Multi-mode system control method, device and equipment of RBCC engine and medium

Abstract

The invention discloses a multi-mode system control method, device and equipment of an RBCC engine and a medium, and relates to the field of automatic control, the multi-mode system control method of the engine comprises the steps that before the RBCC engine operates, the initial working mode of the RBCC engine is determined according to a mode selection instruction sent by an aircraft controller, the working modes of the RBCC engine comprise a rocket mode, a rocket stamping mode and a stamping mode; in the running process of the RBCC engine, according to the working characteristics of a power system of the RBCC engine and the received flight parameters, the real-time working mode requirement of the RBCC engine and the propellant supply amount corresponding to different working modes are determined; according to the working mode requirements of the engine, a rocket thrust chamber and a ramjet combustion chamber of the RBCC engine are controlled to be opened or closed, so that the RBCC engine is subjected to conversion of different working modes; and according to the key point parameters of the RBCC engine and a preset key point parameter range, the propellant supply amount of the RBCC engine is controlled.

Description

Technical Field

[0001] The present invention relates to the field of automatic control, and particularly to a multi-modal system control method, device, equipment and medium for an RBCC engine. Background Art

[0002] The RBCC engine organically combines a rocket engine and a ramjet engine, integrating the characteristics of a rocket engine with a wide range of operating conditions and a high thrust-to-weight ratio, as well as the advantages of a ramjet engine with a high specific impulse and excellent economic performance. It has the characteristics of a wide working airspace, a wide speed range, a compact structure, high reliability, and excellent comprehensive performance. It is an ideal power device for new supersonic missile weapons, near-space hypersonic vehicles, and reusable launch vehicles, and is an important strategic direction for the development of liquid power systems.

[0003] To fully utilize the advantages of the RBCC engine, its control system is usually required to have multi-modal control capabilities such as rocket mode, rocket-ramjet mode, and ramjet mode, and to adjust and control the working mode and propellant flow rate in real time according to the flight mission requirements. However, as a new type of combined power system, most of the domestic and foreign research on the adjustment and control of the RBCC engine focuses on ignition, flame stabilization, mode conversion, and engine performance.

[0004] Therefore, how to formulate a cooperative control method for multiple modes in combination with the working mission requirements of the RBCC engine to enable the RBCC engine to operate stably in multiple modes has become an important research direction for those skilled in the art. Summary of the Invention

[0005] In view of the above technical status, the present invention provides a multi-modal system control method, device, equipment and medium for an RBCC engine to formulate a cooperative control method for multiple modes in combination with the working mission requirements of the RBCC engine to enable the RBCC engine to operate stably in multiple modes.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A multi-modal system control method for an RBCC engine, comprising:

[0008] Before the RBCC engine operates, determine the initial working mode of the RBCC engine according to the mode selection instruction sent by the aircraft controller, wherein the working modes of the RBCC engine include: rocket mode, rocket-ramjet mode, and ramjet mode;

[0009] During the operation of the RBCC engine, determine the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different working modes according to the working characteristics of the power system of the RBCC engine and the received flight parameters;

[0010] According to the requirements of the real-time working mode, control the opening or closing of the rocket thrust chamber and the ram combustion chamber of the RBCC engine, so as to convert the RBCC engine between different working modes;

[0011] Moreover, according to the key point parameters of the RBCC engine and the preset key point parameter ranges, control the propellant supply amount of the RBCC engine.

[0012] In an alternative embodiment of the present application, the determining the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different working modes according to the working characteristics of the power system of the RBCC engine and the received flight parameters includes:

[0013] Conduct ground tests, flight tests and simulation calculations on the RBCC engine to determine the working characteristics of the power system of the RBCC engine;

[0014] According to the working characteristics of the power system and the flight parameters received in real time, determine the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different modes.

[0015] In an alternative embodiment of the present application, the propellant supply amounts corresponding to different modes of the RBCC engine include:

[0016] The first propellant supply amount of the rocket thrust chamber of the RBCC engine in the rocket mode;

[0017] The second propellant supply amount of the rocket thrust chamber and the third propellant supply amount of the ram combustion chamber of the RBCC engine in the rocket-ram mode;

[0018] The fourth propellant supply amount of the ram combustion chamber of the RBCC engine in the ram mode.

