Detection method of aero-engine fuel regulator

Abstract

The invention discloses a detection method for an aero-engine fuel regulator, and the method comprises the steps: carrying out the automatic two-end inspection and automatic calibration of the fuel regulator after constructing a testing device composed of an equivalent controller, a fuel regulator test bed and an upper computer, and measuring the maximum position and the minimum position of a fuel needle and a guide vane; carrying out hysteresis test on the fuel regulator, and measuring the relationship between the flow and the oil needle position in the oil needle lift and return process of the fuel regulator; finally, broken line simulation detection is conducted on the fuel regulator, detection items are dynamically generated according to the configuration file, convenience of all the detection items is completed through an iterator mode, and results are returned. The method can cover the acceptance inspection process of the fuel regulator, and an operator is guided to complete acceptance inspection; result analysis can be completed through automatic detection, the detection efficiency is improved, and the operation threshold of operators is reduced.

Description

Technical Field

[0001] The invention relates to the field of aircraft engine fuel regulator detection, and in particular to a detection method for an aircraft engine fuel regulator. Background Art

[0002] The fuel regulator is one of the core components of the aircraft engine control system and even the entire aircraft. It is produced and accepted by the accessory factory. The acceptance process is complicated, and the operators have a low level of professionalism, which easily leads to problems of low efficiency and high training difficulty.

[0003] At present, a large number of acceptance work in China relies on manual operation and measurement by workers. First of all, the inspection must overcome the position difference of the servo mechanism of the pump adjustment. At present, workers need to manually measure the stroke of the servo and then manually calibrate it. Secondly, the inspection must measure the basic oil supply performance of the pump adjustment, mainly measuring the oil supply of the pump adjustment in the steady state stage and the dynamic change process without deviation. Different types of pump adjustment designs have different working parameters, so the measurement points of different models are different, and manual measurement is mostly used. Finally, the inspection may require measuring the electromagnetic valve disconnection protection mechanism of the pump adjustment. The measurement content is changeable and different for each model, making it difficult to achieve automation.

[0004] In view of the above problems, this application proposes a solution. Summary of the invention

[0005] Purpose of the invention: The purpose of the present invention is to provide a method for detecting an aircraft engine fuel regulator, which can realize automated acceptance of the fuel regulator.

[0006] Technical solution: The detection method of an aircraft engine fuel regulator described in the present invention specifically includes the following steps:

[0007] S1: Construct a test device using an equivalent controller, a fuel regulator test bench and a host computer;

[0008] S2: Automatically check both ends of the fuel regulator and automatically calibrate it, measuring the maximum and minimum positions of the fuel needle and guide vane;

[0009] S3: Perform hysteresis test on the fuel regulator to measure the relationship between flow rate and fuel needle position during the lift and return of the fuel needle;

[0010] S4: Perform disconnection simulation detection on the fuel regulator, dynamically generate detection items according to the configuration file, complete the convenience of each detection item through the iterator mode and return the result.

[0011] Preferably, the equivalent controller simulates a real aircraft engine controller to provide a control signal to the servo mechanism of the fuel regulator.

[0012] Preferably, the fuel regulator test bench simulates a real aircraft engine and provides rotation speed and fuel to the fuel regulator.

[0013] Preferably, the host computer is responsible for communicating with the equivalent controller and the fuel regulator test bench, understanding the parameter status of the equivalent controller and the fuel regulator test bench and sending control instructions to them, and integrating automated test logic.

[0014] Preferably, measuring the maximum and minimum positions of the oil needle and the guide vane in S2 specifically includes the following steps:

[0015] S2.1: Set the oil needle and guide vane to open loop mode, set the minimum output current, wait for a few seconds, and record the minimum position of the oil needle LgtMin and the minimum position of the guide vane AfaMin;

[0016] S2.2: Set the maximum output current, wait for a few seconds, and then record the maximum position of the oil needle LgtMax and the maximum position of the guide vane AfaMax;

[0017] S2.3: Set the communication mode to guide vane parameter modification, set X 0 =0,X 1 =4096,Y 0 =AfaMin,Y 1 =AfaMax, send parameters to the equivalent controller;

[0018] S2.4: Set the communication mode to oil needle parameter modification, set X 0 =0,X 1 =4096, Sends parameters to the equivalent controller.

