Method for calculating and analyzing lightning indirect effect of acceleration control system

Abstract

The invention provides a method for calculating and analyzing the lightning indirect effect of an acceleration control system to shorten and evaluate the influence of the lightning indirect effect on an aero-engine control system. According to the method provided by the invention, electromagnetic field information sensed in an aircraft propulsion system (namely, an area where an engine control system is located in an installed state) in a preset lightning environment is calculated through simulation and stored; and the electromagnetic field information is used as an electromagnetic excitation source to be coupled to a to-be-analyzed airborne cable in the control system and a connected electrical load to solve the electromagnetic response of the control system in the lightning environment. Necessary airborne cable harness design optimization is carried out according to the measured electromagnetic response result and the research and development technical requirements of the engine control system, and the optimized airborne cable and the connected electrical load are re-put into the stored internal electromagnetic field information of the aircraft propulsion system to carry out electromagnetic response simulation calculation; and the design iteration period of the airborne control system is shortened.

Description

Technical Field

[0001] The present invention relates to an aero-engine control system, and more particularly, to a method and device for accelerating the calculation and analysis of the lightning indirect effect of a control system. Background Art

[0002] During the research and development and design stage of a commercial aero-engine control system, lightning indirect effect (i.e., the transient interference level induced by lightning in the control system) protection design needs to be carried out to ensure that the aircraft propulsion system (composed of an aero-engine and a nacelle) can operate reliably and durably in a lightning electromagnetic environment, thereby ensuring the flight safety of the aircraft. Most modern commercial aero-engines use a full-authority digital control system. Compared with traditional mechanical hydraulic control systems, modern control systems are more sensitive to lightning indirect effects and are thus more vulnerable to the negative impacts of lightning indirect effects. To carry out the lightning indirect effect protection design of the control system, it is first necessary to obtain the corresponding protection design requirements, that is, the electromagnetic responses (including harness current, open-circuit voltage, and short-circuit current) induced by the aero-engine control system in a lightning environment, so as to optimize and finalize the design of airborne equipment such as the laying of control system cables based on the electromagnetic responses.

[0003] However, a commercial aero-engine control system consists of nearly a hundred components and accessories, including electronic devices, sensors, solenoid valves, actuating devices, interconnection cables, etc. There are more than a hundred measurement points that need to be calculated and analyzed for lightning protection. If the traditional method of simulation calculation and analysis is used, that is, each time the lightning excitation, the electromagnetic responses (including harness current, open-circuit voltage, and short-circuit current) of each measurement point of the airborne cables and connected electrical loads in the aircraft propulsion system under the lightning excitation are recalculated, it will result in a large amount of repeated calculations. And since the aircraft propulsion system model belongs to a large-size three-dimensional model for electromagnetic response simulation analysis, each time the simulation calculation is rerun, a large amount of simulation calculation resources are required and it takes a long time to end the simulation and feedback the simulation results to the designers. In addition, when using the traditional simulation calculation and analysis, each time the design of the airborne cable harness is optimized (such as the laying of the cable harness installation path, the composition of the wires in each branch of the cable harness, the shielding of the cable harness, etc.) or the electrical characteristics of the connected load are changed, the electromagnetic responses (including harness current, open-circuit voltage, and short-circuit current) of the airborne cables and connected electrical loads in the aircraft propulsion system need to be recalculated. The required long simulation calculation time is not conducive to the designers flexibly carrying out the optimization design of the aero-engine airborne control system.

[0004] Correspondingly, there is a need in the art for a technology to accelerate the calculation and analysis of the lightning indirect effect of a control system. Summary of the Invention

[0005] The present invention content is provided to introduce some concepts in a simplified form that will be further described in the following detailed description. The present invention content is not intended to identify the key features or essential features of the claimed subject matter, nor is it intended to assist in determining the scope of the claimed subject matter.

[0006] In view of the deficiencies in the prior art described above, an object of the present invention is to accelerate the calculation and analysis of the lightning indirect effect of the control system, so as to shorten the design iteration cycle of the control system integrated by the airborne cable harness and electrical components and accessories.

