Aviation turbofan engine switching control method, system and device

Abstract

The present invention relates to the technical field of turbofan engines, and specifically to a method, system and device for switching control of an aviation turbofan engine. The method comprises: establishing an aviation turbofan engine switching control system suitable for aircraft cruising; constructing a state-dependent switching mechanism based on the state of the aviation turbofan engine switching control system; introducing a disturbance-free switching performance index based on the state of the aviation turbofan engine switching control system to obtain a disturbance-free switching mechanism; determining an event trigger sampling mechanism based on the state-dependent switching mechanism and the disturbance-free switching mechanism; obtaining a disturbance-free switching event triggering control scheme based on the disturbance-free switching mechanism and the event triggering sampling mechanism; determining disturbance-free switching event triggering controller parameters according to the state-dependent switching mechanism and the disturbance-free switching event triggering control scheme. The present invention can improve the transient performance of the switching control mechanism, effectively reduce the amount of information in the communication channel, and save system resources.

Description

Technical Field

[0001] The present invention relates to the technical field of turbofan engines, and in particular to an aviation turbofan engine switching control method, system and equipment. Background Art

[0002] Aviation turbofan engine switching control technology is applied in highly complex operating environments and has dynamic characteristics. As the core power unit of modern aircraft, the performance of turbofan engines directly affects the safe, reliable and efficient operation of aircraft. Since the dynamics of aviation turbofan engines are highly nonlinear and they operate in an environment full of restrictions and uncertainties, traditional single engine control systems are difficult to meet their needs under various operating conditions.

[0003] The introduction of engine switching control technology can achieve more accurate and flexible engine adjustment according to the dynamic differences in different engine working modes. This can not only improve the engine's thrust response capability and operating stability, but also optimize fuel consumption and improve flight efficiency while ensuring safety. Therefore, designing a practical switching mechanism and achieving a smooth transition of performance between different modes under the designed switching mechanism and reducing switching disturbances between controllers are issues that need to be urgently addressed in the current research on aviation turbofan engine control systems. Summary of the invention

[0004] In order to solve the technical problems existing in the above-mentioned background technology, the present invention provides an aviation turbofan engine switching control method, system and equipment.

[0005] An aviation turbofan engine switching control method of the present invention comprises:

[0006] S1. Based on the aircraft dynamics model, establish an aviation turbofan engine switching control system suitable for aircraft cruising;

[0007] S2. Based on the state of the aviation turbofan engine switching control system, a state-dependent switching mechanism is constructed to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy;

[0008] S3. Based on the state of the aviation turbofan engine switching control system, the disturbance-free switching performance index is introduced to obtain the disturbance-free switching mechanism;

[0009] S4. Determine an event-triggered sampling mechanism based on a state-dependent switching mechanism and a disturbance-free switching mechanism;

[0010] S5. Based on the disturbance-free switching mechanism and the event-triggered sampling mechanism, a disturbance-free switching event-triggered control scheme is obtained;

[0011] S6. Determine the parameters of the bumpless switching event triggering controller according to the state-dependent switching mechanism and the bumpless switching event triggering control scheme.

[0012] In S1, an aviation turbofan engine switching control system suitable for aircraft cruising is established, specifically:

[0013] ,

[0014] in, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller. and is a given constant matrix,

[0015] is a switching function,

[0016] K is a set of positive integers, d is the number of subsystems, The switch function is used to assign the activation state of the subsystem. t It's switching time.

[0017] The state-dependent switching mechanism in S2 is specifically:

[0018] ,

[0019] ,

[0020] in, Indicates the status of the aviation turbofan engine switching control system. is the collection of all subsystems. i and j Respectively represent i and j subsystems, It is i The Lyapunov function of the subsystem, It is j The Lyapunov function of the subsystem, Indicates that the subsystem i Active aviation turbofan engine switching control system status domain, Refers to the satisfaction subsystem i Activated domains and satisfied subsystems j The intersection of the two activated domains,

[0021] exist t At the moment, if In , and before this moment the subsystem i Activate, then the subsystem In operation;

[0022] exist t At the moment, if In boundary, and before this moment the subsystem Activate, then the subsystem In running state.

[0023] The disturbance-free switching mechanism in S3 is as follows;

[0024] ,

[0025] in, It is the performance index of disturbance-free switching. is the virtual control signal of the engine switching controller, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller.