[0019] Preferably, the hysteresis test includes a static hysteresis test and a dynamic hysteresis test. The static hysteresis test performs flow measurement after the oil needle position is stabilized, and the dynamic hysteresis test measures the flow while the oil needle position is unstable and changes continuously.

[0020] Preferably, the hysteresis test specifically comprises the following steps:

[0021] S3.1: The host computer reads the oil needle position monitoring point LgtArr, the speed detection point NgArr, the start collection time startGatherTime and the end collection time stopGatherTime from the configuration file;

[0022] S3.2: The host computer sets the speed to NgArr[0];

[0023] S3.3: The host computer sets the oil needle to LgtArr[0];

[0024] S3.4: The host computer starts timing, starts collecting flow when the time is greater than the collection time startGatherTime, stops collecting and calculates the flow average when the time is greater than the end collection time stopGatherTime, and the result is included in the lift value;

[0025] S3.5: If the oil needle does not reach the maximum value of LgtArr, the host computer sets the oil needle to the next point of LgtArr and jumps to S3.4;

[0026] S3.6: The host computer starts timing again. When the time is greater than the collection time startGatherTime, it starts to collect flow. When the time is greater than the end collection time stopGatherTime, it stops collecting and calculates the average flow rate. The result is included in the return value. The difference between the lift value and the return value at this speed is calculated.

[0027] S3.7: If the oil needle does not reach the minimum value of LgtArr, set the oil needle to the previous point of LgtArr and jump to S3.6;

[0028] S3.8: If the speed does not reach the maximum value of NgArr, set the speed to the next point of NgArr and jump to S3.3.

[0029] As a preferred method, during the lift and return of the fuel needle of the fuel regulator, after recording the relationship between the pump speed and the pump flow, a table record is formed, specifically:

[0030] The controller communication data is unpacked to obtain a data frame set, the speed and flow data are extracted from the data frame set, the speed and flow data are rounded to one decimal place, the speed and flow data are combined, filled into a speed flow table, and the speed flow table is stored in a database.

[0031] Preferably, the configuration file in S4 is configured with detection items, and the configuration table of the detection items is configured with the name, format and purpose of the detection items.

[0032] Preferably, the S4 disconnection line simulation detection specifically includes the following steps:

[0033] S4.1: Trigger the first test;

[0034] S4.2: According to the current detection item, the host computer sends a disconnection simulation instruction to the equivalent controller, and collects the sampling value after 1 second;

[0035] S4.3: Check whether the recovery value meets the standard;

[0036] S4.4: The current detection item searches whether it has subsequent detection items. If so, the subsequent detection items are triggered and the process returns to S4.2. If not, the detection ends.

[0037] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages:

[0038] The present invention can cover the fuel regulator acceptance process and guide operators to complete the acceptance; provide a partial automatic correction function and enhance fault tolerance; can automatically detect and complete result analysis, improve detection efficiency, and reduce the operating threshold of operators. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 The present invention is a flow chart for recording the relationship between the pump regulating speed and the pump regulating flow rate during the lift and return process of the oil needle of the fuel regulator. DETAILED DESCRIPTION

[0040] The technical solution of the present invention is further described below in conjunction with the accompanying drawings.

[0041] The specific steps of the detection method of the aircraft engine fuel regulator in the present invention are as follows:

[0042] S1: Construct a test device using an equivalent controller, a fuel regulator test bench and a host computer;

[0043] The equivalent controller simulates the real aircraft engine controller and provides control signals to the servo mechanism of the fuel regulator;

[0044] The fuel regulator test bench simulates a real aircraft engine and provides speed and fuel to the fuel regulator;

[0045] The host computer is responsible for communicating with the equivalent controller and fuel regulator test bench, understanding the parameter status of the equivalent controller and fuel regulator test bench and sending control instructions to them, integrating automated test logic.

