Electromagnetic test simulation system of aero-engine control system and operation method of electromagnetic test simulation system

Abstract

The invention provides an electromagnetic test simulation system of an aero-engine control system and an operation method of the electromagnetic test simulation system. The electromagnetic test simulation system comprises an aero-engine operation simulation module; the aero-engine operation monitoring sensor simulation module is configured to receive an operation state signal of the aero-engine operation simulation module and send an operation state sensing signal; the aero-engine electronic controller is configured to receive the running state sensing signal and output a control current signal; the aero-engine hydraulic fuel system simulation module is configured to receive the control current signal and send a fuel supply control signal to the aero-engine operation simulation module; the electromagnetic test interference value injection module is configured to inject an electromagnetic test interference value into the aero-engine electronic controller or the aero-engine hydraulic fuel system simulation module; the aero-engine operation simulation module is configured to provide an aero-engine thrust simulation output value.

Description

Technical Field

[0001] The present invention mainly relates to the field of aero-engines, and particularly relates to an electromagnetic test simulation system for an aero-engine control system and an operation method thereof. Background Art

[0002] During high-altitude flight, an aero-engine will encounter various electromagnetic environments, such as lightning, high-intensity radiated fields (HIRF), and electromagnetic interferences (EMI) of various frequencies. To ensure that the function of the aero-engine thrust control can still guarantee the stable operation of the engine under a complex electromagnetic environment, electromagnetic tests need to be carried out during the design verification and airworthiness certification stages of the engine control system to verify that the engine control system can operate reliably and normally in the electromagnetic environment, thereby ensuring the flight safety of the aircraft. Therefore, it is necessary to provide an electromagnetic test simulation system for an aero-engine control system and an operation method thereof to achieve efficient and convenient electromagnetic tests for aero-engines. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide an electromagnetic test simulation system for an aero-engine control system and an operation method thereof, which can achieve efficient and convenient electromagnetic tests for aero-engines and save costs at the same time.

[0004] To solve the above technical problem, the present invention provides an electromagnetic test simulation system for an aero-engine control system, including: an aero-engine operation simulation module; an aero-engine operation monitoring sensor simulation module, configured to: receive the operation state signal of the aero-engine operation simulation module and send out an operation state sensing signal; an aero-engine electronic controller, configured to: receive the operation state sensing signal and output a control current signal; an aero-engine hydraulic fuel system simulation module, configured to: receive the control current signal and send out a fuel supply control signal to the aero-engine operation simulation module; an electromagnetic test interference value injection module, configured to: inject an electromagnetic test interference value into the aero-engine electronic controller or the aero-engine hydraulic fuel system simulation module; the aero-engine operation simulation module is configured to: provide an aero-engine thrust simulation output value.

[0005] In an embodiment of the present invention, the electromagnetic test interference value injection module includes an operating state sensing signal interference value injection module and a control current interference value injection module; the operating state sensing signal interference value injection module is configured to inject a sensing signal interference value into the aeroengine electronic controller; the control current interference value injection module is configured to inject a control current interference value into the aeroengine hydraulic fuel system simulation module.

[0006] In an embodiment of the present invention, the electromagnetic test includes: voltage spike test, power line audio conduction susceptibility test, induced signal susceptibility test, radio frequency conduction susceptibility test, radio frequency radiation susceptibility test, and / or lightning induced transient susceptibility test.

[0007] In an embodiment of the present invention, the induced signal susceptibility test includes: induced magnetic field test on electrical equipment, induced electric field test on electrical equipment, induced magnetic field test on interconnection cables, induced electric field test on interconnection cables, and / or induced spike test on interconnection cables.

[0008] In an embodiment of the present invention, the aeroengine operation monitoring sensor simulation module includes: a rotational speed monitoring sensor simulation module, a temperature monitoring sensor simulation module, an air pressure monitoring sensor simulation module, and / or a throttle lever angle monitoring sensor simulation module.

[0009] In an embodiment of the present invention, the electromagnetic test simulation system of the aeroengine control system further includes a simulation control module, and the simulation control module is configured to: issue a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states, and receive the aeroengine thrust simulation output values corresponding to different electromagnetic test simulation states.