[0019] In an alternative embodiment of the present application, the controlling the propellant supply amount of the RBCC engine according to the preset key point parameters of the RBCC engine and the preset key point parameter ranges includes:

[0020] Obtain the turbine pump pressure and the electric pump speed of the RBCC engine through preset pressure sensors and speed sensors, and determine the preset target turbine pump pressure and target electric pump speed;

[0021] According to the target turbine pump pressure and the target electric pump speed, adjust the turbine pump pressure and the electric pump speed of the RBCC engine respectively to control the propellant supply amount of the RBCC engine.

[0022] In an alternative embodiment of the present application, controlling the propellant supply amount of the RBCC engine according to the preset key point parameters and the preset key point parameter ranges of the RBCC engine includes:

[0023] Obtaining the pressure data of the key pressure points and the temperature data of the key temperature points of the RBCC engine respectively through preset pressure sensors and temperature sensors;

[0024] Adjusting the propellant supply amount of the RBCC engine according to the preset pressure range of the key pressure points and the preset temperature range of the key temperature points.

[0025] Compared with the prior art, the multi-modal system control method of the engine provided by the present invention combines the working characteristics and flight parameters of the RBCC engine power system, realizes the determination of the requirements for the propellant supply amounts in different modes of the RBCC engine, provides a basis for the subsequent adjustment of the propellant supply amount while ensuring that the RBCC engine can perform flight missions. At the same time, this method combines the calculated real-time working mode requirements, realizes the conversion of different modes of the RBCC engine, and can adjust the supply amount of the propellant of the RBCC engine in real time according to the feedback of the key point parameters of the RBCC. This method can formulate a multi-modal collaborative control method in combination with the working task requirements of the RBCC engine, so that the RBCC engine can work stably in multiple modes.

[0026] The present invention also provides a multi-modal system control device for an RBCC engine, including:

[0027] An initial mode determination unit, configured to determine the initial working mode of the RBCC engine according to the mode selection instruction sent by the aircraft controller before the RBCC engine runs, where the working modes of the RBCC engine include: rocket mode, rocket-ramjet mode, and ramjet mode;

[0028] A propellant supply amount determination unit, configured to determine the real-time working mode requirements and the propellant supply amounts corresponding to different working modes of the RBCC engine according to the working characteristics of the power system of the RBCC engine and the received flight parameters during the operation of the RBCC engine;

[0029] A mode conversion unit, configured to control the opening or closing of the rocket thrust chamber and the ramjet combustion chamber of the RBCC engine according to the real-time working mode requirements to convert the RBCC engine between different working modes;

[0030] A propellant supply control unit is configured to control the propellant supply of the RBCC engine according to the key point parameters of the RBCC engine and a preset range of key point parameters.

[0031] Compared with the prior art, the beneficial effects of the multimodal system control device of the RBCC engine provided by the present invention are the same as those of the multimodal system control method of the RBCC engine described in the above technical solution, and will not be elaborated here.

[0032] The present invention further provides an electronic device, including:

[0033] A processor;

[0034] A memory for storing executable instructions of the processor;

[0035] The processor is configured to execute the multimodal system control method of the above RBCC engine by running the instructions in the memory.

[0036] Compared with the prior art, the beneficial effects of the electronic device provided by the present invention are the same as those of the multimodal system control method of the RBCC engine described in the above technical solution, and will not be elaborated here.

[0037] The present invention further provides a computer storage medium, in which instructions are stored, and when the instructions are run, the multimodal system control method of the above RBCC engine is implemented.

[0038] Compared with the prior art, the beneficial effects of the computer storage medium provided by the present invention are the same as those of the multimodal system control method of the RBCC engine described in the above technical solution, and will not be elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present invention. The illustrative embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0040] Figure 1 is a flowchart of the multimodal cooperative control method of the RBCC engine provided by an embodiment of the present application;

[0041] Figure 2 is a structural diagram of the multimodal system control device of the RBCC engine provided by an embodiment of the present application;

[0042] Figure 3 is a schematic structural diagram of an electronic device provided by an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0043] In order to clearly describe the technical solutions of the embodiments of the present invention, in the embodiments of the present invention, terms such as "first" and "second" are used to distinguish identical or similar items with basically the same functions and roles. For example, the first threshold and the second threshold are only used to distinguish different thresholds, and do not limit their sequence. Those skilled in the art can understand that terms such as "first" and "second" do not limit the quantity and execution order, and terms such as "first" and "second" do not necessarily limit that they are different.

