Method and system for controlling and measuring ground test of aircraft control system

Abstract

The invention discloses a control and measurement method and system for a ground test of an aircraft control system, and the method comprises the steps: a control system transmits a control instruction to control a loading device to carry out the continuous load application of a test piece of the control system within a fixed time, reads the feedback of a sensor in real time according to a certain frequency, and carries out the correction of the control instruction; meanwhile, the data acquisition device synchronously measures the operating system test piece under the test load according to the same frequency of the control system to obtain measurement data, and the measurement data is fed back to the control system through the measurement and control adapter; and the control system performs time synchronization on the load data and the measurement data, and combines and outputs test data. The method has the advantages that the assessment is real; data is accurate: data acquisition equipment is directly connected to a control system, so that delay between a measurement system and a control system is eliminated, a real-time corresponding relation between load and structural response is established, and test data is more accurate; the data volume is large.

Description

Technical Field

[0001] The present application belongs to the field of ground verification test of aircraft control system, and in particular, relates to a control and measurement method and system for ground test of aircraft control system. Background Art

[0002] Completing the ground verification test of the control system is a prerequisite for the aircraft to conduct flight tests. The aircraft structure ground verification test system generally includes a control system, a loading device, and a measurement system. The control system serves as the test brain, controlling the test load and reading the load feedback. The loading device applies the load to the test piece under the command of the control system, and the measurement system reads the strain and deformation in real time through the strain gauges or measurement points on the test piece.

[0003] The ground verification test of the control system simulates the pilot's control load by controlling the hydraulic cylinder or electric cylinder and other loading devices through the test control system, and applies load to the joystick, steering wheel or pedals.

[0004] The existing ground verification test method for the control system is: divide the test load into 10-20 levels, increase the load step by step, and after reaching each level of load, the control system controls the loading device to keep the load unchanged, and then sends a trigger signal to the measurement system. The measurement system records the measurement data of the current load level to obtain the test results.

[0005] The existing ground verification test of the control system adopts the method of graded loading and step-by-step measurement, with fewer measurement levels, such as Figure 1 This method can meet the requirements of structural strength assessment tests such as static tests, but for dynamic assessment tests such as control system motion inspection tests, due to the transmission delay and bandwidth limitation between the control system and the measurement system, it is difficult to obtain a large amount of real-time load / control stick displacement, load / fly-by-wire system voltage and other data of the operating system, and the data level and effectiveness need to be further improved. Summary of the invention

[0006] The purpose of this application is to provide a control and measurement method and system for ground testing of an aircraft control system, so as to solve the problem that it is difficult to ensure data level and effectiveness in existing ground verification tests of control systems.

[0007] The technical solution of the present application is: a control and measurement method for ground test of aircraft control system, comprising:

[0008] The control system issues control instructions to control the loading device to continuously apply load to the test piece of the control system within a fixed time, and reads sensor feedback in real time at a certain frequency to correct the control instructions;

[0009] At the same time, the data acquisition equipment measures the operating system test piece under the test load synchronously at the same frequency as the control system, obtains the measurement data, and feeds it back to the control system through the measurement and control conversion joint; the control system synchronizes the load data and the measurement data in time, and merges and outputs the test data.

[0010] Preferably, the method for obtaining the measurement data is as follows: after the data acquisition device is connected to the control system, the control system no longer triggers a measurement signal to the measurement system, thereby eliminating the influence of the transmission bandwidth between the control system and the measurement system. The control system automatically and in real time reads the measurement value of the data acquisition device at a frequency of 10 to 200 times per second, establishes a corresponding relationship between the feedback value of the measurement sensor and the measurement value of the data acquisition device, and draws a load / structure response curve and a load / electric signal voltage curve.

[0011] Preferably, the control system is provided with a data receiving module, a data processing module and an instruction adjustment module. The data receiving module can receive the load data fed back by the sensor in real time at a set frequency. After receiving the load data, the data processing module calculates the deviation between the load data and the control instruction, and adjusts the control instruction according to the deviation to obtain a new control instruction, which is sent to the instruction adjustment module; the instruction adjustment module sends the received new control instruction to the loading device.

[0012] Preferably, a frequency loading setting module is provided in the data processing module, and the frequency loading setting module can set the loading frequency of the control instructions and the collection frequency of the load data between 10 and 200 times per second as required.