[0010] In an embodiment of the present invention, issuing a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states, and receiving the aeroengine thrust simulation output values corresponding to different electromagnetic test simulation states includes: setting the operating parameters of the aeroengine operation simulation module to make the aeroengine operation simulation module stably operate in a first operating state to be analyzed; setting the curve of the throttle lever angle changing with time output by the aeroengine operation monitoring sensor simulation module as the input signal of the aeroengine electronic controller; obtaining the first aeroengine thrust simulation output value output when the aeroengine operation simulation module stably operates in the first operating state to be analyzed; injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module to make the aeroengine operation simulation module operate in a second operating state to be analyzed; obtaining the second aeroengine thrust simulation output value output when the aeroengine operation simulation module operates in the second operating state to be analyzed.

[0011] In an embodiment of the present invention, the simulation control module is further configured to: calculate the change ratio of the aero-engine thrust simulation output value according to the first aero-engine thrust simulation output value and the second aero-engine thrust simulation output value; and determine whether the aero-engine control system corresponding to the aero-engine operation simulation module, the aero-engine operation monitoring sensor simulation module, and the aero-engine hydraulic fuel system simulation module meets the electromagnetic compatibility standard based on the change ratio of the aero-engine thrust simulation output value and the corresponding electromagnetic test criterion.

[0012] In an embodiment of the present invention, the simulation control module is further configured to: obtain the most sensitive operating point of electromagnetic protection of the aero-engine control system according to the change ratio of the aero-engine thrust simulation output value under different operating states.

[0013] In an embodiment of the present invention, the electromagnetic signal interference value injected by the electromagnetic test interference value injection module and exceeding the defined allowable error includes: injecting different types of electromagnetic signal interference values corresponding to different electromagnetic tests by the electromagnetic test interference value injection module in a specific order.

[0014] In an embodiment of the present invention, there is an injection interval between the different types of electromagnetic signal interference values.

[0015] In an embodiment of the present invention, the operating parameters of the aero-engine operation simulation module include different operating Mach numbers and flight altitudes of the aero-engine.

[0016] The present invention also provides an operation method for an electromagnetic test simulation system of an aeroengine control system. The electromagnetic test simulation system of the aeroengine control system includes an aeroengine operation simulation module, an aeroengine operation monitoring sensor simulation module, an aeroengine electronic controller, an aeroengine hydraulic fuel system simulation module, and an electromagnetic test interference value injection module. The aeroengine operation monitoring sensor simulation module is configured to receive the operation status signal of the aeroengine operation simulation module and issue an operation status sensing signal. The aeroengine electronic controller is configured to receive the operation status sensing signal and output a control current signal. The aeroengine hydraulic fuel system simulation module is configured to receive the control current signal and issue a fuel supply control signal to the aeroengine operation simulation module. The electromagnetic test interference value injection module is configured to inject an electromagnetic test interference value into the aeroengine electronic controller or the aeroengine hydraulic fuel system simulation module. The aeroengine operation simulation module is configured to provide an aeroengine thrust simulation output value. The operation method includes: issuing a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states and receiving the aeroengine thrust simulation output values corresponding to different electromagnetic test simulation states.

[0017] Compared with the prior art, the present invention has the following advantages: In the technical solution of this application, by setting the performance parameters of the aeroengine operation simulation module, the entire flight envelope of the aeroengine is simulated, so as to comprehensively evaluate and verify the electromagnetic compatibility of the aeroengine control system during the entire operation process of the aeroengine. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings are provided to further understand the present application, and they are incorporated and constitute a part of the present application. The drawings show the embodiments of the present application and, together with this specification, serve to explain the principle of the present application.

[0019] In the drawings:

[0020] Figure 1 is a schematic diagram of the composition of an electromagnetic test simulation system of an aeroengine control system according to an embodiment of the present application.

[0021] Figure 2 is a schematic diagram of the composition of an electromagnetic test simulation system of an aeroengine control system according to another embodiment of the present application.

[0022] Figure 3 is a flowchart of the operation method of an electromagnetic test simulation system of an aeroengine control system according to an embodiment of the present application.

[0023] Figure 4It is a flowchart of the operation method of the electromagnetic test simulation system of an aero-engine control system according to another embodiment of the present application.

[0024] Figure 5 It is a flowchart of the operation method of the electromagnetic test simulation system of an aero-engine control system according to another embodiment of the present application.

[0025] Figure 6 It is a schematic diagram of the electromagnetic signal waveform according to an embodiment of the present application.

[0026] Figure 7 It is a schematic diagram of the electromagnetic signal waveform according to another embodiment of the present application.

[0027] Figure 8 It is a schematic diagram of the curve of the throttle lever angle changing with time output by the aero-engine operation monitoring sensor simulation module according to an embodiment of the present application.

