Propellant conveying system and liquid rocket engine

Abstract

The invention relates to the technical field of propellant delivery, in particular to a propellant delivery system and a liquid rocket engine. The propellant conveying system comprises a plurality of combination valves, the combination valves are communicated with the storage tank, and a propellant injection channel and a propellant output channel which are alternatively used are arranged in the combination valves; the liquid collecting ring is of a hollow annular structure, and a plurality of gas conveying pipelines, propellant conveying pipelines and propellant injection pipelines which are used for being communicated with an engine are arranged in an annular cavity of the liquid collecting ring. According to the liquid collecting ring, the complex gas path and the propellant conveying pipeline are integrated into the annular structure of the liquid collecting ring, the assembling procedure is simplified, the assembling time is saved, and the assembling manufacturability and reliability of the liquid power system are improved. Furthermore, a combination valve is arranged between the liquid collecting ring and the storage tank, and the injection channel and the output channel of the storage tank are managed through the combination valve, so that the number of valves of the whole system is reduced, and the modularization degree of the propellant conveying system is improved.

Description

Technical Field

[0001] The present application relates to the technical field of propellant delivery, and in particular to a propellant delivery system and a liquid rocket engine. Background Art

[0002] Liquid rocket engines are the main power source for spacecraft and are an indispensable component of these aircraft. In addition, liquid rocket engines are widely used in attitude control of spacecraft because they can achieve pulse operation and be repeatedly started. They provide power for orbit transfer and space docking of spacecraft; during inertial flight, they provide power for propellant management (propellant sinking and liquid level maintenance). The propellant delivery system is an important guarantee for the reliable operation of liquid rocket engines, which generally includes gas cylinders, tanks, valves and pipeline systems. After the high-pressure gas in the gas cylinder is reduced in pressure, it is passed into the tank to squeeze out the propellant in the tank liquid cavity and transport it to the engine through the propellant delivery system. The propellant burns or decomposes in the engine combustion chamber, converting the chemical energy of the propellant into heat energy, generating high-temperature and high-pressure combustion gas, which expands through the supersonic nozzle, converting the heat energy into kinetic energy, and is ejected backward from the nozzle at high speed, thereby generating thrust, providing the spacecraft with the power required for flight.

[0003] However, the existing propellant delivery system components are dispersed, the number of valves is too large, the delivery pipelines are complex, the risk of airtight leakage is high, and the assembly is dispersed and cumbersome, which limits the production efficiency, reliability and applicability of the propellant delivery system, and restricts the rapid response capability of the launch vehicle. In addition, most liquid power systems design the load-bearing structure and the propellant delivery system separately, resulting in low space utilization of the aircraft, which is not conducive to improving the economy and reliability of the launch vehicle. Therefore, there is an urgent need to develop a propellant delivery system for liquid rocket engines that can reduce the number of valves and pipeline interlacing to simplify the assembly process and assembly procedures, and lightweight the liquid power system structure to improve the space utilization of the aircraft. Summary of the invention

[0004] Regarding the relevant technologies, the components of the propellant delivery system are dispersed, the number of valves is too large, the delivery pipelines are complex and intertwined, and the risk of airtight leakage is high, which limits the production efficiency, reliability and applicability of the propellant delivery system and restricts the rapid response capability of the launch vehicle.

[0005] In a first aspect, an embodiment of the present application provides a propellant delivery system, comprising:

[0006] a plurality of tanks for storing and delivering propellant;

[0007] A plurality of gas cylinders for storing high-pressure gas;

[0008] A plurality of combination valves are connected to the tank, wherein the combination valves are provided with a propellant injection channel and a propellant output channel for selective use, wherein the propellant injection channel is used to deliver propellant to the tank, and the propellant output channel is used to receive propellant from the tank;

[0009] A liquid collecting ring is used for docking with the engine. The liquid collecting ring is a hollow annular structure. A plurality of gas delivery pipelines, propellant delivery pipelines and propellant injection pipelines for communicating with the engine are arranged in the annular cavity of the liquid collecting ring. The gas delivery pipeline and propellant delivery pipeline of the liquid collecting ring are respectively communicated with the propellant output channels inside the gas cylinder and the combination valve, and the propellant injection pipeline of the liquid collecting ring is communicated with the propellant injection channel of the combination valve.

[0010] In combination with the first aspect, in one embodiment, a cavity is provided inside the tank, and a movable partition is provided inside the tank, the partition divides the cavity of the tank into an air cavity and a liquid cavity for storing propellant, the air cavity of the tank is connected to the gas cylinder, and the gas cylinder can supply gas to the tank to move the partition toward the liquid cavity so that the propellant in the tank flows through the combination valve and the liquid collecting ring in sequence and then enters the engine.

