Nitrogen pressurization system and pressurization method of RBCC engine

Abstract

The invention discloses a nitrogen pressurization system and method of an RBCC engine. The technical problem that an existing nitrogen pressurization system is poor in safety and testability is solved. The pressurization system comprises a nitrogen gas cylinder, a stamping fuel oil storage tank, an oxidizing agent storage tank, a fuel storage tank and a power controller. The nitrogen gas cylinder is connected with the inlet end of the stamping fuel oil storage tank, and a self-locking valve, a first-stage pressure reducing valve and a second-stage pressure reducing valve are sequentially arranged on a connecting pipeline. The power controller is electrically connected with the self-locking valve; the outlet end of the stamping fuel storage tank is connected with the stamping combustion chamber; the outlet ends of the oxidant storage tank and the fuel storage tank are respectively connected with a rocket thrust chamber, and a first gas explosion valve and a second gas explosion valve are respectively mounted on connecting pipelines; a first branch is arranged between the self-locking valve and the first-stage pressure reducing valve and connected with the first gas explosion valve and the second gas explosion valve. A second branch is arranged between the first-stage pressure reducing valve and the second-stage pressure reducing valve and connected with the inlet end of the oxidizing agent storage box and the inlet end of the rocket fuel storage box.

Description

Technical Field

[0001] The present invention relates to a propellant pressurization system, and more particularly to a nitrogen pressurization system and a pressurization method for an RBCC engine. Background Art

[0002] A Rocket-Based-Combined-Cycle (RBCC) engine is a propulsion system that combines a rocket engine with a high thrust-to-weight ratio and a scramjet engine with a high specific impulse. It is one of the main power sources for hypersonic vehicles and space transportation systems. Due to the complex combined cycle form of the RBCC engine, higher requirements are imposed on its propellant pressurization system.

[0003] In an RBCC engine, in scenarios where the demand for propellant is not high, a nitrogen extrusion pressurization system is generally selected for the propellant pressurization system to provide supply conditions for the fuel in the ram combustion chamber and the oxidizer and fuel in the rocket thrust chamber. In the existing nitrogen pressurization system of the RBCC engine, electric explosion valves are mostly used for gas storage and sealing at the outlet of the nitrogen cylinder, the outlet of the oxidizer tank of the rocket thrust chamber, and the outlet of the fuel tank. However, since the electric explosion valve is a pyrotechnic device, its safety and testability are poor. Therefore, to a great extent, it increases the maintenance difficulty and test risk of the entire pressurization system. Summary of the Invention

[0004] The object of the present invention is to solve the technical problems of the existing nitrogen pressurization system, which has poor safety and testability and increases the maintenance difficulty and test risk of the entire pressurization system, and to provide a nitrogen pressurization system and a pressurization method for an RBCC engine.

[0005] To achieve the above object, the technical solution provided by the present invention is as follows:

[0006] A nitrogen pressurization system for an RBCC engine, characterized in that:

[0007] It includes a nitrogen cylinder, a ram fuel tank, an oxidizer tank, a fuel tank, and a power controller;

[0008] The nitrogen cylinder is used to store high-pressure nitrogen. The nitrogen cylinder is connected to the inlet end of the ram fuel tank through a pipeline, and a self-locking valve, a first-stage pressure reducing valve, and a second-stage pressure reducing valve are sequentially arranged on this pipeline; the self-locking valve is arranged close to the nitrogen cylinder, and the power controller is electrically connected to the self-locking valve for controlling the opening and closing of the self-locking valve; the first-stage pressure reducing valve and the second-stage pressure reducing valve are used to sequentially perform two-stage pressure reduction on the high-pressure nitrogen;

[0009] The ram fuel tank is used to store fuel, and its outlet end is used to be connected to the ram combustion chamber through a pipeline;

[0010] The oxidizer storage tank is used to store oxidizer, and its outlet end is used to connect to the rocket thrust chamber through a pipeline, and a first air burst valve is installed on this pipeline;

[0011] The fuel storage tank is used to store fuel, and its outlet end is used to connect to the rocket thrust chamber through a pipeline, and a second air burst valve is installed on this pipeline;

[0012] A first branch is provided on the pipeline between the self-locking valve and the first-stage pressure reducing valve, and one end of the first branch away from the self-locking valve is respectively connected to the first air burst valve and the second air burst valve;

[0013] A second branch is provided on the pipeline between the first-stage pressure reducing valve and the second-stage pressure reducing valve. One end of the second branch away from the first-stage pressure reducing valve is respectively connected to the inlet ends of the oxidizer storage tank and the rocket fuel storage tank, and a first isolation valve and a second isolation valve are respectively installed near the oxidizer storage tank and the rocket fuel storage tank.

