A simplified calibration method for aircraft engine angular displacement sensors

Abstract

The present application belongs to the field of aircraft engine control systems, and particularly relates to a simplified calibration method for aircraft engine angular displacement sensors. The method comprises the following steps: Step 1: adding a BIT value-voltage value calibration line for the angular displacement sensor to a digital electronic controller, and converting the voltage signal of the angular displacement sensor into a BIT value according to the BIT value-voltage value calibration line for the angular displacement sensor; Step 2: obtaining the voltage value collected by the digital electronic controller; Step 3: adjusting the operating range of the angular displacement sensor during aircraft engine assembly, and completing mechanical angle pre-calibration to obtain a mechanical angle position-voltage value calibration line; Step 4: inputting the mechanical angle position-voltage value calibration line into the digital electronic controller, and the digital electronic controller generating a mechanical angle position-BIT value calibration line based on the BIT value-voltage value calibration line for the angular displacement sensor and the mechanical angle position-voltage value calibration line.

Description

Technical Field

[0001] The present application relates to the field of aircraft engine control systems, and in particular to a simplified calibration method for aircraft engine angular displacement sensors. Background Art

[0002] Aircraft engine control system calibration is a part of the preparation before bench test and after the aircraft is installed with the engine. According to the feedback from the delivery of aircraft engines to the factory and field installation, users generally have strong opinions on the many parameters of the aircraft engine control system calibration, the long time consumption, and the inconvenience of operation in the bench and installation preparation. Aircraft engine control system calibration is the process of matching the physical quantities collected by various engine sensors with the BIT values collected by the digital electronic controller (the BIT value is the digital quantity collected by the controller, also called the code value, with the unit of BIT), thereby forming a benchmark for each collected parameter of the control system. The purpose of aircraft engine control system calibration is to determine the data benchmark of the digital electronic controller responsible for parameter collection in the engine test system. Since the collected values of the controller for each engine parameter are all digital signals (BIT values), in order to match the digital signals collected by the controller with the true physical meaning of the parameters (see Figure 1 ), it is necessary to calibrate the controller acquisition channel by adding analog sensor signals to the controller to eliminate the differences between individual accessories and ensure the consistency of the system.

[0003] As part of a test system, aircraft engine angular displacement sensors are primarily used to measure fan and compressor blade angles, nozzle angles, and other parameters. They serve as the "eyes" of digital electronic controllers, converting angle signals into voltage signals for transmission to the controller. RVDT angular displacement sensors used in aircraft engines typically consist of an iron core, an armature, a primary coil, and a secondary coil. Within the coils are coaxially mounted stators and rotors, which are connected to the corresponding mechanical structure. When the adjustable blade angle changes, the two secondary coils generate unequal induced electromotive forces, resulting in a voltage output proportional to the rotation angle. This voltage signal is transmitted to the controller for aircraft engine control. The circuit connecting the RVDT angular displacement sensor to the controller consists of five signal paths: two excitation signals and three feedback signals.

[0004] Currently, aircraft engine angular displacement sensors are typically installed in the mechanical structures used to measure the fan's adjustable blade angle, the compressor's adjustable blade angle, and the nozzle angle. After the engine is installed, a digital electronic controller is connected to the aircraft engine via a test bench cable or aircraft cable. The voltage output by the angular displacement sensor is collected through actual mechanical position movement, converted into a bit value signal, and then compared to the actual physical position of the mechanical structure to form a calibration line. However, due to differences between digital electronic controllers, errors will be introduced into the acquisition and conversion process, resulting in the need for recalibration after the engine's digital electronic controller is replaced. This is labor-intensive and time-consuming, and the calibration operation is inconvenient and labor-intensive, affecting overall progress. Replacing the digital electronic controller requires recalibration of the relevant parameters collected by the angular displacement sensor. Furthermore, angular displacement sensor calibration requires high technical skills from the operator. If the operator is not familiar with the process, errors can easily occur, affecting the overall control of the aircraft engine.

[0005] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art. Summary of the Invention

[0006] The purpose of this application is to provide a simplified calibration method for an aircraft engine angular displacement sensor to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is:

[0008] A simplified calibration method for an aircraft engine angular displacement sensor, comprising:

[0009] Step 1: Add a BIT value-voltage value calibration line of the angular displacement sensor to the digital electronic controller, and convert the voltage signal of the angular displacement sensor into a BIT value according to the BIT value-voltage value calibration line of the angular displacement sensor;

[0010] Step 2: obtaining the voltage value collected by the digital electronic controller;

[0011] Step 3: When assembling the aircraft engine, the operating range of the angular displacement sensor is adjusted, and mechanical angle pre-calibration is completed to obtain a mechanical angle position-voltage value calibration line;

[0012] Step 4: Input the mechanical angle position-voltage value calibration line into the digital electronic controller, and the digital electronic controller generates a mechanical angle position-BIT value calibration line based on the angular displacement sensor BIT value-voltage value calibration line and the mechanical angle position-voltage value calibration line.