[0044] It should be noted that in the present invention, words such as "exemplary" or "for example" are used to represent examples, illustrations or explanations. Any embodiment or design solution described as "exemplary" or "for example" in the present invention should not be construed as being more preferred or having more advantages than other embodiments or design solutions. Exactly speaking, the use of words such as "exemplary" or "for example" is intended to present relevant concepts in a specific manner.

[0045] In the present invention, "at least one" means one or more, and "a plurality" means two or more. "And / or" describes the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone, where A and B can be singular or plural. The character " / " generally represents an "or" relationship between the associated objects before and after. "At least one (item)" or its similar expression refers to any combination of these items, including any combination of single item (item) or plural items (items). For example, at least one (item) of a, b or c can represent: a, b, c, the combination of a and b, the combination of a and c, the combination of b and c, or the combination of a, b and c, where a, b and c can be single or multiple.

[0046] The RBCC engine organically combines a rocket engine and a ramjet engine, integrating the characteristics of a rocket engine with a wide operating range and a high thrust-to-weight ratio, as well as the advantages of a ramjet engine with a high specific impulse and excellent economic performance. It has the characteristics of a wide working airspace, a wide speed range, a compact structure, high reliability, and excellent comprehensive performance. It is an ideal power plant for new supersonic missile weapons, near-space hypersonic vehicles, and reusable launch vehicles, and is an important strategic direction for the development of liquid power systems.

[0047] To give full play to the advantages of the RBCC engine, its control system is usually required to have various modal control capabilities such as rocket mode, rocket-ramjet mode, and ramjet mode, and to adjust and control the working mode and propellant flow rate in real time according to the flight mission requirements. However, as a new type of combined power system, most of the domestic and foreign research on the regulation and control of the RBCC engine focuses on ignition, flame stabilization, mode conversion, and engine performance.

[0048] Therefore, how to combine the working task requirements of the RBCC engine to develop a multi-modal cooperative control method to enable the RBCC engine to operate stably in multiple modes has become an important research direction for those skilled in the art.

[0049] In view of this, the embodiments of the present application provide an RBCC engine multi-modal cooperative control method, device, equipment and medium, which will be described in detail one by one in the following embodiments.

[0050] The embodiments of the present application first provide an RBCC engine multi-modal cooperative control method. Please refer to Figure 1 , Figure 1 which is the flowchart of the RBCC engine multi-modal cooperative control method provided by the embodiments of the present application.

[0051] As Figure 1 shown, the RBCC engine multi-modal cooperative control method includes the following S101 to S104:

[0052] S101, before the RBCC engine runs, according to the mode selection instruction sent by the aircraft controller, determine the initial working mode of the RBCC engine, where the working modes of the RBCC engine include: rocket mode, rocket-ramjet mode, and ramjet mode.

[0053] The RBCC engine is a combined cycle engine that combines the advantages of rocket and ramjet engines and can adopt different working modes at different flight stages to improve the overall performance.

[0054] In the embodiments of the present application, before the RBCC engine executes a flight mission, the aircraft controller can send a mode selection instruction to the RBCC engine according to the preset mission plan and possible safety and performance requirements to provide the initial working mode for the RBCC engine, thereby ensuring that the RBCC engine starts based on the initial working mode.

[0055] Among them, the rocket mode means that when the RBCC engine is flying at high altitude, it uses the rocket to provide the main thrust. At this time, the ramjet combustion chamber does not burn because it inhales little or no external air.

[0056] The rocket-ramjet mode means that when the RBCC engine is flying at high speed, it uses the rocket thrust chamber and the ramjet combustion chamber to work together. At this time, the rocket provides additional thrust, and the ramjet combustion chamber generates thrust by inhaling external air for combustion.

[0057] The ramjet mode means that when the RBCC engine is in the cruise mode, it relies on the ramjet combustion chamber for efficient combustion, reduces fuel consumption, and realizes more economical flight.

[0058] S102. During the operation of the RBCC engine, based on the working characteristics of the power system of the RBCC engine and the received flight parameters, determine the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different working modes.

