygen-enriched propellant; 5-tail nozzle; 6-atomizer; 7-igniter; 8-wire. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0031] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0032] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0033] As attached Figure 1 -Appendix Figure 3 As shown, the present invention provides a fuel supply structure for supplying fuel and propellant to an engine, including an oxygen-enriched propellant supply mechanism and a gel fuel supply mechanism. The oxygen-enriched propellant supply mechanism is used to supply oxygen-enriched propellant to the engine, and the gel fuel supply mechanism is used to supply gel fuel, such as metal-based gel fuel, to the engine.

[0034] The oxygen-enriched propellant supply mechanism includes a coating column 4, which includes a coating sleeve 401 with an opening facing the combustion chamber 3, and an oxygen-enriched propellant 402 is disposed inside the coating sleeve 401.

[0035] The gel fuel supply mechanism includes a gel fuel supply device 2, an annular channel 206, and an atomizer 6 arranged in sequence. The gel fuel supply device 2 is used to supply gel fuel. The annular channel 206 is arranged around the outer side of the cover sleeve 401. The downstream end of the annular channel 206 protrudes from the downstream end of the cover sleeve 401. The atomizer 6 is located at the end of the annular channel 206 that protrudes from the downstream end of the cover sleeve 401 and is used to atomize the gel fuel 205 in the annular channel 206 to provide atomized gel fuel 205 to the combustion chamber 3. The annular channel 206 and the cover sleeve 401 together block the upstream end of the combustion chamber 3. The combination of the annular channel 206 and the cover sleeve 401 forms the upper end of the combustion chamber 3, so that the combustion chamber 3 is only connected to the downstream tail nozzle 5.

[0036] In one embodiment, the gel fuel supply device 2 can control the supply flow rate. Specifically, the gel fuel supply device 2 includes a gel fuel storage tank 204 and a propulsion mechanism. The gel fuel storage tank 204 is used to store gel fuel 205, and the propulsion mechanism is used to provide power to supply gel fuel 205 and control the supply flow rate of gel fuel 205.

[0037] One end of the gel fuel storage tank 204 is provided with an outlet 2041 for communicating with the annular channel 206;

[0038] The propulsion mechanism includes a linear drive mechanism and a piston 202 disposed at the output end of the linear drive mechanism. The piston 202 is slidably disposed in the gel fuel storage tank 204, and the space between the piston 202 and the side wall where the outlet 2041 is located is used to accommodate the gel fuel 205.

[0039] In this embodiment, the supply flow rate of gel fuel 205 can be controlled by controlling the linear drive mechanism, thereby realizing an adjustable flow rate / multiple-start supply system. The linear drive mechanism can be a cylinder, hydraulic cylinder, or linear motor, or it can be driven by pneumatic pressure, that is, controlling the air pressure in the cavity on the side of the gel fuel tank 204 away from the outlet 2041 to control the movement of the piston 202.

[0040] In one embodiment, the linear drive mechanism includes a motor 201 and a piston drive rod 203 connected to the output rod of the motor 201. The outer wall of the piston drive rod 203 is provided with external threads, and the piston 202 is provided with a threaded hole that mates with the external threads of the piston drive rod 203. The threaded hole is a through hole. In this case, the cross-section of the piston 202 and the gel fuel tank 204 is a non-circular structure. In this embodiment, the linear drive mechanism uses the motor 201 to drive the piston to propel the gel, which makes it easy to control the supply speed of the gel fuel 205, achieve stable supply and flow regulation of the gel fuel 205, meet the requirements of stable combustion and thrust regulation of the rocket engine, and make thrust regulation more convenient and stable. Multiple starts of the rocket engine can be achieved by switching the supply of gel fuel 205 on and off. In other embodiments, the linear drive mechanism can be a cylinder or a hydraulic cylinder.

[0041] In one embodiment, an annular channel 206 is provided with an end face connection channel 207 at one end away from the combustion chamber 3. The end face connection channel 207 is used to connect the annular channel 206 and the gel fuel supply device 2.

