Frequency domain dependent switching control method and system of aero-engine based on disturbance time-frequency characteristics

Abstract

The invention discloses a frequency domain dependence switching control method and system of an aero-engine based on disturbance time-frequency characteristics, and belongs to the technical field of aero-engine control. According to the method, an error signal is monitored and controlled in real time, and power distribution of the signal in a plurality of predefined limited spectrum intervals is calculated through spectrum analysis; based on the power distribution, performing a switching decision by adopting a strongest power principle in combination with an anti-shake mechanism, and determining a target controller; and executing an undisturbed switching operation, and smoothly transiting the current controller to the target controller. According to the method, through time-frequency domain analysis and intelligent switching, the engine control system always calls the controller suitable for the current disturbance characteristics, so that accurate, rapid and high-robustness control is realized, and the problem that complex disturbance of frequency spectrum change in multiple limited intervals cannot be effectively handled in the prior art is solved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine control technology, and more specifically to a frequency-domain dependent switching control method and system for aero-engines based on disturbance time-frequency characteristics. Background Technology

[0002] During operation, aero engines inevitably experience various external and internal disturbances, such as inlet flow distortion, fuel supply pulsations, and sensor noise. The spectral characteristics of these disturbance signals are often time-varying, and their energy is concentrated within a few finite frequency bands. For example, low-frequency disturbances may originate from changes in flight conditions, mid-frequency disturbances may be related to instability phenomena such as rotating stall, while high-frequency disturbances may come from mechanical vibrations or noise.

[0003] Existing anti-interference control methods for aero-engines mainly rely on fixed-parameter controllers (such as PID controllers) or robust controllers (such as H∞ controllers). Fixed-parameter controllers perform well near the design point, but struggle to cope with complex disturbances involving variations in spectrum and amplitude, exhibiting insufficient robustness. While robust controllers can ensure system stability under certain uncertainties, their design is typically based on worst-case scenarios, resulting in conservative performance under most normal operating conditions, sacrificing response speed and control accuracy.

[0004] In addition, some adaptive control methods can adjust parameters online, but their algorithms are usually quite complex, have high real-time requirements, and are prone to slow convergence, sensitivity to unmodeled dynamics, and parameter drift. Their application in systems like aero engines, which have extremely high requirements for safety and reliability, is limited.

[0005] Therefore, there is an urgent need in the field for a control scheme that can sense changes in the disturbance spectrum in real time and automatically adjust the control strategy to provide anti-interference performance across the entire frequency band, in order to solve the problem that existing technologies cannot effectively cope with complex disturbances in which the spectrum changes in multiple finite intervals. Summary of the Invention

[0006] The purpose of this invention is to provide a frequency domain dependent switching control method and system for aero-engines based on the time-frequency characteristics of disturbances. Through time-frequency domain analysis and intelligent switching, the engine control system can always call the controller suitable for the current disturbance characteristics, thereby achieving precise, fast and robust control, in order to solve the problem that the existing technology cannot effectively deal with complex disturbances in which the spectrum changes in multiple finite intervals.

[0007] To achieve the above objectives, the technical solution adopted by the present invention is as follows: A frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics includes the following steps: S1: Real-time monitoring of control error signals, and calculation of the power distribution of the signal in multiple predefined finite frequency ranges through spectrum analysis; S2: Based on power distribution, the switching decision is made by combining the principle of maximum power with anti-shake mechanism to determine the target controller; S3: Perform a seamless handover operation to smoothly transition the current controller to the target controller.

[0008] Furthermore, the finite frequency range is determined based on engine dynamics analysis, and the frequency band boundaries are adjusted according to different engine models, including low-frequency range, mid-frequency range and high-frequency range; The power distribution includes low-frequency power values ​​in the low-frequency range, mid-frequency power values ​​in the mid-frequency range, and high-frequency power values ​​in the high-frequency range.

