A disturbance-free control method, device, system and storage medium of an aero-engine

Abstract

The present application relates to the technical field of automatic control, and particularly relates to a disturbance-free control method, device and system of an aero-engine and a storage medium, the method comprising: establishing a state space model of an aero-engine control system; designing a state-dependent switching law with a dwell time constraint; establishing a disturbance-free performance index that only constrains the controller at a switching point; designing a switching control scheme with disturbance-free performance based on the designed switching law; and determining a disturbance-free switching controller parameter according to the switching law and the disturbance-free switching control scheme. The method can effectively reduce the chattering and jolt problems caused by controller switching, and is suitable for switching control systems such as aero-engines and power systems.

Description

Technical Field

[0001] This invention relates to the field of automatic control technology, specifically to a disturbance-free control method, device, system, and storage medium for an aero-engine. Background Technology

[0002] The dynamic characteristics of aero-engines vary drastically with different environments and operating points. While nonlinear aero-thermodynamic models within the full envelope are accurate, they lack analytical expressions and are unsuitable for controller design. To obtain mathematical models that facilitate controller design, aero-engines are typically linearized with small deviations at certain operating points. When the engine undergoes significant speed adjustments, it spans multiple operating points, thus forming a multimodal switching system. Therefore, the switching system can better describe the characteristics of the aero-engine system. However, controller switching inevitably introduces problems such as abrupt changes in control signals and system performance degradation due to initial value mismatches. In practical systems, the impact of such transient changes on overall system performance cannot be ignored. For aero-engine control systems, fuel instability (often the control signal is fuel quantity) can lead to drastic changes in the operating point, directly affecting the aircraft's stable attitude and potentially causing engine surge, overheating, overspeeding, and engine shutdown. Therefore, smooth transitions in control signals are particularly important in control design.

[0003] A search revealed that Chinese Patent Publication (Announcement) No. CN115167546A discloses an aero-engine speed regulation control method. The method is roughly described as follows: by establishing a model of an aero-engine switching control system affected by deterministic and random factors, a random hybrid switching mechanism is designed, a dynamic event-triggered sampling mechanism is provided, a switching mechanism is introduced to obtain a disturbance-free switching dynamic event-triggered control scheme, and the event-triggered disturbance-free switching controller parameters are solved to achieve disturbance-free switching of the engine system.

[0004] While the aforementioned aero-engine speed regulation control method solves the problem of smooth transition of system performance before and after switching, the undisturbed performance inequality requirement in this method holds globally. This causes the controller to compromise the system's steady-state performance to some extent while satisfying undisturbed performance requirements, leading to engine vibration and turbulence due to controller switching. Therefore, it is of great significance to study an undisturbed control strategy that targets only the controller switching point and can guarantee both undisturbed controller switching and steady-state system performance. Summary of the Invention

[0005] To address the aforementioned problems, the present invention provides a disturbance-free control method for an aero-engine, the steps of which are as follows:

[0006] Establish a state-space switching model for the aero-engine control system;

[0007] Based on the state-space switching model of the aero-engine control system, a state-dependent switching law with dwell time constraints is designed. The dwell time provides the necessary time for the realization of disturbance-free switching. The state-dependent switching law does not require each subsystem to be stable, which further relaxes the system conditions.

[0008] Based on the designed state-dependent switching law, establish a non-disruptive performance index that only constrains the switching point;

[0009] Based on the designed switching law and disturbance-free performance indicators, a switching control scheme with disturbance-free performance is designed.

[0010] Based on the aforementioned switching law and disturbance-free performance indicators, determine the parameters of the disturbance-free switching controller.

[0011] The method addresses the issue of turbulence and decreased control quality caused by controller switching during the operation of aero-engine control systems. It constructs a disturbanceless switching performance index that only constrains the switching point, introduces time-varying control gain, and provides a disturbanceless switching control strategy to solve the impact of turbulence caused by switching on system performance during the operation of aero-engine control systems.

[0012] In some implementations of the first aspect, the state-space switching model of the aero-engine control system is as follows:

[0013]

[0014] Where x(t) represents the system state, u φ(t) (t) represents the control input, A φ(t) B φ(t) For a matrix of appropriate dimension, It is a switching function. G is the set of positive real numbers, G is a positive integer class, and the switching function φ(t) is used to assign the activation state of the subsystem, τ f f = 0, 1, 2, ... are the switching times when t ∈ [τ] f , τ f+1 When ), φ(t) = f, f belongs to G, that is, the f-th subsystem is activated, and the state trajectory of the f-th subsystem is the state trajectory of the state space switching model (1.1).