[0014] Further, a charging and discharging valve is provided at the inlet end of the nitrogen gas cylinder for controlling the charging of high-pressure nitrogen; the outlet end is connected to the inlet end of the ramjet fuel storage tank through a pipeline;

[0015] A first vent port is further provided at the inlet end of the ramjet fuel storage tank, and a first vent valve is installed on the first vent port; the outlet end is provided with two pipelines, one of which is used to connect to the fuel storage unit, and a fuel filling and discharging valve is provided on this pipeline; the other pipeline is used to connect to the ramjet combustion chamber;

[0016] A second vent port is further provided at the inlet end of the oxidizer storage tank, and a second vent valve is installed on the second vent port; the outlet end is provided with two pipelines, one of which is used to communicate with the oxidizer storage unit, and an oxidizer filling and discharging valve is installed on this pipeline, and the other pipeline is used to connect to the rocket thrust chamber;

[0017] A third vent port is further provided at the inlet end of the fuel storage tank, and a third vent valve is installed on the third vent port; the outlet end is provided with two pipelines, one of which is used to connect to the fuel storage unit, and a fuel filling and discharging valve is installed on this pipeline; the other pipeline is used to connect to the rocket thrust chamber.

[0018] Further, a first safety valve is further provided on the pipeline between the first-stage pressure reducing valve and the second-stage pressure reducing valve; a second safety valve is provided on the pipeline between the second-stage pressure reducing valve and the ramjet fuel storage tank.

[0019] Further, a filter is installed on the pipeline connecting the ramjet fuel storage tank and the ramjet combustion chamber.

[0020] Further, both the first isolation valve and the second isolation valve are diaphragm valves.

[0021] Further, the ramjet fuel tank, oxidizer tank, and fuel tank each include adjacent gas cavities and liquid cavities. The gas cavities are used to introduce corresponding high-pressure nitrogen gas, and the liquid cavities are used to fill the corresponding fuel, oxidizer, or fuel.

[0022] The present invention also provides a nitrogen gas pressurization method for an RBCC engine, comprising the following steps:

[0023] Step 1: Assemble the nitrogen gas pressurization system of the above-mentioned RBCC engine, close the self-locking valve through the power controller, and at the same time open the first-stage pressure reducing valve and the second-stage pressure reducing valve;

[0024] Step 2: Fill a predetermined amount of high-pressure nitrogen gas into the nitrogen gas cylinder, fill a predetermined amount of fuel into the ramjet fuel tank, fill a predetermined amount of oxidizer into the oxidizer tank, and fill a predetermined amount of fuel into the fuel tank;

[0025] Step 3: Open the self-locking valve through the power controller. The high-pressure nitrogen gas is divided into two paths after passing through the self-locking valve. One path of the high-pressure nitrogen gas opens the first gas explosion valve and the second gas explosion valve after passing through the first branch; the other path of the high-pressure nitrogen gas is divided into two paths again after passing through the first-stage pressure reducing valve. One path enters the oxidizer tank and the fuel tank through the second branch, respectively, after passing through the first isolation valve and the second isolation valve, and the remaining path enters the ramjet fuel tank after passing through the second-stage pressure reducing valve;

[0026] Step 4: The high-pressure nitrogen gas extrudes the fuel from the ramjet fuel tank into the combustion chamber of the RBCC engine, and extrudes the oxidizer and fuel from the oxidizer tank and the fuel tank into the thrust chamber of the RBCC engine, thereby completing the nitrogen gas pressurization of the RBCC engine.