[0009] Further, the target controller described in S2 includes: The low-frequency controller, corresponding to the low-frequency range, adopts an integral-enhanced PID structure, which has high gain and strong integral function; The intermediate frequency controller, corresponding to the intermediate frequency range, employs a phase lead compensator to provide intermediate frequency stability margin; The high-frequency controller, corresponding to the high-frequency range, adopts a second-order low-pass filter structure to suppress high-frequency measurement noise.

[0010] Furthermore, the switching decision described in S2 includes: Based on power distribution, the maximum power value is obtained by comparing low-frequency power values, mid-frequency power values, and high-frequency power values; Determine whether the maximum power value is greater than a preset power threshold; When the maximum power value is greater than the preset power threshold, and this state continues for a preset number of control cycles, the controller corresponding to the maximum power value is determined to be the target controller.

[0011] Furthermore, the disturbance-free switching operation described in S3 includes state matching and stable switching. The target controller state is initialized using a state observer, and the output is controlled by stability conditions.

[0012] Furthermore, the stability conditions include: There is no sliding mode; the expression is:

[0013] There exists a sliding mode, expressed as:

[0014]

[0015]

[0016] in, Represents the system matrix. It is a given nonnegative constant. It is a parameter related to the frequency-limited characteristics of the disturbance signal.

[0017] Furthermore, the preset power threshold is greater than or equal to 30% of the total power, and the preset quantity is ≥3.

[0018] Another objective of this invention is to provide a frequency-domain dependent switching control system for an aero-engine based on disturbance time-frequency characteristics. When executed, this system implements the aforementioned frequency-domain dependent switching control method for an aero-engine based on disturbance time-frequency characteristics, comprising: The signal acquisition module is used to acquire engine status signals in real time and generate control error signals; A spectrum analysis module, connected to the signal acquisition module, is used to calculate the power distribution of the error signal within a predefined frequency band through spectrum analysis. A switching logic module, connected to the spectrum analysis module, is used to make switching decisions based on power distribution; A multi-controller library stores multiple sub-controllers optimized for different frequency bands; The switching and execution module, connected to the switching logic module and the multi-controller library, is used to perform seamless switching operations. The system is integrated into the full authority digital electronic control (FADEC) system of the aero-engine, and the modules are connected through a data bus to form a closed-loop control. Another object of the present invention is to provide a computer-readable storage medium storing a computer program that, when executed by a processor, implements the frequency domain-dependent switching control method for aero-engines based on disturbance time-frequency characteristics.

[0019] Another object of the present invention is to provide an electronic device, including a memory and a processor, wherein the memory is used to store a computer program, and the processor runs the computer program to enable the electronic device to perform the frequency domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics.

[0020] In summary, the present invention has at least one of the following beneficial technical effects: Frequency domain targeting: By switching based on frequency domain, "frequency band governance" is achieved, always using the controller that is optimal for the current dominant disturbance, which greatly improves control accuracy and efficiency.

[0021] Strong robustness and adaptability: It can automatically adapt to the dynamic changes of the disturbance spectrum and maintain good control performance under both steady-state and transient conditions, resulting in a wider engine operating range.

[0022] Fast Response: The switching decision is based on fast spectrum analysis logic, which is more rapid than complex online parameter tuning.

[0023] High reliability and ease of implementation: Each sub-controller can be designed in detail offline, and the online part has clear logic and low computational burden, making it very suitable for implementation in existing FADEC systems and of high engineering application value. Attached Figure Description

[0024] Figure 1 This is a system structure block diagram of the present invention; Figure 2 This is a flowchart of the method of the present invention; Figure 3 This is a schematic diagram illustrating the maximum singular value of the closed-loop system under different frequency band disturbances according to the present invention. Figure 4 This is a schematic diagram of the H∞ performance index of the system under high-frequency interference according to the present invention; Figure 5 This is a schematic diagram illustrating the adjustment of the excitation energy output under different scenarios according to the present invention. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0026] To implement a frequency-domain dependent switching control method for aero-engines based on the time-frequency characteristics of disturbances, the system employed in this invention is integrated into the full authority digital electronic control (FADEC) system of the aero-engine. As the core control unit of the engine, FADEC is responsible for real-time processing of sensor data, execution of control algorithms, and output of drive signals. This system is implemented through hardware and software collaboration to ensure high reliability and real-time performance. The overall system structure includes a signal acquisition module, a spectrum analysis module, a switching logic module, a multi-controller library, and a switching and execution module. This system is integrated into the full authority digital electronic control (FADEC) system of the aero-engine, and the modules are connected via a data bus to form a closed-loop control system. Figure 1 ).