[0026] The event-triggered sampling mechanism in S4 is as follows;

[0027] definition To trigger the sampling sequence, To trigger the sampling time,

[0028] in, N is a real number set, the current trigger sampling time Less than the next trigger sampling moment , and the next trigger sampling moment for;

[0029] ,

[0030] in, is the state sampling error of the aviation turbofan engine switching control system; , is a given time interval; , is the event triggering threshold; is a weight coefficient, and is the adjustment parameter, for i or j , i and j Respectively represent i and j subsystems, It is the performance index of disturbance-free switching. t It's switching time.

[0031] The control scheme for triggering the disturbanceless switching event in S5 is as follows:

[0032] Based on the event-triggered sampling mechanism, the state sampling value is calculated, and the event-triggered switching controller is:

[0033] ,

[0034] in, Indicates the status value of the last transmission. To trigger the sampling time, For the next trigger sampling moment, for Aviation turbofan engine switching controller at the moment, is the controller gain to be designed, It is the engine switching controller. t It's switching time.

[0035] The specific method for determining the parameters of the controller triggered by the bumpless switching event in S6 is:

[0036] when When, define , ,

[0037] in, i Indicates i subsystems, and is a given constant matrix such that the following inequality holds;

[0038] ,

[0039] ,

[0040] ,

[0041] ,

[0042] ,

[0043] in, is the preset identity matrix, the constant , , is the adjustment parameter, the matrix , , , is the adjustment matrix, matrix , , , , is a positive definite regulation matrix, is a constant, the matrix is the virtual control gain matrix, is a diagonal matrix, , , is the matrix form of the constraints, For the matrix A simplified representation of , , , is a constraint parameter.

[0044] The specific method of obtaining the parameters of the controller triggered by the disturbanceless switching event is as follows;

[0045] ,

[0046] ,

[0047] ,

[0048] ,

[0049] ,

[0050] ,

[0051] ,

[0052] ,

[0053] ,

[0054] ,

[0055] ,

[0056] ,

[0057] ,

[0058] ,

[0059] ,

[0060] ,

[0061] ,

[0062] ,

[0063] ,

[0064] ,

[0065] ,

[0066] in, , , are the identity matrices in different directions, is a matrix A simplified representation of is a matrix A simplified representation of is a parameter , , , Indicates direction, is the number of subsystems, is a positive definite adjustment matrix; the constant , , , , , is a tuning parameter; scalar Indicates that from the modal i Switch to modal Transfer rate one-half power; represents a positive definite matrix, , , is a positive definite adjustment matrix.

[0067] The present invention provides an aviation turbofan engine switching control system, comprising:

[0068] The engine switching control system establishment module establishes an aviation turbofan engine switching control system suitable for aircraft cruising based on the aircraft dynamics model;

[0069] The state-dependent switching module divides the state of the aviation turbofan engine switching control system and determines a state-dependent switching mechanism to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy;

[0070] The disturbance-free switching module introduces the disturbance-free switching performance index into the state of the aviation turbofan engine switching control system to obtain the disturbance-free switching mechanism and reduce the disturbance generated during the engine switching control.

[0071] An event-triggered sampling module determines an event-triggered sampling mechanism based on a state-dependent switching mechanism and a non-intrusive switching mechanism;

[0072] The non-disturbance switching event trigger control module obtains the non-disturbance switching event trigger control scheme based on the non-disturbance switching mechanism and the event trigger sampling mechanism;

[0073] The disturbanceless switching event trigger controller parameter acquisition module determines the disturbanceless switching event trigger controller parameters according to the state-dependent switching mechanism and the disturbanceless switching event trigger control scheme.

[0074] The present invention provides an aviation turbofan engine switching control device, which includes a processor and a memory. When the processor executes a stored computer program, the steps in the above-mentioned aviation turbofan engine switching control method are implemented.

[0075] Through the above design, the beneficial effects of the present invention are: the introduction of the engine switching control technology can achieve more accurate and flexible engine control according to the dynamic differences of the engine under different states;

[0076] Improve the engine's thrust response capability and operating stability, optimize fuel consumption and improve flight efficiency while ensuring safety;

[0077] Under the designed switching mechanism, a smooth transition of engine performance between different states is achieved, reducing switching disturbances between controllers. BRIEF DESCRIPTION OF THE DRAWINGS

[0078] In the attached picture:

[0079] Figure 1 The present invention is a flow chart of an aviation turbofan engine switching control method. DETAILED DESCRIPTION

[0080] The technical solution of the present invention is as follows:

[0081] Figure 1 is a flow chart of a switching control method of an aviation turbofan engine according to the present invention, as shown in Figure 1 As shown, in one embodiment of the present invention, a method for switching control of an aviation turbofan engine of the present invention is specifically as follows:

[0082] S1. Based on the aircraft dynamics model, establish an aviation turbofan engine switching control system suitable for aircraft cruising;

[0083] S2. Based on the state of the aviation turbofan engine switching control system, a state-dependent switching mechanism is constructed to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy;

[0084] S3. Based on the state of the aviation turbofan engine switching control system, the disturbance-free switching performance index is introduced to obtain the disturbance-free switching mechanism;

[0085] S4. Determine an event-triggered sampling mechanism based on a state-dependent switching mechanism and a disturbance-free switching mechanism;

[0086] S5. Based on the disturbance-free switching mechanism and the event-triggered sampling mechanism, a disturbance-free switching event-triggered control scheme is obtained;

[0087] S6. Determine the parameters of the bumpless switching event triggering controller according to the state-dependent switching mechanism and the bumpless switching event triggering control scheme.

[0088] In S1, an aviation turbofan engine switching control system suitable for aircraft cruising is established, specifically:

[0089] ,

[0090] in, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller. and is a given constant matrix,

[0091] is a switching function,

[0092] K is a set of positive integers, d is the number of subsystems, The switch function is used to assign the activation state of the subsystem. t is the switching moment, i.e. i The subsystem is activated. i The state trajectory of each subsystem is the state trajectory of the above formula.

[0093] Specifically, the aviation turbofan engine switching control system can be broken down into:

[0094] ,

[0095] in, is the low-pressure rotor speed increment, is the high pressure rotor speed increment, is the fuel flow increment,

[0096] and Also as an indication of the system state, As the control input, , parameterize the system matrix and it can be expressed as:

[0097] ,

[0098] ,

[0099] ,

[0100] ,

[0101] in, , , , is the system matrix.

[0102] The state-dependent switching mechanism in S2 is specifically:

[0103] ,

[0104] ,

[0105] in, Indicates the status of the aviation turbofan engine switching control system. is the collection of all subsystems. i and j Respectively represent i and j subsystems, It is i The Lyapunov function of the subsystem, It is j The Lyapunov function of the subsystem, Indicates that the subsystem i Active aviation turbofan engine switching control system status domain, Refers to the satisfaction subsystem i Activated domains and satisfied subsystems j The intersection of the two activated domains,

[0106] ,

[0107] ,

[0108] exist t At the moment, if In , and before this moment the subsystem i Activate, then the subsystem In operation;

[0109] exist t At the moment, if In boundary, and before this moment the subsystem Activate, then the subsystem In running state.

[0110] In this implementation, we can .

[0111] The disturbance-free switching mechanism in S3 can reduce the disturbance caused by the switching of the engine controller, specifically:

[0112] ,

[0113] in, It is the performance index of disturbance-free switching. is the virtual control signal of the engine switching controller, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller.

[0114] ,

[0115] ,

[0116] is the virtual control gain, is the gain of the engine switching controller, To trigger the sampling time, Indicates the status value of the last transmission.

[0117] In this implementation, the specific parameters can be, , .

[0118] The event-triggered sampling mechanism in S4 is as follows;

[0119] definition To trigger the sampling sequence, To trigger the sampling time,

[0120] in, N is a real number set, the current trigger sampling time Less than the next trigger sampling moment , and the next trigger sampling moment for;

[0121] ,

[0122] in, is the state sampling error of the aviation turbofan engine switching control system; , is a given time interval; , is the event triggering threshold; is a weight coefficient, and is the adjustment parameter, for i or j , i and j Respectively represent i and j subsystems, It is the performance index of disturbance-free switching. t It's switching time.

[0123] Use the designed event-triggered sampling mechanism to obtain the state sampling value For the next step of controller design, in this implementation, the specific parameters can be set to , , , .

[0124] State sampling error of switching control system of aviation turbofan engine It can be expressed as:

[0125] .

[0126] The control scheme for triggering the disturbanceless switching event in S5 is as follows:

[0127] Based on the event-triggered sampling mechanism, the state sampling value is calculated, and the event-triggered switching controller is:

[0128] ,

[0129] ,

[0130] in, Indicates the status value of the last transmission. To trigger the sampling time, For the next trigger sampling moment, for Aviation turbofan engine switching controller at the moment, is the controller gain to be designed, It is the engine switching controller. t is the switching moment, which makes the aviation turbofan engine switching control system model stable and satisfies the disturbance-free switching mechanism in S3.