[0027] Further, Step 2 is specifically as follows:

[0028] 2.1. Keep the charge and discharge valve, the first ventilation valve, the fuel filling and discharging valve, the second ventilation valve, the oxidizer filling and discharging valve, the first gas explosion valve, the third ventilation valve, the fuel filling and discharging valve, and the second gas explosion valve closed;

[0029] 2.2. Open the charge and discharge valve, fill a predetermined amount of high-pressure nitrogen gas into the nitrogen gas cylinder, and close the charge and discharge valve after filling;

[0030] 2.3. Open the first ventilation valve and the fuel filling and discharging valve, fill a predetermined amount of fuel into the ramjet fuel tank, and close the first ventilation valve and the fuel filling and discharging valve after filling;

[0031] 2.4. Open the second ventilation valve and the oxidizer filling and discharging valve, fill a predetermined amount of oxidizer into the oxidizer tank, and close the second ventilation valve and the oxidizer filling and discharging valve after filling;

[0032] 2.5. Open the third vent valve and the fuel filling and draining valve, fill a predetermined amount of fuel into the fuel tank, and close the third vent valve and the fuel filling and draining valve after filling is completed.

[0033] Further, in step 3, the first pressure reducing valve reduces the high-pressure nitrogen to 5 ± 3 MPa, and the second pressure reducing valve reduces the high-pressure nitrogen to 0.5 ± 0.3 MPa.

[0034] Further, in step 3, the first pressure reducing valve reduces the high-pressure nitrogen to 5 ± 0.5 MPa, and the second pressure reducing valve reduces the high-pressure nitrogen to 0.5 ± 0.1 MPa.

[0035] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0036] 1. The present invention controls the opening and closing of the self-locking valve through a power controller, and uses the high-pressure nitrogen in the nitrogen gas cylinder to provide a gas source for opening the first air burst valve and the second air burst valve, thereby ensuring the stable and safe pressurization of the ramjet fuel tank, the oxidizer tank and the fuel tank, and providing propellant supply for the RBCC engine.

[0037] 2. The two-stage pressure reduction setting of the first pressure reducing valve and the second pressure reducing valve of the present invention ensures that the high-pressure nitrogen entering each tank meets the pressure requirements of the corresponding tank, thereby improving the safety of the pressurization process.

[0038] 3. The outlet ends of the oxidizer tank and the fuel tank of the present invention respectively adopt the first air burst valve and the second air burst valve. Compared with the method that the electric burst valve requires independent power supply, the maintenance difficulty and test risk of the nitrogen pressurization system are greatly reduced; at the same time, only the self-locking valve needs to be powered separately, thereby optimizing the power supply method and improving the power supply safety.

[0039] 4. The settings of the first safety valve and the second safety valve of the present invention are used to avoid the high-pressure nitrogen being relieved in time through the first safety valve and / or the second safety valve when a certain valve fails during operation, thereby preventing the corresponding pipeline or tank from bursting due to overpressure.

[0040] 5. The present invention provides a nitrogen pressurization system for an RBCC engine, which uses a combination of a self-locking valve and an air burst valve to replace multiple electric burst valves, reduces the complexity of the nitrogen pressurization system, and improves the testability and safety of system use and maintenance.

[0041] 6. The present invention also provides a nitrogen pressurization method for an RBCC engine, which is safe, simple and efficient in operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is a schematic structural diagram of an embodiment of a nitrogen pressurization system for an RBCC engine tank of the present invention.

[0043] The description of the reference numerals is as follows:

[0044] 1 - Nitrogen gas cylinder, 11 - Inflation and deflation valve, 12 - Self - locking valve, 121 - First branch, 13 - First - stage pressure reducing valve, 131 - Second branch, 14 - Second - stage pressure reducing valve, 15 - First safety valve, 16 - Second safety valve, 2 - Ram - jet fuel storage tank, 21 - First ventilation valve, 22 - Fuel filling and discharging valve, 23 - Filter, 3 - Oxidizer storage tank, 31 - Second ventilation valve, 32 - Oxidizer filling and discharging valve, 33 - First gas explosion valve, 34 - First isolation valve, 4 - Fuel storage tank, 41 - Third ventilation valve, 42 - Fuel filling and discharging valve, 43 - Second gas explosion valve, 44 - Second isolation valve, 5 - Power controller. Detailed implementation manners

[0045] To make the objectives, advantages, and features of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Those skilled in the art should understand that these implementation manners are only used to explain the technical principles of the present invention, and the purpose is not to limit the protection scope of the present invention.

[0046] As Figure 1 shown, this embodiment provides a nitrogen boosting system for an RBCC engine, including a nitrogen gas cylinder 1, a ram - jet fuel storage tank 2, an oxidizer storage tank 3, a fuel storage tank 4, and a power controller 5.