[0028] Figure 9 It is the waveform corresponding to the simulation output value of the aero-engine thrust without the injection of electromagnetic signal interference value according to an embodiment of the present application.

[0029] Figure 10 It is the waveform corresponding to the simulation output value of the aero-engine thrust with the injection of electromagnetic signal interference value according to an embodiment of the present application. Detailed implementation manners

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some examples or embodiments of the present application. For those of ordinary skill in the art, without creative efforts, the present application can also be applied to other similar scenarios based on these drawings. Unless obvious from the language context or otherwise stated, the same reference numerals in the figures represent the same structure or operation.

[0031] As shown in the present application and the claims, unless the context clearly indicates an exception, words such as "a", "an", "one" and / or "the" are not specifically singular and may also include plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of the clearly identified steps and elements, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0032] Unless otherwise specifically stated, the relative arrangements of the components and steps described in these embodiments, numerical expressions and values do not limit the scope of the present application. At the same time, it should be understood that for the sake of description, the dimensions of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship.

[0033] In this application, flowcharts are used to illustrate the operations performed by the system according to the embodiments of this application. It should be understood that the operations before or below do not necessarily need to be executed precisely in sequence. Instead, various steps can be executed in reverse order or simultaneously. Also, one or more other operations can be added to these processes, or one or more steps can be removed from these processes.

[0034] Embodiments of this application describe an electromagnetic test simulation system for an aero-engine control system and its operation method.

[0035] Figure 1 It is a schematic diagram of the composition of the electromagnetic test simulation system for an aero-engine control system according to an embodiment of this application. Refer to Figure 1 , the electromagnetic test simulation system 100 for an aero-engine control system includes an aero-engine operation simulation module 111, an aero-engine operation monitoring sensor simulation module 112, an aero-engine hydraulic fuel system simulation module 113, an aero-engine electronic controller 211, and an electromagnetic test interference value injection module 310. The aero-engine operation simulation module 111, the aero-engine operation monitoring sensor simulation module 112, and the aero-engine hydraulic fuel system simulation module 113 constitute, for example, the aero-engine control system simulation module 101. The aero-engine operation simulation module 111 simulates the real-time operation of the aero-engine.

[0036] In some embodiments, the aero-engine operation monitoring sensor simulation module 112 is configured to: receive the operation status signal s1 of the aero-engine operation simulation module 111 and issue an operation status sensing signal s2. The aero-engine electronic controller 211 is configured to: receive the operation status sensing signal s2 and output a control current signal s3. The aero-engine hydraulic fuel system simulation module 113 is configured to: receive the control current signal s3 and issue a fuel supply control signal s4 to the aero-engine operation simulation module 111.

[0037] The electromagnetic test interference value injection module 310 is configured to: inject the electromagnetic test interference value into the aero-engine electronic controller 211 or the aero-engine hydraulic fuel system simulation module 113. The aero-engine operation simulation module 111 is configured to: provide an aero-engine thrust simulation output value r1.

[0038] In some embodiments, the electromagnetic test interference value injection module 310 includes an operation status sensing signal interference value injection module 311 and a control current interference value injection module 312. The operation status sensing signal interference value injection module 311 is configured to: inject the sensing signal interference value d1 into the aero-engine electronic controller 211. The control current interference value injection module 312 is configured to: inject the control current interference value d2 into the aero-engine hydraulic fuel system simulation module 113.

[0039] In some embodiments, the electromagnetic tests include: voltage spike test, power line audio conduction susceptibility test, induced signal susceptibility test, radio frequency conduction susceptibility test, radio frequency radiation susceptibility test, and / or lightning induced transient susceptibility test. The induced signal susceptibility test includes: induced magnetic field test on electrical equipment, induced electric field test on electrical equipment, induced magnetic field test on interconnection cables, induced electric field test on interconnection cables, and / or induced spike test on interconnection cables.

[0040] In some embodiments, the aero-engine operation monitoring sensor simulation module 112 includes: a rotational speed monitoring sensor simulation module, a temperature monitoring sensor simulation module, a barometric pressure monitoring sensor simulation module, and / or a throttle lever angle monitoring sensor simulation module.

[0041] Figure 2 It is a schematic diagram of the composition of the electromagnetic test simulation system of the aero-engine control system according to another embodiment of the present application.

