Control Method, Device, Equipment and Storage Medium of Variable Cycle Aeroengine

Abstract

The present application discloses a control method, device, equipment and storage medium for a variable cycle aeroengine. The control method detects the operating state of the variable cycle aeroengine; if the variable cycle aeroengine is in a mode conversion state, determines the fuel supply state corresponding to the variable cycle aeroengine; and adjusts the operating conditions of the fan according to the fuel supply state. By using the variable cycle aeroengine, during the operation of the aircraft, according to the operating state and fuel supply state of the variable cycle aeroengine in the target aircraft, the operating conditions of the components in the engine are automatically adjusted, so as to flexibly adjust the flight performance of the target aircraft, improve the versatility of the target aircraft, and at the same time is beneficial to ensuring flight safety. The present application can be widely applied in the field of aircraft technology.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and in particular to a control method, device, equipment and storage medium for a variable cycle aeroengine. Background Art

[0002] An aircraft is a flying vehicle that can fly in the atmosphere. It usually relies on the lift generated by its wings to support the weight of the fuselage and moves forward through the thrust or pull provided by the engine.

[0003] In the related art, when an aircraft is in operation, it needs to go through different flight phases, such as the takeoff phase, the climb phase, the cruise phase, etc. The environmental differences in different phases are relatively large, and the requirements for the flight performance of the aircraft are also different. Currently, some aircraft have obvious performance shortcomings, poor versatility and adaptability in complex flight environments due to insufficient engine capabilities. Summary of the Invention

[0004] An object of this application is to solve at least to some extent one of the technical problems existing in the related art.

[0005] To this end, an object of an embodiment of this application is to provide a control method, device, equipment and storage medium for a variable cycle aeroengine.

[0006] To achieve the above technical object, the technical solutions adopted in the embodiments of this application include:

[0007] On the one hand, an embodiment of this application provides a control method for a variable cycle aeroengine. The variable cycle aeroengine is arranged in a target aircraft. The variable cycle aeroengine includes a turbofan engine and a ramjet engine, and the turbofan engine and the ramjet engine are connected through an integrated air flow channel; the turbofan engine includes an inlet cone, a fan, a compressor, a combustion chamber, a telescopic main shaft, a power turbine and an inner nozzle connected in sequence, wherein the blades of the fan can contract and fold towards the direction of the inlet cone, or unfold towards the direction away from the inlet cone.

[0008] The method includes:

[0009] Detect the operating state of the variable cycle aeroengine.

[0010] If the variable cycle aeroengine is in a mode conversion state, determine the corresponding fuel supply state of the variable cycle aeroengine.

[0011] Adjust the operating conditions of the fan according to the fuel supply state.

[0012] In addition, according to the control method for a variable cycle aeroengine of the above embodiment of this application, the following additional technical features may also be provided:

[0013] Further, in an embodiment of the present application, detecting the operating state of the variable cycle aeroengine includes:

[0014] Detecting the fuel-air ratio bleed air demand parameter corresponding to the current normal operation of the variable cycle aeroengine;

[0015] If the fuel-air ratio bleed air demand parameter is greater than a first amount, determining that the variable cycle aeroengine is in a mode conversion state; wherein, the first amount is the maximum fuel-air ratio bleed air parameter that the variable cycle aeroengine can provide in a normal state.

[0016] Further, in an embodiment of the present application, if the variable cycle aeroengine is in a mode conversion state, determining the fuel supply state corresponding to the variable cycle aeroengine includes:

[0017] Querying the standard fuel-air ratio parameter range corresponding to the variable cycle aeroengine;

[0018] Detecting the current first fuel-air ratio parameter of the variable cycle aeroengine;

[0019] If the first fuel-air ratio parameter is lower than the standard fuel-air ratio parameter range, determining that the variable cycle aeroengine is in an over-lean state, or if the first fuel-air ratio parameter exceeds the standard fuel-air ratio parameter range, determining that the variable cycle aeroengine is in an over-rich state.

[0020] Further, in an embodiment of the present application, adjusting the working condition of the fan according to the fuel supply state includes:

[0021] If the variable cycle aeroengine is in an over-lean state, controlling the blades of the fan to expand away from the intake cone..