[0046] S2: Perform automatic two-end inspection and automatic calibration on the fuel regulator, measure the maximum and minimum positions of the fuel needle and guide vane, including the following steps:

[0047] S2.1: Set the oil needle and guide vane to open loop mode, set the minimum output current, wait for a few seconds, and record the minimum position of the oil needle LgtMin and the minimum position of the guide vane AfaMin;

[0048] S2.2: Set the maximum output current, wait for a few seconds, and then record the maximum position of the oil needle LgtMax and the maximum position of the guide vane AfaMax;

[0049] S2.3: Set the communication mode to guide vane parameter modification, set X 0 =0,X 1 =4096,Y 0 =AfaMin,Y 1=AfaMax, send parameters to the equivalent controller;

[0050] S2.4: Set the communication mode to oil needle parameter modification, set X 0 =0,X 1 =4096, Sends parameters to the equivalent controller.

[0051] S3: Perform hysteresis test on the fuel regulator to measure the relationship between flow rate and fuel needle position during the lift and return of the fuel needle;

[0052] The hysteresis test includes static hysteresis test and dynamic hysteresis test. Static hysteresis test measures flow rate after the oil needle position is stabilized, while dynamic hysteresis test measures flow rate while the oil needle position is unstable and changes continuously.

[0053] The hysteresis test specifically includes the following steps:

[0054] S3.1: The host computer reads the oil needle position monitoring point LgtArr, the speed detection point NgArr, the start collection time startGatherTime and the end collection time stopGatherTime from the configuration file;

[0055] S3.2: The host computer sets the speed to NgArr[0];

[0056] S3.3: The host computer sets the oil needle to LgtArr[0];

[0057] S3.4: The host computer starts timing, starts collecting flow when the time is greater than the collection time startGatherTime, stops collecting and calculates the flow average when the time is greater than the end collection time stopGatherTime, and the result is included in the lift value;

[0058] S3.5: If the oil needle does not reach the maximum value of LgtArr, the host computer sets the oil needle to the next point of LgtArr and jumps to S3.4;

[0059] S3.6: The host computer starts timing again. When the time is greater than the collection time startGatherTime, it starts to collect flow. When the time is greater than the end collection time stopGatherTime, it stops collecting and calculates the average flow rate. The result is included in the return value. The difference between the lift value and the return value at this speed is calculated.

[0060] S3.7: If the oil needle does not reach the minimum value of LgtArr, set the oil needle to the previous point of LgtArr and jump to S3.6;

[0061] S3.8: If the speed does not reach the maximum value of NgArr, set the speed to the next point of NgArr and jump to S3.3.

[0062] like Figure 1 As shown in the figure, during the lift and return process of the fuel regulator needle, the operator records the relationship between the pump speed and the pump flow rate and forms a table record, specifically:

[0063] The controller communication data is unpacked to obtain a data frame set, the speed and flow data are extracted from the data frame set, the speed and flow data are rounded to one decimal place, the speed and flow data are combined, filled into a speed flow table, and the speed flow table is stored in a database.

[0064] S4: Perform disconnection simulation detection on the fuel regulator, dynamically generate detection items according to the configuration file, complete the convenience of each detection item through the iterator mode and return the result.

[0065] The configuration file includes detection items, and the configuration table of the detection items includes the name, format and purpose of the detection items. The following table shows the configuration table of disconnection simulation in this embodiment:

[0066]

[0067] The disconnection simulation detection specifically includes the following steps:

[0068] S4.1: Trigger the first test;

[0069] S4.2: According to the current detection item, the host computer sends a disconnection simulation instruction to the equivalent controller, and collects the sampling value after 1 second;

[0070] S4.3: Check whether the recovery value meets the standard;

[0071] S4.4: The current detection item searches whether it has subsequent detection items. If so, the subsequent detection items are triggered and the process returns to S4.2. If not, the detection ends.

