Aero-engine guide vane control system and method based on rotary electromechanical actuator

Abstract

The invention relates to an aero-engine guide vane control system and method based on a rotary electromechanical actuator, and relates to the technical field of aero-engine control. The system comprises a main controller, a motor driving controller, a sensor, a speed reducer and an adjusting mechanism, the main controller is in communication connection with the motor driving controller; the motor driving controller is in communication connection with the sensor and is in control connection with the speed reducer, and the motor driving controller is used for generating a driving instruction; the speed reducer is in control connection with the adjusting mechanism and generates angular displacement data control data and torque control data based on the driving instruction; and the adjusting mechanism comprises a guide vane. The characteristics of a guide vane synchronous ring actuation mechanical structure are fully utilized, a rotary electromechanical actuator is designed to replace existing linear actuation, the overall structure is simplified on the premise that the actuation function performance is guaranteed, a corresponding driving part and a corresponding driving method are configured, and reliability and maintainability are improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine control technology, and in particular to an aircraft engine guide vane control system and method based on a rotary electromechanical actuator. Background Art

[0002] Traditional compressor and turbine guide vane control utilizes hydraulic servo valves and actuators. This hydraulic output uses fuel to generate linear displacement, which drives a synchronizer ring that converts this displacement into rotational displacement, thereby adjusting the guide vane angle. With the development of multi-electric and fully electric aircraft engines, there is also a demand for multi-electric and fully electric actuators in engine control systems. For compressor and turbine guide vane control, the actuation system is evolving from traditional fuel-hydraulic actuation to fully electric actuation.

[0003] The guide vane control in related technologies still uses a compound motion scheme combining the rotation of the synchronizer ring and direct motion. However, the fuel hydraulic actuation method is replaced with a mechanical scheme, using a linear electromechanical actuator to output linear displacement, which is then converted into rotational displacement to adjust the guide vane angle.

[0004] The methods used in related technologies may cause jamming, resulting in reduced engine reliability. Summary of the Invention

[0005] The present invention relates to an aircraft engine guide vane control system and method based on a rotary electromechanical actuator, which can avoid the occurrence of sticking and thus improve engine reliability. The technical solution is as follows: On the one hand, an aircraft engine guide vane control system based on a rotary electromechanical actuator is provided, the system including a main controller, a motor drive controller, a sensor, a speed reducer, and an adjustment mechanism; The main controller is in communication connection with the motor drive controller; The motor drive controller is connected to the sensor for communication and is also connected to the reducer control, and is used to generate drive instructions; The reducer is control-connected to the regulating mechanism, and the reducer generates angular displacement data control data and torque control data based on the driving instruction; The regulating mechanism includes guide vanes.

[0006] In an optional embodiment, the system further includes a power supply and an aviation plug; The power supply is connected to the main controller via an aviation plug.

[0007] In an optional embodiment, the motor drive controller includes an electromagnetic compatibility (EMC) filter module, a motor drive module, and a motor control module; The EMC filter module is used to supply power to the motor drive module; The motor drive module is communicatively connected to the motor controller. The motor drive module is used to send at least one of the bus voltage, current signal, tube shell temperature and capacitor temperature to the motor control module. The motor control module is used to feed back a drive signal to the motor drive module, and the drive signal is used to generate a drive instruction.

[0008] In an optional embodiment, the system further comprises a rotary transformer; The resolver is used to exchange resolver signals with the motor drive controller.

[0009] In an optional embodiment, the system further comprises a permanent magnet synchronous motor; The permanent magnet synchronous motor is connected to the motor drive controller via a three-phase power line; In an optional embodiment, the adjustment mechanism includes a connecting rod mechanism, a synchronizer ring, and a guide vane; The connecting rod mechanism is used to connect the adjustment mechanism and the reducer; The synchronizer ring is used to be driven by the connecting rod mechanism to control the movement of the guide vanes.

[0010] In another aspect, a method for controlling an aircraft engine guide vane based on a rotary electromechanical actuator is provided, wherein the method is applied to any of the above aircraft engine guide vane control systems based on a rotary electromechanical actuator, and the method comprises: Generates and sends control angle instructions to the motor drive controller through the main controller; The motor drive controller generates a drive instruction based on the control angle instruction and sends the drive instruction to the reducer; Angular displacement control data and torque control data are generated by the speed reducer, and the guide vane angle in the adjustment mechanism is controlled by the speed reducer.