[0047] The nitrogen gas cylinder 1 is used to store high - pressure nitrogen. The inlet end of the nitrogen gas cylinder 1 is provided with an inflation and deflation valve 11 for controlling the filling of high - pressure nitrogen. The specific size of the nitrogen gas cylinder 1 is determined according to the required amount of high - pressure nitrogen. The outlet end of the nitrogen gas cylinder 1 is connected to the inlet end of the ram - jet fuel storage tank 2 through a pipeline, and a self - locking valve 12, a first - stage pressure reducing valve 13, and a second - stage pressure reducing valve 14 are arranged in sequence on this pipeline; among them, the self - locking valve 12 is arranged close to the nitrogen gas cylinder 1. In the initial state, both the inflation and deflation valve 11 and the self - locking valve 12 are in the closed state, so as to enclose the high - pressure nitrogen in the nitrogen gas cylinder 1. The initial pressure of the nitrogen gas cylinder 1 is about 30 - 35 MPa. The first - stage pressure reducing valve 13 and the second - stage pressure reducing valve 14 are used to perform two - stage decompression on the high - pressure nitrogen in sequence to ensure that the pressure of the nitrogen entering the corresponding storage tank meets the preset requirements.

[0048] The power controller 5 is electrically connected to the self - locking valve 12 and is used to control the opening and closing of the self - locking valve 12. When it is necessary to boost the pressure of each storage tank, the power controller 5 issues an instruction to open the self - locking valve 12, then the high - pressure nitrogen in the nitrogen gas cylinder 1 provides a high - pressure gas source for the ram - jet fuel storage tank 2, the oxidizer storage tank 3, and the fuel storage tank 4 respectively. When it is necessary to stop working, the power controller 5 issues an instruction again to close the self - locking valve 12, the high - pressure nitrogen is enclosed in the nitrogen gas cylinder 1, and the downstream storage tanks lose the extrusion gas, so the propellant supply stops.

[0049] In the present invention, only by supplying power to control the self-locking valve 12 at the outlet end of the nitrogen gas cylinder 1 through the power controller 5, the nitrogen gas extrusion type pressurization of the ramjet fuel tank 2, the oxidizer tank 3, and the fuel tank 4 can be realized.

[0050] The ramjet fuel tank 2 is used for storing fuel. A first ventilation port is further provided at the inlet end of the ramjet fuel tank 2, and a first ventilation valve 21 is installed on the first ventilation port. Two pipelines are provided at the outlet end of the ramjet fuel tank 2. One of the pipelines is used for connecting the fuel storage unit, and a fuel filling and discharging valve 22 is provided on this pipeline; the other pipeline is used for connecting the ramjet combustion chamber, and a filter 23 is also installed on this pipeline. When fuel needs to be filled, the first ventilation valve 21 is opened, and the ramjet fuel tank 2 is filled with fuel at low pressure through the fuel filling and discharging valve 22. In this process, the purpose of opening the first ventilation valve 21 is to timely discharge the gas in the ramjet fuel tank 2 during the fuel filling process, so as to ensure the safety of fuel filling; after the filling is completed, the first ventilation valve 21 and the fuel filling and discharging valve 22 are closed to ensure the sealing performance of the ramjet fuel tank 2.

[0051] The oxidizer tank 3 is used for storing oxidizer. A second ventilation port is further provided at the inlet end of the oxidizer tank 3, and a second ventilation valve 31 is installed on the second ventilation port. Two pipelines are provided at the outlet end of the oxidizer tank 3. One of the pipelines is used for communicating with the oxidizer storage unit, and an oxidizer filling and discharging valve 32 is installed on this pipeline; the other pipeline is used for connecting the rocket thrust chamber, and a first gas explosion valve 33 is installed on this pipeline. When rocket oxidizer needs to be filled, the second ventilation valve 31 is opened, and the oxidizer is filled at low pressure through the oxidizer filling and discharging valve 32. Similarly, in this process, the second ventilation valve 31 needs to be opened to timely discharge the gas in the oxidizer tank 3; after the filling is completed, the second ventilation valve 31 and the oxidizer filling and discharging valve 32 are closed to ensure the sealing performance of the oxidizer tank 3.

