Pressure-adjustable fuel gas pressurization system and RBCC engine

Abstract

The invention discloses a pressure-adjustable fuel gas pressurization system and an RBCC engine. The technical problem that an existing pressurization system cannot meet the variable working condition adjustment requirement of a thrust chamber of the RBCC engine is solved. The system comprises a pressurizing storage tank, a gunpowder starter, a generator, an oxidizing agent storage tank, a fuel storage tank and a controller, the inlet end of the pressurizing storage tank is connected with the gunpowder starter, and the outlet end is connected with the inlet end of the generator through the first electric explosion valve, the electric pump and the first one-way valve; a pressure sensor is installed at the outlet end of the generator and connected with the controller. The outlet end of the generator is connected with the inlet end of the pressurizing storage box and is connected with the inlet ends of the oxidant storage box and the fuel storage box; the outlet ends of the oxidant storage tank and the fuel storage tank are respectively connected with the thrust chamber; a pressure release valve is mounted between the outlet end of the electric pump and the outlet end of the oxidant valve or the fuel valve; the controller is connected with the gunpowder starter, the electric pump and all the valves and used for sending out corresponding control instructions.

Description

Technical Field

[0001] The present invention relates to a rocket-based combined cycle engine, and particularly to a gas pressurization system with adjustable pressure and an RBCC engine based on the pressurization system. Background Art

[0002] A rocket-based combined cycle engine (RBCC engine) is a composite engine formed by the organic combination of a rocket engine and a ramjet engine. It has flexible working modes, strong maneuverability, and capabilities such as short-time acceleration and long-range flight. It is one of the ideal power systems for hypersonic aircraft, near-space aircraft, and other equipment.

[0003] The propellant storage and supply system of the RBCC engine takes into account the requirements of both engines and has characteristics such as high and low pressure compounding, multi-medium management, and wide-range regulation. However, due to its many thermal components and management components, the system structure is relatively complex. For hypersonic aircraft, the special lift body configuration determines that the loading space of its propellant storage and supply system is limited. At the same time, the long-range cruise working mode of the aircraft requires that its storage and supply system must increase the fuel loading. Therefore, to solve the above two contradictions, it can only be achieved by optimizing the structure of the storage and supply system and reducing the volume ratio of the engine.

[0004] The existing propellant storage and supply systems of RBCC engines mostly adopt an extrusion conveying system, that is, high-pressure gas cylinders are used to store gas to pressurize each storage tank of the engine. This system is generally applicable to scenarios with low propellant demand. When the chamber pressure of the rocket thrust chamber is high and the volume of the storage tank is large, due to the large consumption of gas, the volume ratio of the gas cylinder increases, which in turn affects the compact and lightweight design of the RBCC engine, and ultimately affects the fuel loading and range of the aircraft.

[0005] To solve the above problems, Chinese Patent No. CN 111946490 A discloses a gas pressurization attitude and orbit control propellant system based on an electric pump. It mainly provides high-pressure extrusion gas for each storage tank through a gas pressurization module based on an electric pump and keeps the pressurization pressure fixed, so as to provide a constant medium supply for multiple downstream thrust chambers. However, this type of pressurization system belongs to a constant pressure control system. Since the thrust chamber of the RBCC engine needs to have the ability to adjust under variable working conditions to adapt to the working modes of the engine to perform functions such as injection, combustion assistance, and thrust augmentation, using the above pressurization system cannot meet the variable working condition adjustment requirements of the thrust chamber. Summary of the Invention

[0006] The purpose of the present invention is to solve the technical problem that the existing pressurization system cannot meet the variable working condition adjustment requirements of the thrust chamber of the RBCC engine, and provide a gas pressurization system with adjustable pressure and an RBCC engine.

[0007] To achieve the above object, the technical solution provided by the present invention is as follows:

[0008] A gas boosting system with adjustable pressure, which is used to provide oxidant and fuel for a thrust chamber. The special feature is that it includes a boosting storage tank, a pyrotechnic initiator, a generator, an oxidant storage tank, a fuel storage tank and a controller;

[0009] The boosting storage tank is used to store the boosting medium. Its inlet end is connected to the pyrotechnic initiator, and its outlet end is sequentially connected to the inlet end of the generator through a first electric blasting valve, an electric pump and a first one-way valve; a pressure sensor is installed at the outlet end of the generator, and the pressure sensor is connected to the controller, which is used to collect the pressure signal and transmit it to the controller;

[0010] The outlet end of the generator is connected to the inlet end of the boosting storage tank through a second one-way valve, and at the same time is respectively connected to the inlet ends of the oxidant storage tank and the fuel storage tank through pipelines; the outlet end of the oxidant storage tank is sequentially connected to the thrust chamber through a second electric blasting valve and an oxidant valve; the outlet end of the fuel storage tank is sequentially connected to the thrust chamber through a third electric blasting valve and a fuel valve;

[0011] A pressure relief pipeline is provided between the outlet end of the electric pump and the outlet end of the oxidant valve or the fuel valve, and a pressure relief valve is installed on this pressure relief pipeline;

[0012] The controller is respectively connected to the pyrotechnic initiator, the first electric blasting valve, the electric pump, the second electric blasting valve, the oxidant valve, the third electric blasting valve, the fuel valve and the pressure relief valve, and is used to issue corresponding control instructions respectively.