[0027] This embodiment provides a frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics, such as... Figure 2 As shown, it includes the following steps: S1: Real-time monitoring of control error signals, and calculation of the power distribution of the signal in multiple predefined finite frequency ranges through spectrum analysis; S2: Based on power distribution, the switching decision is made by combining the principle of maximum power with anti-shake mechanism to determine the target controller; S3: Perform a seamless handover operation to smoothly transition the current controller to the target controller.

[0028] The following is a detailed description with reference to specific embodiments.

[0029] S1: Monitors and controls the error signal in real time, and calculates the power distribution of the signal in multiple predefined finite frequency ranges through spectrum analysis.

[0030] Monitoring and control error signals rely on the signal acquisition module. This module consists of high-precision sensors (such as speed sensors and pressure sensors) and signal conditioning circuitry. The sensors acquire engine speed signals in real time (as the controlled output) and compare them with a given speed command (input by the flight management system or pilot) to generate an error signal e(t). The error signal is sent digitally to the spectrum analysis module via an ADC (analog-to-digital converter). The sampling frequency is typically set to 1000Hz to satisfy the Nyquist sampling theorem and ensure signal integrity. The signal conditioning circuitry includes an anti-aliasing filter and a signal amplifier to guarantee the quality of the input signal.

[0031] Before calculating the power (energy) distribution, multiple frequency bands need to be predefined. The frequency band allocation must be based on the typical disturbance characteristics of the aero-engine. Specifically, it is divided as follows: Low frequency range Ω low =[0,1] Hz: This frequency band mainly corresponds to slowly varying disturbances, such as changes in flight altitude and gradual changes in throttle commands. The disturbance model can be represented as a step or ramp signal, and the controller needs high gain to eliminate steady-state errors.

[0032] Mid-frequency range Ω mid =(1,10] Hz: This frequency band covers unstable phenomena such as combustion oscillations and rotational stall. The disturbances have periodic characteristics, and the controller needs to provide phase lead to enhance stability margin.

[0033] High frequency range Ω high =(10,∞) Hz: This frequency band includes mechanical vibration, sensor noise, etc. The model is Gaussian white noise, and the controller needs to use low-pass filtering to suppress high-frequency components.

[0034] The aforementioned band division parameters can be determined through engine dynamics analysis, such as based on Bode plots or singular value curves. In practical applications, the band boundaries are adjustable to accommodate different engine models. For example, for high-bypass engines, the mid-frequency range can be extended to (1, 15] Hz to cover a wider oscillation band. This flexibility in band division allows for customized optimization for specific engine models.

[0035] Spectrum analysis relies on the spectrum analysis module and employs a Short-Time Fourier Transform (STFT) algorithm (such as Cooley-Tukey FFT) with N=1024 points, balancing resolution and computational burden. Real-time performance is guaranteed through pipelined processing, with each window processing time <0.5 ms.

[0036] The power values ​​of the current control error signal within three predefined frequency bands are obtained from the spectrum analysis module: low-frequency power P1, mid-frequency power P2, and high-frequency power P3. These power values ​​satisfy the following equation:

[0037] It reflects the distribution of disturbance energy. Processing efficiency is improved through overlap preservation and parallel computing. The spectrum update period is synchronized with the control period, typically set to 1ms to meet real-time control requirements.

[0038] The output of this step is the power distribution of each frequency band, providing a data basis for switching decisions.