[0011] In combination with the first aspect, in one embodiment, the gas cylinder is connected to the gas cavity of the storage tank through a gas pipeline, and a switch valve and a pressure reducing valve are provided on the gas pipeline, and the pressure reducing valve is used to reduce the pressure of the high-pressure gas in the gas pipeline.

[0012] In combination with the first aspect, in one implementation, the switch valve on the gas pipeline includes a manual valve and an electric control valve.

[0013] In combination with the first aspect, in one implementation, a sequence valve is provided on the gas pipeline, and the sequence valve is used to control the flow direction of the gas in the gas pipeline.

[0014] In combination with the first aspect, in one embodiment, a pneumatic switching part and a combination valve air circuit inlet are provided in the combination valve, and the combination valve air circuit inlet is connected to the gas delivery pipeline of the liquid collecting ring, and the pneumatic switching part is configured as follows: when the combination valve air circuit inlet receives compressed air reaching a set threshold, the pneumatic switching part cuts off the propellant injection channel under the drive of compressed gas, and simultaneously opens the propellant output channel.

[0015] In combination with the first aspect, in one embodiment, a liquid collecting ring propellant injection inlet is provided on the liquid collecting ring, the liquid collecting ring propellant injection inlet is communicated with the propellant injection channel, and the liquid collecting ring propellant injection inlet is communicated with an external propellant supply part.

[0016] In combination with the first aspect, in one embodiment, the upper and lower surfaces of the liquid collecting ring are respectively provided with an upper flange and a lower flange, the upper flange and the lower flange are coaxially arranged, and the liquid collecting ring can be connected to the engine and the mounting base through the upper flange and the lower flange respectively.

[0017] In combination with the first aspect, in one implementation, a plurality of the combination valves are evenly arranged along the circumference of the liquid collecting ring.

[0018] In a second aspect, an embodiment of the present application provides a liquid rocket engine, comprising: a propellant delivery system as described in any one of the above items.

[0019] The beneficial effects brought by the technical solution provided by the embodiment of the present application include at least:

[0020] The present application simplifies the assembly process, saves assembly time, and improves the assembly process and reliability of the liquid power system by integrating the complex gas circuit and propellant delivery pipeline into a ring structure of a liquid collecting ring. Furthermore, a combination valve is set between the liquid collecting ring and the tank, and the combination valve is used to manage the tank injection and output channels, thereby reducing the number of valves in the entire system and improving the modularity of the propellant delivery system. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 This is a schematic diagram of a propellant delivery system in an embodiment of the present application;

[0023] Figure 2 This is a schematic diagram of the structure of the combination valve in the embodiment of the present application;

[0024] Figure 3 This is a schematic diagram of the structure of the liquid collecting ring in the embodiment of the present application;

[0025] Figure 4 Schematic diagram of the pipeline equipment in the embodiment of the present application.

[0026] In the figure: 1, storage tank; 2, gas cylinder; 3, combination valve; 301, combination valve body; 302, combination valve liquid outlet; 303, combination valve gas inlet; 304, combination valve propellant filling inlet; 305, combination valve flange; 306, combination valve docking hole; 307, combination valve liquid inlet; 4, liquid collecting ring; 401, liquid collecting ring body; 402, liquid collecting ring fuel inlet; 403, liquid collecting ring oxidant inlet; 404, liquid collecting ring gas outlet; 405, liquid collecting ring fuel filling outlet; 406, liquid collecting ring oxidant filling outlet; 407, liquid collecting ring interface; 408, liquid collecting ring mounting hole; 409, liquid collecting ring Fuel filling inlet; 410, upper flange; 411, upper flange docking hole; 412, liquid collecting ring oxidant outlet; 413, liquid collecting ring fuel outlet; 414, liquid collecting ring control gas outlet; 415, liquid collecting ring gas path inlet; 416, liquid collecting ring oxidant filling inlet; 417, lower flange; 418, lower flange mounting hole; 5, piping system; 501, gas pipeline; 502, fuel pipeline; 503, oxidant pipeline; 504, manual valve; 505, electric control valve; 506, pressure reducing valve; 507, sequence valve; 508, high-pressure charging valve; 509, fuel filling valve; 510, oxidant filling valve. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0028] Regarding the relevant technologies, the components of the propellant delivery system are dispersed, the number of valves is too large, the delivery pipelines are complex and intertwined, and the risk of airtight leakage is high, which limits the production efficiency, reliability and applicability of the propellant delivery system and restricts the rapid response capability of the launch vehicle.