[0007] According to one aspect of the present invention, a method for accelerating the calculation and analysis of the lightning indirect effect of the control system is provided. The method may include the following steps:

[0008] (a) Import the aircraft propulsion system model to be analyzed into the electromagnetic simulation platform;

[0009] (b) Set the lightning excitation that generates the lightning environment;

[0010] (c) Run the simulation calculation to obtain and save the electromagnetic field information induced inside the aircraft propulsion system under the lightning excitation;

[0011] (d) Import the control system to be analyzed (composed of an airborne cable harness and connected electrical loads such as electronic devices, sensors, solenoid valves, etc.), and set the measuring device at the measuring point (if measuring the harness current, the measuring point is located on the airborne cable harness and the measuring device is a current measuring probe; if measuring the open-circuit voltage, the measuring point is located at the interface of the electronic device connected to the airborne cable harness and the measuring device is a voltmeter; if measuring the short-circuit current, the measuring point is located at the interface of the electronic device connected to the airborne cable harness and the measuring device is an ammeter);

[0012] (e) Couple the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical loads to calculate the electromagnetic response;

[0013] (f) Replace the airborne cable harness to be analyzed and its connected electrical loads, set the measuring device at the measuring point, and repeat step (e) until all the airborne cable harnesses to be analyzed are completed;

[0014] (g) Compare the calculated electromagnetic response with the electromagnetic response threshold to optimize the laying path design of each airborne cable harness as required; and

[0015] (h) For the optimized airborne cable harness design and the connected electrical loads, repeat steps (d)-(g).

[0016] In one embodiment, the lightning excitation may include: the strike-in and strike-out positions of the lightning on the nacelle surface, the lightning waveform, the amplitude and phase of the lightning current.

[0017] In one embodiment, the method may further include: replacing the lightning excitation; and repeating steps (c)-(h) based on the replaced lightning excitation.

[0018] In one embodiment, the measuring device may include at least one of the following: a voltmeter, an ammeter, a current measurement probe.

[0019] In one embodiment, the electromagnetic response threshold may be determined according to the engine R & D technical requirements.

[0020] In one embodiment, optimizing the design of each airborne cable harness may include adjusting the laying path design of each airborne cable harness, adjusting the cable harness geometric topology, adjusting the conductor composition in each airborne cable branch, adjusting the harness shielding layer, etc., so as to reduce the interference voltage and / or interference current caused by the lightning environment in the control system.

[0021] In one embodiment, the electromagnetic response may include at least one of the following: harness current, open circuit voltage, short circuit current.

[0022] In one embodiment, in order to calculate the open circuit voltage and / or the short circuit current, step (e) may further include: replacing the grounding state of the electrical load connected to the airborne cable harness to be analyzed and setting the measuring device at the measuring point, coupling the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical load with the replaced grounding state, so as to calculate the open circuit voltage and / or the short circuit current.

[0023] In another aspect of the present invention, there is provided an apparatus for accelerating the calculation and analysis of the indirect lightning effect of a control system, the apparatus may include: a memory; and one or more processors coupled to the memory, and the one or more processors may be configured to execute each step of the method according to the present invention.

[0024] In yet another aspect of the present invention, there is provided a non-transitory computer-readable medium storing a computer program, and the computer program, when executed by a processor, executes each step of the method according to the present invention.

[0025] The method and apparatus provided by the present invention have the following advantages:

[0026] (1) Shorten the calculation and analysis time required for re-evaluating the electromagnetic response after modifying the grounding state of the electrical load connected to the airborne cable of the control system;

[0027] (2) Shorten the calculation and analysis time required for re-evaluating the electromagnetic response after modifying the electromagnetic response measuring point position of the control system;

[0028] (3) Shorten the computational analysis time required to re-evaluate the electromagnetic response after modifying the on-board cable harness design of the control system;

[0029] (4) Comprehensively master the electromagnetic response of the control system in various lightning environments, discover weak points in the protection design against indirect lightning effects, and perform targeted design optimization on the weak points during the CAD design stage of the engine control system, effectively avoiding design iterations of the control system caused by insufficient protection against indirect lightning effects exposed during the test stage after production and processing.