[0059] During the actual execution of flight missions, the RBCC engine will automatically select and switch the working mode of the RBCC engine according to different flight mission requirements, and then precisely control the flow supply of the propellant. For example, during the rocket takeoff or rapid climb phase, the RBCC engine needs to generate the maximum thrust. At this time, the control system will select the rocket-ramjet mode and enter the maximum thrust mode to ensure sufficient thrust output; during the cruise phase, the main goal is to improve fuel efficiency and reduce fuel consumption. At this time, the control system will select the ramjet mode and enter the highest specific impulse mode; when flying at extremely high altitudes, the control system will select the rocket mode to reduce the ramjet propellant consumption.

[0060] During the actual application process, when the RBCC engine enters the rocket-ramjet mode, the rocket thrust chamber and the ramjet combustion chamber of the RBCC engine work simultaneously. In the rocket mode, only the rocket thrust chamber needs to work, while in the ramjet mode, only the ramjet combustion chamber of the RBCC engine needs to be started.

[0061] Furthermore, to ensure that the RBCC engine has enough fuel to complete the flight mission, before the RBCC engine executes the flight mission, it is necessary to first determine the propellant supply amounts required for different working modes of the RBCC engine and the real-time working mode requirements during the flight process of the RBCC engine in combination with the specific requirements of the flight mission.

[0062] Specifically, the above S102 includes:

[0063] Conduct ground tests, flight tests, and simulation calculations on the RBCC engine to determine the working characteristics of the power system of the RBCC engine;

[0064] Based on the working characteristics of the power system and the real-time received flight parameters, determine the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different modes.

[0065] Among them, the flight parameters include but are not limited to flight altitude, flight speed, attitude angles (such as pitch angle, yaw angle, etc.), acceleration, etc. corresponding to the flight mission, which are used to reflect the specific parameter information of the RBCC engine in a specific flight stage.

[0066] The working characteristics of the power system can be understood as the performance of the RBCC engine under different operating conditions, including: thrust curve, combustion chamber temperature, propellant flow rate, etc. In the actual application process, the working characteristics of the power system can be obtained through multiple ground tests, flight tests and simulation calculations, and a corresponding mathematical model is established for analysis.

[0067] Furthermore, after obtaining the flight parameters and the working characteristics of the power system, based on this, the real-time working mode requirements of the RBCC engine and the propellant supply amounts corresponding to different modes can be determined.

[0068] In the embodiment of the present application, the propellant supply amounts corresponding to different modes include: the first propellant supply amount of the rocket thrust chamber of the RBCC engine in the rocket mode; the second propellant supply amount of the rocket thrust chamber and the third propellant supply amount of the ram combustion chamber of the RBCC engine in the rocket-ram mode; the fourth propellant supply amount of the ram combustion chamber of the RBCC engine in the ram mode.

[0069] The real-time working mode requirements, that is, according to the flight parameters of the RBCC rocket engine, the real-time working mode requirements for the RBCC engine to maintain the flight state of the aircraft or change the flight state of the aircraft are obtained.

[0070] S103, according to the real-time working mode requirements, control the opening or closing of the rocket thrust chamber and the ram combustion chamber of the RBCC engine to convert the RBCC engine between different working modes.

[0071] Corresponding to the actual flight mission, when the flight mission requires the RBCC engine to start the rocket-ram mode during acceleration and climb; during economic cruise, the propellant supply cut-off valve set in the rocket thrust chamber of the RBCC engine changes from the open state to the closed state, and then stops the propellant supply of the rocket thrust chamber, so that the RBCC engine changes from the rocket-ram mode to the ram mode; when it is necessary to fly at high altitude, the rocket mode is turned on to utilize the rocket to provide the main thrust.

[0072] S104, according to the key point parameters of the RBCC engine and the preset key point parameter range, control the propellant supply amount of the RBCC engine.

[0073] Specifically, the purpose of controlling the propellant supply amount of the RBCC engine is to adjust the real-time propellant supply amount of the RBCC engine by real-time monitoring of the state parameters of the RBCC engine and then combining the target requirements of the flight mission in different modes, so that the RBCC engine can always maintain the best state during the execution of the flight mission.

