Control method, device and equipment of variable cycle aero-engine and storage medium

Abstract

The invention discloses a control method, device and equipment for a variable-cycle aero-engine and a storage medium. The control method comprises the steps that the running state of the variable-cycle aero-engine is detected; if the variable-cycle aero-engine is in the mode conversion state, the oil supply state corresponding to the variable-cycle aero-engine is determined; and the working condition of the fan is adjusted according to the oil supply state. According to the method, the variable cycle aero-engine is used, and in the operation process of the aircraft, the working conditions of devices in the engine are automatically adjusted according to the operation state and the oil supply state of the variable cycle aero-engine in the target aircraft, so that the flight performance of the target aircraft is flexibly adjusted, and the universality of the target aircraft is improved; and meanwhile, the flight safety is guaranteed. The aircraft can be widely applied to the technical field of aircrafts.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to a control method, device, equipment and storage medium for a variable cycle aircraft engine. Background Art

[0002] An airplane is an aircraft that can fly in the atmosphere, usually relying on the lift generated by its wings to support the weight of the fuselage and achieving forward movement through the thrust or pull provided by the engines.

[0003] In related technologies, when an aircraft is in operation, it needs to go through different stages, such as take-off, climb, and cruise. The environments in different stages vary greatly, and the flight performance requirements for the aircraft are also different. Currently, due to insufficient engine capacity, some aircraft have obvious performance shortcomings in complex flight environments, poor versatility, and poor adaptability. Summary of the invention

[0004] The purpose of this application is to solve one of the technical problems existing in the related art to at least a certain extent.

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

[0006] In order to achieve the above technical objectives, the technical solutions adopted by the embodiments of the present application include:

[0007] On the one hand, an embodiment of the present application provides a control method for a variable cycle aircraft engine, wherein the variable cycle aircraft engine is arranged in a 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 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;

[0008] The method comprises:

[0009] Detecting the operating state of the variable cycle aircraft engine;

[0010] If the variable cycle aircraft engine is in a mode conversion state, determining a fuel supply state corresponding to the variable cycle aircraft engine;

[0011] The operating condition of the fan is adjusted according to the oil supply status.

[0012] In addition, the control method of a variable cycle aircraft engine according to the above embodiment of the present application may also have the following additional technical features:

[0013] Furthermore, in one embodiment of the present application, the detecting the operating state of the variable cycle aircraft engine includes:

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

[0015] 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.

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

[0017] Querying the standard oil-gas ratio parameter range corresponding to the variable cycle aircraft engine;

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

[0019] 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.

[0020] Further, in one embodiment of the present application, adjusting the operating condition of the fan according to the oil supply state includes:

[0021] 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.

[0022] Further, in one embodiment of the present application, adjusting the operating condition of the fan according to the oil supply state includes:

[0023] 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.

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

[0025] Furthermore, in one embodiment of the present application, the method further includes:

[0026] 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.

[0027] On the other hand, an embodiment of the present application provides a control device for a variable cycle aircraft engine, wherein the variable cycle aircraft engine is arranged in a 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 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;

[0028] The device comprises:

[0029] A first detection unit, used to detect the operating state of the variable cycle aircraft engine;

[0030] 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;

[0031] An execution unit is used to adjust the working condition of the fan according to the oil 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 above-mentioned control method of a variable cycle aircraft engine.

[0036] On the other hand, an embodiment of the present application further provides a computer-readable storage medium, which stores a program executable by a processor. When the program executable by the processor is executed by the processor, it is used to implement the above-mentioned control method of a variable cycle aircraft engine.

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

[0038] The embodiment of the present application discloses a control method for a variable cycle aircraft engine, which detects the operating state of the variable cycle aircraft engine; if the variable cycle aircraft engine is in a mode conversion state, determines the corresponding fuel supply state of the variable cycle aircraft engine; and adjusts the working condition of the fan according to the fuel supply state. The method uses a variable cycle aircraft engine, and during the operation of the aircraft, according to the operating state and fuel supply state of the variable cycle aircraft engine in the target aircraft, automatically adjusts the working condition of the components in the engine, thereby flexibly adjusting the flight performance of the target aircraft, improving the versatility of the target aircraft, and at the same time facilitating flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following introduction is made to the drawings of the embodiments of the present application or the related technical solutions in the prior art. It should be understood that the drawings introduced below are only for the convenience of clearly describing some embodiments of the technical solutions of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative work.