[0013] Furthermore, a safety valve is also provided on the pressure relief pipeline and is installed in parallel with the pressure relief valve, and the inlet of the safety valve faces the outlet end of the electric pump.

[0014] The present invention also provides an RBCC engine, and its special feature is that:

[0015] It includes a gas boosting system with adjustable pressure as described above, a thrust chamber, and a ramjet engine;

[0016] The inlet end of the thrust chamber is respectively connected to the outlets of the oxidant valve and the fuel valve, and the outlet end is connected to the combustion chamber of the ramjet engine.

[0017] The present invention also provides another gas boosting system with adjustable pressure, and its special feature is that:

[0018] It includes a boosting storage tank, a pyrotechnic initiator, a generator, an oxidant storage tank and a controller;

[0019] The pressurized storage tank is used to store the pressurizing medium, and the pressurizing medium is fuel; the inlet end of the pressurized storage tank is connected to the pyrotechnic initiator, and the outlet end is sequentially connected to the inlet end of the generator through the first electric explosion valve, the electric pump and the first check valve; the outlet end of the first electric explosion valve is connected to the thrust chamber through the fuel valve; a pressure sensor is installed at the outlet end of the generator, and the pressure sensor is connected to the controller for collecting the pressure signal and transmitting it to the controller;

[0020] The outlet end of the generator is connected to the inlet end of the pressurized storage tank through the second check valve, and at the same time is connected to the inlet end of the oxidizer storage tank through a pipeline; the outlet end of the oxidizer storage tank is sequentially connected to the thrust chamber through the second electric explosion valve and the oxidizer valve;

[0021] A pressure relief pipeline is provided between the outlet end of the electric pump and the outlet end of the fuel valve, and a pressure relief valve is installed on the pressure relief pipeline;

[0022] The controller is respectively connected to the pyrotechnic initiator, the first electric explosion valve, the electric pump, the second electric explosion valve, the oxidizer valve, the fuel valve and the pressure relief valve for respectively sending out corresponding control instructions.

[0023] Further, a safety valve is also provided on the pressure relief pipeline and is installed in parallel with the pressure relief valve, and the inlet of the safety valve faces the outlet end of the electric pump.

[0024] The present invention also provides another RBCC engine, which is characterized in that:

[0025] It includes the above-mentioned another gas pressurization system with adjustable pressure, a thrust chamber, and a ramjet engine;

[0026] The inlet end of the thrust chamber is respectively connected to the outlets of the oxidizer valve and the fuel valve, and the outlet end is connected to the combustion chamber of the ramjet engine.

[0027] The present invention also provides a third gas pressurization system with adjustable pressure, which is characterized in that:

[0028] It includes a pressurized storage tank, a pyrotechnic initiator, a generator, a fuel storage tank and a controller;

[0029] The pressurized storage tank is used to store the pressurizing medium, and the pressurizing medium is oxidizer; the inlet end of the pressurized storage tank is connected to the pyrotechnic initiator, and the outlet end is sequentially connected to the inlet end of the generator through the first electric explosion valve, the electric pump and the first check valve; the outlet end of the first electric explosion valve is connected to the thrust chamber through the oxidizer valve; a pressure sensor is installed at the outlet end of the generator, and the pressure sensor is connected to the controller for collecting the pressure signal and transmitting it to the controller;

[0030] The outlet end of the generator is connected to the inlet end of the pressurized storage tank through a second one-way valve, and is also connected to the inlet end of the fuel storage tank through a pipeline; the outlet end of the fuel storage tank is sequentially connected to the thrust chamber through a third electric blasting valve and a fuel valve;

[0031] A pressure relief pipeline is provided between the outlet end of the electric pump and the outlet end of the oxidant valve, and a pressure relief valve is installed on this pressure relief pipeline;

[0032] The controller is respectively connected to the pyrotechnic initiator, the first electric blasting valve, the electric pump, the third electric blasting valve, the oxidant valve, the fuel valve and the pressure relief valve, and is used to issue corresponding control instructions respectively.

[0033] Furthermore, a safety valve installed in parallel with the pressure relief valve is also provided on the pressure relief pipeline, and the inlet of the safety valve faces the outlet end of the electric pump.

[0034] The present invention also provides a third type of RBCC engine, and its special feature lies in:

[0035] Including the above-mentioned third type of gas pressurization system with adjustable pressure, a thrust chamber, and a ramjet engine;

[0036] The inlet end of the thrust chamber is respectively connected to the outlets of the oxidant valve and the fuel valve, and the outlet end is connected to the combustion chamber of the ramjet engine.