[0029] In a first aspect, the present application provides a propellant delivery system, characterized in that it comprises: a plurality of tanks 1, a plurality of gas cylinders 2, a plurality of combination valves 3 and a liquid collecting ring 4; wherein,

[0030] The tank 1 is used to store and output propellant; the gas cylinder 2 is used to store high-pressure gas; the combination valve 3 is connected to the tank 1, and the combination valve 3 is provided with a propellant injection channel and a propellant output channel for selective use, the propellant injection channel is used to transport propellant to the tank 1, and the propellant output channel is used to receive the propellant from the tank 1; a liquid collecting ring 4 is used to dock with the engine, the liquid collecting ring 4 is a hollow annular structure, and a plurality of gas delivery pipelines and propellant delivery pipelines and propellant injection pipelines for communicating with the engine are provided in the annular cavity of the liquid collecting ring 4, the gas delivery pipeline and propellant delivery pipeline of the liquid collecting ring 4 are respectively connected to the propellant output channels inside the gas cylinder 2 and the combination valve 3, and the propellant injection pipeline of the liquid collecting ring 4 is connected to the propellant injection channel of the combination valve 3.

[0031] It is worth noting that the present application simplifies the assembly process, saves assembly time, and improves the assembly process and reliability of the liquid power system by integrating the complex gas circuit and propellant delivery pipeline into a ring structure of a liquid collecting ring. Furthermore, a combination valve is set between the liquid collecting ring and the tank, and the combination valve is used to manage the tank injection and output channels, which reduces the number of valves in the entire system and improves the modularity of the propellant delivery system.

[0032] Further, the plurality of tanks 1 include a fuel tank for storing fuel and an oxidant tank for storing oxidant. Figure 1 As shown, the propellant delivery system includes four tanks 1, including two fuel tanks and two oxidizer tanks. The four tanks 1 are fixed on the mounting plate through mounting flanges and fasteners.

[0033] It can be understood that the material, shape, size and quantity of the storage tank 1 can be set according to actual needs.

[0034] In some preferred embodiments, a cavity is provided inside the tank 1, and a movable partition is provided inside the tank 1, and the partition divides the cavity of the tank 1 into an air cavity and a liquid cavity for storing propellant, and the air cavity of the tank 1 is connected to the gas cylinder 2, and the gas cylinder 2 can move the partition toward the liquid cavity by supplying gas to the tank 1 so that the propellant in the tank 1 flows through the combination valve 3 and the liquid collecting ring 4 in sequence and then enters the engine.

[0035] It is worth noting that after the compressed gas in the gas cylinder 2 is injected into the tank 1, the isolating member moves from the gas cavity to the liquid cavity under a certain pressure difference and fits tightly with the liquid cavity shell to squeeze out the propellant stored in the liquid cavity of the tank 1, thereby achieving the purpose of conveying the propellant.

[0036] In some optional implementations, the gas cylinder 2 is fixed on the mounting plate by means of a wrapping belt and a support, and the material, shape, size and quantity of the gas cylinder 2 can be set according to actual needs.

[0037] In some preferred embodiments, a pneumatic switching part and a combination valve air circuit inlet 303 are provided in the combination valve 3, and the combination valve air circuit inlet 303 is connected to the gas delivery pipeline of the liquid collecting ring 4, and the pneumatic switching part is configured as follows: when the combination valve air circuit inlet 303 receives compressed air reaching a set threshold, the pneumatic switching part cuts off the propellant injection channel under the drive of compressed gas, and simultaneously opens the propellant output channel.

[0038] It is worth noting that in the present application, a pneumatic switching unit is provided inside the combination valve 3 to control the on-off of the propellant injection channel and the propellant output channel. In the non-use stage, the combination valve 3 keeps the propellant injection channel open, and the external propellant supply source is connected to the propellant injection pipeline of the liquid collecting ring 4. The propellant from the external propellant supply source flows through the liquid collecting ring 4 and the combination valve 3 in turn into the storage tank 1 for long-term storage. When the propellant is needed, the gas cylinder 2 supplies gas to the gas circuit inlet 303 of the combination valve to trigger the pneumatic switching unit to cut off the propellant injection channel and open the propellant output channel of the combination valve 3.

[0039] Preferably, the pneumatic switching part is a cutter in the combination valve 3, and the cutter will be driven by compressed gas and break the isolation diaphragm to connect the propellant delivery channel.

[0040] Specifically, the number of the combination valves 3 is determined according to the number of the storage tanks 1 , and the combination valves 3 are connected between the storage tanks 1 and the liquid collecting ring 4 .

[0041] Furthermore, if Figure 2 As shown, the combination valve 3 comprises a combination valve body 301 , on which a combination valve liquid path outlet 302 , a combination valve gas path inlet 303 , a combination valve propellant injection inlet 304 , and a combination valve liquid path inlet 307 are provided.