[0052] The fuel tank 4 is used for storing fuel. A third ventilation port is further provided at the inlet end of the fuel tank 4, and a third ventilation valve 41 is installed on the third ventilation port. Two pipelines are provided at the outlet end of the fuel tank 4. One of the pipelines is used for connecting the fuel storage unit, and a fuel filling and discharging valve 42 is installed on this pipeline; the other pipeline is used for connecting the rocket thrust chamber, and a second gas explosion valve 43 is installed on this pipeline. When rocket fuel needs to be filled, the third ventilation valve 41 is opened, and the fuel is filled at low pressure through the fuel filling and discharging valve 42. Similarly, in this process, the third ventilation valve 41 needs to be opened to timely discharge the gas in the fuel tank 4; after the filling is completed, the fuel filling and discharging valve 42 and the third ventilation valve 41 are closed to ensure the sealing performance of the fuel tank 4.

[0053] In this embodiment, a first branch 121 is provided on the pipeline between the self-locking valve 12 and the first-stage pressure reducing valve 13. One end of the first branch 121 away from the self-locking valve 12 is respectively connected to the first air-burst valve 33 and the second air-burst valve 43. The high-pressure nitrogen gas from the nitrogen gas cylinder 1 passes through the self-locking valve 12 and then through the first branch 121 and reaches the first air-burst valve 33 and the second air-burst valve 43 respectively, so as to provide a high-pressure gas source for the first air-burst valve 33 and the second air-burst valve 43 and open them.

[0054] A second branch 131 is provided on the pipeline between the first-stage pressure reducing valve 13 and the second-stage pressure reducing valve 14. One end of the second branch 131 away from the first-stage pressure reducing valve 13 is respectively connected to the inlet ends of the oxidizer storage tank 3 and the fuel storage tank 4, and a first isolation valve 34 and a second isolation valve 44 are respectively installed near the oxidizer storage tank 3 and the fuel storage tank 4. The high-pressure nitrogen gas from the nitrogen gas cylinder 1 passes through the self-locking valve 12 and the first-stage pressure reducing valve 13, and the pressure drops to within 10 Mpa. Then, one of the high-pressure nitrogen gas passes through the second branch 131 and reaches the first isolation valve 34 and the second isolation valve 44 respectively, which is used to ensure the tightness of the oxidizer storage tank 3 and the fuel storage tank 4. The first isolation valve 34 and the second isolation valve 44 in this embodiment are preferably diaphragm valves. The diaphragm valves are broken and opened under the impact of high-pressure nitrogen gas, then the high-pressure nitrogen gas enters the oxidizer storage tank 3 and the fuel storage tank 4 through the corresponding diaphragm valves respectively to pressurize them. Then, the oxidizer in the oxidizer storage tank 3 and the fuel in the fuel storage tank 4 enter the rocket thrust chamber through the first air-burst valve 33 and the second air-burst valve 43 respectively under the extrusion of nitrogen gas, and a combustion reaction occurs in the rocket thrust chamber, providing the necessary conditions for the start of the engine.

[0055] The high-pressure nitrogen gas from the nitrogen gas cylinder 1 passes through the self-locking valve 12 and the first-stage pressure reducing valve 13, and the pressure drops to within 10 Mpa. Then, another high-pressure nitrogen gas passes through the second-stage pressure reducing valve 14 again and drops to within 1 Mpa, and then enters the ramjet fuel storage tank 2 through the pipeline to pressurize it. When the nitrogen gas pressure in the ramjet fuel storage tank 2 reaches a certain value, the fuel will be extruded through the pipeline to the downstream ramjet combustion chamber. A filter 23 is also provided on this pipeline, which is mainly used to filter impurities in the fuel, so as to ensure stable combustion of the fuel in the ramjet combustion chamber. In addition, in order to improve the safety of the nitrogen gas pressurization system, a first safety valve 15 is also provided on the pipeline between the first-stage pressure reducing valve 13 and the second-stage pressure reducing valve 14 in this embodiment; a second safety valve 16 is provided on the pipeline between the second-stage pressure reducing valve 14 and the ramjet fuel storage tank 2. When a certain valve fails during operation, the high-pressure nitrogen gas in the pipeline can be relieved through the corresponding safety valve, so as to prevent the corresponding pipeline or storage tank from bursting due to overpressure.