[0039] S2: Based on power distribution, the switching decision is made by combining the principle of maximum power with anti-shake mechanism to determine the target controller.

[0040] Based on the aforementioned three pre-divided frequency ranges, three controllers were designed offline in the controller library: K1 (Low-frequency controller): Utilizes an integral-enhanced PID structure, featuring high gain and strong integral action to eliminate steady-state errors. Controller parameters are tuned through simulation and experimentation to ensure robustness in the low-frequency range.

[0041] K2 (Intermediate Frequency Controller): Employs a phase lead compensator to provide ample intermediate frequency stability margin. The design takes into account the engine's phase lag characteristics in the intermediate frequency range, improving stability through compensation.

[0042] K3 (High-Frequency Controller): Its structure is a second-order low-pass filter, with low-pass filtering characteristics to suppress high-frequency measurement noise. The filter cutoff frequency is set according to the sensor characteristics to avoid attenuation of the effective signal.

[0043] After the controller design is completed, its robustness is verified through hardware-in-the-loop (HIL) simulation. The HIL test platform includes a real engine model and hardware interfaces to simulate disturbances under various operating conditions and verify controller performance. The test content includes step response, frequency response, and stability analysis to ensure that each controller meets the design specifications within the target frequency band.

[0044] To ensure the system can automatically adapt to changes in disturbances, the optimal controller is always used. The specific decision-making process is as follows.

[0045] Based on the principle of maximum power, the system calculates the maximum value among P1, P2, and P3, denoted as P. max Then, determine P. max Is it greater than a preset threshold Th (e.g., total power ( The system checks if the frequency of the signal has remained stable for at least three control cycles (30%), and if so, whether this state has been stable for at least three control cycles (anti-jitter mechanism). The anti-jitter mechanism aims to avoid frequent switching caused by frequency fluctuations and enhance system stability.

[0046] When the maximum power value is greater than the preset power threshold, and this state continues for a preset number of control cycles, the controller corresponding to the maximum power value is determined to be the target controller.

[0047] In this embodiment, when the above conditions are met (i.e., P) max >T h And the duration counter is ≥3), the system will determine the duration based on P. max The specific value determines the target controller (the corresponding controller to which the switch is intended): If P max If the current active controller is not the low-frequency controller K1, the system will trigger a switch to K1. K1 is dedicated to handling slowly varying disturbances and features high gain and strong integral action.

[0048] If P max If the current controller is P2 and is not the intermediate frequency controller K2, then a switch to K2 is triggered. K2 provides phase lead compensation for intermediate frequency disturbances such as combustion oscillations.

[0049] If P max If the current controller is P3 and is not the high-frequency controller K3, then a switch to K3 is triggered. K3 focuses on suppressing high-frequency noise and vibration and has low-pass filtering characteristics.

[0050] If P max If no switching conditions are met (e.g., the current controller is already the target controller), or the maximum value does not last long enough, the system remains in its current state.

[0051] Additionally, for the counter, if P max Not greater than the threshold T h If the duration is insufficient, the system resets the duration counter to reassess the disturbance state. This ensures that the switching decision is triggered only when the disturbance energy is concentrated and stable.

[0052] The entire process described above is executed cyclically, enabling the system to dynamically adapt to changes in the disturbance spectrum. The decision-making logic is based on fuzzy rules to avoid oscillations near the boundaries.

[0053] The decision-making algorithm has low computational burden, making it suitable for implementation in embedded processors within FADEC systems, with a response latency of less than 0.05 seconds. Real-time performance is ensured through code optimization and hardware acceleration. The system also records decision logs for subsequent analysis and optimization.

[0054] S3: Perform a seamless handover operation to smoothly transition the current controller to the target controller.

[0055] This process ensures a smooth switching process and maintains system stability. Bumpy-free switching is key to ensuring smooth control.