[0011] In an optional embodiment, before the main controller generates and sends the control angle instruction to the motor drive controller, the following steps are included: Perform power-on initialization self-test on the motor drive controller.

[0012] In an optional embodiment, generating a drive instruction based on a control angle instruction by a motor drive controller includes: Determine the correspondence between the guide vane control angle and the motor angular position; Angular position calibration based on the corresponding relationship; Combined with the calibration results of the angular position calibration, an angular position command, a motor angular position signal and a q-axis current detection value are generated; A closed-loop calculation is performed based on the angular position command, the motor angular position signal, and the q-axis current detection value to generate a drive command.

[0013] The beneficial effects of the technical solution provided by this application include at least: By making full use of the mechanical structural characteristics of the guide vane synchronous ring actuation, a rotary electromechanical actuator is designed to replace the existing linear actuation while ensuring the actuation function performance. The overall structure is simplified, and corresponding drive components and drive methods are configured to improve reliability and maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0015] Figure 1 A schematic structural diagram of an aircraft engine guide vane control system based on a rotary electromechanical actuator provided by an exemplary embodiment of the present application is shown.

[0016] Figure 2 A schematic structural diagram of another aircraft engine guide vane control system based on a rotary electromechanical actuator provided by an exemplary embodiment of the present application is shown.

[0017] Figure 3 A flow chart of an exemplary method for controlling an aircraft engine guide vane based on a rotary electromechanical actuator provided in the present application is shown. DETAILED DESCRIPTION

[0018] In order to make the objectives, technical solutions and advantages of this application clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0019] Figure 1 A schematic structural diagram of an aircraft engine guide vane control system based on a rotary electromechanical actuator provided by an exemplary embodiment of the present application is shown. Figure 2 The schematic diagram of another aircraft engine guide vane control system based on a rotary electromechanical actuator provided by an exemplary embodiment of the present application is shown. Figure 1The system includes a main controller 1, a motor drive controller 2, a sensor 3, a reducer 4 and an adjustment mechanism 5; the main controller is communicatively connected to the motor drive controller; the motor drive controller is communicatively connected to the sensor and is control-connected to the reducer, and the motor drive controller is used to generate drive instructions; the reducer is control-connected to the adjustment mechanism, and the reducer generates angular displacement data control data and torque control data based on the drive instructions; the adjustment mechanism includes guide vanes.

[0020] It should be noted that in the embodiments of the present application, the main controller can be implemented as a computer device with data processing capabilities. The present application does not limit the specific implementation form of the main controller. In one example, the main controller can be implemented as a CPU, and in another example, the main controller can be implemented as an ECU. Alternatively, the main controller can also be implemented as a host industrial computer corresponding to a PLC device.

[0021] In the embodiment of the present application, the drive motor is an energy driving mechanism of the rotary electromechanical actuator, providing energy input for the rotary electromechanical actuator.

[0022] The sensor is installed in the drive motor to measure and feedback the motor's angular position, and transmit the signal to the motor drive controller to complete the angular position closed-loop control.

[0023] The motor drive controller receives the actuator angular position given instruction, calculates the motor angular position feedback from the sensor, and sends a switch instruction to the drive module to control the drive motor to reach the specified angular position.

[0024] The reducer is driven by the drive motor and converts the angular displacement and torque output by the drive motor into angular displacement and torque suitable for the guide vane control requirements.

[0025] It should be noted that in some embodiments of the present application, the system further includes a housing for integrated installation. The drive motor, sensor, and reduction gear are all installed inside the housing, while the motor drive controller is installed outside the housing and, together with the adjustment mechanism, performs the function of controlling the guide vanes in the engine.

[0026] Next, combine Figure 2 , the specific structure of the aircraft engine guide vane control system based on the rotating electromechanical actuator involved in this application is explained.

[0027] In an optional embodiment, the system further includes a power supply 6 and an aviation plug 7 , and the power supply 6 is connected to the main controller 1 via the aviation plug 7 .

[0028] In one example, the connection between the main controller and the aviation power supply is a 28V DC power supply, and the connection between the power supply and the aviation plug is a 270V DC power supply. In some examples, the main controller and the motor drive controller are connected via an aviation plug.