[0030] These and other aspects of the present invention will be more fully understood after reading the following detailed description. After studying the following description of specific implementations of the present invention in conjunction with the accompanying drawings, other aspects, features, and implementations of the present invention will be apparent to those of ordinary skill in the art. Although the features of the present invention may be discussed below with respect to certain implementations and drawings, all implementations of the present invention may include one or more of the advantageous features discussed herein. In other words, although one or more implementations may be discussed as having certain advantageous features, one or more of such features may also be used in accordance with the various implementations of the present invention discussed herein. In a similar manner, although some implementations may be discussed below as being implemented as devices, systems, or methods, it should be understood that such implementations may be implemented in various devices, systems, and methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to understand the manner in which the above-described features of the present invention are used in detail, the above briefly summarized content may be described in more specific detail with reference to the embodiments, some of which are shown in the drawings. However, it should be noted that the drawings only show certain typical aspects of the present invention and should not be considered as limiting its scope, as the description may allow for other equally effective aspects.

[0032] Figure 1 A schematic diagram of an aircraft propulsion system model and a lightning environment setting according to an embodiment of the present invention is illustrated.

[0033] Figure 2 A flowchart of a method for accelerating the computational analysis of indirect lightning effects of a control system according to an embodiment of the present invention is illustrated.

[0034] Figure 3 A flowchart of another method for accelerating the computational analysis of indirect lightning effects of a control system according to an embodiment of the present invention is illustrated.

[0035] Figure 4 A general hardware device capable of executing the method of the present invention according to an embodiment of the present invention is illustrated. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0036] The following detailed description presented in conjunction with the accompanying drawings is intended as a description of various configurations and is not intended to represent the only configurations in which the concepts described herein can be practiced. This detailed description includes specific details to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts can be practiced without these specific details. Additionally, alternative configurations can be designed without departing from the scope of the invention. Further, well-known elements will not be described in detail or will be omitted so as not to obscure the relevant details of the invention.

[0037] The present invention proposes a method for accelerating the calculation and analysis of the lightning indirect effect of a control system to shorten the evaluation of the impact of the lightning indirect effect on an aeroengine control system. The method proposed by the present invention simulates and calculates the electromagnetic field information induced inside the aircraft propulsion system (i.e., the area where the engine control system is located in the installed state) under a preset lightning environment, and then uses the electromagnetic field information as an electromagnetic excitation source to couple it to the airborne cables and connected electrical loads to be analyzed in the control system to solve the electromagnetic response of the control system under the lightning environment (including harness current, open-circuit voltage, and short-circuit current). According to the measured electromagnetic response results, necessary optimization of the airborne cable harness is carried out in accordance with the research and development technical requirements of the engine control system, and the optimized airborne cables and their connected electrical loads are placed back into the electromagnetic field information of the saved aircraft propulsion system for electromagnetic response simulation calculation, thereby shortening the design iteration cycle of the airborne control system of the aeroengine.

[0038] The relevant terms and their explanations in the present invention are as follows:

[0039] Electromagnetic interference (EMI): Electromagnetic noise generated by a system or device during normal operation that is unfavorable to the normal operation of other systems or devices.

[0040] Electromagnetic compatibility (EMC): A system or device can operate normally in its electromagnetic environment and at the same time will not cause interference to other systems and devices.

[0041] Aircraft propulsion system: Composed of two parts, an aeroengine and a nacelle, which provides flight power for the aircraft.

[0042] Lightning indirect effect / lightning indirect effect: The electrical transient process induced by lightning in the aircraft propulsion system circuit.

[0043] Figure 1 A schematic diagram of an aircraft propulsion system model and lightning environment settings according to an embodiment of the present invention is illustrated. As Figure 1 shown, the aircraft propulsion system model 100 includes an aeroengine and a nacelle. In Figure 1In the example shown, lightning strikes into the nacelle on the left side (shown as the incoming lightning 120) and strikes out from the aeroengine on the right side (shown as the outgoing lightning 130). In one example, the lightning environment may include the incoming position of the incoming lightning 120, the lightning waveform, the current amplitude, the current phase, and the outgoing position of the outgoing lightning 130, the lightning waveform, the current amplitude, the current phase.

[0044] As described above, there are a large number of airborne cables (e.g., more than 20 bundles of airborne cables), numerous electrical loads, and diverse lightning excitation environments in the aeroengine control system. If each simulation must start from calculating the electromagnetic field information according to the lightning excitation, it will be very time-consuming for so many cable harnesses to be analyzed and the connected electrical loads. The present invention aims to solve this problem.