[0042] The end face connection channel 207 covers the end of the cover sleeve 401 away from the outlet. In this embodiment, by setting the end face connection channel 207, the cover sleeve 401 can be fully covered, realizing a stable connection between the annular channel 206 and the outlet 2041 of the gel fuel storage tank 204.

[0043] In one embodiment, the annular channel 206 has a circular structure, and the covering sleeve 401 has a cylindrical structure. The circular structure can be adapted to the circular structure of the combustion chamber 3, ensuring smooth flow of fuel and propellant.

[0044] In one embodiment, several atomizers 6 are arranged in a ring array at the end of the ring channel 206 to ensure the amount and uniformity of fuel supply.

[0045] In one embodiment, the atomizing port of the atomizer 6 is oriented toward the axis of the combustion chamber 3, thereby increasing the depth to which the atomized gel fuel 205 enters the combustion chamber 3 and improving the mixing effect of the gel fuel 205 with the oxygen-rich high-temperature gas.

[0046] The present invention also provides a solid-liquid hybrid rocket engine, comprising the aforementioned fuel supply structure, combustion chamber 3, and tail nozzle 5 arranged sequentially. The gel fuel 205 supplied by the fuel supply structure is mixed with oxygen-rich high-temperature gas in the combustion chamber 3 and then combusted. The resulting high-temperature, high-pressure gas is discharged from the combustion chamber 3 through the tail nozzle 5, generating thrust.

[0047] In one embodiment, the solid-liquid hybrid rocket engine also includes an outer shell 1, which is hollow inside and open at one end, forming the tail nozzle of the tail nozzle 5.

[0048] The fuel supply structure is located on the upstream side within the hollow outer shell 1. The annular channel 206 and the covering sleeve 401 together seal the middle of the outer shell 1. The combustion chamber 3 and the tail nozzle 5 are sequentially formed on the downstream side of the outer shell 1, located within the annular channel 206 and the covering sleeve 401. In this embodiment, the outer shell 1 can be integrally formed, with the annular channel 206 and the covering sleeve 401 dividing the hollow interior of the outer shell 1 into three independent regions. The upstream region is used to install the linear drive mechanism, the midstream region is used to install the annular channel 206 and the covering sleeve 401, and the downstream region is used to form the combustion chamber 3 and the tail nozzle 5. This design allows for full utilization of the outer shell 1 and is rationally laid out.

[0049] In one embodiment, an ignition device is also included;

[0050] The ignition device includes an igniter 7 fixedly mounted on an oxygen-enriched propellant 402 within a sheath 401 and a wire 8 connecting the igniter 7. The wire 8 passes through the outer casing 1 and connects to the outside. The wire 8 controls the opening of the igniter 7. By using the igniter 7 and the wire 8, engine ignition can be achieved. Repeated ignition occurs during engine operation by reducing the gel flow rate to maintain the combustion chamber flame at a level that merely sustains combustion. At this point, almost no fuel is consumed, and the engine does not generate power; this is considered engine shutdown. When repeated restarting is required, the gel flow rate is increased to induce intense combustion in the combustion chamber, generating high-temperature gas, at which point the engine restarts. Therefore, the igniter 7 and the wire 8 are not reused, and the wire 8 does not necessarily need to be inside the combustion chamber; it is sufficient to connect the wire to the outside for ease of operation.

[0051] The working process of the solid-liquid hybrid rocket engine in this invention is as follows:

[0052] S1, after the engine officially starts working, the wire 8 in the external environment is ignited to make the igniter 7 work. The igniter 7 ignites the oxygen-enriched propellant 402 in the envelope 4 to produce oxygen-enriched gas that enters the combustion chamber 3.

[0053] S2, motor 201 starts, driving piston 202 towards the piston via piston drive rod 203. Figure 1 and Figure 2 The middle right side moves, squeezing the gel fuel 205 toward the outlet 2041. After passing through the annular channel 206, the gel fuel 205 enters the atomizer 6, is atomized, and then sprayed into the combustion chamber 3. At this time, the atomized gel droplets are fully mixed with the high-temperature oxygen-rich gas and then ignited and burned.