[0013] In at least one embodiment of the present application, in step 1, the BIT value-voltage value calibration line includes a BIT value-VA voltage value calibration line and a BIT value-VB voltage value calibration line.

[0014] In at least one embodiment of the present application, in step 2, the voltage values collected by the digital electronic controller include a VA voltage value and a VB voltage value.

[0015] In at least one embodiment of the present application, in step three, the mechanical angle includes the fan adjustable blade angle, the compressor adjustable blade angle and the nozzle angle.

[0016] In at least one embodiment of the present application, in step three, the mechanical angle position-voltage value calibration line includes a mechanical angle position-VA voltage value calibration line and a mechanical angle position-VB voltage value calibration line.

[0017] The invention has at least the following beneficial technical effects:

[0018] The simplified calibration method for aircraft engine angular displacement sensors of the present application achieves that the relevant parameters collected by the angular displacement sensors no longer need to be calibrated after the aircraft engine is put on the test bench or installed on the aircraft, thereby reducing the workload before the aircraft engine test bench, saving time and manpower, and improving efficiency; after replacing the digital electronic controller, the relevant parameters collected by the angular displacement sensors no longer need to be calibrated; and the dependence on the proficiency of the calibration operator is reduced, reducing the probability of errors caused by recalibration. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the role of calibration in the control system;

[0020] Figure 2 1 is a schematic diagram of the output characteristics of an RVDT sensor according to one embodiment of the present application;

[0021] Figure 3 is a schematic diagram of an RVDT processing circuit according to one embodiment of the present application;

[0022] Figure 4 This is a schematic diagram of the calibration conversion relationship of a digital electronic controller according to one embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be understood as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0024] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be understood as limiting the scope of protection of this application.

[0025] The following is combined with Figures 2 to 4 This application is described in further detail.

[0026] This application provides a simplified calibration method for aircraft engine angular displacement sensors, including:

[0027] Step 1: Add a BIT value-voltage value calibration line of the angular displacement sensor to the digital electronic controller, and convert the voltage signal of the angular displacement sensor into a BIT value according to the BIT value-voltage value calibration line of the angular displacement sensor; wherein the BIT value-voltage value calibration line includes a BIT value-VA voltage value calibration line and a BIT value-VB voltage value calibration line;

[0028] Step 2: Obtain the voltage value collected by the digital electronic controller; wherein the voltage value collected by the digital electronic controller includes the VA voltage value and the VB voltage value;

[0029] Step 3: During aircraft engine assembly, the operating range of the angular displacement sensor is adjusted, and mechanical angle pre-calibration is completed to obtain a mechanical angle position-voltage value calibration line; wherein the mechanical angle includes the fan adjustable blade angle, the compressor adjustable blade angle, and the nozzle angle, etc., and the mechanical angle position-voltage value calibration line includes a mechanical angle position-VA voltage value calibration line and a mechanical angle position-VB voltage value calibration line;

[0030] Step 4: Input the mechanical angle position-voltage value calibration line into the digital electronic controller, and the digital electronic controller generates a mechanical angle position-BIT value calibration line based on the angular displacement sensor BIT value-voltage value calibration line and the mechanical angle position-voltage value calibration line.

[0031] The simplified calibration method for aircraft engine angular displacement sensors of the present application is based on the principle of digital electronic controller processing LVDT circuits. It adds a BIT value-voltage value calibration line in the digital electronic controller and combines it with the mechanical position angle-voltage value calibration line required to be measured by the engine to achieve the purpose of simplified calibration of aircraft engine angular displacement sensors.

[0032] The simplified calibration method of aircraft engine angular displacement sensors in the present application, in the principle of digital electronic controller processing LVDT circuit, the RVDT linear displacement sensor converts the mechanical position angle required to be measured by the aircraft engine into a voltage value and transmits it to the digital electronic controller, and the digital electronic controller converts the voltage signal transmitted by the RVDT angular displacement sensor into a BIT value for control. The principle of RVDT circuit processing inside the digital electronic controller is as follows: the output amplitude of the angular displacement sensor changes linearly with the angle, and the sensor has an electrical zero point. When the sensor rotates across the electrical zero point, the phase of the sensor output signal is opposite to or the same as the phase of the excitation signal. The output characteristics of the RVDT sensor are as follows: Figure 2 As shown, within the electrical angle range of 0° to X°, the sensor output voltage changes linearly, and the output signal phase is opposite to the excitation signal phase; within the electrical angle range of 0° to -X°, the sensor output voltage changes linearly, and the output signal phase is the same as the excitation signal phase. The RVDT sensor has a 5-wire structure, 2-wire excitation, and 3-wire feedback; feedback A and B are the sensor angle feedback output coils, and the other feedback is the sensor compensation terminal M. The feedback signal of the compensation terminal M is in phase with the excitation signal and is a square wave with a fixed amplitude. Figure 3 As shown, a fixed-frequency square wave excitation source is generated by the frequency division of the crystal oscillator circuit within the module. This square wave excitation source is superimposed on the feedback signal from the sensor compensation terminal M and then enters the shaping circuit. The output circuit then outputs a peak-to-peak, fixed-frequency square wave excitation signal. The sensor converts the angle change into an AC voltage signal as the feedback signal output. The feedback processing circuit processes the feedback AC voltage signal through synchronous rectification, summation, filtering, amplification, and voltage division to generate the feedback signal acquisition value. The processed feedback signal acquisition value has a one-to-one correspondence with the sensor angle. Due to the influence of component tolerances during the manufacturing process of digital electronic controllers, the conversion relationship of the output voltage of the RVDT angular displacement sensor may vary between different controllers.