[0015] In some implementations of the first aspect, based on the state-space switching model, a state-dependent switching law with residence time constraints is designed, including:

[0016] Given a time constant T and a constant L, let τ f+1 -τ f≥T, where L represents the time interval [τ] f , τ f+1 The number of time periods to be segmented, defined Where l represents the time interval [τ] f , τ f+1 The first stage of )

[0017] Time interval [τ] f , τ f+1 Divide it into L segments, represented as:

[0018]

[0019] Design the following switching law with residence time constraints that has state dependencies:

[0020]

[0021] Among them, ● T Let represent the transpose of a vector or matrix ●, x represent the system state, s is a subsystem different from f, and Q f,L Q s,0 It is a positive definite matrix.

[0022] When t∈[τ] f , τ f When T), subsystem f is activated. The duration of subsystem f's operation is T. Based on the state-space switching model, the switching function is φ(t) = f.

[0023] When t≥τ f During +T, based on the switching rules, the switching between subsystems is determined according to the system's operating status. When x T Q f,L x≤min s∈G\f x T Q s,0 If x, then subsystem f has not switched to another subsystem, and subsystem f continues to run, with the switching function φ(t) = f;

[0024] When x T Q f,L x > min s∈G\f x T Q s,0 If x, then the subsystem f switches, and the switching function φ(t) switches to x. T Q s,0 The smallest subsystem containing x.

[0025] In some implementations of the first aspect, based on the designed switching law, a non-disruptive performance index constrained only by the switching point is established, as shown in the following formula:

[0026] The following non-disruptive performance index is constructed:

[0027]

[0028] Where τ n For the switching time, when the f-th subsystem is running, τ n =τ f When the subsystem switches to the s-th subsystem, τ n =τ s η φ This refers to the non-disruptive performance index.

[0029] The non-disruptive performance index (3.1) at any switching time τ n Both are true; the term to the left of "≤" in the formula represents the control input signal u. φ(t) (t) at switching time τ n The jitter amplitude at the location controls the input signal u. φ(t) (t) at switching time τ n The signal is discontinuous, meaning that the control signal jitter is only limited at the switching moment.

[0030] In some implementations of the first aspect, based on the designed switching law and disturbance-free performance indicators, a switching control scheme with disturbance-free performance for the aero-engine control system is designed, including:

[0031] The formula for a switching controller with disturbance-free performance is as follows:

[0032]

[0033] Among them, K φ(t) (t) is the time-varying gain matrix to be designed, such that

[0034] (i) The state-space switching model (1.1) is stable;

[0035] (ii) The designed switching controller (4.1) meets the disturbance-free performance index.

[0036]

[0037] In some implementations of the first aspect, the parameters of the bumpless handover controller are determined based on the aforementioned switching law and bumpless handover performance indicators, including:

[0038] For any subsystem f, s, k ∈ G, s ≠ f ≠ k, based on the given time constant T and positive integer L, a preset constant α is used. fs ≥0, β fs ≥0, η f ≥0, matrix K f,l and K f,L Positive definite matrix Q f,L Q s,0Let l = 0, 1, 2, ..., L-1, such that the inequalities in 5.1-5.5 hold.

[0039]

[0040]

[0041]

[0042]

[0043]

[0044] Based on the state-dependent switching law with residence time constraints, the time-varying gain matrix K is obtained. φ(t) (t) is

[0045]

[0046] The second aspect provides a disturbance-free control device for an aero-engine control system, comprising:

[0047] The acquisition module is used to acquire switching signals from the aero-engine controller;

[0048] The initial module is used to establish the state-space switching model of the aero-engine control system; based on the state-space switching model of the aero-engine control system, it is used to design the state-dependent switching law with dwell time constraints; it is also used to establish the non-disturbance performance index that only constrains the switching point according to the designed state-dependent switching law.

[0049] The processing module is used to design a disturbance-free performance switching control scheme for the aero-engine switching control system based on the designed state-dependent switching law and disturbance-free performance index; it is also used to determine the disturbance-free switching controller parameters according to the switching law and disturbance-free performance index.