[0045] Figure 2 The flowchart of a method 200 for accelerating the calculation and analysis of the indirect lightning effect of a control system according to an embodiment of the present invention is illustrated. In one example, the method 200 may be executed by the hardware device 400 described below with reference to Figure 4 illustrated. In another example, the method 200 may be executed by any other suitable software, hardware, and / or a combination of software and hardware.

[0046] In step 210, the method 200 may include: importing the aircraft propulsion system model to be analyzed into the electromagnetic simulation platform. In one example, the electromagnetic simulation platform may be a commercial electromagnetic simulation software, such as CST (3D electromagnetic field simulation software), etc. The aircraft propulsion system model may be any aircraft propulsion system model that has been modeled for a specific aircraft type, which includes various cable harnesses, electrical loads, etc. in the control system of the aircraft propulsion system.

[0047] In step 220, the method 200 may include: setting the lightning excitation that generates the lightning environment. In one example, the lightning excitation may include the positions of the incoming and outgoing lightning strikes on the nacelle surface, the lightning waveform, the amplitude and phase of the lightning current.

[0048] In step 230, method 200 may include: running a simulation calculation to obtain and save the electromagnetic field information induced inside the aircraft propulsion system (i.e., the environment where the control system is located) under lightning excitation. In one example, the electromagnetic field information may include electric field strength, magnetic field strength, and so on. In the present invention, by saving the electromagnetic field information induced inside the aircraft propulsion system under a preset lightning environment (i.e., the area where the engine control system is located in the installed state), this electromagnetic field information can then be coupled as an electromagnetic excitation source to various airborne cable harnesses to be analyzed and the connected electrical loads in the control system, so as to solve the electromagnetic response of the control system under this preset lightning environment, rather than having to recalculate from scratch the electromagnetic field information induced inside the aircraft propulsion system under the preset lightning excitation every time a simulation is performed for each airborne cable harness to be analyzed as in the prior art, thus significantly accelerating the simulation speed. In other words, for a certain lightning excitation, it is only necessary to execute step 230 once.

[0049] In step 240, method 200 may include: importing the airborne cable harnesses to be analyzed and the connected electrical loads, and setting up measuring devices at the measurement points. In one example, the electrical loads may include various types of sensors, solenoid valves, electronic devices (such as electronic control units), alternators, etc. In one example, the airborne cable harnesses to be analyzed may be the airborne cable harnesses connected between the controller of the control system and the electrical loads. In one example, the measurement points may be set at any suitable positions on the airborne cable harnesses to be analyzed. For example, they may be set 5 cm away from the end connected to the controller. In one example, the measuring devices may include (simulation) voltmeters, ammeters, current measurement probes, or any other suitable measuring devices.

[0050] In step 250, method 200 may include: coupling the saved electromagnetic field information with the airborne cable harnesses to be analyzed and the connected electrical loads to calculate the electromagnetic response. In one example, the calculated electromagnetic response may include wire harness current, open circuit voltage, and short circuit current.

[0051] In step 260, method 200 may include: replacing the airborne cable harnesses to be analyzed and their connected electrical loads, setting up measuring devices at the measurement points, and repeating step 250 until all the airborne cable harnesses to be analyzed have been analyzed.

[0052] In step 270, method 200 may include: comparing the calculated electromagnetic response with an electromagnetic response threshold to optimize each airborne cable harness design (which may include adjusting the laying path design of each airborne cable harness, adjusting the cable harness geometric topology, adjusting the wire composition in each airborne cable branch, adjusting the harness shielding layer, etc.). In one embodiment, the electromagnetic response threshold may be determined according to the research and development technical requirements of the engine control system. In one embodiment, if the calculated electromagnetic response does not meet the electromagnetic response threshold (i.e., does not meet the relevant indicators in the research and development technical requirements of the engine control system), then the corresponding airborne cable harness needs to be optimized. The optimization may include adjusting the laying path design of the corresponding airborne cable harness, adjusting the cable harness geometric topology (i.e., the connection relationship with the electrical load), adjusting the wire composition in each airborne cable branch, and adjusting the harness shielding layer to reduce the interference voltage and / or interference current caused by the lightning environment.