[0037] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0038] 1. For the gas pressurization system with adjustable pressure provided by the present invention, the pressurized storage tank, the oxidant storage tank and the fuel storage tank are separately arranged. When the system is not working, the first electric blasting valve, the second electric blasting valve and the third electric blasting valve are all in the closed state, so that each storage tank is in a closed state; when pressure adjustment is required, through the joint cooperation of the pressure sensor, the controller, the electric pump and the pressure relief valve, the system pressure can be adjusted to a predetermined value, so as to meet the requirements of large-range variable working condition adjustment of the thrust chamber of the RBCC engine. The system is simple, flexible and has strong adaptability.

[0039] 2. In the gas pressurization system with adjustable pressure provided by the present invention, by providing a safety valve installed in parallel with the pressure relief valve on the pressure relief pipeline, it is beneficial for the system to quickly and safely relieve pressure under overpressure faults, thereby improving the safety of the system.

[0040] 3. The gas pressurization system with adjustable pressure provided by the present invention does not require additional adjustment mechanisms. The system scheme is simple and the overall assembly structure is compact, meeting the use requirements of the RBCC engine.

[0041] 4. According to the design requirements, the present invention can also share the pressurized tank with the oxidizer tank or the fuel tank, thereby making the overall structure more compact and meeting the compact and lightweight design requirements of the RBCC engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 It is a schematic structural diagram of the first embodiment of the present invention.

[0043] Figure 2 It is a schematic structural diagram of the second embodiment of the present invention.

[0044] Figure 3 It is a schematic structural diagram of the third embodiment of the present invention.

[0045] The description of the reference numerals in the drawings is as follows:

[0046] 1 - Pressurized tank, 2 - Pyrotechnic initiator, 3 - Generator, 4 - Oxidizer tank, 5 - Fuel tank, 6 - Controller, 7 - First electric explosion valve, 8 - Electric pump, 9 - First check valve, 10 - Pressure sensor, 11 - Second check valve, 12 - Second electric explosion valve, 13 - Oxidizer valve, 14 - Third electric explosion valve, 15 - Fuel valve, 16 - Thrust chamber, 17 - Pressure relief pipeline, 18 - Pressure relief valve, 19 - Safety valve. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0047] The design concept of the present invention is as follows: In the existing technical solutions, the system pressure is a constant value and cannot meet the requirements of large - range variable - condition regulation of the RBCC thrust chamber. Based on this, the present invention sets the system pressure according to the working mode of the thrust chamber, and gives the rotational speed and start command of the electric pump according to the pressure closed - loop requirement, thereby ensuring the supply matching of the thrust chamber in different modes. At the same time, a pressure relief valve 18 is set on the outlet branch of the electric pump 8 as the pressure relief channel for the pressurizing medium. When the thrust chamber switches from a high - condition to a low - condition, the pressure relief valve 18 is electrically opened. As the pressurizing medium behind the pump is discharged, the inlet pressure of the generator 3, the pressurized tank 1, the oxidizer tank 4, the fuel tank 5, and the inlet pressure of the electric pump 8 decrease in turn. When the system pressure drops to the pressure range corresponding to the low - condition of the thrust chamber, the pressure relief valve 18 is closed, and then the electric pump 8 performs rotational speed and start - stop control according to the pressure closed - loop.

[0048] 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 drawings and specific embodiments. Those skilled in the art should understand that these embodiments are only used to explain the technical principle of the present invention, and the purpose is not to limit the protection scope of the present invention.

[0049] Embodiment 1

[0050] As Figure 1As shown in the figure, this embodiment provides a gas boosting system with adjustable pressure, which includes a boosting storage tank 1, a pyrotechnic initiator 2, a generator 3, an oxidizer storage tank 4, a fuel storage tank 5, and a controller 6.

[0051] The boosting storage tank 1 is used to store the boosting medium. Its inlet end is connected to the pyrotechnic initiator 2, and its outlet end is sequentially connected to the inlet end of the generator 3 through a first electric blasting valve 7, an electric pump 8, and a first check valve 9. The inlet of the first check valve 9 faces the outlet end of the electric pump 8. A pressure sensor 10 is installed at the outlet end of the generator 3, and the pressure sensor 10 is connected to the controller 6, which is used to collect the pressure of the high-temperature gas at the outlet end of the generator 3 and transmit it to the controller 6.

[0052] The outlet end of the generator 3 is connected to the inlet end of the boosting storage tank 1 through a second check valve 11, and the inlet of the second check valve 11 faces the outlet end of the generator 3; at the same time, the outlet end of the generator 3 is also connected to the inlet ends of the oxidizer storage tank 4 and the fuel storage tank 5 through pipelines respectively. The outlet end of the oxidizer storage tank 4 is sequentially connected to the thrust chamber 16 through a second electric blasting valve 12 and an oxidizer valve 13. The outlet end of the fuel storage tank 5 is sequentially connected to the thrust chamber 16 through a third electric blasting valve 14 and a fuel valve 15.