[0056] The fundamental purpose of the seamless switching algorithm is to ensure that the entire closed-loop system of the aero-engine control system remains stable and does not experience severe oscillations or instability when switching from one sub-controller (e.g., K1 for low-frequency disturbances) to another (e.g., K3 for high-frequency disturbances) based on changes in the disturbance spectrum. The seamless switching operation includes state matching and stable switching. A state observer is used to initialize the target controller's state, and the output is controlled by stability conditions.

[0057] State matching involves setting the initial state of the target controller to the output value of the current controller, implemented using a state observer. The observer is designed based on an engine model and uses Kalman filtering to improve estimation accuracy.

[0058] To ensure the system does not diverge during switching, the compatibility between controllers is analyzed to avoid oscillations caused by switching. Stability conditions are given for two different scenarios: the system has no sliding mode and the system has a sliding mode. (1) Ideal scenario: The switching is instantaneous, there is no intermediate state, that is, there is no sliding mode, and the expression is:

[0059] in, Represents the known system matrix. and These are the known and unknown parameters related to the frequency-limited characteristics of the disturbance signal, respectively. This formula is a "universal recipe." If we can find parameters that satisfy this complex inequality for a set of controllers, then any switching between these controllers will ensure the stability of the entire system. This is akin to finding a common "stability contract" for all sub-controllers.

[0060] (2) More practical scenario: The switching is not instantaneous; there will be a brief, uncertain "sliding mode" or "transition period" between the two controllers, i.e., there is a sliding mode, expressed as:

[0061]

[0062]

[0063] in, Represents the known system matrix. It is a given nonnegative constant. and These are the known and unknown parameters related to the frequency-limited characteristics of the disturbance signal (obtained by solving the above inequalities). In this way, when the engine encounters disturbances in different frequency bands, the system can automatically and smoothly switch to the most effective control mode, always maintaining optimal performance.

[0064] This approach does not require all controllers to adhere to a global rule. Instead, it ensures that the switch from controller A to controller B is stable, the switch from B to C is stable, and so on. As long as each pair of adjacent controllers can safely "handshake," the entire switchover path is stable.

[0065] The bumpless handover algorithm was verified through simulation and experiments. Test scenarios included fast handover and boundary handover to evaluate output smoothness and system stability. Verification results show that the control signal is continuous and without abrupt changes. Figure 3 This diagram illustrates the maximum singular values ​​of the closed-loop system under different frequency band disturbances according to the present invention. The blue solid line, red solid line, yellow solid line, and purple dashed line represent low-frequency, mid-frequency, high-frequency, and full-frequency band disturbances, respectively. The diagram demonstrates the disturbance suppression performance of each controller. The maximum singular values ​​of K1, K2, and K3 within their respective frequency bands are all lower than those of the full-frequency controller, proving the advantage of frequency band targeting. This provides a theoretical basis for disturbance-free handover, ensuring improved system performance after handover.

[0066] Based on the above, multi-scenario simulation verification was conducted to comprehensively evaluate the invention. The simulation platform used was MATLAB / Simulink, and the engine model was based on nonlinear aero-thermodynamic equations, including detailed component models and environmental effects.

[0067] Scenario 1: High-frequency disturbance suppression test Assume the disturbance is the sum of a high-frequency triangular signal: The test aimed to assess the system's ability to suppress high-frequency disturbances. These disturbances simulate the high-frequency noise encountered by a real engine, such as mechanical vibrations.

[0068] Consider two stationary cases regarding the perturbation spectrum. Suppose there is interference with a finite high-frequency spectrum; a natural approach is to represent the interference as the sum of triangular signals. Figure 4This diagram illustrates the H∞ performance index of the system under high-frequency interference according to the present invention. The blue, red, yellow, and purple solid lines represent the low-frequency controller, mid-frequency controller, high-frequency controller, and full-frequency controller, respectively. As shown in the diagram, the L2 norm of the full-frequency controller and the low-frequency controller is almost twice that of the high-frequency controller and the frequency-dependent switching controller of the present invention. This indicates that under these conditions, the performance of the frequency-dependent switching controller is superior to that of the full-frequency controller and the low-frequency controller, and is close to that of the high-frequency controller. This demonstrates the superior performance of the method of the present invention under high-frequency disturbances.