[0074] Specifically, the above S104 includes:

[0075] Obtain the turbine pump pressure and electric pump speed of the RBCC engine through preset pressure sensors and speed sensors, and determine the preset target turbine pump pressure and target electric pump speed;

[0076] Adjust the turbine pump pressure and electric pump speed of the RBCC engine respectively according to the target turbine pump pressure and target electric pump speed to control the propellant supply amount of the RBCC engine.

[0077] In the actual application process, the turbine pump is a key component for transporting propellants (fuel and oxidizer) from the storage tank to the combustion chamber. The pressure of the turbine pump directly affects the flow rate of the propellant and the thrust of the engine. The electric pump is another device for transporting propellants, usually used to assist the turbine pump or work independently in certain working modes. The speed of the electric pump determines the speed at which it transports the propellant. Preset pressure sensors and speed sensors can be used to monitor the working pressure of the turbine pump and the working speed of the electric pump in real time.

[0078] It can be understood that in the actual application process, the real-time pressure of the turbine pump and the real-time speed of the electric pump may not reach the preset target turbine pump pressure and target electric pump speed due to reasons such as temperature deviation and flow resistance deviation. In this case, based on the collected turbine pump pressure and electric pump speed, as well as the difference between the target turbine pump pressure and the target electric pump, the turbine pump and the electric pump can be appropriately adjusted, thereby controlling the propellant supply amount of the RBCC engine.

[0079] In another alternative embodiment of the present application, the control of the propellant supply amount of the RBCC engine further includes: controlling the propellant supply amount of the RBCC engine based on the temperature at the key temperature point and the pressure at the key pressure point in the ram combustion chamber.

[0080] Specifically, the above S103 further includes:

[0081] Obtain the pressure data at the key pressure point and the temperature data at the key temperature point of the RBCC engine through preset pressure sensors and temperature sensors respectively;

[0082] Adjust the propellant supply amount of the RBCC engine according to the preset pressure range at the key pressure point and the preset temperature range at the key temperature point.

[0083] Among them, the key pressure points refer to the positions that have an important impact on the engine performance, such as the combustion chamber inlet, the turbine pump outlet, etc. The pressure at these positions directly affects the flow rate and combustion efficiency of the propellant. The key temperature points refer to the positions that have an important impact on the engine performance and safety, such as the combustion chamber wall surface, the turbine blade, etc. The temperature at these positions directly affects the combustion efficiency and material durability.

[0084] During the actual application process, preset pressure sensors and temperature sensors can be used to monitor the pressure at the key temperature points in real time, and combined with the preset temperature range and pressure range of the key temperature points and key pressure points, the supply amount of the propellant can be adjusted in real time.

[0085] For example, when the temperature at the key points of the ramjet combustion chamber of the RBCC engine is less than the preset temperature range, the supply amount of the propellant to the ramjet combustion chamber is increased.

[0086] In another alternative embodiment of the present application, the adjustment of the propellant supply amount can also be combined with the temperature of the propellant itself.

[0087] It can be understood that the temperature of the propellant directly affects its density. When the temperature rises, the density of liquid propellants (such as liquid hydrogen, liquid oxygen) will decrease; when the temperature drops, the density will increase. Since the temperature affects the density of the propellant, the control system needs to adjust the supply amount according to the actual temperature to ensure a constant mass flow rate. For example, when the temperature of the propellant is relatively low, although the volume flow rate of the propellant remains unchanged, the mass flow rate of the propellant will increase, so the supply amount needs to be reduced accordingly.

[0088] In summary, the multi-modal system control method of the RBCC engine provided by the embodiments of the present application combines the working characteristics and flight parameters of the power system of the RBCC engine, realizes the determination of the requirements for the implementation working mode and the supply amount of the propellant in different modes of the RBCC engine, provides a basis for the subsequent adjustment of the propellant supply amount while ensuring that the RBCC engine can perform flight missions. At the same time, this method combines the requirements of the engine working mode, realizes the conversion of different modes of the RBCC engine, and can adjust the supply amount of the propellant of the RBCC engine in real time according to the feedback of the key point parameters of the RBCC. This method can formulate a multi-modal collaborative control method in combination with the working task requirements of the RBCC engine, so that the RBCC engine can work stably in multiple modes.