[0053] To adjust the system pressure, this embodiment also provides a pressure relief pipeline 17 between the outlet end of the electric pump 8 and the outlet end of the oxidizer valve 13 or the fuel valve 15. A pressure relief valve 18 is installed on the pressure relief pipeline 17. When the system pressure is too high, opening the pressure relief valve 18 can reduce the system pressure to a predetermined value. The outlet end of the pressure relief pipeline 17 is located at the outlet end of the oxidizer valve 13 or the fuel valve 15, and its specific position depends on the properties of the added medium. If the boosting medium is an oxidizer, the outlet end of the pressure relief pipeline 17 is located at the outlet end of the oxidizer valve 13; if the boosting medium is a fuel, the outlet end of the pressure relief pipeline 17 is located at the outlet end of the fuel valve 15 ( Figure 1 as shown in the figure). This embodiment also provides a safety valve 19 installed in parallel with the pressure relief valve 18 on the pressure relief pipeline 17, and the inlet of the safety valve 19 faces the outlet end of the electric pump 8. The design purpose of the safety valve 19 is that when the system is over-pressurized or fails, the safety valve 19 is forced to open, and the boosting medium is directly discharged from the highest pressure point at the outlet of the electric pump 8 to the front of the thrust chamber where the pressure is lower through the safety valve 19. The discharge flow is large and the discharge effect is obvious, which can quickly solve the problem of system overpressure. When the system pressure returns to the normal value, the valve core of the safety valve 19 automatically closes under the action of the spring pre-tightening force.

[0054] In this embodiment, for the overpressure fault that may occur in the pressurization system, an emission scheme combined with the thrust chamber combustion is proposed. In the existing gas pressurization scheme, a safety valve is set on the outlet branch of the electric pump, and the outlet of the safety valve is connected to the inlet of the electric pump. When a system overpressure fault occurs, the safety valve is forced to open, and at this time, the pressurization medium flows from the outlet of the electric pump to the inlet. Since the gas pressurization system is a closed-loop system, this measure cannot solve the system overpressure problem. The scheme of this embodiment is proposed based on the closed assembly structure of the integration of the RBCC engine and the aircraft. By combining the system overpressure discharge with the thrust chamber combustion, it not only avoids the pollution of other components caused by the direct discharge of the pressurization medium into the accessory compartment, but also avoids the heat back-invasion problem caused by setting an emission port on the RBCC combustion chamber. This design method is ingenious, and the design scheme is simple and reliable.

[0055] In this embodiment, the controller 6 controls each valve. Specifically, the controller 6 is respectively connected to the pyrotechnic initiator 2, the first electric explosion valve 7, the electric pump 8, the second electric explosion valve 12, the oxidant valve 13, the third electric explosion valve 14, the fuel valve 15 and the pressure relief valve 18, and is used to issue corresponding control commands according to the pressurization requirements.

[0056] The working process of a gas pressurization system with adjustable pressure in this embodiment is as follows:

[0057] In the non-working state, the first electric explosion valve 7, the second electric explosion valve 12, and the third electric explosion valve 14 are all in the closed state, so as to seal the pressurization medium, oxidant, and fuel in the corresponding storage tanks respectively, enabling each storage tank to have the ability of long-term storage under normal pressure.

[0058] During the system startup process, first, the controller 6 sends detonation commands to the first electric explosion valve 7, the second electric explosion valve 12, and the third electric explosion valve 14 respectively, causing them to detonate and form a passage at their respective detonation points. At this time, the pressurization medium in the pressurization storage tank 1, the oxidant in the oxidant storage tank 4, and the fuel in the fuel storage tank 5 are slowly filled from the corresponding storage tanks to their downstream respectively.

[0059] Then, the controller 6 sends a detonation command to the pyrotechnic initiator 2. The pyrotechnic initiator 2 detonates and generates high-temperature gas. The high-temperature gas enters the gas cavity in the pressurization storage tank 1 along the pipeline to pressurize it; as the air pressure in the gas cavity increases, the pressurization medium is squeezed out from the liquid cavity of the pressurization storage tank 1, and then enters the electric pump 8 through the first electric explosion valve 7. At this time, the electric pump 8 is started through the controller 6 (the rotational speed of the electric pump 8 is n), and the pressurization medium is further pressurized and overcomes the spring force of the first one-way valve 9 at the inlet of the generator 3 to supply a large flow of pressurization medium to the generator 3. The pressurization medium is catalytically decomposed in the generator 3 to generate high-temperature gas.