[0069] Scenario 2: Spectrum Time-Varying Perturbation Test The system's adaptability is tested by considering the time-varying spectrum of the disturbance signal. The disturbance gradually transitions from high-frequency dominance to mid-frequency dominance, simulating the changes in operating conditions during actual flight.

[0070] Figure 5 This diagram illustrates the adjustment of the excitation energy output under different scenarios according to the present invention. In the diagram, the blue circles, red squares, yellow rhombuses, and purple triangles represent the low-frequency controller, medium-frequency controller, high-frequency controller, and full-frequency controller, respectively. Figure 5 We observed that the interference suppression performance of the high-frequency controller is very poor. Even when inserted out-of-band low-frequency components exist within a very short time window, the proposed frequency-domain dependent switching technique still performs excellently in suppressing system interference. As the number of out-of-band components increases, the bandgap dominance of the spectrum becomes increasingly blurred, making it difficult to consider the signal d(t) as high-frequency dominant. In such cases, using a full-band H∞ controller or a low-frequency controller might be a better choice. This invention, through intelligent switching, automatically selects the optimal controller, avoiding performance degradation.

[0071] Simulation results show that the method of this invention outperforms traditional methods in terms of control accuracy, response speed, and robustness. Specific indicators include: control error reduced by more than 30%, switching response time <50ms, and stability margin improved by 20%. These data validate the effectiveness of the method.

[0072] This invention achieves high-precision control of aero-engines under complex spectral disturbances through a systematic implementation process. The core advantages of the method include: automatic adaptation to disturbance changes through real-time spectrum sensing and intelligent switching; disturbance-free switching technology ensuring system stability and avoiding secondary impacts; low implementation cost and high reliability based on existing FADEC systems; and simulation verification of the method's effectiveness, providing an innovative solution for aero-engine control. Future development can further integrate artificial intelligence technology to optimize switching strategies and improve performance.

[0073] This embodiment also provides a frequency-domain dependent switching control system for aero-engines based on disturbance time-frequency characteristics. When executed, this system implements the aforementioned frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics, including a signal acquisition module, a spectrum analysis module, a switching logic module, a multi-controller library, and a switching and execution module. This system is integrated into the full-authority digital electronic control (FADEC) system of the aero-engine, with each module connected via a data bus to form a closed-loop control. This integration method fully utilizes the existing hardware resources of the FADEC system; new functions can be implemented simply through software upgrades, significantly reducing engineering implementation costs. Specifically, the functions and implementation methods of each module are as follows: Signal acquisition module: Used to acquire engine status signals in real time and generate control error signals. This module consists of high-precision sensors and signal conditioning circuitry.

[0074] Spectrum Analysis Module: Connected to the signal acquisition module, this module calculates the power distribution of the error signal within a predefined frequency band through spectrum analysis. It performs real-time spectrum calculations and utilizes a parallel processing architecture to achieve rapid spectrum analysis of the error signal.

[0075] Switching logic module: Connected to the spectrum analysis module, used for switching decisions based on power distribution.

[0076] This module stores frequency band division parameters and switching rules, including the principle of maximum power and anti-shake mechanism.

[0077] Multi-controller library: Stores multiple sub-controllers optimized for different frequency bands. This library is stored in non-volatile memory and contains sub-controllers designed offline for different frequency bands.

[0078] Switching and Execution Module: Connected to the switching logic module and the multi-controller library, this module performs bumpless switching operations. It executes the bumpless switching algorithm via the CPU.

[0079] The system monitors the status of each module in real time and automatically switches to safe mode when an anomaly is detected.

[0080] This embodiment also provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the frequency domain-dependent switching control method for aero-engines based on disturbance time-frequency characteristics.

[0081] This embodiment also provides an electronic device, including a memory and a processor. The memory is used to store a computer program, and the processor runs the computer program to enable the electronic device to execute the frequency domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics.