[0054] S3, the high-temperature and high-pressure gas generated by the combustion of gel fuel is discharged from the combustion chamber 3 through the tail nozzle 5, generating thrust.

[0055] During engine operation, the supply speed of gel fuel 205 can be controlled by adjusting the output power of motor 201, thereby achieving real-time and precise adjustment of engine thrust. Moreover, since the oxygen-enriched propellant 402 and gel fuel 205 are in a separate state, if the power output of motor 201 is cut off, the supply of gel fuel 205 will stop, and the engine will shut down, which can effectively improve the engine's low vulnerability.

[0056] The above description is merely an embodiment and does not constitute any limitation on the present invention. Any person skilled in the art can make many possible variations, modifications, or alterations to the technical solutions of the present invention without departing from the scope of the present invention. Therefore, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the present invention, should fall within the protection scope of the present invention.

Claims

1. A fuel supply structure, characterized in that, This includes an oxygen-enriched propellant supply mechanism and a gel fuel supply mechanism; The oxygen-enriched propellant supply mechanism includes a coating column (4), the coating column (4) includes a coating sleeve (401) with an opening facing the combustion chamber (3), and the coating sleeve (401) is used to place an oxygen-enriched propellant (402). The gel fuel supply mechanism includes a gel fuel supply device (2), an annular channel (206) and an atomizer (6) arranged in sequence. The annular channel (206) is arranged around the outer side of the cover sleeve (401). The downstream of the annular channel (206) protrudes from the downstream side of the cover sleeve (401). The atomizer (6) is located at the end of the annular channel (206) that protrudes from the downstream side of the cover sleeve (401). The annular channel (206) and the cover sleeve (401) together block the upstream end of the combustion chamber (3). The gel fuel supply device (2) includes a gel fuel storage tank (204) and a propulsion mechanism; One end of the gel fuel storage tank (204) is provided with an outlet (2041) for communicating with the annular channel (206). The propulsion mechanism includes a linear drive mechanism and a piston (202) disposed at the output end of the linear drive mechanism. The piston (202) is slidably disposed in the gel fuel storage tank (204). The space between the piston (202) and the side wall where the outlet (2041) is located is used to accommodate gel fuel (205). The linear drive mechanism includes a motor (201) and a piston drive rod (203) connected to the output rod of the motor (201). The outer wall of the piston drive rod (203) is provided with an external thread, and the piston (202) is provided with a threaded hole that mates with the external thread of the piston drive rod (203). An annular channel (206) is provided with an end face connection channel (207) at one end away from the combustion chamber (3). The end face connection channel (207) is used to connect the annular channel (206) and the gel fuel supply device (2). The end face connection channel (207) covers the end of the cover sleeve (401) facing away from the outlet; The annular channel (206) has a circular structure, and the covering sleeve (401) has a cylindrical structure; Atomizers (6) are arranged in a ring array at the end of the ring channel (206); The atomizing port of the atomizer (6) is set towards the axis of the combustion chamber (3).

2. A solid-liquid hybrid rocket engine, characterized in that, It includes the fuel supply structure, combustion chamber (3) and tail nozzle (5) as described in claim 1, arranged in sequence.

3. The solid-liquid hybrid rocket engine as described in claim 2, characterized in that, It also includes an outer shell (1), which is hollow inside and open at one end, forming the tail nozzle of the tail nozzle pipe (5); The fuel supply structure is located on the upstream side inside the hollow shell (1). The annular channel (206) and the covering sleeve (401) are combined to seal the middle of the shell (1). The shell (1) is located on the downstream side of the annular channel (206) and the covering sleeve (401) to form the combustion chamber (3) and the tail nozzle (5) in sequence.

4. The solid-liquid hybrid rocket engine as described in claim 3, characterized in that, It also includes an ignition device; The ignition device includes an igniter (7) fixedly mounted on an oxygen-enriched propellant column (402) inside the cover (401) and a wire (8) connected to the igniter (7). The wire (8) is connected to the outside of the outer casing (1).

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