[0131] The specific method for determining the parameters of the controller triggered by the bumpless switching event in S6 is:

[0132] when When, define , ,

[0133] in, i Indicates i subsystems, and is a given constant matrix such that the following inequality holds;

[0134] ,

[0135] ,

[0136] ,

[0137] ,

[0138] ,

[0139] in, is the preset identity matrix, the constant , , is the adjustment parameter, the matrix , , , is the adjustment matrix, matrix , , , , is a positive definite regulation matrix, is a constant, the matrix is the virtual control gain matrix, is a diagonal matrix, , , is the matrix form of the constraints, For the matrix A simplified representation of , , , is a constraint parameter.

[0140] The specific method of obtaining the parameters of the controller triggered by the disturbanceless switching event is as follows;

[0141] ,

[0142] ,

[0143] ,

[0144] ,

[0145] ,

[0146] ,

[0147] ,

[0148] ,

[0149] ,

[0150] ,

[0151] ,

[0152] ,

[0153] ,

[0154] ,

[0155] ,

[0156] ,

[0157] ,

[0158] ,

[0159] ,

[0160] ,

[0161] ,

[0162] in, , , are the identity matrices in different directions, is a matrix A simplified representation of is a matrix A simplified representation of is a parameter , , , Indicates direction, is the number of subsystems, is a positive definite adjustment matrix; the constant , , , , , is a tuning parameter; scalar Indicates that from the modal i Switch to modal Transfer rate one-half power; represents a positive definite matrix, , , is a positive definite adjustment matrix.

[0163] In this implementation, let , , select , , , , through the data given above, we can get:

[0164] ,

[0165] ,

[0166] ,

[0167] ,

[0168] ,

[0169] ,

[0170] Control gain Given by:

[0171] .

[0172] The present invention provides an aviation turbofan engine switching control system, comprising:

[0173] The engine switching control system establishment module establishes an aviation turbofan engine switching control system suitable for aircraft cruising based on the aircraft dynamics model;

[0174] The state-dependent switching module divides the state of the aviation turbofan engine switching control system and determines a state-dependent switching mechanism to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy;

[0175] The disturbance-free switching module introduces the disturbance-free switching performance index into the state of the aviation turbofan engine switching control system to obtain the disturbance-free switching mechanism and reduce the disturbance generated during the engine switching control.

[0176] An event-triggered sampling module determines an event-triggered sampling mechanism based on a state-dependent switching mechanism and a non-intrusive switching mechanism;

[0177] The non-disturbance switching event trigger control module obtains the non-disturbance switching event trigger control scheme based on the non-disturbance switching mechanism and the event trigger sampling mechanism;

[0178] The disturbanceless switching event trigger controller parameter acquisition module determines the disturbanceless switching event trigger controller parameters according to the state-dependent switching mechanism and the disturbanceless switching event trigger control scheme.

[0179] The present invention provides an aviation turbofan engine switching control device, which includes a processor and a memory. When the processor executes a stored computer program, the above-mentioned aviation turbofan engine switching control method is implemented.

[0180] Through the above design, the beneficial effects of the present invention are: the introduction of the engine switching control technology can achieve more accurate and flexible engine control according to the dynamic differences of the engine under different states;

[0181] Improve the engine's thrust response capability and operating stability, optimize fuel consumption and improve flight efficiency while ensuring safety;

[0182] Under the designed switching mechanism, a smooth transition of engine performance between different states is achieved, reducing switching disturbances between controllers.

Claims

1. A method for switching control of an aviation turbofan engine, characterized in that: The method comprises: S1. Based on the aircraft dynamics model, establish an aviation turbofan engine switching control system suitable for aircraft cruising; S2. Based on the state of the aviation turbofan engine switching control system, a state-dependent switching mechanism is constructed to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy; S3. Based on the state of the aviation turbofan engine switching control system, the disturbance-free switching performance index is introduced to obtain the disturbance-free switching mechanism; The disturbance-free switching mechanism is as follows; , in, is the performance index of disturbance-free switching. is the virtual control signal of the engine switching controller, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller; S4. Determine an event-triggered sampling mechanism based on a state-dependent switching mechanism and a disturbance-free switching mechanism; S5. Based on the disturbance-free switching mechanism and the event-triggered sampling mechanism, a disturbance-free switching event-triggered control scheme is obtained; S6. Determine the parameters of the bumpless switching event triggering controller according to the state-dependent switching mechanism and the bumpless switching event triggering control scheme.