[0022] Further, in an embodiment of the present application, adjusting the working condition of the fan according to the fuel supply state includes:

[0023] If the variable cycle aeroengine is in an over-rich state, controlling the blades of the fan to contract and fold towards the intake cone.

[0024] Further, in an embodiment of the present application, the ramjet includes a fuel nozzle, a afterburner, a vector nozzle and a power recovery system.

[0025] Further, in an embodiment of the present application, the method further includes:

[0026] If the variable cycle aeroengine is in a mode conversion state, control the telescopic main shaft and the inner nozzle to retract and extend synchronously with the blades of the fan.

[0027] On the other hand, an embodiment of the present application provides a control device for a variable cycle aeroengine. The variable cycle aeroengine is arranged in a target aircraft. The variable cycle aeroengine includes a turbofan engine and a ramjet engine. The turbofan engine and the ramjet engine are connected through an integrated air flow channel. The turbofan engine includes an inlet cone, a fan, a compressor, a combustion chamber, a telescopic main shaft, a power turbine, and an inner nozzle connected in sequence. Among them, the blades of the fan can contract and fold towards the direction of the inlet cone, or unfold towards the direction away from the inlet cone.

[0028] The device includes:

[0029] A first detection unit for detecting the operating state of the variable cycle aeroengine;

[0030] A second detection unit for determining the fuel supply state corresponding to the variable cycle aeroengine if the variable cycle aeroengine is in a mode conversion state;

[0031] An execution unit for adjusting the operating conditions of the fan according to the fuel supply state.

[0032] On the other hand, an embodiment of the present application provides a computer device, including:

[0033] At least one processor;

[0034] At least one memory for storing at least one program;

[0035] When the at least one program is executed by the at least one processor, the at least one processor implements the control method of a variable cycle aeroengine as described above.

[0036] On the other hand, an embodiment of the present application further provides a computer-readable storage medium, in which a program executable by a processor is stored. The program executable by the processor is used to implement the control method of a variable cycle aeroengine as described above when executed by the processor.

[0037] The advantages and beneficial effects of the present application will be partially given in the following description, partially will become obvious from the following description, or be understood through the practice of the present application:

[0038] A control method for a variable cycle aeroengine disclosed in an embodiment of the present application detects the operating state of the variable cycle aeroengine; if the variable cycle aeroengine is in a mode conversion state, determines the corresponding fuel supply state of the variable cycle aeroengine; and adjusts the operating conditions of the fan according to the fuel supply state. This method uses a variable cycle aeroengine, and during the operation of an aircraft, automatically adjusts the operating conditions of components inside the engine according to the operating state and fuel supply state of the variable cycle aeroengine in the target aircraft, thereby flexibly adjusting the flight performance of the target aircraft, improving the versatility of the target aircraft, and being conducive to ensuring flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following introduces the drawings related to the technical solutions in the embodiments of the present application or the prior art. It should be understood that the drawings below only conveniently and clearly show some embodiments of the technical solutions in the present invention. For those skilled in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0040] Figure 1 FIG. is a schematic structural diagram of a variable cycle aeroengine provided in an embodiment of the present application;

[0041] Figure 2 FIG. is a schematic flow chart of a control method for a variable cycle aeroengine provided in an embodiment of the present application;

[0042] Figure 3 FIG. is a schematic diagram showing the blades of a fan shrinking and folding towards the intake cone in an embodiment of the present application;

[0043] Figure 4 FIG. is a schematic structural diagram of a variable cycle aeroengine when closing the inner nozzle and shrinking the telescopic main shaft in an embodiment of the present application;

[0044] Figure 5 FIG. is a schematic structural diagram of a computer device provided in an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0045] The present application will be further described below in conjunction with the drawings in the specification and specific embodiments. The described embodiments should not be regarded as limitations on the present application. All other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present application.

[0046] In the following description, reference is made to "some embodiments", which describe a subset of all possible embodiments. However, it can be understood that "some embodiments" can be the same subset or different subsets of all possible embodiments, and can be combined with each other without conflict.