[0060] Then, the high-temperature gas flows out of the outlet of the generator 3 and is divided into three paths (the three paths have no sequence): the first path flows into the gas chamber of the pressurized storage tank 1 to continue pressurization, forming a closed flow path of the pressurizing medium; the second path flows into the gas chamber of the oxidizer storage tank 4 for pressurization, and after pressurization, the oxidizer in the liquid chamber is extruded out and enters in front of the oxidizer valve 13; the third path flows into the gas chamber of the fuel storage tank 5 for pressurization, and after pressurization, the fuel in the liquid chamber is extruded out and enters in front of the fuel valve 15.

[0061] Finally, with the continuous generation of high-temperature gas, the pressure of the entire pressurization system gradually climbs. The system pressure is monitored in real time by the pressure sensor 10 and transmitted to the controller 6. The controller 6 determines the magnitude of this pressure: when the system pressure is less than the set pressure P1 - dP, the controller 6 sends an instruction with a rotational speed of n to the electric pump 8 again. The electric pump 8 starts again, the pressure after the pump rises, the first one-way valve 9 at the inlet end of the generator 3 is opened, the flow rate in the generator 3 increases, the system gas is replenished, and the system pressure climbs. When the system pressure reaches the set pressure range P1 + dP, the controller 6 sends an instruction with a rotational speed of zero to the electric pump 8, the electric pump 8 stops, the pressure after the pump drops suddenly, the first one-way valve 9 at the inlet end of the generator 3 closes, and the system stalls. At this time, the system startup is completed.

[0062] When the controller 6 receives any of the following working instructions, its pressure regulation method is as follows:

[0063] (1) When the controller 6 receives the working instruction for the full operating condition (or high operating condition) of the thrust chamber, it sets the system pressure within the range of P2 ± dP (i.e., the corresponding high operating condition pressure range), and determines the current system pressure: if the current system pressure is lower than the set pressure P2 - dP, the controller 6 sends an instruction with a rotational speed of n to the electric pump 8 to make the system pressure climb rapidly; when the system pressure reaches P2 + dP, the controller 6 sends an instruction with a rotational speed of zero to the electric pump 8, and at the same time opens the oxidizer valve 13 and the fuel valve 15, then the oxidizer and fuel are supplied into the thrust chamber 16 through the pipeline for mixing and combustion, generating high-temperature and high-pressure gas to provide thrust for RBCC.

[0064] (2) When the controller 11 receives the working instruction of the working condition in the thrust chamber, it sets the system pressure to the range of P3±dP (i.e., the corresponding medium working condition pressure range), and determines the current system pressure: If the current system pressure is higher than the set pressure P3+dP, the controller 6 sends an instruction with zero speed to the electric pump 8, and at the same time opens the pressure relief valve 18 of the pressurizing medium. At this time, the outlet pressure of the electric pump 8 rapidly decreases, and the system pressure decreases accordingly. When the system pressure is equal to the set pressure P3+dP, the pressure relief valve 18 of the pressurizing medium is closed, and at the same time the oxidizer valve 13 and the fuel valve 15 are opened. If the current system pressure is lower than P3-dP, the controller 6 sends an instruction with speed n to the electric pump 8, then the system pressure rapidly climbs. When the system pressure reaches P3+dP, the controller 6 sends an instruction with zero speed to the electric pump 8, and at the same time opens the oxidizer valve 13 and the fuel valve 15. The oxidizer and fuel are supplied into the thrust chamber 16 according to the corresponding supply flow rates for mixing and combustion, generating high-temperature and high-pressure gas to provide thrust for the RBCC.

[0065] (3) When the controller 6 receives the low working condition instruction of the thrust chamber, it sets the system pressure to the range of P4±dP (i.e., the corresponding low working condition pressure range), and determines the current system pressure: If the current system pressure is higher than the set pressure P4+dP, the controller 6 sends an instruction with zero speed to the electric pump 8, and at the same time opens the pressure relief valve 18 of the pressurizing medium. The outlet pressure of the electric pump 8 rapidly decreases, and the system pressure decreases accordingly. When the system pressure is equal to the set pressure P4+dP, the pressure relief valve 18 of the pressurizing medium is closed, and at the same time the oxidizer valve 13 and the fuel valve 15 are opened; If the current system pressure is lower than P4-dP, the controller 6 sends an instruction with speed n to the electric pump 8, the system pressure rapidly climbs. When the system pressure reaches P4+dP, the controller 6 sends an instruction with zero speed to the electric pump 8, and at the same time opens the oxidizer valve 13 and the fuel valve 15. Then the oxidizer and fuel are supplied into the thrust chamber 16 according to the low working condition supply flow rates for mixing and combustion, generating high-temperature and high-pressure gas to provide ignition ability and thrust for the RBCC.

[0066] During the system shutdown process, the controller 6 cuts off the power supply of the oxidizer valve 13 and the fuel valve 15 to close them, and sends an instruction with zero speed to the electric pump 8. Due to the system pressure balance, the first one-way valve 9 at the inlet end of the generator 3 closes, and there is no flow supply to the generator 3. The system maintains the current pressure and the system pressure slowly decreases as the gas pipeline of the system dissipates heat.