[0050] The third aspect provides a disturbance-free control system for an aero-engine control system, including a processor and a memory, wherein the processor executes program data stored in the memory to implement a disturbance-free control method for the aero-engine.

[0051] The fourth aspect provides a readable storage medium for storing control program data, which, when executed by a processor, enables a method for seamless control of switching aero engines.

[0052] The beneficial effects of this invention are as follows:

[0053] (1) Based on the working principle of aero engines, the aero engine system is modeled as a multi-modal switching system.

[0054] (2) A new undisturbed constraint performance index was constructed, which only constrains the value of the controller at the switching point rather than the entire state interval, so as to ensure the undisturbed performance without compromising the steady-state performance.

[0055] (3) A time-varying controller gain was designed, making it easier to achieve the disturbance-free performance index;

[0056] (4) A state-dependent switching law with dwell time constraints was designed. On the one hand, it does not require each subsystem to be stable, thus relaxing the restrictions on the system. On the other hand, the existence of dwell time provides a time guarantee for each subsystem to achieve disturbance-free switching. Attached Figure Description

[0057] Figure 1 A flowchart of a disturbance-free control method for aero-engines;

[0058] Figure 2 The switching signal for the aircraft engine switching system model;

[0059] Figure 3 A schematic diagram of the low-pressure rotor speed of an aero-engine system;

[0060] Figure 4 A schematic diagram of the high-pressure rotor speed of an aero-engine system;

[0061] Figure 5 The fuel quantity is used as the control input for the aircraft engine system;

[0062] Figure 6 For the control increment of aero-engine subsystem 1;

[0063] Figure 7 For the control increment of aircraft engine subsystem 2;

[0064] Figure 8 This is a structural diagram of the disturbance-free control device for an aero-engine. Detailed Implementation

[0065] Exemplary embodiments of this disclosure will now be described in more detail with reference to the accompanying drawings.

[0066] Example

[0067] This invention provides a disturbance-free control method for aero-engines, such as... Figure 1 As shown, the specific implementation steps are as follows (the GE-90 turbofan engine is used as an example to illustrate the specific implementation of the method):

[0068] Step 1: Establish a state-space switching model for the aero-engine control system;

[0069] Based on switching system theory, the state-space switching model of the aero-engine control system is established as follows:

[0070]

[0071] Where x(t) represents the system state, u φ(t) (t) represents the control input, A φ(t) B φ(t) For a matrix of appropriate dimension, It is a switching function. G is the set of positive real numbers, G is a positive integer class, and the switching function φ(t) is used to assign the activation state of the subsystem, τ f f = 0, 1, 2, ... are the switching times when t ∈ [τ] f , τ f+1 When ), φ(t) = f, f belongs to G, that is, the f-th subsystem is activated, and the state trajectory of the f-th subsystem is the state trajectory of the state space switching model (1.1).

[0072] More specifically, the aircraft engine control system is constructed into a switching system model according to two different operating points, as follows:

[0073]

[0074]

[0075] Where φ:[0,∞)→[1,2] is the switching signal. Δn F It is the low-pressure rotor speed increment, Δn c It is the increase in high-voltage rotor speed, ΔW F It is the fuel flow increment, Δn F and Δn c As the system state, ΔW F As a control input, the system operates to the corresponding operating point, and the corresponding subsystem is activated. Therefore, the state-space switching model (1.1) is written in the following form:

[0076]

[0077] Among them, A φ and B φ The fitted data is as follows:

[0078]

[0079]

[0080] Step 2: Based on the state-space switching model of the aero-engine control system, design a state-dependent switching law with dwell time constraints. The dwell time provides the necessary time for the realization of disturbance-free switching. The state-dependent switching law does not require each subsystem to be stable, which further relaxes the system conditions.

[0081] Based on the state-space switching model, a state-dependent switching law with residence time constraints is designed, which can be specifically:

[0082] Given a time constant T and a constant L, let τ f+1 -τ f ≥T, where L represents the time interval [τ] f , τ f+1 The number of time periods to be segmented, defined τ f,0 =τ f , τ f,L =τ f +T, l=0,1,2,…,L-1, where l represents the time interval [τ f , τ f+1 The first stage of )

[0083] Time interval [τ] f , τ f+1 Divide it into L segments, represented as:

[0084]

[0085] Design the following switching law with residence time constraints that has state dependencies:

[0086]

[0087] Among them, ● T Let represent the transpose of a vector or matrix ●, x represent the system state, s is a subsystem different from f, and Q f,L Q s,0 It is a positive definite matrix.