[0042] Reference Figure 2 , in some embodiments, the electromagnetic test simulation system 200 of the aero-engine control system further includes a simulation control module 201, and the simulation control module 201 is configured to: issue a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states, and receive the aero-engine thrust simulation output value r1 corresponding to different electromagnetic test simulation states. The simulation control instruction includes, for example, Figure 2 cr1, cr2, and cr3 in

[0043] In some embodiments, the simulation control module 201 issues a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states, and receiving the aero-engine thrust simulation output value corresponding to different electromagnetic test simulation states includes: Step 301, setting the operating parameters of the aero-engine operation simulation module 111 to make the aero-engine operation simulation module 111 stably operate in the first operation state to be analyzed. Step 302, setting the curve of the throttle lever angle varying with time output by the aero-engine operation monitoring sensor simulation module 112 as the input signal of the aero-engine electronic controller 211; Step 303, obtaining the first aero-engine thrust simulation output value output when the aero-engine operation simulation module 111 stably operates in the first operation state to be analyzed; Step 304, injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module 310 to make the aero-engine operation simulation module 111 operate in the second operation state to be analyzed; the electromagnetic signal interference value exceeding the defined allowable error is obtained, for example, through electromagnetic tests. Step 305, obtaining the second aero-engine thrust simulation output value output when the aero-engine operation simulation module 111 operates in the second operation state to be analyzed.

[0044] In some embodiments, the electromagnetic signal interference values exceeding the defined allowable error injected by the electromagnetic test interference value injection module 310 include: injecting different types of electromagnetic signal interference values corresponding to different electromagnetic tests by the electromagnetic test interference value injection module 310 in a specific order. There is, for example, an injection interval between different types of electromagnetic signal interference values.

[0045] In some embodiments, in addition to the foregoing steps 301 to 305, the simulation control module 201 is further configured to perform the following operations: step 406, calculate the change ratio of the aeroengine thrust simulation output value according to the first aeroengine thrust simulation output value and the second aeroengine thrust simulation output value; step 407, based on the change ratio of the aeroengine thrust simulation output value and the corresponding electromagnetic test criterion, determine whether the aeroengine control system corresponding to the aeroengine operation simulation module 111, the aeroengine operation monitoring sensor simulation module 112, and the aeroengine hydraulic fuel system simulation module 113 meets the electromagnetic compatibility standard.

[0046] In some embodiments, in addition to the foregoing steps 301 to 305 and steps 406 to 407, the simulation control module 201 is further configured to perform the following operation: step 508, obtain the most sensitive operating point of the electromagnetic protection of the aeroengine control system according to the change ratio of the aeroengine thrust simulation output value under different operating states.

[0047] In some embodiments, the operating parameters of the aeroengine operation simulation module 111 include different operating Mach numbers and flight altitudes of the aeroengine. The most sensitive operating point of the electromagnetic protection of the aeroengine control system includes specific operating Mach numbers and flight altitudes.

[0048] The present application also provides an operating method for an electromagnetic test simulation system of an aeroengine control system.

[0049] As described above, the electromagnetic test simulation system of the aeroengine control system includes an aeroengine operation simulation module, an aeroengine operation monitoring sensor simulation module, an aeroengine hydraulic fuel system simulation module, an aeroengine electronic controller, and an electromagnetic test interference value injection module. The connection relationships of the various modules in the electromagnetic test simulation system of the aeroengine control system will not be elaborated herein.

[0050] The operating method of the electromagnetic test simulation system of the aeroengine control system includes: issuing a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states, and receiving the aeroengine thrust simulation output values corresponding to the different electromagnetic test simulation states.

[0051] Figure 3It is a flowchart of the operation method of the electromagnetic test simulation system of an aero-engine control system according to an embodiment of the present application. Refer to Figure 3 , in some embodiments, issuing a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states and receiving the aero-engine thrust simulation output values corresponding to different electromagnetic test simulation states includes: Step 301, setting the operating parameters of the aero-engine operation simulation module to make the aero-engine operation simulation module stably operate in the first operation state to be analyzed. Step 302, setting the throttle lever angle change curve over time output by the aero-engine operation monitoring sensor simulation module as the input signal of the aero-engine electronic controller; Step 303, obtaining the first aero-engine thrust simulation output value output when the aero-engine operation simulation module stably operates in the first operation state to be analyzed. Step 304, injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module to make the aero-engine operation simulation module operate in the second operation state to be analyzed; the electromagnetic signal interference value exceeding the defined allowable error is obtained through electromagnetic tests, for example. Step 305, obtaining the second aero-engine thrust simulation output value output when the aero-engine operation simulation module operates in the second operation state to be analyzed.