[0072] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A method for detecting an aircraft engine fuel regulator, characterized in that: The specific steps include: S1: Construct a test device using an equivalent controller, a fuel regulator test bench and a host computer; S2: Automatically check both ends of the fuel regulator and automatically calibrate it, measuring the maximum and minimum positions of the fuel needle and guide vane; S3: Perform hysteresis test on the fuel regulator to measure the relationship between flow rate and fuel needle position during the lift and return of the fuel needle; S4: Perform disconnection simulation detection on the fuel regulator, dynamically generate detection items according to the configuration file, complete the convenience of each detection item through the iterator mode and return the result.

2. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The equivalent controller simulates a real aircraft engine controller and provides a control signal to the servo mechanism of the fuel regulator.

3. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The fuel regulator test bench simulates a real aircraft engine and provides rotation speed and fuel to the fuel regulator.

4. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The host computer is responsible for communicating with the equivalent controller and the fuel regulator test bench, understanding the parameter status of the equivalent controller and the fuel regulator test bench and sending control instructions to them, and integrating automated test logic.

5. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The measuring of the maximum and minimum positions of the oil needle and the guide vane in S2 specifically includes the following steps: S2.1: Set the oil needle and guide vane to open loop mode, set the minimum output current, wait for a few seconds, and record the minimum position of the oil needle LgtMin and the minimum position of the guide vane AfaMin; S2.2: Set the maximum output current, wait for a few seconds, and then record the maximum position of the oil needle LgtMax and the maximum position of the guide vane AfaMax; S2.3: Set the communication mode to guide vane parameter modification, set X0 = 0, X1 = 4096, Y0 = AfaMin, Y1 = AfaMax, and send the parameters to the equivalent controller; S2.4: Set the communication mode to oil needle parameter modification, set X0=0, X1=4096, Sends parameters to the equivalent controller.

6. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The hysteresis test includes a static hysteresis test and a dynamic hysteresis test. The static hysteresis test measures the flow rate after the oil needle position is stabilized, and the dynamic hysteresis test measures the flow rate while the oil needle position is unstable and changes continuously.

7. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The hysteresis test specifically comprises the following steps: S3.1: The host computer reads the oil needle position monitoring point LgtArr, the speed detection point NgArr, the start collection time startGatherTime and the end collection time stopGatherTime from the configuration file; S3.2: The host computer sets the speed to NgArr[0]; S3.3: The host computer sets the oil needle to LgtArr[0]; S3.4: The host computer starts timing, starts collecting flow when the time is greater than the collection time startGatherTime, stops collecting and calculates the flow average when the time is greater than the end collection time stopGatherTime, and the result is included in the lift value; S3.5: If the oil needle does not reach the maximum value of LgtArr, the host computer sets the oil needle to the next point of LgtArr and jumps to S3.4; S3.6: The host computer starts timing again. When the time is greater than the collection time startGatherTime, it starts to collect flow. When the time is greater than the end collection time stopGatherTime, it stops collecting and calculates the average flow rate. The result is included in the return value. The difference between the lift value and the return value at this speed is calculated. S3.7: If the oil needle does not reach the minimum value of LgtArr, set the oil needle to the previous point of LgtArr and jump to S3.6; S3.8: If the speed does not reach the maximum value of NgArr, set the speed to the next point of NgArr and jump to S3.

3.

8. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: During the lift and return of the fuel regulator needle, record the relationship between the pump speed and pump flow rate and form a table record, specifically: The controller communication data is unpacked to obtain a data frame set, the speed and flow data are extracted from the data frame set, the speed and flow data are rounded to one decimal place, the speed and flow data are combined, filled into a speed flow table, and the speed flow table is stored in a database.

9. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The configuration file in S4 is configured with detection items, and the configuration table of the detection items is configured with the name, format and purpose of the detection items.

10. The method for detecting an aircraft engine fuel regulator according to claim 1, characterized in that: The S4 interruption line simulation detection specifically includes the following steps: S4.1: Trigger the first test; S4.2: According to the current detection item, the host computer sends a disconnection simulation instruction to the equivalent controller, and collects the sampling value after 1 second; S4.3: Check whether the recovery value meets the standard; S4.4: The current detection item searches whether it has subsequent detection items. If so, the subsequent detection items are triggered and the process returns to S4.

2. If not, the detection ends.

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