[0047] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terms used herein are for the purpose of describing embodiments of this application only and are not intended to limit this application.

[0048] An aircraft is an aerial vehicle capable of flying in the atmosphere. It usually relies on the lift generated by its wings to support the weight of the fuselage and achieves forward movement through the thrust or pull provided by the engine.

[0049] In the related art, when an aircraft is in operation, it needs to go through different aircraft phases, such as the takeoff phase, the climb phase, the cruise phase, etc. The environmental differences in different phases are relatively large, and the requirements for the flight performance of the aircraft are also different. Currently, some aircraft have obvious performance short - comings, poor versatility, and poor adaptability in complex flight environments due to insufficient engine capabilities.

[0050] In view of this, in the embodiments of this application, a control method for a variable - cycle aero - engine is provided, which detects the operating state of the variable - cycle aero - engine; if the variable - cycle aero - engine is in a mode - conversion state, determines the corresponding fuel - supply state of the variable - cycle aero - engine; and adjusts the operating conditions of the fan according to the fuel - supply state. This method uses a variable - cycle aero - engine, and during the operation of the aircraft, according to the operating state and fuel - supply state of the variable - cycle aero - engine in the target aircraft, automatically adjusts the operating conditions of the components inside the engine, thereby flexibly adjusting the flight performance of the target aircraft, improving the versatility of the target aircraft, and at the same time being beneficial to ensuring flight safety.

[0051] Before introducing the control method for the variable - cycle aero - engine provided in the embodiments of this application, first, a variable - cycle aero - engine provided in the embodiments of this application is introduced and described. This variable - cycle aero - engine is arranged in the target aircraft, and the target aircraft here can be any type of aircraft, and this application does not limit this.

[0052] Please refer to Figure 1 , Figure 1 shows a schematic structural diagram of a variable - cycle aero - engine provided in the embodiments of this application. The variable - cycle aero - engine in the embodiments of this application is composed of a front large - bypass - ratio turbofan engine and a rear ramjet engine combined. The front turbofan engine part can provide conventional propulsion force during low - altitude, medium - low - speed, and conventional - cruise - state flights. The rear ramjet engine is combined with an afterburner and is responsible for providing instant acceleration performance and additional propulsion force during transonic flight. The front and rear parts are connected through an integrated air - flow channel to ensure smooth air flow inside the engine. At the same time, the systems complement each other to ensure that the aircraft has the best thrust when the speed and altitude change during each flight phase, and ensure the safety and efficiency of the flight process.

[0053] In the embodiments of the present application, as Figure 1 shown, the turbofan engine includes an intake cone 1, a fan 2, a compressor 4, a combustion chamber 5, a telescopic main shaft 6, a power turbine 7, and an inner nozzle 8 connected in sequence. The outer side of the compressor 4 is the bypass duct 3, and the inner side is the core duct. Considering that the optimal working environment of the engine varies in different flight stages of the target aircraft, in order to ensure that the engine can operate in a suitable intake environment, in the embodiments of the present application, the designs of the intake cone 1, the fan 2, the telescopic main shaft 6, and the inner nozzle 8 are adaptively adjusted. Specifically, the blades of the fan 2 in the embodiments of the present application can move, for example, they can contract and fold towards the intake cone 1 or expand away from the intake cone 1, so as to provide different intake capabilities, enabling the engine to optimize the air intake volume at different Mach numbers. At the same time, it can reduce the resistance generated by the blades of the engine fan 2 and the core engine during flight, and protect the internal structure of the core engine during supersonic flight. In the embodiments of the present application, the main shaft of the turbofan engine is the telescopic main shaft 6, which can extend or shorten according to requirements, and the inner nozzle 8 can move to close or open.