[0067] In summary, it can be seen that the pressure of the gas pressurization system in this embodiment can be controlled both high and low. The adjustable pressurization system meets the variable flow supply under the liquid path extrusion system, so as to meet the large-range variable working condition adjustment requirements of the thrust chamber of the RBCC engine. The system is simple, flexible and has strong adaptability.

[0068] In this embodiment, the pressurizing medium in the pressurized tank 1, the oxidizer in the oxidizer tank 4, and the fuel in the fuel tank 5 are three different media. The system pressure corresponds to the working conditions of the thrust chamber. Through dynamic closed-loop control of the system pressure, variable working condition adjustment of the thrust chamber is achieved. The liquid circuit is a simple and mature extrusion system, which can achieve large-range continuous variable flow rate adjustment without a liquid circuit adjustment mechanism, with low pressure requirements and a simple structure.

[0069] The gas pressurization system of this embodiment has the following advantages:

[0070] 1. It has the ability to adjust the system pressure and meet the supply capacity of the adjustable thrust chamber of RBCC.

[0071] The system pressure is adjusted in real time according to the working conditions of the thrust chamber. At the same time, the outlet pressure of the gas generator 3 is monitored by the pressure sensor 10 and fed back to the controller 6. The controller 6 controls the start and stop of the electric pump 8, so as to realize the closed-loop control and adjustment of the system pressure. At the same time, a pressure relief valve 18 and its switch judgment logic are added. When the system pressure is greater than the required pressure, the electric pump 8 is turned off and the pressure relief valve 18 is opened, and the pressures of the outlet of the electric pump 18, the outlet of the generator 3, the oxidizer tank 4, the fuel tank 5, the pressurized tank 1, the inlet of the electric pump 18, etc. are reduced in turn. When the system pressure drops to the upper limit of the required pressure, the pressure relief valve 18 is closed, and the pressurization system resumes closed-loop pressure control. In this scheme, the system pressure can be high or low, which can meet the propellant supply requirements of the large-range adjustable working conditions of the thrust chamber of the RBCC engine. The system is flexible, simple, and has strong adaptability.

[0072] 2. It has the ability of system overpressure self-protection and improves the system safety.

[0073] The existing gas pressurization system is a closed-loop system. If the control system fails and the electric pump runs out of control, the system pressure will rise rapidly until it exceeds the strength limit of the tank, valve, and pipeline, which is likely to cause damage to the product structure. In this embodiment, a safety valve 19 is provided. Through the interaction between the preset spring force of the valve core and the inlet liquid pressure, the safety valve channel is automatically opened and closed to automatically discharge and relieve the overpressure of the pressurizing medium. The inlet of the safety valve 19 is set at the outlet of the electric pump 8, which is the highest point of the system pressure; the outlet of the safety valve 19 is set in front of the fuel injection of the thrust chamber, which is the lowest point of the system pressure. This setting is beneficial to the rapid realization of the pressure relief of the gas pressurization system and effectively improves the system safety.

[0074] 3. The fuel path of the thrust chamber integrates the pressure relief and discharge ports of the gas pressurization system, which is beneficial to the integrated structure design of RBCC.

[0075] In this embodiment, the pressure relief port and the discharge port of the gas boosting system are integrally arranged in front of the fuel path of the thrust chamber spray, which is applicable to the application scenario of the integrated closed design of the RBCC engine and the aircraft accessory compartment. On the one hand, it avoids discharging the pressurized medium after the electric pump to the inlet of the electric pump, which cannot effectively relieve the pressure of the closed-loop system; on the other hand, it avoids discharging the boosting system to the accessory compartment, polluting the accessory compartment or causing risks such as deflagration; on the third hand, it avoids discharging the pressurized medium to high-temperature components such as the RBCC engine combustion chamber or the tail nozzle, resulting in the problem of thermal back-dipping. The system pressure relief and discharge medium in this embodiment are both normal-temperature pressurized liquids, and the pipelines and valves are easy to manage, the structure is simple, the effect is obvious, which is beneficial to the integrated design of the RBCC engine and the aircraft.

[0076] In addition, this embodiment also provides an RBCC engine, which includes the above-mentioned gas boosting system with adjustable pressure, a thrust chamber 16 and a ramjet engine; wherein, the inlet end of the thrust chamber 16 is respectively connected to the outlets of an oxidizer valve 13 and a fuel valve 15, and the outlet end is connected to the combustion chamber of the ramjet engine.

[0077] Embodiment Two

[0078] As Figure 2 shown, this embodiment provides another gas boosting system with adjustable pressure, which includes a boosting storage tank 1, a pyrotechnic initiator 2, a generator 3, an oxidizer storage tank 4 and a controller 6. The difference between this embodiment and Embodiment One is that this embodiment has no independent fuel storage tank, and the fuel storage tank shares the boosting storage tank 1, that is, the pressurized medium in the boosting storage tank 1 is fuel.