[0053] In step 280, method 200 may include: repeating steps 240 - 270 for the optimized airborne cable harness design and the connected electrical load. Thus, the simulation can be performed again for the optimized airborne cable harness design to verify whether it meets the research and development technical requirements of the engine control system.

[0054] Figure 3 The flowchart of another method 300 for calculating and analyzing the indirect lightning effect of an acceleration control system according to an embodiment of the present invention is illustrated. In one example, method 300 may be executed by the hardware device 400 described with reference to Figure 4 as follows. In another example, method 300 may be executed by any other suitable software, hardware, and / or a combination of software and hardware.

[0055] In step 310, method 300 may include: importing the aircraft propulsion system model to be analyzed into the electromagnetic simulation platform, as described in step 210 with reference to Figure 2 above.

[0056] In step 320, method 300 may include: setting the lightning excitation that generates the lightning environment, as described in step 220 with reference to Figure 2 above.

[0057] In step 330, method 300 may include: running the simulation calculation to obtain and save the electromagnetic field information induced inside the aircraft propulsion system under the lightning excitation, as described in step 230 with reference to Figure 2 above.

[0058] In step 340, method 300 may include: importing the airborne cable harness to be analyzed and the connected electrical load, and setting the measuring device at the measuring point, as described in step 280 with reference to Figure 2as described in step 240 in

[0059] At step 350, method 300 may include: coupling the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical load to calculate the electromagnetic response (e.g., harness current), as described in Figure 2 step 250 in

[0060] At step 355, method 300 may include: changing the grounding state of the electrical load connected to the airborne cable harness to be analyzed and setting up the measuring device at the measurement point, coupling the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical load with the changed grounding state to calculate the electromagnetic response (e.g., open - circuit voltage and / or short - circuit current).

[0061] At step 360, method 300 may include: replacing the airborne cable harness to be analyzed and its connected electrical load, setting up the measuring device at the measurement point, and repeating steps 350 - 355 until all the airborne current harnesses to be analyzed are completed, as described in Figure 2 step 260 in

[0062] At step 370, method 300 may include: comparing the calculated electromagnetic response with the electromagnetic response threshold to optimize the design of each airborne cable harness, as described in Figure 2 step 270 in

[0063] At step 380, method 300 may include: for the optimized airborne cable harness design and the connected electrical load, repeating steps 340 - 370, as described in Figure 2 step 280 in

[0064] At step 390, method 300 may include: according to the engineering requirements, changing the lightning environment settings and repeating steps 330 - 380. Thus, simulations and optimizations can be run for different lightning environments so that the designed airborne cable harness path can well meet the research and development technical requirements of the engine control system.

[0065] Figure 4 Illustrates a general hardware device 400 that can execute the method of the present invention according to an exemplary embodiment of the present disclosure.

[0066] Referring to Figure 4 , the hardware device 400 will now be described. The hardware device 400 is an example of a hardware device applicable to various aspects of the present disclosure. The hardware device 400 can be any machine configured to perform processing and / or computing, and can be, but is not limited to, a workstation, a server, a desktop computer, a laptop computer, a tablet computer, a personal digital assistant, a smart phone, an airborne device, or any combination thereof.

[0067] The hardware device 400 may include elements that are possibly connected to or in communication with the bus 402 via one or more interfaces. For example, the hardware device 400 may include the bus 402, as well as one or more processors 404, one or more input devices 406, and one or more output devices 408. The one or more processors 404 may be any type of processor and may include, but are not limited to, one or more general-purpose processors and / or one or more dedicated processors (such as specialized processing chips). The input device 406 may be any type of device that can input information into the hardware device and may include, but are not limited to, a mouse, a keyboard, a touch screen, a microphone, and / or a remote control. The output device 408 may be any type of device that can present information and may include, but are not limited to, a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The hardware device 400 may also include a non-transitory storage device 410 or be connected to the non-transitory storage device 410. The non-transitory storage device 410 may be any storage device that is non-transitory and can implement data storage and may include, but are not limited to, a disk drive, an optical storage device, a solid-state storage, a floppy disk, a flexible disk, a hard disk, a magnetic tape, or any other magnetic medium, an optical disk, or any other optical medium, a ROM (read-only memory), a RAM (random access memory), a cache memory, and / or any other memory chip or memory cartridge, and / or any other medium from which a computer can read data, instructions, and / or code. The non-transitory storage device 410 may be separable from the interface. The non-transitory storage device 410 may have data / instructions / code for implementing the above methods and steps. The hardware device 400 may also include a communication device 412. The communication device 412 may be any type of device or system that can implement communication with external devices and / or networks and may include, but are not limited to, a modem, a network card, an infrared communication device, wireless communication devices and / or chip sets such as Bluetooth TM devices, 802.11 devices, WiFi devices, WiMax devices, cellular communication facilities, and the like.