[0052] Figure 6 It is a schematic diagram of the electromagnetic signal waveform according to an embodiment of the present application. Figure 7 It is a schematic diagram of the electromagnetic signal waveform according to another embodiment of the present application. Refer to Figure 6 , the fluctuation upper limit value 611 and the fluctuation lower limit value 612 constitute the defined allowable error of the electromagnetic signal, and the specific ratio or amplitude of the defined allowable error is determined according to the specific engineering environment. Figure 6 This section of the electromagnetic signal 601 in exceeds the defined allowable error defined by the fluctuation upper limit value 611 and the fluctuation lower limit value 612. And Figure 7 This section of the electromagnetic signal 701 in does not exceed the defined allowable error defined by the fluctuation upper limit value 711 and the fluctuation lower limit value 712. Therefore, in Step 304, the corresponding electromagnetic signal interference value in Figure 6 is injected into the corresponding signal input terminal through the electromagnetic test interference value injection module.

[0053] In some embodiments, injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module includes: injecting different types of electromagnetic signal interference values corresponding to different electromagnetic tests in a specific order through the electromagnetic test interference value injection module. There is an injection interval between different types of electromagnetic signal interference values, for example.

[0054] Figure 8 It is a schematic diagram of the throttle lever angle change curve over time output by the aero-engine operation monitoring sensor simulation module according to an embodiment of the present application. Refer to Figure 8, the duration of each step corresponding to the stepped change of the throttle lever angle is, for example, t z . Figure 9 is the waveform corresponding to the simulated output value of the thrust of the aero-engine without the injection of electromagnetic signal interference values in an embodiment of the present application.

[0055] As described above, the electromagnetic tests include: voltage spike test, power line audio conduction susceptibility test, induced signal susceptibility test, radio frequency conduction susceptibility test, radio frequency radiation susceptibility test, and / or lightning-induced transient susceptibility test. The induced signal susceptibility test includes: induced magnetic field test on electrical equipment, induced electric field test on electrical equipment, induced magnetic field test on interconnection cables, induced electric field test on interconnection cables, and / or induced spike test on interconnection cables. The electromagnetic signal interference value corresponding to each electromagnetic test subject is, for example, k i (i = 1, 2,..., 6). The electromagnetic signal interference value corresponding to each electromagnetic test subject is obtained, for example, by operating the aero-engine control system in an actual electromagnetic test environment and obtaining the electromagnetic response output by the aero-engine control system.

[0056] In some embodiments, the electromagnetic test interference value injection module injects different types of electromagnetic signal interference values corresponding to different electromagnetic tests in a specific order, for example: from 0 to t 1 No electromagnetic signal interference data injection (corresponding to the case where the aero-engine operates in an electromagnetic-free environment), t 1 ~t 2 Inject the electromagnetic response output by the aero-engine control system in the electromagnetic test subject k 1 (that is, the electromagnetic signal interference value obtained in the electromagnetic test subject k 1 ), t 2 ~t 3 No electromagnetic test acquisition data injection (corresponding to the case where the aero-engine operates in an electromagnetic-free environment after the electromagnetic interference source disappears, allowing t 2 =t 3 ), t 3 ~t 4 Inject the electromagnetic response output by the aero-engine control system in the electromagnetic test subject k 2 (that is, the electromagnetic signal interference value obtained in the electromagnetic test subject k 2 ), t 4 ~t 5 No electromagnetic test acquisition data injection (corresponding to the case where the aero-engine operates in an electromagnetic-free environment after the electromagnetic interference source disappears, allowing t 4 =t 5 ), t 5 ~t 6 Inject the electromagnetic response output by the aero-engine control system in the electromagnetic test subject k 3The electromagnetic response output by the aero-engine control system (i.e., the electromagnetic test subject k 3 the electromagnetic signal interference value obtained therein), t 6 ~t z There is no injection of electromagnetic test acquisition data. The above-mentioned injection order of the electromagnetic signal interference value is only an example. Actually, it can also be other input orders. For example, first inject the electromagnetic signal interference value obtained in the electromagnetic test subject k 4 then inject the electromagnetic signal interference value obtained in the electromagnetic test subject k 2 then inject the electromagnetic signal interference value obtained in the electromagnetic test subject k 6 the injection order of the electromagnetic signal interference value obtained therein, or more types of electromagnetic signal interference values can also be continuously injected.