[0040] Figure 1 A schematic diagram of the structure of a variable cycle aircraft engine provided in an embodiment of the present application;

[0041] Figure 2 A schematic flow chart of a control method for a variable cycle aircraft engine provided in an embodiment of the present application;

[0042] Figure 3 A schematic diagram of a fan blade provided in an embodiment of the present application being retracted and folded in the direction of an air inlet cone;

[0043] Figure 4 This is a schematic structural diagram of a time-variable cycle aircraft engine with an inner nozzle closed and a retractable main shaft provided in an embodiment of the present application;

[0044] Figure 5 A schematic diagram of the structure of a computer device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0045] The present application is further described below in conjunction with the accompanying drawings and specific embodiments. The described embodiments should not be regarded as limiting the present application, and all other embodiments obtained by ordinary technicians in this field without creative work are 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, but it will be understood that “some embodiments” may be the same subset or different subsets of all possible embodiments and may be combined with each other without conflict.

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

[0048] An airplane is an aircraft that can fly in the atmosphere, usually relying on the lift generated by its wings to support the weight of the fuselage and achieving forward movement through the thrust or pull provided by the engines.

[0049] In related technologies, when an aircraft is in operation, it needs to go through different stages, such as take-off, climb, and cruise. The environments in different stages vary greatly, and the flight performance requirements for the aircraft are also different. Currently, due to insufficient engine capacity, some aircraft have obvious performance shortcomings in complex flight environments, poor versatility, and poor adaptability.

[0050] In view of this, a control method for a variable cycle aircraft engine is provided in an embodiment of the present application, which detects the operating state of the variable cycle aircraft engine; if the variable cycle aircraft engine is in a mode conversion state, determines the corresponding fuel supply state of the variable cycle aircraft engine; and adjusts the working condition of the fan according to the fuel supply state. The method uses a variable cycle aircraft engine, and during the operation of the aircraft, according to the operating state and fuel supply state of the variable cycle aircraft engine in the target aircraft, automatically adjusts the working condition of the components in the engine, thereby flexibly adjusting the flight performance of the target aircraft, improving the versatility of the target aircraft, and at the same time facilitating flight safety.

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

[0052] Please refer to Figure 1 , Figure 1 The schematic diagram of the structure of a variable cycle aircraft engine provided in the embodiment of the present application is shown. The variable cycle aircraft engine in the embodiment of the present application is composed of a large bypass ratio turbofan engine at the front and a ramjet engine at the rear. The turbofan engine part at the front can provide conventional propulsion during low altitude, medium and low speed, and conventional cruising flight. The rear ramjet engine is combined with the afterburner to provide instantaneous acceleration performance and additional propulsion during transonic flight. The front and rear parts are connected by an integrated airflow channel to ensure smooth airflow 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 at each flight stage, ensuring a safe and efficient flight process.

[0053] In the present application embodiment, Figure 1 As 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 an outer duct 3, and the inner side is an inner duct. Considering that the optimal working environment of the engine of the target aircraft is different at different flight stages, in order to ensure that the engine can operate in a suitable intake environment, in the embodiment of the present application, the design of the intake cone 1, the fan 2, the telescopic main shaft 6 and the inner nozzle 8 is adaptively adjusted. Specifically, the blades of the fan 2 in the embodiment of the present application can move, for example, they can be retracted and folded in the direction of the intake cone 1, or unfolded in the direction away from the intake cone 1, so as to provide different intake capabilities, so that the engine can optimize the air intake at different Mach numbers, and at the same time 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 embodiment of the present application, the main shaft of the turbofan engine is a telescopic main shaft 6, which can be extended or shortened according to demand, and the inner nozzle 8 can be closed or opened.

[0054] For a ramjet engine, it may 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 spray fuel into the afterburner 10 in the form of fine droplets. These fine droplets can evaporate quickly and mix with air to form a combustible mixture, thereby improving combustion efficiency and thrust. The afterburner 10 is a combustion area outside the combustion chamber 5, which is mainly used to further increase the thrust. The vector nozzle 12 is a nozzle that can change the direction of exhaust. By adjusting the direction of the nozzle, the thrust direction generated by the engine can be changed, thereby achieving control of the aircraft's attitude. The power recovery system 11 can be a device that recovers usable 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 device, it can be converted into electrical energy for use by the aircraft, which can not only improve the overall energy utilization efficiency, but also reduce the need for a separate generator, thereby reducing weight and maintenance costs.

[0055] Please refer to Figure 2 , Figure 2 is a flow chart of a control method for a variable cycle aircraft engine provided in an embodiment of the present application, with reference to Figure 2 The control method of the variable cycle aircraft engine includes but is not limited to:

[0056] Step 210: detecting the operating state of the variable cycle aircraft engine;

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

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

[0059] In an embodiment of the present application, a control method for a variable cycle aircraft engine is provided. The method uses a variable cycle aircraft engine. During the operation of an aircraft, the method automatically adjusts the operating conditions of components in the engine according to the operating state and fuel supply state of the variable cycle aircraft engine in a target aircraft, thereby flexibly adjusting the flight performance of the target aircraft, improving the versatility of the target aircraft, and at the same time facilitating flight safety.