[0042] It is worth noting that the combination valve liquid circuit inlet 307 and the combination valve liquid circuit outlet 302 can be connected to form the propellant delivery channel, and the combination valve propellant filling inlet 304 and the combination valve liquid circuit inlet 307 can be connected to form the propellant filling channel. Before the engine works, the propellant is added to the liquid cavity of the tank 1 through the combination valve propellant filling inlet 304 or the propellant is sealed in the liquid cavity of the tank 1 for a long time; when the engine works, the compressed gas is introduced through the combination valve gas circuit inlet 303 to drive the cutter to cut the isolation diaphragm to connect the propellant delivery channel and interrupt the propellant filling channel. The number of combination valves 3 can be set according to actual needs.

[0043] In some optional embodiments, a plurality of combination valves 3 are evenly arranged along the circumference of the liquid collecting ring 4, and each combination valve body 301 is provided with a combination valve flange 305. The combination valve flange 305 is provided with a plurality of evenly distributed combination valve docking holes 306 along the circumference to dock with the liquid collecting ring mounting hole 408.

[0044] It should be noted that the combination valve 3 of the present application can adopt a universal modular design to cope with different liquid collecting ring interfaces.

[0045] In some specific implementations, such as Figure 3 As shown, the liquid collecting ring 4 includes a liquid collecting ring body 401. The liquid collecting ring body 401 is a hollow annular structure, including three layers of pipelines, the upper, middle and lower layers are respectively fuel, gas and oxidant pipelines, and only the inlet and outlet are reserved.

[0046] It can be understood that an annular pipeline is arranged inside the liquid collecting ring body 401, and only the inlet and outlet are reserved to achieve multi-point uniform input and output, ensure the dynamic balance of input and output, thereby reducing flow resistance and suppressing water hammer.

[0047] In some preferred embodiments, the liquid collecting ring 4 of the present application is provided with four liquid collecting ring interfaces 407 along the circumferential direction. The liquid collecting ring interfaces 407 are used to connect the combination valve 3.

[0048] Furthermore, in order to optimize the overall pipeline layout of the propellant delivery system, the liquid collecting ring interfaces 407 are arranged close to the fuel tank or the oxidizer tank and are symmetrical to each other. At the same time, the number of the liquid collecting ring interfaces 407 can be set according to actual needs.

[0049] Specifically, two liquid collecting ring fuel interfaces and two liquid collecting ring oxidant interfaces are provided on the liquid collecting ring interface 407. Figure 3 As shown, the liquid ring fuel interface is provided with a liquid ring fuel inlet 402, a liquid ring gas outlet 404 and a liquid ring fuel filling outlet 405, and the liquid ring oxidant interface is provided with a liquid ring oxidant inlet 403, a liquid ring gas outlet 404 and a liquid ring oxidant filling outlet 406. The liquid ring 4 is provided with a liquid ring propellant filling inlet, the liquid ring propellant injection inlet is communicated with the propellant injection channel, and the liquid ring propellant is communicated with an external propellant supply part.

[0050] It is worth noting that the liquid collecting ring fuel inlet 402 and the liquid collecting ring oxidant inlet 403 are respectively communicated with the combination valve liquid path outlet 302 of the two combination valves 3. The liquid collecting ring gas path outlet 404 is communicated with the combination valve gas path inlet 303 of the combination valve 3. The liquid collecting ring fuel filling outlet 405 and the liquid collecting ring oxidant filling outlet 406 are respectively communicated with the combination valve propellant filling inlet 304 of the two combination valves 3.

[0051] Furthermore, the liquid collecting ring body 401 is also provided with a liquid collecting ring fuel filling inlet 409, a liquid collecting ring gas path inlet 415 and a liquid collecting ring oxidant filling inlet 416 connected to the pipeline system 5 along the circumferential direction. The bottom of the liquid collecting ring body 401 is provided with a liquid collecting ring oxidant outlet 412, a liquid collecting ring fuel outlet 413 and a liquid collecting ring control gas outlet 414, which are connected to the engine and are used to transport propellant and compressed gas to the inside of the engine.

[0052] In some preferred embodiments, the upper and lower surfaces of the liquid collecting ring 4 are respectively provided with an upper flange 410 and a lower flange 417, the upper flange 410 and the lower flange 417 are coaxially arranged, and the liquid collecting ring 4 can be connected to the engine and the mounting base through the upper flange 410 and the lower flange 417 respectively.