[0079] The outlet end of the generator 3 is connected to the inlet end of the boosting storage tank 1 through a second one-way valve 11, and is simultaneously connected to the inlet end of the oxidizer storage tank 4 through a pipeline; the outlet end of the oxidizer storage tank 4 is sequentially connected to the thrust chamber 16 through a second electric blasting valve 12 and an oxidizer valve 13.

[0080] A pressure relief pipeline 17 is provided between the outlet end of the electric pump 8 and the outlet end of the fuel valve 15, and a pressure relief valve 18 is installed on this pressure relief pipeline 17. At the same time, a safety valve 19 is also installed on the pressure relief pipeline 17 in parallel with the pressure relief valve 18, and the inlet of the safety valve 19 faces the outlet end of the electric pump 8.

[0081] The controller 6 is respectively connected to the pyrotechnic initiator 2, the first electric blasting valve 7, the electric pump 8, the second electric blasting valve 12, the oxidizer valve 13, the fuel valve 15 and the pressure relief valve 18, and is used to issue corresponding control instructions respectively.

[0082] The pressure adjustment method of this embodiment is the same as that of Embodiment One, and will not be elaborated here.

[0083] Embodiment Three

[0084] AsFigure 3 As shown, this embodiment also provides a third gas pressure - adjustable boosting system, including a boosting storage tank 1, a pyrotechnic initiator 2, a generator 3, a fuel storage tank 5, and a controller 6. The difference between this embodiment and the first embodiment is that in this embodiment, there is no independent oxidizer storage tank, and the oxidizer storage tank shares the boosting storage tank 1, that is, the boosting medium in the boosting storage tank 1 is the oxidizer.

[0085] The outlet end of the generator 3 is connected to the inlet end of the boosting storage tank 1 through a second one - way valve 11, and is also connected to the inlet end of the fuel storage tank 5 through a pipeline; the outlet end of the fuel storage tank 5 is sequentially connected to the thrust chamber 16 through a third electric blasting valve 14 and a fuel valve 15.

[0086] A pressure - relief pipeline 17 is provided between the outlet end of the electric pump 8 and the outlet end of the oxidizer valve 13, and a pressure - relief valve 18 is installed on the pressure - relief pipeline 17. A safety valve 19 is also installed on the pressure - relief pipeline 17 in parallel with the pressure - relief valve 18, and the inlet of the safety valve 19 faces the outlet end of the electric pump 8.

[0087] The controller 6 is respectively connected to the pyrotechnic initiator 2, the first electric blasting valve 7, the electric pump 8, the third electric blasting valve 14, the oxidizer valve 13, the fuel valve 15, and the pressure - relief valve 18, and is used to issue corresponding control instructions respectively.

[0088] The pressure - regulating method of this embodiment is the same as that of the first embodiment, and will not be elaborated here.

[0089] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; 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 recorded 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 gas boosting system with adjustable pressure, which is used to provide oxidant and fuel for a thrust chamber (16), and is characterized in that: it includes a boosting storage tank (1), a pyrotechnic initiator (2), a generator (3), an oxidant storage tank (4), a fuel storage tank (5) and a controller (6); The boosting storage tank (1) is used to store a boosting medium, its inlet end is connected to the pyrotechnic initiator (2), and its outlet end is sequentially connected to the inlet end of the generator (3) through a first electric blasting valve (7), an electric pump (8) and a first check valve (9); A pressure sensor (10) is installed at the outlet end of the generator (3), and the pressure sensor (10) is connected to the controller (6) for collecting pressure signals and transmitting them to the controller (6); The outlet end of the generator (3) is connected to the inlet end of the boosting storage tank (1) through a second check valve (11), and is simultaneously connected to the inlet ends of the oxidant storage tank (4) and the fuel storage tank (5) through pipelines respectively; The outlet end of the oxidant storage tank (4) is sequentially connected to the thrust chamber (16) through a second electric blasting valve (12) and an oxidant valve (13); The outlet end of the fuel storage tank (5) is sequentially connected to the thrust chamber (16) through a third electric blasting valve (14) and a fuel valve (15); A pressure relief pipeline (17) is provided between the outlet end of the electric pump (8) and the outlet end of the oxidant valve (13) or the fuel valve (15), and a pressure relief valve (18) is installed on the pressure relief pipeline (17); The controller (6) is respectively connected to the pyrotechnic initiator (2), the first electric blasting valve (7), the electric pump (8), the second electric blasting valve (12), the oxidant valve (13), the third electric blasting valve (14), the fuel valve (15) and the pressure relief valve (18) for respectively sending corresponding control instructions.

2. The gas boosting system with adjustable pressure according to claim 1, and is characterized in that: A safety valve (19) is also provided on the pressure relief pipeline (17) and is installed in parallel with the pressure relief valve (18), and the inlet of the safety valve (19) faces the outlet end of the electric pump (8).