[0033] The simplified calibration method of the aircraft engine angular displacement sensor of this application is based on the fact that different digital electronic controllers have different values for the RVDT angular displacement sensor. The simplified calibration process of the angular displacement sensor is mainly based on the error generated by the digital electronic controller's own acquisition and conversion process when it leaves the factory. A calibration conversion relationship diagram is established. Figure 4 ,in:

[0034] The positive direction of the X-axis represents the mechanical angle position that the engine needs to measure;

[0035] The negative direction of the X-axis represents the standard value of the engine (which can be voltage, bit value, dimensionless number, etc.);

[0036] The positive direction of the Y axis represents the bit value collected by the newly replaced digital electronic controller;

[0037] The negative direction of the Y-axis represents the bit value collected by the original digital electronic controller.

[0038] The simplified calibration method for aircraft engine angular displacement sensors of the present application, based on the above analysis, obtains the following simplified calibration process for angular displacement sensors: 1) adding an angular displacement sensor BIT value-voltage value calibration line (i.e., the voltage value and BIT conversion relationship) to each digital electronic controller, converting the received angular displacement sensor voltage signal into a BIT value according to the calibration line, thereby eliminating errors caused by hardware differences in the digital electronic controller; 2) displaying the voltage value collected inside the digital electronic controller on a computer; 3) adjusting the operating range of the angular displacement sensor during aircraft engine assembly, and completing the required mechanical angle pre-calibration. Pre-calibration requires a fixed digital electronic controller during the assembly stage to record the mechanical angle position-voltage value correspondence and form a mechanical angle position-voltage value calibration line; 4) inputting the mechanical angle position-voltage value calibration line into the digital electronic controller, and combining the angular displacement sensor voltage value-BIT value calibration line inside the controller to form a new mechanical angle position-BIT value calibration line.

[0039] The simplified calibration method for aircraft engine angular displacement sensors disclosed herein, upon implementation, can replace the existing calibration method for angular displacement sensors after the engine is installed on the stage, without compromising accuracy. This method eliminates the need for angular displacement sensor calibration after the engine is installed on the stage, on the aircraft, or after the digital electronic controller is replaced. This method not only reduces the workload for aircraft engine installation, saving time and manpower and improving efficiency, but also reduces the probability of errors occurring during post-engine calibration. It can be applied to the simplified calibration of aircraft engine angular displacement sensors and has promising market application prospects.

[0040] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A simplified calibration method for aircraft engine angular displacement sensors, characterized in that: include: Step 1: Add a BIT value-voltage value calibration line of the angular displacement sensor to the digital electronic controller, and convert the voltage signal of the angular displacement sensor into a BIT value according to the BIT value-voltage value calibration line of the angular displacement sensor; Step 2: obtaining the voltage value collected by the digital electronic controller; Step 3: When assembling the aircraft engine, the operating range of the angular displacement sensor is adjusted, and mechanical angle pre-calibration is completed to obtain a mechanical angle position-voltage value calibration line; Step 4: Input the mechanical angle position-voltage value calibration line into the digital electronic controller, and the digital electronic controller generates a mechanical angle position-BIT value calibration line based on the angular displacement sensor BIT value-voltage value calibration line and the mechanical angle position-voltage value calibration line.

2. The simplified calibration method for aircraft engine angular displacement sensors according to claim 1, characterized in that: In step 1, the BIT value-voltage value calibration line includes a BIT value-VA voltage value calibration line and a BIT value-VB voltage value calibration line.

3. The simplified calibration method for aircraft engine angular displacement sensors according to claim 2, characterized in that: In step 2, the voltage values collected by the digital electronic controller include VA voltage value and VB voltage value.

4. The simplified calibration method for aircraft engine angular displacement sensors according to claim 3, characterized in that: In step three, the mechanical angle includes the fan adjustable blade angle, the compressor adjustable blade angle and the nozzle angle.

5. The simplified calibration method for aircraft engine angular displacement sensors according to claim 4, characterized in that: In step three, the mechanical angle position-voltage value calibration line includes a mechanical angle position-VA voltage value calibration line and a mechanical angle position-VB voltage value calibration line.

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