[0056] In this embodiment, the stamping fuel tank 2, the oxidizer tank 3, and the fuel tank 4 all include adjacent gas cavities and liquid cavities. The gas cavity is used to introduce corresponding high-pressure nitrogen gas, and the liquid cavity is used to fill the corresponding fuel, oxidizer, or fuel. When the air pressure of the high-pressure nitrogen gas in each tank reaches a predetermined amount, it will squeeze the adjacent walls of the gas cavity and the liquid cavity, and extrude the corresponding substance (fuel, oxidizer, or fuel) in the liquid cavity out of the corresponding tank, thereby realizing the supply of propellants for the RBCC engine.

[0057] Meanwhile, this embodiment also provides a nitrogen gas pressurization method for an RBCC engine, including the following steps:

[0058] Step 1: Assemble the nitrogen gas pressurization system of the RBCC engine in this embodiment, and close the self-locking valve 12 through the power controller 5. At this time, both the first-stage pressure reducing valve 13 and the second-stage pressure reducing valve 14 are in the open state.

[0059] Step 2: Respectively fill a predetermined amount of high-pressure nitrogen gas into the nitrogen gas cylinder 1, fill a predetermined amount (calculated according to specific requirements) of fuel into the stamping fuel tank 2, fill a predetermined amount of oxidizer into the oxidizer tank 3, and fill a predetermined amount of fuel into the fuel tank 4. The specific filling process is as follows:

[0060] 2.1. Keep the charging and discharging valve 11, the first ventilation valve 21, the fuel filling and discharging valve 22, the second ventilation valve 31, the oxidizer filling and discharging valve 32, the first air explosion valve 33, the third ventilation valve 41, the fuel filling and discharging valve 42, and the second air explosion valve 43 all in the closed state.

[0061] 2.2. Open the charging and discharging valve 11, and fill a predetermined amount of high-pressure nitrogen gas into the nitrogen gas cylinder 1. After filling, close the charging and discharging valve 11.

[0062] 2.3. Open the first ventilation valve 21 and the fuel filling and discharging valve 22, and fill a predetermined amount of fuel into the stamping fuel tank 2. After filling, close the first ventilation valve 21 and the fuel filling and discharging valve 22.

[0063] 2.4. Open the second ventilation valve 31 and the oxidizer filling and discharging valve 32, and fill a predetermined amount of oxidizer into the oxidizer tank 3. After filling, close the second ventilation valve 31 and the oxidizer filling and discharging valve 32.

[0064] 2.5. Open the third ventilation valve 41 and the fuel filling and discharging valve 42, and fill a predetermined amount of fuel into the fuel tank 4. After filling, close the third ventilation valve 41 and the fuel filling and discharging valve 42.

[0065] Step 3: Open the self-locking valve 12 through the power controller 5. Then the high-pressure nitrogen is divided into two paths after passing through the self-locking valve 12. One path of the high-pressure nitrogen reaches the first air-burst valve 33 and the second air-burst valve 43 respectively after passing through the first branch 121, opening the first air-burst valve 33 and the second air-burst valve 43 to provide a passage for the subsequent extrusion of the oxidant and fuel.

[0066] The other path of the high-pressure nitrogen is reduced in pressure to 5 ± 0.5 MPa through the first-stage pressure reducing valve 13. This pressure is slightly higher than that after being divided into two paths again. One path passes through the second branch 131 to reach the first isolation valve 34 and the second isolation valve 44 respectively. The first isolation valve 34 and the second isolation valve 44 are opened under the action of the high-pressure nitrogen, so that the high-pressure nitrogen enters the oxidant storage tank 3 and the fuel storage tank 4 respectively. At this time, the pressure of the nitrogen entering the oxidant storage tank 3 and the fuel storage tank 4 is slightly higher than the internal pressure of the oxidant storage tank 3 and the fuel storage tank 4. If it is too low, the corresponding oxidant or fuel cannot be extruded, and if it is too high, it will exceed the pressure-bearing capacity of the corresponding storage tank, causing damage to the storage tank.

[0067] The remaining path of the high-pressure nitrogen after being reduced in pressure by the first-stage pressure reducing valve 13 is further reduced to 0.3 MPa - 0.6 MPa after passing through the second-stage pressure reducing valve 14, and then enters the ramjet fuel storage tank 2. The purpose of the second-stage pressure reduction is to make the air pressure entering the ramjet fuel storage tank 2 slightly higher than its internal pressure. If it is too low, the fuel cannot be extruded, and if it is too high, it will exceed the pressure-bearing capacity of the ramjet fuel storage tank 2, causing damage to the ramjet fuel storage tank 2.