[0057] Figure 10 is the waveform corresponding to the aero-engine thrust simulation output value when there is an injection of electromagnetic signal interference value in an embodiment of the present application. Refer to Figure 9 and Figure 10 , it can be seen that after different types of electromagnetic signal interference values are injected at different time sequences, the aero-engine thrust simulation output value fluctuates. It should be noted that Figure 8 only takes the time interval from 0 - t z to illustrate the time sequence of the injection of the electromagnetic signal interference value. The actual electromagnetic signal interference value is not injected into the throttle lever angle, but into the corresponding signal input end of the electromagnetic test simulation system of the aero-engine control system, such as the signal input end of the aero-engine electronic controller and the signal input end of the aero-engine hydraulic fuel system simulation module.

[0058] In an embodiment, the injected electromagnetic signal interference value is, for example:

[0059]

[0060]

[0061] Among them, the signal with the unit of millivolt (mV) is, for example, the electromagnetic signal interference value obtained by converting the sensor signal.

[0062] Figure 4 is the flowchart of the operation method of the electromagnetic test simulation system of the aero-engine control system in another embodiment of the present application.

[0063] Refer to Figure 4, in some other embodiments, the operation method of the electromagnetic test simulation system of the aero-engine control system further includes, in addition to steps 401 to 405 similar to the aforementioned steps 301 to 305: step 406, calculating the change ratio of the aero-engine thrust simulation output value according to the first aero-engine thrust simulation output value and the second aero-engine thrust simulation output value; step 407, based on the change ratio of the aero-engine thrust simulation output value and the corresponding electromagnetic test criterion, determining whether the aero-engine control system corresponding to the aero-engine operation simulation module, the aero-engine operation monitoring sensor simulation module, and the aero-engine hydraulic fuel system simulation module meets the electromagnetic compatibility standard.

[0064] Figure 5 It is a flowchart of the operation method of the electromagnetic test simulation system of the aero-engine control system according to another embodiment of the present application.

[0065] Reference Figure 5 , in some other embodiments, the operation method of the electromagnetic test simulation system of the aero-engine control system further includes, in addition to steps 501 to 507 similar to the aforementioned steps 401 to 407: step 508, obtaining the most sensitive operating point of the electromagnetic protection of the aero-engine control system according to the change ratio of the aero-engine thrust simulation output value under different operating states.

[0066] As described above, the operating parameters of the aero-engine operation simulation module include different operating Mach numbers and flight altitudes of the aero-engine. The most sensitive operating point of the electromagnetic protection of the aero-engine control system includes specific operating Mach numbers and flight altitudes.

[0067] The electromagnetic test simulation system of the aero-engine control system of the present application includes an aero-engine hydraulic fuel system simulation module, so that the hardware device of the hydraulic fuel system does not need to be used in the electromagnetic test simulation, reducing the complexity of the electromagnetic test simulation, improving the safety of the electromagnetic test simulation, and eliminating the influence of abnormal or faulty fuel systems on the electromagnetic test simulation process.

[0068] The electromagnetic test simulation system of the aero-engine control system of the present application and its operation method simulate the entire flight envelope of the aero-engine (i.e., the entire flight cycle in which the aero-engine provides power for the aircraft) by setting the performance parameters (such as flight altitude, Mach number) of the aero-engine operation simulation module, so as to comprehensively evaluate and verify the electromagnetic compatibility of the aero-engine control system during the entire operation process of the aero-engine.

[0069] By comparing the thrust fluctuation changes caused by adjusting the performance-related parameters (such as flight altitude, Mach number) in the aero-engine operation simulation module, the most sensitive operating points of the aero-engine corresponding to each electromagnetic test subject are determined, providing a technical basis for the safety design and airworthiness certification of the aero-engine. The solution of this application can evaluate the thrust control fluctuation caused by a single electromagnetic test interference value or the composite superposition of multiple electromagnetic test interference values.

[0070] The solution of this application can analyze the data after the electromagnetic test based on closed-loop simulation. Therefore, there is no need to monitor the thrust fluctuation of the aero-engine control system caused by the electromagnetic environment in real time during the test, reducing the complexity of the electromagnetic test and the manpower required during the electromagnetic test.

[0071] The electromagnetic test simulation system and its operation method for the aero-engine control system of this application can continuously inject or time-share inject the electromagnetic test interference values from different electromagnetic test subjects, so as to more realistically reproduce the thrust control function fluctuation of the aero-engine control system when the aero-engine encounters various electromagnetic environment coupling interferences such as high-intensity radiated field (HIRF), lightning strike, and electromagnetic interference (EMI) in the real operating environment, and provide the effectiveness of the simulation system.