[0060] Specifically, in the embodiment of the present application, when the target aircraft is operating, the operating state of the variable cycle aircraft engine can be detected. The operating state here can be divided into a normal state and a mode conversion state. Among them, when the fan blade expansion rate of the variable cycle aircraft engine is the maximum and the fan speed does not exceed the predetermined maximum speed, the engine is in the normal state. Figure 1 , Figure 1 The fan in the normal state is the state in which the blades are fully extended. The normal state can also be understood as the state in which the flight speed of the target aircraft is less than the variable cycle aircraft engine under the phoneme. In the embodiment of the present application, when the variable cycle aircraft engine is in the normal state, its control strategy is the same as the control method of the conventional turbofan engine, which will not be described in detail here.

[0061] In addition to the above-mentioned normal state, the variable cycle aircraft engine can also operate in a mode conversion state. Specifically, in the embodiment of the present application, the condition corresponding to the mode conversion state is that the oil-to-air ratio air bleed demand parameter required for 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 aircraft engine, the oil-to-air ratio air bleed demand parameter corresponding to the current normal operation of the variable cycle aircraft engine can be detected, and it can be compared with the first amount. The first amount here is the maximum oil-to-air ratio air bleed parameter that can be provided by the variable cycle aircraft engine in the normal state. If it is found that the oil-to-air ratio air bleed demand parameter corresponding to the current normal operation is greater than the first amount, it can be determined that the variable cycle aircraft engine is in a mode conversion state. In the embodiment of the present application, there is no restriction on the size of the first amount.

[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 by related devices, such as the pitot tube and static pressure hole on the target aircraft to calculate, and of course, it can also be calculated based on other auxiliary systems (such as inertial navigation system, global positioning system), etc., and this application does not limit this.

[0063] Specifically, in some embodiments, if the variable cycle aircraft engine is in a mode conversion state, determining a fuel supply state corresponding to the variable cycle aircraft engine includes:

[0064] Querying the standard oil-gas ratio parameter range corresponding to the variable cycle aircraft engine;

[0065] Detecting a current first fuel-air ratio parameter of the variable cycle aircraft engine;

[0066] 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.

[0067] In the embodiment of the present application, when determining the fuel supply state corresponding to the variable cycle aircraft engine, the corresponding standard oil-gas ratio parameter range can be queried according to the model information of the variable cycle aircraft engine, and the standard oil-gas ratio parameter range can characterize the range of the oil-gas ratio parameter corresponding to the operation of the variable cycle aircraft engine under normal circumstances. Then, the oil-gas ratio parameter corresponding to the current actual operation of the variable cycle aircraft engine can be detected in real time, recorded as the first oil-gas ratio parameter. If the first oil-gas ratio parameter is lower than the standard oil-gas ratio parameter range, it can be determined that the current variable cycle aircraft engine is insufficiently supplied with fuel, and therefore, at this time, it can be further determined that the variable cycle aircraft engine is in an overly lean oil state; conversely, if the first oil-gas ratio parameter exceeds the standard oil-gas ratio parameter range, it can be determined that the current variable cycle aircraft engine is supplied with too much fuel, and therefore, at this time, it can be further determined that the variable cycle aircraft engine is in an overly rich oil state.

[0068] Here, it should be noted that, in some embodiments, a threshold value may also be set. When determining the fuel supply state of the variable cycle aircraft engine, the difference between the first oil-gas ratio parameter and the standard oil-gas ratio parameter range may be calculated. If the difference is a positive number and is greater than the set threshold value, it may be determined that the variable cycle aircraft engine is in an over-rich oil state. If the difference is a negative number and its absolute value is greater than the set threshold value, it may be determined that the variable cycle aircraft engine is in an over-lean oil state. In the embodiment of the present application, there is no restriction on the size of the threshold value.

[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 aircraft engine is also provided, the device comprising:

[0075] A first detection unit, used to detect the operating state of the variable cycle aircraft engine;

[0076] 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;

[0077] An execution unit is used to adjust the working condition of the fan according to the oil supply state.

[0078] Understandably, Figure 2 The contents of the control method embodiment of a variable cycle aircraft engine shown in the figure are applicable to the control device embodiment of the variable cycle aircraft engine. The functions specifically implemented by the control device embodiment of the variable cycle aircraft engine are similar to those of the embodiment of the control method of the variable cycle aircraft engine shown in the figure. Figure 2 The control method embodiment of a variable cycle aircraft engine shown in FIG. 1 is the same as that of the embodiment of the variable cycle aircraft engine shown in FIG. 1 , and the beneficial effects achieved are the same as those achieved in FIG. Figure 2 The beneficial effects achieved by the control method embodiment of a variable cycle aircraft engine shown are also the same.