[0054] For a ramjet engine, it can include a fuel nozzle 9, an afterburner 10, a vector nozzle 12, and a power recovery system 11. Among them, the fuel nozzle 9 can inject fuel in the form of fine droplets into the afterburner 10. These fine droplets can quickly evaporate and mix with air to form a combustible mixture, thereby improving the combustion efficiency and thrust. The afterburner 10 is a combustion area outside the combustion chamber 5, mainly used to further increase the thrust. The vector nozzle 12 is a nozzle that can change the exhaust direction. By adjusting the direction of the nozzle, the direction of the thrust generated by the engine can be changed, thereby realizing the control of the aircraft attitude. The power recovery system 11 can be a device that recovers available energy from the engine exhaust and converts it into electrical energy. For example, by using high-temperature and high-pressure exhaust gas to drive a turbine or other mechanical devices, it can be converted into electrical energy for the aircraft to use. This can not only improve the overall energy utilization efficiency, but also reduce the demand for a separate generator, thereby reducing weight and maintenance costs.

[0055] Please refer to Figure 2 , Figure 2 which is a schematic flow diagram of a control method for a variable cycle aeroengine provided by the embodiments of the present application. Referring to Figure 2 , the control method for the variable cycle aeroengine includes but is not limited to:

[0056] Step 210, detecting the operating state of the variable cycle aeroengine;

[0057] Step 220: If the variable cycle aero-engine is in a mode conversion state, determine the fuel supply state corresponding to the variable cycle aero-engine;

[0058] Step 230: Adjust the operating condition of the fan according to the fuel supply state.

[0059] In an embodiment of the present application, a control method for a variable cycle aero-engine is provided. This method uses a variable cycle aero-engine. During the operation of an aircraft, according to the operating state and fuel supply state of the variable cycle aero-engine in the target aircraft, the operating conditions of the components inside the engine are automatically adjusted, so as to flexibly adjust the flight performance of the target aircraft, improve the versatility of the target aircraft, and at the same time help ensure flight safety.

[0060] Specifically, in an embodiment of the present application, during the operation of the target aircraft, the operating state of the variable cycle aero-engine can be detected. Here, the operating state can be divided into a normal state and a mode conversion state. Among them, when the fan blade deployment rate of the variable cycle aero-engine is the largest and the fan speed does not exceed a predetermined maximum speed, the engine is operating in the normal state at this time. Specifically, please refer to Figure 1 , Figure 1 the fan in which is in a state where the blades are fully deployed. The normal state can also be understood as the state of the variable cycle aero-engine when the flight speed of the target aircraft is less than the speed of sound. In an embodiment of the present application, when the variable cycle aero-engine is in the normal state, its control strategy is the same as that of a conventional turbofan engine, and will not be elaborated here.

[0061] In addition to the above normal state, the variable cycle aero-engine can also operate in a mode conversion state. Specifically, in an embodiment of the present application, the condition corresponding to the mode conversion state is that the fuel-air ratio bleed air demand parameter required for the normal operation of the engine has exceeded the maximum amount that can be provided in the normal state. Therefore, when detecting the operating state of the variable cycle aero-engine, the fuel-air ratio bleed air demand parameter corresponding to the current normal operation of the variable cycle aero-engine can be detected and compared with a first amount. Here, the first amount is the maximum fuel-air ratio bleed air parameter that the variable cycle aero-engine can provide in the normal state. If it is found that the fuel-air ratio bleed air demand parameter corresponding to the current normal operation is greater than the first amount, it can be determined that the variable cycle aero-engine is in the mode conversion state. In an embodiment of the present application, the size of the first amount is not limited.

[0062] In some embodiments, the state when the flight speed of the target aircraft exceeds the speed of sound (or is about to exceed the speed of sound) can also be determined as the mode conversion state. Here, the flight speed of the target aircraft can be detected through relevant devices, such as by calculating using the pitot tube and static pressure hole on the target aircraft. Of course, it can also be calculated based on other auxiliary systems (such as inertial navigation system, global positioning system), etc. This application does not limit this.

[0063] Specifically, in some embodiments, determining the fuel supply state corresponding to the variable cycle aeroengine when the variable cycle aeroengine is in the mode conversion state includes:

[0064] Query the standard fuel-air ratio parameter range corresponding to the variable cycle aeroengine;

[0065] Detect the current first fuel-air ratio parameter of the variable cycle aeroengine;

[0066] If the first fuel-air ratio parameter is lower than the standard fuel-air ratio parameter range, determine that the variable cycle aeroengine is in an over-lean state, or, if the first fuel-air ratio parameter exceeds the standard fuel-air ratio parameter range, determine that the variable cycle aeroengine is in an over-rich state.