[0013] Preferably, after acquiring each load data, the data processing module records the time of the current load data, and then calculates whether the time of the acquired measurement data and the time of the load data exceed the time interval threshold; if not, it determines that the load data and the measurement data match each other until all load data and measurement data are matched.

[0014] As a specific implementation, a control and measurement system for ground testing of an aircraft control system includes a loading device, a data acquisition device, a control system, and a measurement and control conversion joint;

[0015] The loading device includes a power part and a sensor, wherein the power part is a hydraulic cylinder or an electric push rod, and the sensor includes a force sensor and a torque sensor. The hydraulic cylinder or the electric push rod can convert hydraulic pressure / electricity into a test load to load the test piece of the control system, and the force sensor and the torque sensor are used to measure the load feedback during the test process;

[0016] The measurement and control conversion joint is used to convert the electrical signal of the data acquisition device into an electrical signal type that can be read by the control system; the control system is used to control the loading device to apply the load.

[0017] The control and measurement method and system of the aircraft control system ground test of the present application have the following advantages:

[0018] Realistic assessment: Simulate the pilot's operation time and load process for continuous loading, making the assessment more realistic;

[0019] Accurate data: Connecting the data acquisition equipment directly to the control system eliminates the delay between the measurement and control systems, establishes a real-time correspondence between load and structural response, and makes the test data more accurate;

[0020] Large amount of data: After eliminating the influence of transmission bandwidth factors, the hierarchical measurement is changed to continuous measurement, and the amount of test data is increased by more than 30 times, providing richer data support for test assessment and research. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0022] Figure 1 It is a schematic diagram of the ground verification test method in the background technology;

[0023] Figure 2 This is a schematic diagram of the loading and measurement method for the ground test of the control system of this application.

[0024] 1. Control system; 2. Loading device; 3. Manipulation system test piece; 4. Data acquisition equipment; 5. Measurement and control conversion joint. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] A control and measurement system for ground testing of an aircraft control system comprises a loading device 2, a data acquisition device 4, a control system 1 and a measurement and control conversion joint 5.

[0027] The loading device 2 includes a power component and a sensor. The power component is a hydraulic cylinder or an electric push rod. The sensor includes a force sensor and a torque sensor. The hydraulic cylinder or the electric push rod is responsible for converting hydraulic pressure / electricity into a test load and loading it onto the control system test piece 3. The force sensor and the torque sensor are used to measure the load feedback during the test.

[0028] The measurement and control conversion connector 5 is used to convert the electrical signal of the data acquisition device 4 into an electrical signal type that can be read by the control system 1, and directly connect the strain / displacement data acquisition device 4 to the control system 1, eliminating the transmission between the measurement and control systems, so that the control system 1 can directly read the data of the acquisition device in real time.

[0029] The control system 1 is used to control the loading device 2 to apply load.

[0030] As a specific implementation method, it also includes a control and measurement method for a ground test of an aircraft control system, including: in order to more realistically simulate the control process of the aircraft pilot, the control system 1 issues a control instruction to control the loading device 2 to continuously apply a load to the control system test piece 3 within a fixed time, and reads the sensor feedback in real time at a certain frequency, corrects the control instruction, and maintains the accuracy of dynamic load loading; no graded load maintenance is performed during loading.

[0031] At the same time, the data acquisition device 4 measures the operating system test piece under the test load synchronously at the same frequency as the control system 1, obtains the measurement data, and feeds it back to the control system 1 through the measurement and control conversion joint 5; the control system 1 synchronizes the load data and the measurement data in time, and merges and outputs the test data.

[0032] Preferably, the method for obtaining the measurement data is as follows: after the data acquisition device 4 is connected to the control system 1, the control system 1 no longer triggers a measurement signal to the measurement system, thereby eliminating the influence of the transmission bandwidth between the control system 1 and the measurement system. The control system 1 automatically and in real time reads the measurement value of the data acquisition device 4 at a frequency of 10 to 200 times per second, and establishes a corresponding relationship between the feedback value of the measurement sensor and the measurement value of the data acquisition device 4, and draws a load / structure response curve and a load / electric signal voltage curve, etc.

[0033] Preferably, the control system 1 is provided with a data receiving module, a data processing module and an instruction adjustment module. The data receiving module can receive the load data fed back by the sensor in real time at a set frequency. After receiving the load data, the data processing module calculates the deviation between the load data and the control instruction, and adjusts the control instruction according to the deviation to obtain a new control instruction, which is sent to the instruction adjustment module; the instruction adjustment module sends the received new control instruction to the loading device 2, thereby realizing continuous and accurate loading of the manipulation system test piece 3.