[0029] In an optional embodiment, the motor drive controller includes an EMC filter module 21, a motor drive module 22 and a motor control module 23; The EMC filter module is used to supply power to the motor drive module; The motor drive module is communicatively connected to the motor controller. The motor drive module is used to send at least one of the bus voltage, current signal, tube shell temperature and capacitor temperature to the motor control module. The motor control module is used to feed back a drive signal to the motor drive module, and the drive signal is used to generate a drive instruction.

[0030] In this case, the system further includes a rotary transformer 8 ; the rotary transformer is used to exchange rotary signals with the motor drive controller.

[0031] In an optional embodiment, the system further includes a permanent magnet synchronous motor 9; the permanent magnet synchronous motor is communicatively connected to the motor drive controller via a three-phase power line; the permanent magnet synchronous motor is used to feed back the winding temperature to the motor drive controller.

[0032] In an optional embodiment, the regulating mechanism includes a connecting rod mechanism 51, a synchronizer ring 52 and a guide vane 53; the connecting rod mechanism is used to connect the regulating mechanism and the reducer; the synchronizer ring is used to be driven by the connecting rod mechanism to control the movement of the guide vane.

[0033] Combine Figure 1 as well as Figure 2 The system shown, Figure 3 A flow chart of an exemplary method for controlling an aircraft engine guide vane based on a rotary electromechanical actuator provided by the present application is shown. The process includes: Step 301: Generate a control angle instruction through the main controller and send it to the motor drive controller.

[0034] It should be noted that before sending the control angle command, the motor drive controller needs to perform an initialization power-on self-test.

[0035] Step 302: Generate a drive instruction based on the control angle instruction through the motor drive controller and send it to the reducer.

[0036] In an embodiment of the present application, the process includes: determining the correspondence between the guide vane control angle and the motor angular position; performing angular position calibration based on the correspondence; generating an angular position instruction, a motor angular position signal, and a q-axis current detection value based on the calibration result of the angular position calibration; performing a closed-loop calculation based on the angular position instruction, the motor angular position signal, and the q-axis current detection value to generate a drive instruction.

[0037] That is, in one example, the motor drive controller reads the given angular position instruction, the motor angular position signal output by the sensor, and the q-axis current detection value sent back by the motor drive controller, calculates the motor angular position loop, motor speed loop, and current loop control laws, and obtains the q-axis current given value. The q-axis current given value calculated according to the steps generates a PWM wave, sends a duty cycle signal, controls the on and off of each IGBT of the inverter, supplies three-phase voltage to the drive motor, and outputs torque after deceleration by the reducer.

[0038] In one example, the specific implementation logic includes: a) Given an angular position command θ*, the deviation e1 is calculated based on the actual angular position θ as the input of the position loop controller, and the calculated output is the motor angular velocity given ω*; b) Calculate the deviation e2 based on the actual angular velocity ω as the input of the speed loop controller, and calculate the output as the current loop given iq*; c) Calculate the deviation e3 as the α-axis voltage Uα based on the current iq converted from the actual three-phase currents ia, ib, and ic after CLARKE transformation and PARK transformation. At the same time, calculate the β-axis voltage uβ based on id=0. Generate the three-phase AC voltages ua, ub, and uc as the SVPWM input signals through PARK inverse transformation and CLARKE inverse transformation. d) SVPWM generates a duty cycle signal to control the on / off duration of the inverter switch tube, thereby generating the desired three-phase voltage for the motor and driving the motor to output torque. The motor's three-phase current, rotor angular velocity, and angular position are all measured by sensors and feedback is calculated.

[0039] Step 303: Generate angular displacement control data and torque control data through a speed reducer, and control the guide vane angle in the regulating mechanism through the speed reducer.

[0040] This process is the structure in which the reducer controls the guide vane angle in the adjustment mechanism.

[0041] In summary, the system and method provided in the embodiments of the present application fully utilize the mechanical structural characteristics of the guide vane synchronous ring actuation, design a rotary electromechanical actuator to replace the existing linear actuation to ensure the actuation function performance, simplify the overall structure, and configure corresponding drive components and drive methods to improve reliability and maintainability.