[0079] Reference Figure 5 , the embodiment of the present application further discloses a computer device, including:

[0080] at least one processor 510;

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

[0082] When at least one program is executed by at least one processor 510, the at least one processor 510 implements the following Figure 2 An embodiment of a control method for a variable cycle aircraft engine is shown.

[0083] It is understandable that if Figure 2 The contents of the control method embodiment of a variable cycle aircraft engine shown in FIG. 1 are all applicable to the computer device embodiment. The functions specifically implemented by the computer device embodiment are similar to those in FIG. Figure 2 The control method embodiment of a variable cycle aircraft engine shown in FIG. 1 is the same as that of FIG. 1 , and the beneficial effects achieved are the same as those of FIG. Figure 2 The beneficial effects achieved by the control method embodiment of a variable cycle aircraft engine shown are also the same.

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

[0085] It is understandable that if Figure 2 The contents of the control method embodiment of a variable cycle aircraft engine shown in FIG. 1 are applicable to the embodiment of the computer-readable storage medium. The functions specifically implemented by the embodiment of the computer-readable storage medium are similar to those in FIG. Figure 2 The control method embodiment of a variable cycle aircraft engine shown in FIG. 1 is the same as that of FIG. 1 , and the beneficial effects achieved are the same as those of FIG. Figure 2 The beneficial effects achieved by the control method embodiment of a variable cycle aircraft engine shown are also the same.

[0086] In some selectable embodiments, the function / operation mentioned in the block diagram may not occur in the order mentioned in the operation diagram. For example, depending on the function / operation involved, the two boxes shown in succession can actually be executed substantially simultaneously or the boxes can sometimes be executed in reverse order. In addition, the embodiment presented and described in the flow chart of the application is provided by way of example, for the purpose of providing a more comprehensive understanding of technology. The disclosed method is not limited to the operation and logic flow presented herein. Selectable embodiments are expected, wherein the order of various operations is changed and the sub-operation of a part described as a larger operation is performed independently.

[0087] In addition, although the present application is described in the context of functional modules, it should be understood that, unless otherwise specified, one or more of the functions and / or features can be integrated into a single physical system and / or software module, or one or more functions and / or features can be implemented in a separate physical system or software module. It can also be understood that a detailed discussion of the actual implementation of each module is unnecessary for understanding the present application. More specifically, in view of the properties, 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 conventional techniques of engineers. Therefore, those skilled in the art can implement the present application set forth in the claims without excessive experimentation using ordinary techniques. 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 attached claims and their equivalents.

[0088] If the 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 the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, which is stored in a storage medium and includes several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0089] The logic and / or steps represented in the flowchart or otherwise described herein, for example, can be considered as an ordered list of executable instructions for implementing logical functions, and can be embodied 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 system that can fetch instructions from an instruction execution system, system or device and execute the instructions), or in conjunction with these instruction execution systems, systems or devices. For the purpose of this specification, "computer-readable medium" can be any system that can contain, store, communicate, propagate or transport a program for use by an instruction execution system, system or device, or in conjunction with these instruction execution systems, systems or devices.

[0090] More specific examples of computer-readable media (a non-exhaustive list) include the following: an electrical connection with one or more wires (electronic systems), a portable computer disk case (magnetic systems), a random access memory (RAM), a read-only memory (ROM), an erasable and programmable read-only memory (EPROM or flash memory), a fiber optic system, and a portable compact disk read-only memory (CDROM). In addition, the computer-readable medium may even be a paper or other suitable medium on which the program is printed, since the program may be obtained electronically, for example, by optically scanning the paper or other medium, followed by editing, deciphering or, if necessary, processing in another suitable manner, and then stored in a computer memory.

[0091] It should be understood that the various parts of the present application can be implemented by hardware, software, firmware or a combination thereof. In the above-mentioned 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, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function for a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0092] In the above description of this specification, the description with reference to the terms "one embodiment / example", "another embodiment / example" or "certain embodiments / examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may 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 skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the claims and their equivalents.

[0094] The above is a specific description of the preferred implementation of the present application, but the present application is not limited to the embodiments. Those skilled in the art can make various equivalent modifications or substitutions without violating the spirit of the present application. These equivalent modifications or substitutions are all included in the scope defined by the claims of the present application.

[0095] In the description of this specification, the description with reference to the terms "one embodiment", "another embodiment" or "certain embodiments" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiments or examples are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may 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 skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that 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 fuel supply state corresponding to the variable cycle aircraft engine; The operating condition of the fan is adjusted according to the oil supply status.

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. The control method of a variable cycle aircraft engine according to claim 1, characterized in that: 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 follow the blades of the fan to be retracted and extended synchronously.

8. 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; An execution unit is used to adjust the working condition of the fan according to the oil supply state.

9. 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 1-7.

10. 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 7 when executed by the processor.

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