[0089] The present application also provides a multi-modal system control device for an RBCC engine. Please refer to Figure 2 , Figure 2 This is the structural diagram of the multi-modal system control device for the RBCC engine provided by the embodiments of the present application. As Figure 2 shown, the multi-modal system control device for the RBCC engine includes:

[0090] An initial mode determination unit 201, configured to determine an initial operating mode of the RBCC engine according to a mode selection instruction sent by an aircraft controller before the RBCC engine operates, where the operating modes of the RBCC engine include: a rocket mode, a rocket-ramjet mode, and a ramjet mode;

[0091] A propellant supply amount determination unit 202, configured to determine real-time operating mode requirements of the RBCC engine and propellant supply amounts corresponding to different operating modes according to operating characteristics of a power system of the RBCC engine and received flight parameters during operation of the RBCC engine;

[0092] A mode conversion unit 203, configured to control opening or closing of a rocket thrust chamber and a ram combustion chamber of the RBCC engine according to the real-time engine operating mode requirements, so as to convert the RBCC engine between different operating modes;

[0093] A propellant supply amount control unit 204, configured to control the propellant supply amount of the RBCC engine according to key point parameters of the RBCC engine and a preset key point parameter range.

[0094] In an alternative embodiment of the present application, the determining the real-time operating mode requirements of the RBCC engine and the propellant supply amounts corresponding to different operating modes according to the operating characteristics of the power system of the RBCC engine and the received flight parameters includes:

[0095] Conducting ground tests, flight tests, and simulation calculations on the RBCC engine to determine the operating characteristics of the power system of the RBCC engine;

[0096] Determining the real-time operating mode requirements of the RBCC engine and the propellant supply amounts corresponding to different modes according to the operating characteristics of the power system and the real-time received flight parameters.

[0097] In an alternative embodiment of the present application, the propellant supply amounts corresponding to different modes of the RBCC engine include:

[0098] A first propellant supply amount of the rocket thrust chamber of the RBCC engine in the rocket mode;

[0099] A second propellant supply amount of the rocket thrust chamber and a third propellant supply amount of the ram combustion chamber of the RBCC engine in the rocket-ramjet mode;

[0100] A fourth propellant supply amount of the ram combustion chamber of the RBCC engine in the ramjet mode.

[0101] In an alternative embodiment of the present application, controlling the propellant supply amount of the RBCC engine according to the preset key point parameters and the preset key point parameter ranges of the RBCC engine includes:

[0102] Obtaining the turbine pump pressure and the electric pump speed of the RBCC engine through preset pressure sensors and speed sensors, and determining the preset target turbine pump pressure and target electric pump speed;

[0103] Adjusting the turbine pump pressure and the electric pump speed of the RBCC engine respectively according to the target turbine pump pressure and the target electric pump speed to control the propellant supply amount of the RBCC engine.

[0104] In an alternative embodiment of the present application, controlling the propellant supply amount of the RBCC engine according to the preset key point parameters and the preset key point parameter ranges of the RBCC engine includes:

[0105] Obtaining the pressure data of the key pressure points and the temperature data of the key temperature points of the RBCC engine through preset pressure sensors and temperature sensors respectively;

[0106] Adjusting the propellant supply amount of the RBCC engine according to the preset pressure range of the key pressure points and the preset temperature range of the key temperature points.

[0107] The above device embodiment provided in this embodiment and the method embodiment of the present application belong to the same inventive concept. For the technical details not described in detail in this embodiment, reference may be made to the specific processing content of the multi-modal system control method of the RBCC engine provided in the above embodiments of the present application, which will not be elaborated here.

[0108] This application embodiment also provides an electronic device, as Figure 3 shown, Figure 3 which is a schematic structural diagram of an electronic device provided in this application embodiment.

[0109] As Figure 3 shown, the electronic device includes:

[0110] A processor 210;

[0111] A memory 200 for storing executable instructions of the processor 210;

[0112] The processor 210 is configured to execute the multi-modal system control method of the RBCC engine disclosed in any of the above embodiments by running the instructions in the memory 200.

[0113] The processor 210, the memory 200, the communication interface 220, the input device 230, and the output device 240 are interconnected with each other through a bus. Among them:

[0114] The bus may include a path for transmitting information between various components of the computer system.