[0042] The system and method provided in the embodiments of the present application adopt a purely mechanical actuation mode without a complex valve-controlled hydraulic system, thereby bringing the advantages of low complexity, no fuel leakage, and no risk of blockage, while having high maintainability.

[0043] The system and method provided in the embodiments of the present application adopt a rotary-rotary direct drive motion conversion method, which optimizes the system structure, reduces complexity, and reduces the risk of jamming.

[0044] The system and method provided in the embodiments of the present application fully consider the integrated design of components such as the rotating electromechanical actuator motor, drive controller, reducer, and adjustment mechanism, and have a high degree of integration.

[0045] The system and method provided in the embodiments of the present application are optimized only for the actuator and input linkage mechanism, and have good versatility and engineering applicability.

[0046] The above are only optional embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present application should be included in the scope of protection of the present application.

Claims

1. An aircraft engine guide vane control system based on a rotary electromechanical actuator, characterized in that: The aero-engine guide vane control system based on the rotary electromechanical actuator comprises a main controller, a motor drive controller, a sensor, a reducer and an adjustment mechanism; The main controller is communicatively connected with the motor drive controller; The motor drive controller is in communication connection with the sensor and in control connection with the reducer, and the motor drive controller is used to generate a drive instruction; The reducer is control-connected to the regulating mechanism, and the reducer generates angular displacement data control data and torque control data based on the driving instruction; The regulating mechanism includes guide vanes.

2. The aero-engine guide vane control system based on a rotary electromechanical actuator according to claim 1, characterized in that: The system also includes a power supply and an aviation plug; The power supply is connected to the main controller via the aviation plug.

3. The aero engine guide vane control system based on a rotary electromechanical actuator according to claim 1, characterized in that: The motor drive controller includes an electromagnetic compatibility (EMC) filter module, a motor drive module and a motor control module; The EMC filter module is used to supply power to the motor drive module; The motor drive module is communicatively connected to the motor controller, and the motor drive module is used to send at least one of bus voltage, current signal, tube shell temperature and capacitor temperature to the motor control module, and the motor control module is used to feed back a drive signal to the motor drive module, and the drive signal is used to generate a drive instruction.

4. The aero-engine guide vane control system based on a rotary electromechanical actuator according to claim 3, characterized in that: The system also includes a rotary transformer; The rotary transformer is used to exchange rotary transformer signals with the motor drive controller.

5. The aircraft engine guide vane control system based on a rotary electromechanical actuator according to claim 3, characterized in that: The system also includes a permanent magnet synchronous motor; The permanent magnet synchronous motor is communicatively connected to the motor drive controller via a three-phase power line; The permanent magnet synchronous motor is used to feed back the winding temperature to the motor drive controller.

6. The aircraft engine guide vane control system based on a rotary electromechanical actuator according to claim 1, characterized in that: The regulating mechanism comprises a connecting rod mechanism, a synchronizing ring and a guide vane; The connecting rod mechanism is used to connect the adjusting mechanism and the reducer; The synchronizer ring is used to be driven by the connecting rod mechanism to control the movement of the guide vane.

7. A method for controlling guide vanes of an aircraft engine based on a rotary electromechanical actuator, characterized in that: The method is applied to an aircraft engine guide vane control system based on a rotary electromechanical actuator as claimed in any one of claims 1 to 6, and the method comprises: Generate a control angle command through the main controller and send it to the motor drive controller; The motor drive controller generates a drive instruction based on the control angle instruction and sends it to the reducer; Angular displacement control data and torque control data are generated by the reducer, and the guide vane angle in the adjustment mechanism is controlled by the reducer.

8. The method according to claim 7, characterized in that Before the main controller generates and sends a control angle instruction to the motor drive controller, the following steps are included: Perform a power-on initialization self-test on the motor drive controller.

9. The method according to claim 7, characterized in that: The step of generating a drive instruction based on the control angle instruction by the motor drive controller includes: Determine the corresponding relationship between the guide vane control angle and the motor angular position; Performing angular position calibration based on the corresponding relationship; Combined with the calibration result of the angular position calibration, an angular position command, a motor angular position signal and a q-axis current detection value are generated; The drive command is generated by performing a closed-loop calculation based on the angular position command, the motor angular position signal, and the q-axis current detection value.

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