2. The method for switching control of an aviation turbofan engine according to claim 1, characterized in that: The S1 establishes an aviation turbofan engine switching control system suitable for aircraft cruising, specifically: ， in, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller. and is a given constant matrix, is a switching function, K is a set of positive integers, d is the number of subsystems, The switch function is used to assign the activation state of the subsystem. t It's switching time.

3. The aviation turbofan engine switching control method according to claim 1, characterized in that: The state-dependent switching mechanism in S2 is specifically: , in, Indicates the status of the aviation turbofan engine switching control system. is the collection of all subsystems. i and j Respectively represent i and j subsystems, It is i The Lyapunov function of the subsystem, It is j The Lyapunov function of the subsystem, Indicates that the subsystem i Active aviation turbofan engine switching control system status domain, exist t At the moment, if In , and before this moment the subsystem Activate, then the subsystem In running state.

4. The aviation turbofan engine switching control method according to claim 1, characterized in that: The event-triggered sampling mechanism in S4 is specifically: definition To trigger the sampling sequence, To trigger the sampling time, in, N is a set of real numbers, the current trigger sampling time Less than the next trigger sampling moment , and the next trigger sampling moment for; ， in, is the state sampling error of the aviation turbofan engine switching control system; , is a given time interval; , is the event triggering threshold; is a weight coefficient, and is the adjustment parameter, for i or j , i and j Respectively represent i and j subsystems, is the performance index of disturbance-free switching. t It's switching time.

5. The aviation turbofan engine switching control method according to claim 1, characterized in that: The control scheme for triggering the disturbance-free switching event in S5 is specifically as follows: Based on the event-triggered sampling mechanism, the state sampling value is calculated, and the event-triggered switching controller is: ， in, Indicates the status value of the last transmission. To trigger the sampling time, is the next trigger sampling moment, for Aviation turbofan engine switching controller at the moment, is the controller gain to be designed, It is the engine switching controller. t It's switching time.

6. The aviation turbofan engine switching control method according to claim 1, characterized in that: The specific method for determining the parameters of the controller triggered by the bumpless switching event in S6 is: when When, define , , in, i Indicates i subsystems, and is a given constant matrix such that the following inequality holds; ， ， ， ， ， in, is the preset identity matrix, the constant , , is the adjustment parameter, the matrix , , , is the adjustment matrix, matrix , , , , is a positive definite regulation matrix, is a constant, the matrix is the virtual control gain matrix, is a diagonal matrix, , , is the matrix form of the constraints, For the matrix A simplified representation of , , , is a constraint parameter.

7. The aviation turbofan engine switching control method according to claim 6, characterized in that: The specific method of obtaining the parameters of the controller triggered by the disturbanceless switching event is as follows; ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， ， in, , , are the identity matrices in different directions, is a matrix A simplified representation of is a matrix A simplified representation of is a parameter , , , Indicates direction, is the number of subsystems, is a positive definite adjustment matrix; the constant , , , , , is a tuning parameter; scalar Indicates that from the modal i Switch to modal Transfer rate one-half power; represents a positive definite matrix, , , is a positive definite adjustment matrix.

8. An aviation turbofan engine switching control system, characterized in that: The system comprises: The engine switching control system establishment module establishes an aviation turbofan engine switching control system suitable for aircraft cruising based on the aircraft dynamics model; The state-dependent switching module divides the state of the aviation turbofan engine switching control system and determines a state-dependent switching mechanism to switch from the subsystem currently running in the aviation turbofan engine to the subsystem with the lowest energy; The disturbance-free switching module introduces the disturbance-free switching performance index into the state of the aviation turbofan engine switching control system to obtain the disturbance-free switching mechanism and reduce the disturbance generated during the engine switching control. An event-triggered sampling module determines an event-triggered sampling mechanism based on a state-dependent switching mechanism and a non-intrusive switching mechanism; The disturbance-free switching mechanism is as follows; , in, is the performance index of disturbance-free switching. is the virtual control signal of the engine switching controller, Indicates the status of the aviation turbofan engine switching control system. It is the engine switching controller; The non-disturbance switching event trigger control module obtains the non-disturbance switching event trigger control scheme based on the non-disturbance switching mechanism and the event trigger sampling mechanism; The disturbanceless switching event trigger controller parameter acquisition module determines the disturbanceless switching event trigger controller parameters according to the state-dependent switching mechanism and the disturbanceless switching event trigger control scheme.

9. An aviation turbofan engine switching control device, characterized in that: It comprises a processor and a memory, and when the processor executes a stored computer program, it implements an aviation turbofan engine switching control method as described in any one of claims 1-7.

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