[0068] The bus 402 may include, but is not limited to, an Industry Standard Architecture (ISA) bus, a Micro Channel Architecture (MCA) bus, an Enhanced ISA (EISA) bus, a Video Electronics Standards Association (VESA) local bus, and a Peripheral Component Interconnect (PCI) bus.

[0069] The hardware device 400 may also include a working memory 414. The working memory 414 may be any type of working memory that can store instructions and / or data useful for the operation of the processor 404 and may include, but are not limited to, a random access memory and / or a read-only memory device.

[0070] Software elements can be located in the working memory 414, including but not limited to the operating system 416, one or more application programs 418, drivers, and / or other data and code. Instructions for performing the above methods and steps can be included in one or more application programs 418. The executable code or source code of the instructions of the software elements can be stored in a non-transitory computer-readable storage medium (such as the above storage device 410), and can possibly be read into the working memory 414 through compilation and / or installation. The executable code or source code of the instructions of the software elements can also be downloaded from a remote location.

[0071] From the above embodiments, those skilled in the art can clearly know that the present disclosure can be implemented by software with necessary hardware, or by hardware, firmware, etc. Based on such an understanding, the embodiments of the present disclosure can be partially implemented in software form. The computer software can be stored in a readable storage medium such as a floppy disk, hard disk, optical disc, or flash memory of a computer. The computer software includes a series of instructions to enable a computer (such as a personal computer, server station, or network terminal) to execute the method according to the corresponding embodiments of the present disclosure or a part thereof.

[0072] Other aspects

[0073] The examples set forth herein are for illustrative purposes to explain certain concepts of the present invention. Those of ordinary skill in the art will understand that these examples are merely illustrative in nature, and other examples may fall within the scope of the present invention and the appended claims. Based on the teachings herein, those skilled in the art should appreciate that the aspects disclosed herein can be implemented independently of any other aspect and two or more of these aspects can be combined in various ways. For example, any number of the aspects set forth herein can be used to implement a device or practice a method. Additionally, other structures, functions, or a combination of structures and functions that are complementary to or different from one or more of the aspects set forth herein can be used to implement such a device or practice such a method.

[0074] In the description herein, it should be understood that the terms "first", "second", "third" are used for descriptive purposes only and cannot be construed as indicating or implying relative importance.

[0075] Those skilled in the art will appreciate that information and signals can be represented using any of a variety of different technologies and techniques. For example, data, instructions, commands, information, signals, bits, symbols, and chips that may be referred to throughout the above description can be represented by voltage, current, electromagnetic waves, magnetic fields or magnetic particles, optical fields or optical particles, or any combination thereof.

[0076] In addition, those skilled in the art will appreciate that the various illustrative logical blocks, modules, circuits, and algorithmic steps described in connection with the aspects disclosed herein can be implemented as electronic hardware, computer software, or combinations of both. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps have been described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the overall system. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.

[0077] One or more of the components, steps, features, and / or functions described above can be rearranged and / or combined into a single component, step, feature, or function, or implemented in several components, steps, or functions. Additional elements, components, steps, and / or functions can also be added without departing from the novel features disclosed herein. The apparatus, devices, and / or components described above can be configured to perform one or more of the methods, features, or steps described herein. The novel algorithms described herein can also be efficiently implemented in software and / or embedded in hardware.

[0078] It should be understood that the specific order or hierarchy of the steps in the disclosed methods is an illustration of an example process. Based on design preferences, it should be understood that the specific order or hierarchy of the steps in these methods can be rearranged. The appended method claims present the elements of the various steps in a sample order, and are not meant to be limited to the specific order or hierarchy presented, unless specifically recited herein.