[0082] Embodiments of the present invention may be provided as methods, systems, or computer program products. Therefore, the present invention may take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0083] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0084] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0085] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0086] Contents not described in detail in this specification are prior art known to those skilled in the art. It is hereby indicated that the above description is intended to help those skilled in the art understand this invention, but does not limit the scope of protection of this invention. Any equivalent substitutions, modifications, improvements, or simplifications of the above descriptions that do not depart from the essential content of this invention fall within the scope of protection of this invention.

Claims

1. A frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics, characterized in that, Includes the following steps: S1: Real-time monitoring of control error signals, and calculation of the power distribution of the signal in multiple predefined finite frequency ranges through spectrum analysis; S2: Based on power distribution, the switching decision is made by combining the principle of maximum power with anti-shake mechanism to determine the target controller; S3: Perform a seamless handover operation to smoothly transition the current controller to the target controller.

2. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 1, characterized in that: The finite frequency range is determined based on engine dynamics analysis, and the frequency band boundaries are adjusted according to different engine models, including low-frequency range, mid-frequency range and high-frequency range; The power distribution includes low-frequency power values ​​in the low-frequency range, mid-frequency power values ​​in the mid-frequency range, and high-frequency power values ​​in the high-frequency range.

3. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 2, characterized in that, The target controller described in S2 includes: The low-frequency controller, corresponding to the low-frequency range, adopts an integral-enhanced PID structure, which has high gain and strong integral function; The intermediate frequency controller, corresponding to the intermediate frequency range, employs a phase lead compensator to provide intermediate frequency stability margin; The high-frequency controller, corresponding to the high-frequency range, adopts a second-order low-pass filter structure to suppress high-frequency measurement noise.

4. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 3, characterized in that, The handover decision described in S2 includes: Based on power distribution, the maximum power value is obtained by comparing low-frequency power values, mid-frequency power values, and high-frequency power values; Determine whether the maximum power value is greater than a preset power threshold; When the maximum power value is greater than the preset power threshold, and this state continues for a preset number of control cycles, the controller corresponding to the maximum power value is determined to be the target controller.

5. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 1, characterized in that: The disturbance-free switching operation described in S3 includes state matching and stable switching. The target controller state is initialized using a state observer, and the output is controlled by stability conditions.

6. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 5, characterized in that, The stability conditions include: There is no sliding mode; the expression is: ； There exists a sliding mode, expressed as: ； ； ； in, Represents the system matrix. It is a given nonnegative constant. It is a parameter related to the frequency-limited characteristics of the disturbance signal.

7. The frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics according to claim 4, characterized in that: The preset power threshold is greater than or equal to 30% of the total power, and the preset quantity is ≥3.

8. A frequency-domain dependent switching control system for an aero-engine based on disturbance time-frequency characteristics, characterized in that, When executed, the system implements the frequency-domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics as described in any one of claims 1-7, comprising: The signal acquisition module is used to acquire engine status signals in real time and generate control error signals; A spectrum analysis module, connected to the signal acquisition module, is used to calculate the power distribution of the error signal within a predefined frequency band through spectrum analysis. A switching logic module, connected to the spectrum analysis module, is used to make switching decisions based on power distribution; A multi-controller library stores multiple sub-controllers optimized for different frequency bands; The switching and execution module, connected to the switching logic module and the multi-controller library, is used to perform seamless switching operations. The system is integrated into the full authority digital electronic control (FADEC) system of the aero-engine, and the modules are connected through a data bus to form a closed-loop control.

9. A computer-readable storage medium, characterized in that, It stores a computer program that, when executed by a processor, implements the frequency domain dependent switching control method for aero-engines based on disturbance time-frequency characteristics as described in any one of claims 1-7.

10. An electronic device, characterized in that, It includes a memory and a processor, wherein the memory is used to store a computer program, and the processor runs the computer program to cause the electronic device to perform the frequency domain dependent switching control method for an aero-engine based on the disturbance time-frequency characteristics as described in any one of claims 1-7.

Images