[0067] In the embodiments of the present application, when determining the fuel supply state corresponding to the variable cycle aeroengine, the standard fuel-air ratio parameter range corresponding to it can be queried according to the model information of the variable cycle aeroengine. This standard fuel-air ratio parameter range can represent the range where the fuel-air ratio parameter corresponding to the normal operation of the variable cycle aeroengine is located. Then, the fuel-air ratio parameter corresponding to the current actual operation of the variable cycle aeroengine can be detected in real time, denoted as the first fuel-air ratio parameter. If the first fuel-air ratio parameter is lower than the standard fuel-air ratio parameter range, it can be determined that the fuel supply of the current variable cycle aeroengine is insufficient. Therefore, at this time, it can be further determined that the variable cycle aeroengine is in an over-lean state; relatively, if the first fuel-air ratio parameter exceeds the standard fuel-air ratio parameter range, it can be determined that the fuel supply of the current variable cycle aeroengine is too high. Therefore, at this time, it can be further determined that the variable cycle aeroengine is in an over-rich state.

[0068] Here, it should be noted that in some embodiments, a threshold can also be set. When determining the fuel supply state of the variable cycle aeroengine, the difference between the first fuel-air ratio parameter and the standard fuel-air ratio parameter range can be calculated. If this difference is positive and greater than the set threshold, it can be determined that the variable cycle aeroengine is in an over-rich state. If this difference is negative and its absolute value is greater than the set threshold, it can be determined that the variable cycle aeroengine is in an over-lean state. In the embodiments of the present application, the size of this threshold is not limited.

[0069] In the embodiment of the present application, the working condition of the fan can be adjusted according to the corresponding fuel supply state of the variable cycle aircraft engine. Specifically, for example, if the variable cycle aircraft engine is in an overly lean fuel state, the blades of the fan can be controlled to expand in a direction away from the intake cone, so that the intake volume of the variable cycle aircraft engine will be reduced, and the speed of the fan will be appropriately reduced, so that the oil-gas ratio parameter of the variable cycle aircraft engine can be appropriately increased to be close to the standard oil-gas ratio parameter range, thereby improving the fuel supply state of the variable cycle aircraft engine.

[0070] In contrast, if the variable cycle aircraft engine is in an overly oil-rich state, the fan blades can be controlled to shrink and fold in the direction of the intake cone until the fan blades and the intake cone form a complete and seamless whole. In this way, the air intake volume of the variable cycle aircraft engine will increase, and the fan speed will be appropriately increased, thereby appropriately increasing the oil-to-air ratio parameters of the variable cycle aircraft engine to make them close to the standard oil-to-air ratio parameter range, thereby improving the fuel supply state of the variable cycle aircraft engine. In addition, reducing the deployment rate of the fan blades can also eliminate the wear of the fan blades by the supersonic airflow, while further reducing the engine resistance. For example, please refer to Figure 3 , Figure 3 A schematic diagram showing the blades of a fan provided in an embodiment of the present application being retracted and folded in the direction of an air intake cone.

[0071] Specifically, in some embodiments, the method further includes:

[0072] If the variable cycle aircraft engine is in a mode conversion state, the telescopic main shaft and the inner nozzle are controlled to follow the blades of the fan to be retracted and extended synchronously.

[0073] In an embodiment of the present application, if the variable cycle aircraft engine is in a mode conversion state, the supersonic airflow entering the engine can meet the pressure condition of the rear ramjet engine. At this time, the telescopic main shaft and the inner nozzle can be synchronously controlled according to the control logic of the fan blades. Specifically, if the fan blades shrink and fold in the direction of the intake cone at this time, the inner nozzle can be controlled to close in linkage, and at the same time, the telescopic main shaft can be controlled to drive the turbofan engine to shrink and move away from the ramjet engine. The combined cone of the turbofan engine will shrink backwards, and the intake airflow can be guided to bypass the core engine and directly enter the ramjet engine, thereby reducing the internal resistance of the engine and improving combustion efficiency. For example, please refer to Figure 4 , Figure 4 A schematic diagram of the structure of a time-varying cycle aircraft engine with an inner nozzle closed and a retractable main shaft provided in an embodiment of the present application is shown. Relatively speaking, if the blades of the fan are deployed in a direction away from the air intake cone at this time, the inner nozzle can be controlled to be opened in a linkage manner, and at the same time, the retractable main shaft can be controlled to drive the turbofan engine to retract and move in a direction close to the ramjet engine, and the combined cone of the turbofan engine will extend forward.