[0072] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still belong to the spirit and scope of the exemplary embodiments of this application.

[0073] At the same time, this application uses specific terms to describe the embodiments of this application. Such as "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.

[0074] Some aspects of the present application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above-mentioned hardware or software can all be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can be one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors or combinations thereof.

[0075] Similarly, it should be noted that, in order to simplify the presentation of the disclosure of the present application and thus help the understanding of one or more embodiments of the invention, in the foregoing description of the embodiments of the present application, sometimes multiple features are incorporated into one embodiment, drawing or description thereof. However, this disclosure method does not mean that the features required by the subject matter of the present application are more than those mentioned in the claims. In fact, the features of the embodiments are fewer than all the features of the single embodiments disclosed above.

[0076] Although the present application has been described with reference to the current specific embodiments, those of ordinary skill in the art in the technical field of the present application should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions can be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. An electromagnetic test simulation system for an aeroengine control system, comprising: an aeroengine operation simulation module; an aeroengine operation monitoring sensor simulation module configured to: receive the operation status signal of the aeroengine operation simulation module and issue an operation status sensing signal; an aeroengine electronic controller configured to: receive the operation status sensing signal and output a control current signal; an aeroengine hydraulic fuel system simulation module configured to: receive the control current signal and issue a fuel supply control signal to the aeroengine operation simulation module; an electromagnetic test interference value injection module configured to: inject an electromagnetic test interference value into the aeroengine electronic controller or the aeroengine hydraulic fuel system simulation module; the aeroengine operation simulation module is configured to: provide an aeroengine thrust simulation output value.

2. The electromagnetic test simulation system for an aeroengine control system according to claim 1, wherein, the electromagnetic test interference value injection module includes an operation status sensing signal interference value injection module and a control current interference value injection module; the operation status sensing signal interference value injection module is configured to: inject a sensing signal interference value into the aeroengine electronic controller; the control current interference value injection module is configured to: inject a control current interference value into the aeroengine hydraulic fuel system simulation module.

3. The electromagnetic test simulation system for an aeroengine control system according to claim 1, wherein, the electromagnetic test includes: voltage spike test, power line audio conduction susceptibility test, induced signal susceptibility test, radio frequency conduction sensitivity test, radio frequency radiation sensitivity test and / or lightning induced transient susceptibility test.

4. The electromagnetic test simulation system for an aeroengine control system according to claim 3, wherein, the induced signal susceptibility test includes: induced magnetic field test on electrical equipment, induced electric field test on electrical equipment, induced magnetic field test on interconnection cables, induced electric field test on interconnection cables and / or induced spike test on interconnection cables.

5. The electromagnetic test simulation system for an aeroengine control system according to claim 1, wherein, the aeroengine operation monitoring sensor simulation module includes: a rotational speed monitoring sensor simulation module, a temperature monitoring sensor simulation module, a barometric pressure monitoring sensor simulation module and / or a throttle lever angle monitoring sensor simulation module.

6. The electromagnetic test simulation system for an aeroengine control system according to claim 1, wherein, it further includes a simulation control module, and the simulation control module is configured to: issue a simulation control instruction to make the electromagnetic test simulation system enter different electromagnetic test simulation states and receive the aeroengine thrust simulation output values corresponding to different electromagnetic test simulation states.

7. The electromagnetic test simulation system for an aeroengine control system according to claim 6, wherein, Sending simulation control instructions to cause the electromagnetic test simulation system to enter different electromagnetic test simulation states and receiving the corresponding aero-engine thrust simulation output values for different electromagnetic test simulation states includes: Setting the operating parameters of the aero-engine operation simulation module to enable the aero-engine operation simulation module to stably operate in the first operating state to be analyzed; Setting the curve of the throttle lever angle changing with time output by the aero-engine operation monitoring sensor simulation module as the input signal of the aero-engine electronic controller; Obtaining the first aero-engine thrust simulation output value output when the aero-engine operation simulation module stably operates in the first operating state to be analyzed; Injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module to cause the aero-engine operation simulation module to operate in the second operating state to be analyzed; Obtaining the second aero-engine thrust simulation output value output when the aero-engine operation simulation module operates in the second operating state to be analyzed.