[0115] The processor 210 can be a general-purpose processor, such as a general-purpose central processing unit (CPU), a microprocessor, etc., or an application-specific integrated circuit (ASIC), or one or more integrated circuits for controlling the execution of the program of the solution of the present invention. It can also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0116] The processor 210 may include a main processor, and may also include a baseband chip, a modem, etc.

[0117] The memory 200 stores the program for implementing the technical solution of the present invention, and may also store an operating system and other critical services. Specifically, the program may include program code, and the program code includes computer operation instructions. More specifically, the memory 200 may include a read-only memory (ROM), other types of static storage devices that can store static information and instructions, a random access memory (RAM), other types of dynamic storage devices that can store information and instructions, a disk memory, a flash memory, etc.

[0118] The input device 230 may include a device for receiving data and information input by a user, such as a keyboard, a mouse, a camera, a scanner, a touch screen, etc.

[0119] The output device 240 may include a device for allowing information to be output to a user, such as a display screen, a printer, a speaker, etc.

[0120] The communication interface 220 may include a device of any transceiver type for communicating with other devices or communication networks, such as Ethernet, a radio access network (RAN), a wireless local area network (WLAN), etc.

[0121] The processor 210 executes the program stored in the memory 200 and calls other devices, and can be used to implement each step of any one of the multi-modal system control methods of the RBCC engine provided in the above embodiments of the present application.

[0122] In addition to the above methods and devices, an embodiment of the present application may also be a computer program product, which includes computer program instructions. When the computer program instructions are run by a processor, the processor is caused to execute the steps in the multi-modal system control method of the RBCC engine in various embodiments of the present application.

[0123] The computer program product may be written in any combination of one or more programming languages to write program code for performing the operations of the embodiments of the present application. The programming languages include object-oriented programming languages, such as Java, C++, etc., and also include conventional procedural programming languages, such as the "C" language or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, executed as an independent software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0124] In addition, an embodiment of the present application may also be a storage medium, on which a computer program is stored. The computer program is executed by a processor to perform the steps in the multi-modal system control method of the RBCC engine in various embodiments of the present application.

[0125] For the foregoing method embodiments, for the sake of simple description, they are all expressed as a series of action combinations. However, those skilled in the art should know that the present application is not limited by the described action sequence, because according to the present application, certain steps may be in other sequences or performed simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily essential to the present application.

[0126] It should be noted that the various embodiments in this specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the various embodiments can be referred to each other. For the device embodiments, since they are basically similar to the method embodiments, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiments.

[0127] The steps in the methods of the various embodiments of the present application can be adjusted, combined, and deleted according to actual needs. The technical features recorded in the various embodiments can be replaced or combined.

[0128] The modules and sub-modules in the devices and terminals in the various embodiments of the present application can be combined, divided, and deleted according to actual needs.

[0129] In several embodiments provided by the present application, it should be understood that the disclosed terminals, devices and methods can be implemented in other ways. For example, the terminal embodiments described above are merely illustrative. For example, the division of modules or sub-modules is only a logical function division. In actual implementation, there may be other division methods. For example, multiple sub-modules or modules can be combined or integrated into another module, or some features can be ignored or not executed. Another point is that the displayed or discussed coupling, direct coupling or communication connection to each other can be through some interfaces, and the indirect coupling or communication connection of devices or modules can be in electrical, mechanical or other forms.

[0130] The modules or sub-modules described as separate components may or may not be physically separated. The components as modules or sub-modules may or may not be physical modules or sub-modules, that is, they may be located in one place, or may be distributed to multiple network modules or sub-modules. Some or all of the modules or sub-modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0131] In addition, each functional module or sub-module in various embodiments of the present application can be integrated in a processing module, or each module or sub-module can exist physically alone, or two or more modules or sub-modules can be integrated in one module. The above-mentioned integrated modules or sub-modules can be implemented in the form of hardware, or in the form of software functional modules or sub-modules.

[0132] Those skilled in the art can further realize that the units and algorithm steps of each example described in combination with the embodiments disclosed in this article can be implemented by electronic hardware, computer software, or a combination of the two. To clearly illustrate the interchangeability of hardware and software, the composition and steps of each example have been generally described according to functions in the above description. Whether these functions are executed in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of the present application.

[0133] The steps of the method or algorithm described in combination with the embodiments disclosed in this article can be directly implemented by hardware, software units executed by a processor, or a combination of the two. The software units can be placed in a random access memory (RAM), memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium well-known in the technical field.