[0034] A frequency loading setting module is provided in the data processing module, and the frequency loading setting module can set the loading frequency of the control instructions and the collection frequency of the load data between 10 and 200 times per second as required.

[0035] Since the measured data and the load data have reached the basic synchronization, the time interval threshold is set in the data processing module. After each load data is obtained, the data processing module records the time of the current load data, and then calculates whether the time of the obtained measured data and the time of the load data exceed the time interval threshold. If not, it is determined that the load data and the measured data match each other until all load data and measured data are matched. This achieves accurate data collection under continuous loading.

[0036] Through the above design, this application has the following advantages:

[0037] Realistic assessment: Simulate the pilot's operation time and load process for continuous loading, making the assessment more realistic;

[0038] Accurate data: Connecting the data acquisition equipment directly to the control system eliminates the delay between the measurement and control systems, establishes a real-time correspondence between load and structural response, and makes the test data more accurate;

[0039] Large amount of data: After eliminating the influence of transmission bandwidth factors, the hierarchical measurement is changed to continuous measurement, and the amount of test data is increased by more than 30 times, providing richer data support for test assessment and research.

[0040] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0041] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A control and measurement method for ground test of aircraft control system, characterized in that: include: The control system (1) issues a control command to control the loading device (2) to continuously apply a load to the control system test piece (3) within a fixed time, and reads sensor feedback in real time at a certain frequency to correct the control command; At the same time, the data acquisition device (4) measures the operating system test piece under the test load synchronously at the same frequency as the control system (1), obtains measurement data, and feeds it back to the control system (1) through the measurement and control conversion joint (5); the control system (1) synchronizes the load data and the measurement data in time, and merges and outputs the test data.

2. The control and measurement method for ground test of aircraft control system according to claim 1, characterized in that: The method for obtaining the measurement data is as follows: after the data acquisition device (4) is connected to the control system (1), the control system (1) no longer triggers a measurement signal to the measurement system, thereby eliminating the influence of the transmission bandwidth between the control system (1) and the measurement system. The control system (1) automatically and in real time reads the measurement value of the data acquisition device (4) at a frequency of 10 to 200 times per second, establishes a corresponding relationship between the feedback value of the measurement sensor and the measurement value of the data acquisition device (4), and draws a load / structure response curve and a load / electric signal voltage curve.

3. The control and measurement method for ground test of aircraft control system according to claim 1, characterized in that: The control system (1) is provided with a data receiving module, a data processing module and an instruction adjustment module. The data receiving module can receive load data fed back by the sensor in real time at a set frequency. After receiving the load data, the data processing module calculates the deviation between the load data and the control instruction, and adjusts the control instruction according to the deviation to obtain a new control instruction, which is sent to the instruction adjustment module. The instruction adjustment module sends the received new control instruction to the loading device (2).

4. The control and measurement method for ground test of aircraft control system according to claim 3, characterized in that: The data processing module is provided with a frequency loading setting module, which can set the loading frequency of the control instructions and the collection frequency of the load data between 10 and 200 times per second as required.

5. The control and measurement method for ground test of aircraft control system according to claim 3, characterized in that: After acquiring each load data, the data processing module records the time of the current load data, and then calculates whether the time of the acquired measurement data and the time of the load data exceed the time interval threshold. If not, it determines that the load data and the measurement data match each other until all load data and measurement data are matched.

6. A control and measurement system for ground testing of an aircraft control system, using the control and measurement method according to any one of claims 1 to 5, characterized in that: It comprises a loading device (2), a data acquisition device (4), a control system (1) and a measurement and control conversion joint (5); The loading device (2) comprises a power part and a sensor, wherein the power part is a hydraulic cylinder or an electric push rod, and the sensor comprises a force sensor and a torque sensor, wherein the hydraulic cylinder or the electric push rod can convert hydraulic pressure / electricity into a test load and load it to the control system test piece (3), and the force sensor and the torque sensor are used to measure the load feedback during the test process; The measurement and control conversion joint (5) is used to convert the electrical signal of the data acquisition device (4) into an electrical signal type that can be read by the control system (1); the control system (1) is used to control the loading device (2) to apply the load.

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