[0053] Furthermore, the lower flange 417 is coaxially arranged below the upper flange 410, and the inner diameter of the lower flange 417 is equal to the outer diameter of the upper flange 410, and the lower flange 417 is provided with a plurality of evenly distributed lower flange mounting holes 418 along the circumferential direction. The liquid collecting ring is connected to the engine through the upper flange 410 and fasteners, and is fixed to the mounting base plate through the lower flange 417 and fasteners. The upper flange 410, the lower flange 417 of the liquid collecting ring 4 and the four main beams therebetween constitute the main load-bearing and force-transmitting structure.

[0054] Preferably, in order to improve the impact deformation resistance and structural stability of the liquid collecting ring 4, reinforcing ribs may be provided between the upper flange 410 and the lower flange 417 or V-shaped side beams may be designed between adjacent main beams.

[0055] It is worth mentioning that the liquid collecting ring 4 can be used as an integrated design of the liquid rocket engine bracket and the propellant delivery pipeline, and the liquid power system structure can be lightweight to improve the space utilization of the aircraft.

[0056] In some specific implementations, the propellant delivery system further includes a pipeline system 5, and the pipeline system 5 includes a gas pipeline 501, a fuel pipeline 502, and an oxidant pipeline 503. Further, the gas cylinder 2 is connected to the gas cavity of the tank 1 through the gas pipeline 501, and a group of gas circuit valves are provided on the gas pipeline 501, and the gas circuit valves include: a manual valve 504, an electric control valve 505, a pressure reducing valve 506, and a sequence valve 507, and the above-mentioned gas circuit valves are connected in sequence through the gas pipeline 501.

[0057] It is understandable that the pressure reducing valve 506 reduces the pressure of the high-pressure gas at the outlet of the electric control valve 505 and then delivers it to the gas cavity of the tank 1 to provide the required stable extrusion pressure. The sequence valve 507 is used to control the flow direction of the gas in the gas pipeline 501 to prevent the diaphragm of the tank 1 from rupturing, causing the propellant to flow in reverse and mix in the pipeline to cause a safety accident.

[0058] When in use, before the engine starts, the manual valve 504 and the electric control valve 505 are normally closed, which are used to seal the high-pressure gas in the upstream gas cylinder 2 to ensure storage safety and operation safety; after the propellant is added to the liquid cavity of the tank 1, the manual valve 504 is opened, and the electric control valve 505 is remotely energized to connect the gas channel between the gas cylinder outlet and the tank gas cavity inlet, the pressure reducing valve 506 reduces the pressure of the high-pressure gas at the outlet of the electric control valve 505 and transports it to the gas cavity of the tank 1 to provide the required stable extrusion pressure, and the sequence valve 507 is used to control the gas flow direction.

[0059] In some optional implementations, the pipeline system 5 also includes: a high-pressure inflation pipeline, a fuel filling pipeline, and an oxidant filling pipeline, each of which is provided with a high-pressure inflation valve 508, a fuel filling valve 509 and an oxidant filling valve 510, respectively.

[0060] It is understandable that the high pressure filling valve 508 is used to fill the high pressure gas into the gas cylinder 2. The fuel filling valve 509 and the oxidant filling valve 510 are used to fill the propellant into the tank 1. Preferably, an operation panel can be provided in the pipeline system 5 to simplify the system assembly and testing process.

[0061] The working principle of the propellant delivery system of this application includes:

[0062] Before the engine works: the manual valve 504 and the electric control valve 505 are in the normally closed state, the high-pressure gas is filled into the gas cylinder 2 through the high-pressure filling valve 508, and the propellant is filled into the tank 1 through the fuel filling valve 509 and the oxidizer filling valve 510, and the propellant delivery system enters the pre-start state.

[0063] When the propellant delivery system starts working: open the manual valve 504, remotely energize the electric control valve 505, and connect the gas channel between the gas cylinder 2 and the tank 1. The compressed gas is divided into three paths after being reduced in pressure by the pressure reducing valve 506.

[0064] The first gas is delivered to the combination valve 3 through the liquid collecting ring 4 to drive the cutter of the pneumatic switching part to cut the isolation diaphragm to connect the propellant delivery channel of the combination valve and interrupt the propellant filling channel of the combination valve.

[0065] The second gas is transported to the interior of the engine through the liquid collecting ring 4.

[0066] The third gas is delivered to the gas cavity of the tank 1 to squeeze out the propellant in the liquid cavity of the tank 1. The propellant is then delivered to the inside of the engine through the combination valve 3 and the liquid collecting ring 4.