[0074] In an embodiment of the present application, a control device for a variable cycle aeroengine is further provided. The device includes:

[0075] A first detection unit, configured to detect the operating state of the variable cycle aeroengine;

[0076] A second detection unit, configured to determine the fuel supply state corresponding to the variable cycle aeroengine if the variable cycle aeroengine is in a mode conversion state;

[0077] An execution unit, configured to adjust the operating conditions of the fan according to the fuel supply state.

[0078] It can be understood that Figure 2 The content in the embodiment of a control method for a variable cycle aeroengine shown is applicable to the embodiment of the control device for the variable cycle aeroengine. The functions specifically implemented by the embodiment of the control device for the variable cycle aeroengine are the same as those in Figure 2 the embodiment of a control method for a variable cycle aeroengine shown, and the beneficial effects achieved are also the same as those in Figure 2 the embodiment of a control method for a variable cycle aeroengine shown.

[0079] Referring to Figure 5 , an embodiment of the present application also discloses a computer device, including:

[0080] At least one processor 510;

[0081] At least one memory 520, configured to store at least one program;

[0082] When at least one program is executed by at least one processor 510, at least one processor 510 is caused to implement the embodiment of a control method for a variable cycle aeroengine as shown in Figure 2 .

[0083] It can be understood that, as in Figure 2 the embodiment of a control method for a variable cycle aeroengine shown, the content is applicable to the embodiment of the computer device. The functions specifically implemented by the embodiment of the computer device are the same as those in the embodiment of a control method for a variable cycle aeroengine as shown in Figure 2 , and the beneficial effects achieved are also the same as those in the embodiment of a control method for a variable cycle aeroengine as shown in Figure 2 .

[0084] An embodiment of the present application also discloses a computer-readable storage medium, in which a program executable by a processor is stored. The program executable by the processor is used to implement as in Figure 2An embodiment of a control method for a variable cycle aeroengine as shown.

[0085] It can be understood that the content in an embodiment of a control method for a variable cycle aeroengine as shown Figure 2 is applicable to this embodiment of the computer-readable storage medium. The functions specifically implemented in this embodiment of the computer-readable storage medium are the same as those in an embodiment of a control method for a variable cycle aeroengine as shown Figure 2 and the beneficial effects achieved are also the same as those achieved in an embodiment of a control method for a variable cycle aeroengine as shown Figure 2 and shown.

[0086] In some alternative embodiments, the functions / operations mentioned in the block diagrams may not occur in the order mentioned in the operation diagrams. For example, depending on the functions / operations involved, two consecutive blocks shown may actually be executed substantially simultaneously or the blocks can sometimes be executed in the reverse order. In addition, the embodiments presented and described in the flowcharts of the present application are provided by way of example for the purpose of providing a more comprehensive understanding of the technology. The disclosed methods are not limited to the operations and logical flows presented herein. Alternative embodiments are contemplated where the order of various operations is changed and where sub-operations described as part of a larger operation are executed independently.

[0087] Furthermore, although the present application has been described in the context of functional modules, it should be understood that, unless otherwise stated to the contrary, one or more of the functions and / or features may be integrated in a single physical system and / or software module, or one or more functions and / or features may be implemented in separate physical systems or software modules. It can also be understood that a detailed discussion of the actual implementation of each module is not necessary for understanding the present application. More precisely, considering the attributes, functions, and internal relationships of the various functional modules in the system disclosed herein, the actual implementation of the module will be understood within the ordinary skills of an engineer. Therefore, those skilled in the art can implement the present application as set forth in the claims without undue experimentation. It can also be understood that the specific concepts disclosed are merely illustrative and are not intended to limit the scope of the present application, which is determined by the full scope of the appended claims and their equivalents.