8. The electromagnetic test simulation system of the aero-engine control system according to claim 7, wherein, the simulation control module is further configured to: calculate the change ratio of the aero-engine thrust simulation output value according to the first aero-engine thrust simulation output value and the second aero-engine thrust simulation output value; judge whether the aero-engine control system corresponding to the aero-engine operation simulation module, the aero-engine operation monitoring sensor simulation module and the aero-engine hydraulic fuel system simulation module meets the electromagnetic compatibility standard based on the change ratio of the aero-engine thrust simulation output value and the corresponding electromagnetic test criterion.

9. The electromagnetic test simulation system of the aero-engine control system according to claim 8, wherein, the simulation control module is further configured to: obtain the most sensitive operating point of the electromagnetic protection of the aero-engine control system according to the change ratio of the aero-engine thrust simulation output value under different operating states.

10. The electromagnetic test simulation system of the aero-engine control system according to claim 7, wherein, injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module includes: injecting different types of electromagnetic signal interference values corresponding to different electromagnetic tests through the electromagnetic test interference value injection module in a specific order.

11. The electromagnetic test simulation system of the aero-engine control system according to claim 10, wherein, there is an injection interval between the different types of electromagnetic signal interference values.

12. The electromagnetic test simulation system of the aero-engine control system according to claim 7, wherein, the operating parameters of the aero-engine operation simulation module include different operating Mach numbers and flight altitudes of the aero-engine.

13. A method for operating an electromagnetic test simulation system of an aeroengine control system, the electromagnetic test simulation system of the aeroengine control system comprising an aeroengine operation simulation module, an aeroengine operation monitoring sensor simulation module, an aeroengine electronic controller, an aeroengine hydraulic fuel system simulation module, and an electromagnetic test interference value injection module; The aeroengine operation monitoring sensor simulation module is configured to: receive the operation state signal of the aeroengine operation simulation module and issue an operation state sensing signal; the aeroengine electronic controller is configured to: receive the operation state sensing signal and output a control current signal; the aeroengine hydraulic fuel system simulation module is configured to: receive the control current signal and issue a fuel supply control signal to the aeroengine operation simulation module; the electromagnetic test interference value injection module is configured to: inject an electromagnetic test interference value into the aeroengine electronic controller or the aeroengine hydraulic fuel system simulation module; the aeroengine operation simulation module is configured to: provide an aeroengine thrust simulation output value; The operation method comprises: Issuing a simulation control instruction to cause the electromagnetic test simulation system to enter different electromagnetic test simulation states and receiving the aeroengine thrust simulation output values corresponding to the different electromagnetic test simulation states.

14. According to the method for operating an electromagnetic test simulation system of an aeroengine control system as claimed in claim 13, wherein, Issuing a simulation control instruction to cause the electromagnetic test simulation system to enter different electromagnetic test simulation states and receiving the aeroengine thrust simulation output values corresponding to the different electromagnetic test simulation states comprises: Setting the operation parameters of the aeroengine operation simulation module to cause the aeroengine operation simulation module to stably operate in a first operation state to be analyzed; Setting the curve of the throttle lever angle varying with time output by the aeroengine operation monitoring sensor simulation module as the input signal of the aeroengine electronic controller; Obtaining the first aeroengine thrust simulation output value output when the aeroengine operation simulation module stably operates in the first operation state to be analyzed; Injecting an electromagnetic signal interference value exceeding the defined allowable error through the electromagnetic test interference value injection module to cause the aeroengine operation simulation module to operate in a second operation state to be analyzed; Obtaining the second aeroengine thrust simulation output value output when the aeroengine operation simulation module operates in the second operation state to be analyzed.

15. According to the method for operating an electromagnetic test simulation system of an aeroengine control system as claimed in claim 14, wherein, further comprises: Calculating the change ratio of the aeroengine thrust simulation output value according to the first aeroengine thrust simulation output value and the second aeroengine thrust simulation output value; Based on the change ratio of the thrust simulation output value of the aero-engine and the corresponding electromagnetic test criterion, determine whether the aero-engine control system corresponding to the aero-engine operation simulation module, the aero-engine operation monitoring sensor simulation module, and the aero-engine hydraulic fuel system simulation module meets the electromagnetic compatibility standard.

16. The operation method of the electromagnetic test simulation system of the aero-engine control system according to claim 15, characterized in that, further comprising: Obtain the most sensitive operating point of electromagnetic protection of the aero-engine control system according to the change ratio of the thrust simulation output value of the aero-engine under different operating states.

Images