[0067] In a second aspect, the present application provides a liquid rocket engine, which includes: a propellant delivery system, the propellant delivery system includes: a plurality of tanks 1, a plurality of gas cylinders 2, a plurality of combination valves 3 and a liquid collecting ring 4; wherein,

[0068] The tank 1 is used to store and output propellant; the gas cylinder 2 is used to store high-pressure gas; the combination valve 3 is connected to the tank 1, and the combination valve 3 is provided with a propellant injection channel and a propellant output channel for selective use, the propellant injection channel is used to transport propellant to the tank 1, and the propellant output channel is used to receive the propellant from the tank 1; a liquid collecting ring 4 is used to dock with the engine, the liquid collecting ring 4 is a hollow annular structure, and a plurality of gas delivery pipelines and propellant delivery pipelines and propellant injection pipelines for communicating with the engine are provided in the annular cavity of the liquid collecting ring 4, the gas delivery pipeline and propellant delivery pipeline of the liquid collecting ring 4 are respectively connected to the propellant output channels inside the gas cylinder 2 and the combination valve 3, and the propellant injection pipeline of the liquid collecting ring 4 is connected to the propellant injection channel of the combination valve 3.

[0069] Further, the plurality of tanks 1 include a fuel tank for storing fuel and an oxidant tank for storing oxidant. Figure 1 As shown, the propellant delivery system includes four tanks 1, including two fuel tanks and two oxidizer tanks. The four tanks 1 are fixed on the mounting plate through mounting flanges and fasteners.

[0070] It can be understood that the material, shape, size and quantity of the storage tank 1 can be set according to actual needs.

[0071] In some preferred embodiments, a cavity is provided inside the tank 1, and a movable partition is provided inside the tank 1, and the partition divides the cavity of the tank 1 into an air cavity and a liquid cavity for storing propellant, and the air cavity of the tank 1 is connected to the gas cylinder 2, and the gas cylinder 2 can move the partition toward the liquid cavity by supplying gas to the tank 1 so that the propellant in the tank 1 flows through the combination valve 3 and the liquid collecting ring 4 in sequence and then enters the engine.

[0072] In some optional implementations, the gas cylinder 2 is fixed on the mounting plate by means of a wrapping belt and a support, and the material, shape, size and quantity of the gas cylinder 2 can be set according to actual needs.

[0073] In some preferred embodiments, a pneumatic switching part and a combination valve air circuit inlet 303 are provided in the combination valve 3, and the combination valve air circuit inlet 303 is connected to the gas delivery pipeline of the liquid collecting ring 4, and the pneumatic switching part is configured as follows: when the combination valve air circuit inlet 303 receives compressed air reaching a set threshold, the pneumatic switching part cuts off the propellant injection channel under the drive of compressed gas, and simultaneously opens the propellant output channel.

[0074] Preferably, the pneumatic switching part is a cutter in the combination valve 3, and the cutter will be driven by compressed gas and break the isolation diaphragm to connect the propellant delivery channel.

[0075] Specifically, the number of the combination valves 3 is determined according to the number of the storage tanks 1 , and the combination valves 3 are connected between the storage tanks 1 and the liquid collecting ring 4 .

[0076] Furthermore, if Figure 2 As shown, the combination valve 3 comprises a combination valve body 301 , on which a combination valve liquid path outlet 302 , a combination valve gas path inlet 303 , a combination valve propellant injection inlet 304 , and a combination valve liquid path inlet 307 are provided.

[0077] In some optional embodiments, a plurality of combination valves 3 are evenly arranged along the circumference of the liquid collecting ring 4, and each combination valve body 301 is provided with a combination valve flange 305. The combination valve flange 305 is provided with a plurality of evenly distributed combination valve docking holes 306 along the circumference to dock with the liquid collecting ring mounting hole 408.

[0078] It should be noted that the combination valve 3 of the present application can adopt a universal modular design to cope with different liquid collecting ring interfaces.

[0079] In some specific implementations, such as Figure 3 As shown, the liquid collecting ring 4 includes a liquid collecting ring body 401. The liquid collecting ring body 401 is a hollow annular structure, including three layers of pipelines, the upper, middle and lower layers are respectively fuel, gas and oxidant pipelines, and only the inlet and outlet are reserved.

[0080] It can be understood that an annular pipeline is arranged inside the liquid collecting ring body 401, and only the inlet and outlet are reserved to achieve multi-point uniform input and output, ensure the dynamic balance of input and output, thereby reducing flow resistance and suppressing water hammer.

[0081] In some preferred embodiments, the liquid collecting ring 4 of the present application is provided with four liquid collecting ring interfaces 407 along the circumferential direction. The liquid collecting ring interfaces 407 are used to connect the combination valve 3.

[0082] Furthermore, in order to optimize the overall pipeline layout of the propellant delivery system, the liquid collecting ring interfaces 407 are arranged close to the fuel tank or the oxidizer tank and are symmetrical to each other. At the same time, the number of the liquid collecting ring interfaces 407 can be set according to actual needs.