[0088] If a function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods in various embodiments of this application. The aforementioned storage medium includes: USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs, etc., all kinds of media that can store program codes.

[0089] The logic and / or steps represented in the flowchart or described in other ways herein, for example, can be considered as a definite sequence list of executable instructions for implementing logical functions, and can be specifically implemented in any computer-readable medium for use by an instruction execution system, system, or device (such as a computer-based system, a system including a processor, or other systems that can fetch instructions from the instruction execution system, system, or device and execute the instructions), or in combination with these instruction execution systems, systems, or devices. For the purposes of this specification, a "computer-readable medium" can be any system that can contain, store, communicate, propagate, or transport a program for use by or in combination with an instruction execution system, system, or device.

[0090] More specific examples (non-exhaustive list) of computer-readable media include the following: electrical connection parts with one or more wirings (electronic systems), portable computer disk cartridges (magnetic systems), random access memories (RAMs), read-only memories (ROMs), erasable programmable read-only memories (EPROMs or flash memories), optical fiber systems, and portable compact disc read-only memories (CDROMs). Additionally, a computer-readable medium can even be paper or other suitable media on which a program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other media, then editing, interpreting, or processing it in other suitable ways if necessary, and then storing it in a computer memory.

[0091] It should be understood that each part of the present application can be implemented by hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented by hardware, as in another embodiment, any one or a combination of the following techniques well known in the art can be used: discrete logic circuits having logic gate circuits for implementing logic functions on data signals, application specific integrated circuits having appropriate combinational logic gate circuits, programmable gate arrays (PGAs), field programmable gate arrays (FPGAs), etc.

[0092] In the above description of this specification, the descriptions referring to the terms "one embodiment / example", "another embodiment / example", or "certain embodiments / examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0093] Although the embodiments of the present application have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and purposes of the present application, and the scope of the present application is defined by the claims and their equivalents.

[0094] The above has specifically described the preferred embodiments of the present application, but the present application is not limited to the embodiments. Those skilled in the art can make various equivalent deformations or substitutions without departing from the spirit of the present application, and these equivalent deformations or substitutions are all included within the scope defined by the claims of the present application.

[0095] In the description of this specification, the descriptions referring to the terms "one embodiment", "another embodiment", or "certain embodiments", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0096] Although the embodiments of the present application have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and purposes of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. A control method for a variable cycle aircraft engine, characterized in that: The variable cycle aircraft engine is arranged in the target aircraft, and the variable cycle aircraft engine comprises a turbofan engine and a ramjet engine, wherein the turbofan engine and the ramjet engine are connected via an integrated airflow channel; the turbofan engine comprises an intake cone, a fan, a compressor, a combustion chamber, a telescopic main shaft, a power turbine and an inner nozzle which are connected in sequence, wherein the blades of the fan can be retracted and folded in the direction of the intake cone, or unfolded in the direction away from the intake cone; The method comprises: Detecting the operating state of the variable cycle aircraft engine; If the variable cycle aircraft engine is in a mode conversion state, determining a corresponding fuel supply state of the variable cycle aircraft engine; the mode conversion state is a state when the flight speed of the target aircraft exceeds the speed of sound; According to the oil supply state, adjusting the working condition of the fan; The method further comprises: If the variable cycle aircraft engine is in a mode conversion state, the telescopic main shaft and the inner nozzle are controlled to be retracted and extended synchronously following the blades of the fan; The controlling the telescopic main shaft and the inner nozzle to follow the blades of the fan to be retracted and extended synchronously comprises: If the blades of the fan are retracted and folded toward the direction of the air intake cone, the linkage control is used to close the inner nozzle, and the telescopic main shaft is controlled to drive the turbofan engine to retract and move in the direction away from the ramjet engine; or, if the blades of the fan are unfolded in the direction away from the air intake cone, the linkage control is used to open the inner nozzle, and the telescopic main shaft is controlled to drive the turbofan engine to retract and move in the direction close to the ramjet engine.