[0088] When t∈[τ] f , τ f When T), subsystem f is activated. The duration of subsystem f's operation is T. Based on the state-space switching model, the switching function is φ(t) = f.

[0089] When t≥τ f During +T, based on the switching rules, the switching between subsystems is determined according to the system's operating status. When x T Q f,L x≤min s∈G\f x T Q s,0If x, then subsystem f has not switched to another subsystem, and subsystem f continues to run, with the switching function φ(t) = f;

[0090] When x T Q f,L x > min s∈G\f x T Q s,0 If x, then the subsystem f switches, and the switching function φ(t) switches to x. T Q s,0 The smallest subsystem containing x.

[0091] More specifically, we can set L=1 and T=2, and obtain the following from the fitting:

[0092]

[0093]

[0094] Step 3: Based on the designed state-dependent switching law, establish an unperturbed performance index that only constrains the switching point;

[0095] Based on the designed switching law, an unperturbed performance index constrained only by the switching point is established, as shown in the following formula:

[0096]

[0097] Where τ n For the switching time, η φ This refers to the non-disruptive performance index.

[0098] The disturbance-free performance index (3.1) at any switching time τ n Both are true; the term to the left of "≤" in the formula represents the control input signal u. φ(t) (t) at switching time τ n The jitter amplitude at the location controls the input signal u. φ(t) (t) at switching time τ n The signal is discontinuous at the point of transition, thus limiting the jitter of the control signal only at the point of transition.

[0099] Furthermore, when the f-th subsystem is running, τ n =τ f The switching function φ(t) = f is used to establish an unperturbed performance index that is constrained only by the switching time:

[0100]

[0101] Given specific parameters η φ =3.8686.

[0102] Step 4: Based on the designed switching law and disturbance-free performance indicators, design a switching control scheme with disturbance-free performance;

[0103] Based on the designed switching law and disturbance-free performance indicators, a disturbance-free switching control scheme for the aero-engine control system is designed. The formula for the disturbance-free switching controller is as follows:

[0104] u φ(t) (t)=K φ(t) (t)x(t) (4.1)

[0105] Among them, K φ(t) (t) is the time-varying gain matrix to be designed, such that

[0106] (i) The state-space switching model (1.1) is stable;

[0107] (ii) The switching controller (4.1) meets the disturbance-free performance index.

[0108]

[0109] Step 5: Determine the parameters of the disturbance-free switching controller based on the aforementioned switching law and disturbance-free performance indicators.

[0110] Based on the aforementioned switching law and bumpless handover performance indicators, the parameters of the bumpless handover controller are determined, including:

[0111] For any subsystem f, s, k ∈ G, s ≠ f ≠ k, based on the given time constant T and positive integer L, a preset constant α is used. fs ≥0, β fs ≥0, η f ≥0, matrix K f,l and K f,L Positive definite matrix Q f,L Q s,0 Let l = 0, 1, 2, ..., L-1, such that the inequalities in 5.1-5.5 hold.

[0112]

[0113]

[0114]

[0115]

[0116]

[0117] In this example, based on the data given above, we can obtain...

[0118] α 12=0.2, α 21 =0.2,β 12 =0.2,β 21 =0.2,

[0119] K 1,0 =[-0.00250.0067],K 1,1 =[-0.00530.0080],

[0120] K 2,0 =[-0.00240.0069],K 2,1 = [-0.00560.0084],

[0121] Based on the state-dependent switching law with residence time constraints, the time-varying gain matrix K is obtained. φ(t) (t) is

[0122]

[0123] like Figure 2 As shown in the figure, Method(i) represents the switching signal waveform at the switching point of the aerospace engine system model using the disturbance-free control method proposed in this invention; Method(ii) represents the traditional multimodal switching control method mentioned in the background art, which does not consider the switching signal waveform of the aerospace engine system model for disturbance-free control; Method(iii) represents the disturbance-free control method in the invention patent with publication number CN115167546A, which represents the switching signal waveform of the aerospace engine system model across the entire range. In the figure, the horizontal axis represents time, and the vertical axis represents the modal data of the aerospace engine switching system model. Figure 2 This indicates that the switching frequency of the switching signal proposed in this invention is significantly lower than that of Method(ii) and Method(iii), which provides a time guarantee for the realization of the non-interference performance.