[0134] Finally, it should also be noted that in this text, 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 actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the element.

[0135] The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may 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 is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A multi-mode system control method for a RBCC engine, characterized in that: include: Before the RBCC engine is operated, the initial operating mode of the RBCC engine is determined according to the mode selection instruction sent by the aircraft controller, wherein the operating modes of the RBCC engine include: rocket mode, rocket ramjet mode and ramjet mode; During the operation of the RBCC engine, according to the operating characteristics of the power system of the RBCC engine and the received flight parameters, determining the real-time operating mode requirements of the RBCC engine and the propellant supply corresponding to different operating modes; According to the real-time working mode requirement, controlling the rocket thrust chamber and the ramjet combustion chamber of the RBCC engine to open or close, so as to convert the RBCC engine into different working modes; And, according to the key point parameters of the RBCC engine and the preset key point parameter range, the propellant supply amount of the RBCC engine is controlled.

2. The method according to claim 1, characterized in that: Determining the real-time working mode requirement of the RBCC engine and the propellant supply amount corresponding to different working modes according to the working characteristics of the power system of the RBCC engine and the received flight parameters includes: Conducting ground tests, flight tests, and simulation calculations on the RBCC engine to determine operating characteristics of a power system of the RBCC engine; According to the operating characteristics of the power system and the flight parameters received in real time, the real-time operating mode requirements of the RBCC engine and the propellant supply corresponding to different modes are determined.

3. The method according to claim 1 or 2, characterized in that: The propellant supply corresponding to different modes of the RBCC engine includes: The first propellant supply amount of the rocket thrust chamber of the RBCC engine in the rocket mode; The second propellant supply amount of the rocket thrust chamber and the third propellant supply amount of the ramjet combustion chamber of the RBCC engine in the rocket ramjet mode; A fourth propellant supply amount of the ramjet combustion chamber of the RBCC engine in the ramjet mode.

4. The method according to claim 1, characterized in that The controlling the propellant supply amount of the RBCC engine according to the preset key point parameters and the preset key point parameter range of the RBCC engine comprises: Obtaining the turbo pump pressure and electric pump speed of the RBCC engine through a preset pressure sensor and a speed sensor, and determining a preset target turbo pump pressure and a target electric pump speed; According to the target turbopump pressure and the target electric pump speed, the turbopump pressure and the electric pump speed of the RBCC engine are adjusted respectively to control the propellant supply amount of the RBCC engine.

5. The method according to claim 1, characterized in that The controlling the propellant supply amount of the RBCC engine according to the preset key point parameters and the preset key point parameter range of the RBCC engine comprises: Obtaining pressure data of a key pressure point and temperature data of a key temperature point of the RBCC engine through a preset pressure sensor and a preset temperature sensor respectively; The propellant supply of the RBCC engine is adjusted according to the preset pressure range of the critical pressure point and the preset temperature range of the critical temperature point.

6. A multi-mode system control device for a RBCC engine, characterized in that: include: an initial mode determination unit, used to determine the initial working mode of the RBCC engine according to the mode selection instruction sent by the aircraft controller before the RBCC engine is operated, wherein the working modes of the RBCC engine include: rocket mode, rocket ramjet mode and ramjet mode; a propellant supply amount determination unit, used to determine the real-time working mode requirement of the RBCC engine and the propellant supply amount corresponding to different working modes according to the working characteristics of the power system of the RBCC engine and the received flight parameters during the operation of the RBCC engine; A mode conversion unit, used to control the rocket thrust chamber and the ramjet combustion chamber of the RBCC engine to open or close according to the engine working mode requirements, so as to convert the RBCC engine into different working modes; A propellant supply control unit is used to control the propellant supply of the RBCC engine according to the key point parameters of the RBCC engine and a preset key point parameter range.

7. An electronic device, characterized in that: include: processor; a memory for storing instructions executable by the processor; The processor is used to execute the multi-modal system control method of the RBCC engine as described in any one of claims 1 to 5 by running instructions in the memory.

8. A computer storage medium, characterized in that The computer storage medium stores instructions, and when the instructions are executed, the multi-modal system control method of the RBCC engine described in any one of claims 1 to 5 is executed.

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