[0068] Step 4: When the high-pressure nitrogen in each storage tank reaches the predetermined amount, the high-pressure nitrogen will extrude the fuel from the ramjet fuel storage tank 2 into the combustion chamber of the RBCC engine. At the same time, the oxidant and fuel are respectively extruded from the oxidant storage tank 3 and the fuel storage tank 4 into the thrust chamber of the RBCC engine, thus completing the nitrogen pressurization of the RBCC engine and providing a booster supply for the engine.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present invention.

Claims

1. A nitrogen supercharging system for an RBCC engine, characterized in that: It includes a nitrogen gas cylinder (1), a ramjet fuel tank (2), an oxidizer tank (3), a fuel tank (4), and a power controller (5); The nitrogen gas cylinder (1) is used to store high-pressure nitrogen; the nitrogen gas cylinder (1) is connected to the inlet end of the ramjet fuel tank (2) through a pipeline, and a self-locking valve (12), a first pressure reducing valve (13), and a second pressure reducing valve (14) are successively arranged on this pipeline; the self-locking valve (12) is arranged close to the nitrogen gas cylinder (1), and the power controller (5) is electrically connected to the self-locking valve (12) to control the opening and closing of the self-locking valve (12); the first pressure reducing valve (13) and the second pressure reducing valve (14) are used to successively perform two-stage decompression on the high-pressure nitrogen; The ramjet fuel tank (2) is used to store fuel, and its outlet end is used to be connected to the ramjet combustion chamber through a pipeline; the oxidizer tank (3) is used to store oxidizer, and its outlet end is used to be connected to the rocket thrust chamber through a pipeline, and a first air burst valve (33) is installed on this pipeline; the fuel tank (4) is used to store fuel, and its outlet end is used to be connected to the rocket thrust chamber through a pipeline, and a second air burst valve (43) is installed on this pipeline; A first branch (121) is arranged on the pipeline between the self-locking valve (12) and the first pressure reducing valve (13), and one end of the first branch (121) far from the self-locking valve (12) is respectively connected to the first air burst valve (33) and the second air burst valve (43); A second branch (131) is arranged on the pipeline between the first pressure reducing valve (13) and the second pressure reducing valve (14), and one end of the second branch (131) far from the first pressure reducing valve (13) is respectively communicated with the inlet ends of the oxidizer tank (3) and the rocket fuel tank (4), and a first isolation valve (34) and a second isolation valve (44) are respectively installed at the positions where the second branch is close to the oxidizer tank (3) and the rocket fuel tank (4).

2. The nitrogen supercharging system for an RBCC engine according to claim 1, characterized in that: The inlet end of the nitrogen gas cylinder (1) is provided with a charging and discharging valve (11) for controlling the charging of high-pressure nitrogen; the outlet end is connected to the inlet end of the ramjet fuel tank (2) through a pipeline; The inlet end of the ramjet fuel tank (2) is further provided with a first ventilation port, and a first ventilation valve (21) is installed on the first ventilation port; the outlet end is provided with two pipelines, one of which is used to connect the fuel storage unit, and a fuel filling and discharging valve (22) is arranged on this pipeline; the other pipeline is used to connect the ramjet combustion chamber; The inlet end of the oxidizer tank (3) is further provided with a second ventilation port, and a second ventilation valve (31) is installed on the second ventilation port; the outlet end is provided with two pipelines, one of which is used to communicate with the oxidizer storage unit, and an oxidizer filling and discharging valve (32) is installed on this pipeline, and the other pipeline is used to connect the rocket thrust chamber; The inlet end of the fuel tank (4) is further provided with a third vent, and a third vent valve (41) is installed on the third vent; the outlet end is provided with two pipelines, one of which is used to connect the fuel storage unit, and a fuel filling and discharging valve (42) is installed on this pipeline; the other pipeline is used to connect the rocket thrust chamber.

3. The nitrogen gas pressurization system of the RBCC engine according to claim 1 or 2, characterized in that: A first safety valve (15) is further provided on the pipeline between the primary pressure reducing valve (13) and the secondary pressure reducing valve (14); a second safety valve (16) is provided on the pipeline between the secondary pressure reducing valve (14) and the ramjet fuel tank (2).