[0124] like Figure 3-4 As shown in the figure, the rotor speed data of an aero-engine under low-pressure and high-pressure conditions are illustrated by the three different control methods described above. From... Figure 3-4 It can be seen that, compared with Method(ii) and Method(iii), the control method proposed in this invention can quickly adjust the rotor speed of the aero-engine under low pressure and high pressure conditions.

[0125] like Figure 5 The diagram shows the control signals of the three different control methods for the fuel quantity of the aircraft engine. Compared with Method(ii) and Method(iii), the control method proposed in this invention controls the fuel quantity of the engine more quickly and stably.

[0126] like Figure 6-7 The diagram shows the control gain data trajectory of the three different control methods in each subsystem, indicating that the control gain disturbance of the proposed control method is significantly reduced compared with Method(ii) and Method(iii).

[0127] Figure 3-7 This indicates that the disturbance-free control strategy proposed in this invention greatly reduces the disturbances caused by the switching of the controller, while also ensuring the adjustment speed of the system. The above results are attributed to the fact that we designed a time-varying control gain matrix instead of a time-invariant control gain matrix, and that we adopted a disturbance-free performance index that is only limited at the switching point. This allows the designed controller to be limited only at the switching point and not in the global range, thus achieving good disturbance-free performance and good steady-state performance.

[0128] Furthermore, this invention provides a disturbance-free control device for an aero-engine, such as... Figure 8 As shown, the device includes:

[0129] The acquisition module is used to acquire switching signals from the aero-engine controller;

[0130] The initial module is used to establish the state-space switching model of the aero-engine control system; based on the state-space switching model of the aero-engine control system, it is used to design the state-dependent switching law with dwell time constraints; it is also used to establish the non-disturbance performance index that only constrains the switching point according to the designed state-dependent switching law.

[0131] The processing module is used to design a disturbance-free performance switching control scheme for the aero-engine switching control system based on the designed state-dependent switching law and disturbance-free performance index; it is also used to determine the disturbance-free switching controller parameters according to the switching law and disturbance-free performance index.

[0132] Furthermore, the present invention also provides a disturbance-free control system for an aero-engine, including a processor and a memory, wherein the processor executes program data stored in the memory to implement a disturbance-free control method for the aero-engine.

[0133] Finally, the present invention also provides a readable storage medium for storing control program data, which, when executed by a processor, enables a disturbance-free control method for an aero-engine.

[0134] It should be noted that the exemplary embodiments mentioned in this invention describe methods or systems based on a series of steps or apparatus. However, this invention is not limited to the order of the steps described above; that is, the steps can be performed in the order mentioned in the embodiments, or in a different order, or several steps can be performed simultaneously.

[0135] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations, additions, or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A disturbance-free control method for an aero-engine, characterized in that, The method includes: Establish a state-space switching model for the aero-engine control system; Based on the state-space switching model of the aero-engine control system, a state-dependent switching law with dwell time constraints is designed. Based on the designed state-dependent switching law, establish a non-disruptive performance index that only constrains the switching point; Based on the designed switching law and disturbance-free performance indicators, a switching control scheme with disturbance-free performance is designed. Based on the aforementioned switching law and disturbance-free performance indicators, determine the parameters of the disturbance-free switching controller.

2. The method according to claim 1, characterized in that, The state-space switching model for establishing the aero-engine control system is as follows: （1.1） in x ( t () indicates the system state. u φ(t) ( t ) indicates control input. A φ(t) , B φ(t) For a matrix of appropriate dimension, φ (t):ℝ + =[0,∞)→G ≜{1,2,…, g } is a switching function, ℝ + G is the set of positive real numbers, G is a positive integer class, and the switching function is... φ (t) is used to assign the activation state of the subsystem, τ f , f = 0, 1, 2, ... are the switching times, when t∈[τ] f , τ f+1 )hour, φ (t)= f, f Belonging to G, i.e., the first f The first subsystem is activated, the... f The state trajectory of each subsystem is the state trajectory of the state space switching model (1.1).