[0079] Although aspects of the present invention have been described so far with reference to the accompanying drawings, the above methods, systems, and devices are merely examples, and the scope of the present invention is not limited to these aspects, but is defined only by the appended claims and their equivalents. Various components may be omitted or replaced by equivalent components. Additionally, the steps may be implemented in an order different from that described in the present invention. Furthermore, the various components may be combined in various ways. It is also important to note that as technology evolves, many of the components described may be replaced by equivalent components that emerge later. Various modifications to the present invention will be apparent to those skilled in the art, and the general principles defined herein may be applied to other variations without departing from the scope of the present invention. Thus, the present invention is not limited to the examples and designs described herein, but should be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for accelerating the calculation and analysis of the lightning indirect effect of a control system, the method comprises the following steps: (a) Import the aircraft propulsion system model to be analyzed into the electromagnetic simulation platform; (b) Set the lightning excitation for generating the lightning environment; (c) Run the simulation calculation to obtain and save the electromagnetic field information induced inside the aircraft propulsion system under the lightning excitation; (d) Import the airborne cable harness to be analyzed and the connected electrical loads, and set the measuring devices at the measuring points; (e) Couple the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical loads to calculate the electromagnetic response; (f) Replace the airborne cable harness to be analyzed and the connected electrical loads, set the measuring devices at the measuring points, and repeat step (e) until all the airborne cable harnesses to be analyzed are completed; (g) Compare the calculated electromagnetic response with the electromagnetic response threshold to optimize the design of each airborne cable harness as required; and (h) For the optimized design of the airborne cable harness and the connected electrical loads, repeat steps (d)-(g).

2. The method according to claim 1, wherein the lightning excitation comprises: The strike-in and strike-out positions of lightning on the nacelle surface, the lightning waveform, the amplitude and phase of the lightning current.

3. The method according to claim 1, further comprises: Replace the lightning excitation; and Based on the replaced lightning excitation, repeat steps (c)-(h).

4. The method according to claim 1, wherein the measuring device comprises at least one of the following: a voltmeter, an ammeter, a current measurement probe.

5. The method according to claim 1, wherein the electromagnetic response threshold is determined according to the R & D technical requirements of the engine control system.

6. The method according to claim 1, wherein optimizing the design of each airborne cable harness includes adjusting the installation and laying path of each airborne cable harness, the composition of the wires in each branch of the cable harness, the shielding of the cable harness, etc. for design modification / optimization to reduce the interference voltage and / or interference current caused by the lightning environment.

7. The method according to claim 1, wherein the electromagnetic response comprises at least one of the following: harness current, open-circuit voltage, short-circuit current.

8. The method according to claim 7, wherein in order to calculate the open-circuit voltage and / or the short-circuit current, step (e) further comprises: Replace the grounding state of the electrical load connected to the airborne cable harness to be analyzed and set the measuring devices at the measuring points, couple the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical loads with the replaced grounding state to calculate the open-circuit voltage and / or the short-circuit current.

9. A device for accelerating the calculation and analysis of the lightning indirect effect of a control system, comprises: A memory; and One or more processors coupled to the memory, the one or more processors being configured to perform the following steps: (a) Import the aircraft propulsion system model to be analyzed into the electromagnetic simulation platform; (b) Set the lightning excitation for generating the lightning environment; (c) Run the simulation calculation to obtain and save the electromagnetic field information induced inside the aircraft propulsion system under the lightning excitation; (d) Import the airborne cable harness to be analyzed and the connected electrical loads, and set up the measuring devices at the measuring points; (e) Couple the saved electromagnetic field information with the airborne cable harness to be analyzed and the connected electrical loads to calculate the electromagnetic response; (f) Replace the airborne cable harness to be analyzed and its connected electrical loads, set up the measuring devices at the measuring points, and repeat step (e) until all the airborne cable harnesses to be analyzed are completed; (g) Compare the calculated electromagnetic response with the electromagnetic response threshold to optimize the design of each airborne cable harness as required; and For the optimized design of the airborne cable harness and the connected electrical loads, repeat steps (d)-(g).

10. A non-transitory computer-readable medium storing a computer program, wherein the computer program, when executed by a processor, performs the method according to any one of claims 1-8.

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