4. The nitrogen gas pressurization system of the RBCC engine according to claim 3, characterized in that: A filter (23) is installed on the pipeline connecting the ramjet fuel tank (2) and the ramjet combustion chamber.

5. The nitrogen gas pressurization system of the RBCC engine according to claim 4, characterized in that: Both the first isolation valve (34) and the second isolation valve (44) are diaphragm valves.

6. The nitrogen gas pressurization system of the RBCC engine according to claim 5, characterized in that: The ramjet fuel tank (2), the oxidizer tank (3) and the fuel tank (4) all include adjacent gas chambers and liquid chambers. The gas chambers are used to introduce corresponding high-pressure nitrogen gas, and the liquid chambers are used to fill the corresponding fuel, oxidizer or fuel.

7. A nitrogen supercharging method for an RBCC engine, characterized in that, Including the following steps: Step 1, assemble the nitrogen gas pressurization system of the RBCC engine according to any one of claims 1 to 6, close the self-locking valve (12) through the power controller (5), and at the same time open the primary pressure reducing valve (13) and the secondary pressure reducing valve (14); Step 2, respectively fill a predetermined amount of high-pressure nitrogen gas into the nitrogen gas cylinder (1), fill a predetermined amount of fuel into the ramjet fuel tank (2), fill a predetermined amount of oxidizer into the oxidizer tank (3), and fill a predetermined amount of fuel into the fuel tank (4); Step 3, open the self-locking valve (12) through the power controller (5), and the high-pressure nitrogen gas is divided into two paths after passing through the self-locking valve (12). One path of high-pressure nitrogen gas opens the first gas explosion valve (33) and the second gas explosion valve (43) after passing through the first branch (121); the other path of high-pressure nitrogen gas is divided into two paths again after passing through the primary pressure reducing valve (13). One path enters the oxidizer tank (3) and the fuel tank (4) through the first isolation valve (34) and the second isolation valve (44) respectively through the second branch (131), and the remaining one path enters the ramjet fuel tank (2) after passing through the secondary pressure reducing valve (14); Step 4, the high-pressure nitrogen gas extrudes the fuel from the ramjet fuel tank (2) into the combustion chamber of the RBCC engine, and extrudes the oxidizer and fuel from the oxidizer tank (3) and the fuel tank (4) into the thrust chamber of the RBCC engine respectively, so as to complete the nitrogen gas pressurization of the RBCC engine.

8. The nitrogen boosting method of the RBCC engine according to claim 7, characterized in that, Step 2 specifically is: 2.

1. Keep the charge and discharge valve (11), the first ventilation valve (21), the fuel filling and draining valve (22), the second ventilation valve (31), the oxidizer filling and draining valve (32), the first air explosion valve (33), the third ventilation valve (41), the fuel filling and draining valve (42) and the second air explosion valve (43) closed; 2.

2. Open the charge and discharge valve (11), and fill a predetermined amount of high-pressure nitrogen into the nitrogen gas cylinder (1). After filling, close the charge and discharge valve (11); 2.

3. Open the first ventilation valve (21) and the fuel filling and draining valve (22), and fill a predetermined amount of fuel into the ramjet fuel tank (2). After filling, close the first ventilation valve (21) and the fuel filling and draining valve (22); 2.

4. Open the second ventilation valve (31) and the oxidizer filling and draining valve (32), and fill a predetermined amount of oxidizer into the oxidizer tank (3). After filling, close the second ventilation valve (31) and the oxidizer filling and draining valve (32); 2.

5. Open the third ventilation valve (41) and the fuel filling and draining valve (42), and fill a predetermined amount of fuel into the fuel tank (4). After filling, close the third ventilation valve (41) and the fuel filling and draining valve (42).

9. The nitrogen gas pressurization method of the RBCC engine according to claim 7, characterized in that: In step 3, the primary pressure reducing valve (13) reduces the high-pressure nitrogen to 5 ± 3 MPa, and the secondary pressure reducing valve (14) reduces the high-pressure nitrogen to 0.5 ± 0.3 MPa.

10. The nitrogen gas pressurization method of the RBCC engine according to claim 9, characterized in that: In step 3, the primary pressure reducing valve (13) reduces the high-pressure nitrogen to 5 ± 0.5 MPa, and the secondary pressure reducing valve (14) reduces the high-pressure nitrogen to 0.5 ± 0.1 MPa.

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