3. An RBCC engine, and is characterized in that: it includes the gas boosting system with adjustable pressure according to claim 1 or 2, a thrust chamber (16), and a ramjet engine; The inlet end of the thrust chamber (16) is respectively connected to the outlets of the oxidant valve (13) and the fuel valve (15), and the outlet end is connected to the combustion chamber of the ramjet engine.

4. A gas boosting system with adjustable pressure, which is used to provide oxidant and fuel for a thrust chamber (16), and is characterized in that: it includes a boosting storage tank (1), a pyrotechnic initiator (2), a generator (3), an oxidant storage tank (4) and a controller (6); The pressurized storage tank (1) is used to store the pressurizing medium, and the pressurizing medium is fuel; the inlet end of the pressurized storage tank (1) is connected to the pyrotechnic initiator (2), and the outlet end is sequentially connected to the inlet end of the generator (3) through the first electric explosion valve (7), the electric pump (8) and the first check valve (9); the outlet end of the first electric explosion valve (7) is connected to the thrust chamber (16) through the fuel valve (15); a pressure sensor (10) is installed at the outlet end of the generator (3), and the pressure sensor (10) is connected to the controller (6) for collecting pressure signals and transmitting them to the controller (6). The outlet end of the generator (3) is connected to the inlet end of the pressurized storage tank (1) through the second check valve (11), and is simultaneously connected to the inlet end of the oxidizer storage tank (4) through a pipeline; the outlet end of the oxidizer storage tank (4) is sequentially connected to the thrust chamber (16) through the second electric explosion valve (12) and the oxidizer valve (13). A pressure relief pipeline (17) is provided between the outlet end of the electric pump (8) and the outlet end of the fuel valve (15), and a pressure relief valve (18) is installed on the pressure relief pipeline (17). The controller (6) is respectively connected to the pyrotechnic initiator (2), the first electric explosion valve (7), the electric pump (8), the second electric explosion valve (12), the oxidizer valve (13), the fuel valve (15) and the pressure relief valve (18) for respectively issuing corresponding control instructions.

5. The pressure-adjustable gas pressurization system according to claim 4, wherein: A safety valve (19) is further provided on the pressure relief pipeline (17) and is installed in parallel with the pressure relief valve (18), and the inlet of the safety valve (19) faces the outlet end of the electric pump (8).

6. An RBCC engine, characterized in that: It includes the pressure-adjustable gas pressurization system according to claim 4 or 5, a thrust chamber (16), and a ramjet engine; The inlet end of the thrust chamber (16) is respectively connected to the outlets of the oxidizer valve (13) and the fuel valve (15), and the outlet end is connected to the combustion chamber of the ramjet engine.

7. A pressure-adjustable gas pressurization system for supplying oxidizer and fuel to a thrust chamber (16), characterized in that: It includes a pressurized storage tank (1), a pyrotechnic initiator (2), a generator (3), a fuel storage tank (5) and a controller (6); The pressurized storage tank (1) is used to store the pressurizing medium, and the pressurizing medium is oxidizer; the inlet end of the pressurized storage tank (1) is connected to the pyrotechnic initiator (2), and the outlet end is sequentially connected to the inlet end of the generator (3) through the first electric explosion valve (7), the electric pump (8) and the first check valve (9); the outlet end of the first electric explosion valve (7) is connected to the thrust chamber (16) through the oxidizer valve (13); a pressure sensor (10) is installed at the outlet end of the generator (3), and the pressure sensor (10) is connected to the controller (6) for collecting pressure signals and transmitting them to the controller (6). The outlet end of the generator (3) is connected to the inlet end of the pressurized storage tank (1) through a second one-way valve (11), and is simultaneously connected to the inlet end of the fuel storage tank (5) through a pipeline; the outlet end of the fuel storage tank (5) is sequentially connected to the thrust chamber (16) through a third electric blasting valve (14) and a fuel valve (15); A pressure relief pipeline (17) is provided between the outlet end of the electric pump (8) and the outlet end of the oxidant valve (13), and a pressure relief valve (18) is installed on the pressure relief pipeline (17); The controller (6) is respectively connected to the pyrotechnic initiator (2), the first electric blasting valve (7), the electric pump (8), the third electric blasting valve (14), the oxidant valve (13), the fuel valve (15) and the pressure relief valve (18) for respectively issuing corresponding control instructions.

8. The pressure-adjustable gas pressurization system according to claim 7, characterized in that: A safety valve (19) installed in parallel with the pressure relief valve (18) is further provided on the pressure relief pipeline (17), and the inlet of the safety valve (19) faces the outlet end of the electric pump (8).

9. An RBCC engine, characterized in that: It includes the pressure-adjustable gas pressurization system according to claim 7 or 8, a thrust chamber (16), and a ramjet engine; The inlet end of the thrust chamber (16) is respectively connected to the outlets of the oxidant valve (13) and the fuel valve (15), and the outlet end is connected to the combustion chamber of the ramjet engine.

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