[0083] Specifically, two liquid collecting ring fuel interfaces and two liquid collecting ring oxidant interfaces are provided on the liquid collecting ring interface 407. Figure 3 As shown, the liquid ring fuel interface is provided with a liquid ring fuel inlet 402, a liquid ring gas outlet 404 and a liquid ring fuel filling outlet 405, and the liquid ring oxidant interface is provided with a liquid ring oxidant inlet 403, a liquid ring gas outlet 404 and a liquid ring oxidant filling outlet 406. The liquid ring 4 is provided with a liquid ring propellant filling inlet, the liquid ring propellant injection inlet is communicated with the propellant injection channel, and the liquid ring propellant is communicated with an external propellant supply part.

[0084] Furthermore, the liquid collecting ring body 401 is also provided with a liquid collecting ring fuel filling inlet 409, a liquid collecting ring gas path inlet 415 and a liquid collecting ring oxidant filling inlet 416 connected to the pipeline system 5 along the circumferential direction. The bottom of the liquid collecting ring body 401 is provided with a liquid collecting ring oxidant outlet 412, a liquid collecting ring fuel outlet 413 and a liquid collecting ring control gas outlet 414, which are connected to the engine and are used to transport propellant and compressed gas to the inside of the engine.

[0085] In some preferred embodiments, the upper and lower surfaces of the liquid collecting ring 4 are respectively provided with an upper flange 410 and a lower flange 417, the upper flange 410 and the lower flange 417 are coaxially arranged, and the liquid collecting ring 4 can be connected to the engine and the mounting base through the upper flange 410 and the lower flange 417 respectively.

[0086] Furthermore, the lower flange 417 is coaxially arranged below the upper flange 410, and the inner diameter of the lower flange 417 is equal to the outer diameter of the upper flange 410, and the lower flange 417 is provided with a plurality of evenly distributed lower flange mounting holes 418 along the circumferential direction. The liquid collecting ring is connected to the engine through the upper flange 410 and fasteners, and is fixed to the mounting base plate through the lower flange 417 and fasteners. The upper flange 410, the lower flange 417 of the liquid collecting ring 4 and the four main beams therebetween constitute the main load-bearing and force-transmitting structure.

[0087] Preferably, in order to improve the impact deformation resistance and structural stability of the liquid collecting ring 4, reinforcing ribs may be provided between the upper flange 410 and the lower flange 417 or V-shaped side beams may be designed between adjacent main beams.

[0088] In some specific implementations, the propellant delivery system further includes a pipeline system 5, and the pipeline system 5 includes a gas pipeline 501, a fuel pipeline 502, and an oxidant pipeline 503. Further, the gas cylinder 2 is connected to the gas cavity of the tank 1 through the gas pipeline 501, and a group of gas circuit valves are provided on the gas pipeline 501, and the gas circuit valves include: a manual valve 504, an electric control valve 505, a pressure reducing valve 506, and a sequence valve 507, and the above-mentioned gas circuit valves are connected in sequence through the gas pipeline 501.

[0089] When in use, before the engine starts, the manual valve 504 and the electric control valve 505 are normally closed, which are used to seal the high-pressure gas in the upstream gas cylinder 2 to ensure storage safety and operation safety; after the propellant is added to the liquid cavity of the tank 1, the manual valve 504 is opened, and the electric control valve 505 is remotely energized to connect the gas channel between the gas cylinder outlet and the tank gas cavity inlet, the pressure reducing valve 506 reduces the pressure of the high-pressure gas at the outlet of the electric control valve 505 and transports it to the gas cavity of the tank 1 to provide the required stable extrusion pressure, and the sequence valve 507 is used to control the gas flow direction.

[0090] In some optional implementations, the pipeline system 5 also includes: a high-pressure inflation pipeline, a fuel filling pipeline, and an oxidant filling pipeline, each of which is provided with a high-pressure inflation valve 508, a fuel filling valve 509 and an oxidant filling valve 510, respectively.

[0091] The working principle of the propellant delivery system of this application includes:

[0092] Before the engine works: the manual valve 504 and the electric control valve 505 are in the normally closed state, the high-pressure gas is filled into the gas cylinder 2 through the high-pressure filling valve 508, and the propellant is filled into the tank 1 through the fuel filling valve 509 and the oxidizer filling valve 510, and the propellant delivery system enters the pre-start state.

[0093] When the propellant delivery system starts working: open the manual valve 504, remotely energize the electric control valve 505, and connect the gas channel between the gas cylinder 2 and the tank 1. The compressed gas is divided into three paths after being reduced in pressure by the pressure reducing valve 506.