2. The control method of a variable cycle aircraft engine according to claim 1, characterized in that: The detecting the operating state of the variable cycle aircraft engine comprises: Detecting the oil-to-air ratio bleed air demand parameter corresponding to the current normal operation of the variable cycle aircraft engine; If the oil-to-air ratio bleed air requirement parameter is greater than a first amount, it is determined that the variable cycle aircraft engine is in a mode conversion state; wherein the first amount is the maximum oil-to-air ratio bleed air parameter that can be provided by the variable cycle aircraft engine in a normal state.

3. The control method of a variable cycle aircraft engine according to claim 1, characterized in that: If the variable cycle aircraft engine is in a mode conversion state, determining a corresponding fuel supply state of the variable cycle aircraft engine includes: Querying the standard oil-gas ratio parameter range corresponding to the variable cycle aircraft engine; Detecting a current first fuel-air ratio parameter of the variable cycle aircraft engine; If the first oil-gas ratio parameter is lower than the standard oil-gas ratio parameter range, it is determined that the variable cycle aircraft engine is in an overly lean oil state; or, if the first oil-gas ratio parameter exceeds the standard oil-gas ratio parameter range, it is determined that the variable cycle aircraft engine is in an overly rich oil state.

4. The control method of a variable cycle aircraft engine according to claim 3, characterized in that: The step of adjusting the operating condition of the fan according to the oil supply state includes: If the variable cycle aircraft engine is in an overly lean fuel state, the blades of the fan are controlled to expand in a direction away from the intake cone.

5. The control method of a variable cycle aircraft engine according to claim 3, characterized in that: The step of adjusting the operating condition of the fan according to the oil supply state includes: If the variable cycle aircraft engine is in an over-fuel-rich state, the blades of the fan are controlled to shrink and fold toward the direction of the air intake cone.

6. The control method of a variable cycle aircraft engine according to claim 1, characterized in that: The ramjet engine includes a fuel nozzle, an afterburner, a vectoring nozzle and an electric power recovery system.

7. A control device for a variable cycle aircraft engine, characterized in that: The variable cycle aircraft engine is arranged in the target aircraft, and the variable cycle aircraft engine comprises a turbofan engine and a ramjet engine, wherein the turbofan engine and the ramjet engine are connected via an integrated airflow channel; the turbofan engine comprises an intake cone, a fan, a compressor, a combustion chamber, a telescopic main shaft, a power turbine and an inner nozzle which are connected in sequence, wherein the blades of the fan can be retracted and folded in the direction of the intake cone, or unfolded in the direction away from the intake cone; The device comprises: A first detection unit, used to detect the operating state of the variable cycle aircraft engine; A second detection unit is used to determine a fuel supply state corresponding to the variable cycle aircraft engine if the variable cycle aircraft engine is in a mode conversion state; the mode conversion state is a state when the flight speed of the target aircraft exceeds the speed of sound; An execution unit, used for adjusting the working condition of the fan according to the oil supply state; The device is also used for: If the variable cycle aircraft engine is in a mode conversion state, the telescopic main shaft and the inner nozzle are controlled to be retracted and extended synchronously following the blades of the fan; The controlling the telescopic main shaft and the inner nozzle to follow the blades of the fan to be retracted and extended synchronously comprises: If the blades of the fan are retracted and folded toward the direction of the air intake cone, the linkage control is used to close the inner nozzle, and the telescopic main shaft is controlled to drive the turbofan engine to retract and move in the direction away from the ramjet engine; or, if the blades of the fan are unfolded in the direction away from the air intake cone, the linkage control is used to open the inner nozzle, and the telescopic main shaft is controlled to drive the turbofan engine to retract and move in the direction close to the ramjet engine.

8. A computer device, characterized in that: include: at least one processor; at least one memory for storing at least one program; When the at least one program is executed by the at least one processor, the at least one processor implements the control method of a variable cycle aircraft engine as described in any one of claims 1-6.

9. A computer-readable storage medium storing a program executable by a processor, characterized in that: The processor-executable program is used to implement a control method for a variable-cycle aircraft engine as described in any one of claims 1 to 6 when executed by the processor.

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