3. The method according to claim 1, characterized in that, The aforementioned design of a state-dependent switching law with dwell time constraints based on the switching model of the aero-engine control system includes: Given a time constant T and a constant L, let τ f+1 - τ f ≥T, where L represents the time interval [τ] f , τ f+1 The number of time periods that are divided, defined as τ. f,l ≜τ f +lT / L, τ f,0 = τ f , τ f,L = τ f + T, l=0,1,2,…,L-1 ,in l Represents the time interval [τ] f , τ f+1 ) l Each stage Time interval [τ] f , τ f+1 Divide it into L segments, represented as: （2.1） Design the following switching law with residence time constraints that has state dependencies: （2.2） Among them, ● T This represents the transpose of a vector or matrix. x Indicates the system status. s It is different f Subsystems Q f,L , Q s,0 It is a positive definite matrix; When t∈[τ] f , τ f +T When ), subsystem f Activation, subsystem f The duration of operation T, based on the state-space switching model, and the switching function. φ (t)= f ; when t ≥ τ f +T At that time, based on the switching rules, the switching between subsystems is determined according to the system's operating status. x T Q f,L x ≤min s∈G\f x T Q s,0 x Then the subsystem f Not switched to other subsystems, subsystem f Continue running, switch functions φ (t)= f ; when x T Q f,L x >min s∈G\f x T Q s,0 x Then the subsystem f A switch occurs; the switch function. φ (t) Switch to x T Q s,0 x The smallest subsystem it belongs to.

4. The method according to claim 2, characterized in that, Based on the switching law of the design, a disturbance-free performance index constrained only by the switching point is established, as shown in the following formula: (3.1) Where τ n To switch times, when the first f When the subsystem is running, τ n = τ f When the subsystem switches to the first s When the subsystem is running, τ n = τ s ; η φ This refers to the non-disruptive performance index.

5. The method according to claim 4, characterized in that, The non-disruptive performance index (3.1) at any switching time τ n Both are true; the term to the left of "≤" in the formula represents the control input signal. u φ(t) ( t At the switching time τ n The jitter amplitude at the location controls the input signal. u φ(t) ( t At the switching time τ n The signal is discontinuous, meaning that the control signal jitter is only limited at the switching moment.

6. The method according to claim 4, characterized in that, The aforementioned switching control scheme with non-disruptive performance, based on the designed switching law and non-disruptive performance indicators, includes: The formula for a switching controller with disturbance-free performance is as follows: (4.1) in, K φ(t) ( t ) is the time-varying gain matrix to be designed, such that (i) The state-space switching model is stable; (ii) The designed switching controller (4.1) meets the disturbance-free performance index. (3.1)。 7. The method according to claim 2, characterized in that, The step of determining the parameters of the disturbance-free switching controller based on the designed switching law and disturbance-free performance indicators includes: For any subsystem f , s , k ∈G, s≠f≠k Based on the given time constant T and positive integer L, a preset constant is determined. α fs ≥0, β fs ≥0, η f ≥0, matrix K f,l and K f,L Positive definite matrix Q f,L , Q s,0 , l=0,1,2,…,L-1 This makes the inequalities 5.1-5.5 hold. （5.1） （5.2） （5.3） （5.4） （5.5） Based on the state-dependent switching law with residence time constraints, the time-varying gain matrix is ​​obtained. K φ(t) ( t )for （5.6）。 8. A disturbance-free control device for an aircraft engine, characterized in that... include: The acquisition module is used to acquire switching signals from the aircraft engine controller. The initial module is used to establish the state-space switching model of the aero-engine control system; The initial module is also used to design state-dependent switching laws with dwell time constraints based on the state-space switching model of the aero-engine control system. The initial module is also used to establish a non-disruptive performance index that only constrains the switching point, based on the state-dependent switching law of the design. The processing module is also used to design a non-disruptive performance switching control scheme for the aero-engine switching control system based on the designed state-dependent switching law and non-disruptive performance index. The processing module is also used to determine the parameters of the disturbance-free switching controller based on the switching law and disturbance-free performance index.

9. A disturbance-free control system for an aero-engine, characterized in that... It includes a processor and a memory, wherein the processor implements the disturbance-free control method for an aero-engine according to any one of claims 1-7 when executing program data stored in the memory.

10. A readable storage medium, characterized in that, Used to store control program data, wherein the control program data, when executed by a processor, implements the disturbance-free control method for an aero-engine according to any one of claims 1-7.

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