[0094] The first gas is delivered to the combination valve 3 through the liquid collecting ring 4 to drive the cutter of the pneumatic switching part to cut the isolation diaphragm to connect the propellant delivery channel of the combination valve and interrupt the propellant filling channel of the combination valve.

[0095] The second gas is transported to the interior of the engine through the liquid collecting ring 4.

[0096] The third gas is delivered to the gas cavity of the tank 1 to squeeze out the propellant in the liquid cavity of the tank 1. The propellant is then delivered to the inside of the engine through the combination valve 3 and the liquid collecting ring 4.

[0097] To summarize, the propellant delivery system of the present application adopts an integrated design and modular layout, and integrates the load-bearing structure of the liquid power system with the propellant delivery pipeline, thereby solving the problems of scattered distribution of components of the existing propellant delivery system, excessive number of valves, complex interlacing of delivery pipelines, high risk of airtight leakage, scattered and cumbersome assembly, and low space utilization of the aircraft, thereby improving the reliability, economy and space utilization of the propellant delivery system.

[0098] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0099] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0100] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A propellant delivery system, characterized in that: include: A plurality of tanks (1) for storing and discharging propellant; A plurality of gas cylinders (2) for storing high-pressure gas; a plurality of combination valves (3) connected to the tank (1), wherein the combination valve (3) is provided with a propellant injection channel and a propellant output channel for selective use, wherein the propellant injection channel is used to deliver propellant to the tank (1), and the propellant output channel is used to receive propellant from the tank (1); A liquid collecting ring (4) is used for docking with the engine. The liquid collecting ring (4) is in a hollow annular structure. A plurality of gas delivery pipelines, propellant delivery pipelines and propellant injection pipelines for communicating with the engine are arranged in the annular cavity of the liquid collecting ring (4). The gas delivery pipeline and propellant delivery pipeline of the liquid collecting ring (4) are respectively communicated with the propellant output channels inside the gas cylinder (2) and the combination valve (3), and the propellant injection pipeline of the liquid collecting ring (4) is communicated with the propellant injection channel of the combination valve (3).

2. The propellant delivery system of claim 1, wherein: The tank (1) is provided with a cavity inside, and a movable partition is provided inside the tank (1). The partition divides the cavity of the tank (1) into an air cavity and a liquid cavity for storing propellant. The air cavity of the tank (1) is connected with the gas cylinder (2), and the gas cylinder (2) can move the partition toward the liquid cavity by supplying gas to the tank (1), so that the propellant in the tank (1) flows through the combination valve (3) and the liquid collecting ring (4) in sequence and then enters the engine.

3. The propellant delivery system of claim 2, wherein: The gas cylinder (2) is connected to the gas cavity of the storage tank (1) via a gas pipeline (501). The gas pipeline (501) is provided with a switch valve and a pressure reducing valve (506). The pressure reducing valve is used to reduce the pressure of the high-pressure gas in the gas pipeline (501).

4. The propellant delivery system of claim 3, wherein: The switch valve on the gas pipeline (501) includes a manual valve (504) and an electric control valve (505).

5. The propellant delivery system of claim 3, wherein: The gas pipeline (501) is provided with a sequence valve (507), and the sequence valve (507) is used to control the flow direction of the gas in the gas pipeline (501).

6. The propellant delivery system of claim 1, wherein: The combination valve (3) is provided with a pneumatic switching unit and a combination valve gas circuit inlet (303), the combination valve gas circuit inlet (303) being in communication with the gas delivery pipeline of the liquid collecting ring (4), and the pneumatic switching unit being configured such that when the combination valve gas circuit inlet (303) receives compressed air reaching a set threshold, the pneumatic switching unit, driven by the compressed gas, cuts off the propellant injection channel and simultaneously opens the propellant output channel.

7. The propellant delivery system of claim 1, wherein: The liquid collecting ring (4) is provided with a liquid collecting ring propellant injection inlet, the liquid collecting ring propellant injection inlet is communicated with the propellant injection channel, and the liquid collecting ring propellant injection inlet is communicated with an external propellant supply part.

8. The propellant delivery system of claim 1, wherein: The upper and lower surfaces of the liquid collecting ring (4) are respectively provided with an upper flange (410) and a lower flange (417); the upper flange (410) and the lower flange (417) are coaxially arranged, and the liquid collecting ring (4) can be connected to the engine and the mounting base plate respectively through the upper flange (410) and the lower flange (417).

9. The propellant delivery system of claim 1, wherein: The plurality of combined valves (3) are evenly arranged along the circumference of the liquid collecting ring (4).

10. A liquid rocket engine, characterized in that: include: A propellant delivery system as claimed in any one of claims 1 to 9.

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