A flight control system test data processing and analysis method

Abstract

The present invention relates to a flight control system test data processing and analysis method, which obtains flight control system test data, including at least the time history data of the control force, control displacement, and rudder deflection parameters in the control process; forms an array and assigns it to (X, Y), determines the number of rows and columns of the image matrix T according to the accuracy requirement and the size range of the test data; and interpolates and fills the rounded data along the time series according to the accuracy distance; maps the interpolated and filled data to the image matrix T, and calculates the sum Z of the values ​​of each row element of the matrix T; reads the corresponding Z value according to the definition of the rod force idle stroke, the transmission idle stroke, the friction force, and the hysteresis loop parameters of the system, and obtains the corresponding value. The method can greatly improve the data reading efficiency, overcome the disadvantage that the process data and the return data cannot be completely aligned, and improve the accuracy of data reading.

Description

Technical Field

[0001] The invention belongs to the field of aviation engineering experiments, and in particular relates to a flight control system test data processing and analysis method. Background Art

[0002] During the development and design of the flight control system, it is necessary to measure the flight control system's rod force idle travel, transmission idle travel, friction, and system hysteresis loop parameters. f ) refers to the range of travel of the joystick handle or pedal when the control force is zero, see Figure 1 . Transmission idle travel (Δx δ ) refers to the range of travel of the joystick handle or pedal when the control surface deflection is zero, see Figure 2 The friction force (f) is half of the maximum value of the positive and negative stroke rod force difference, see Figure 3 . System hysteresis loop Δx max It refers to the maximum value of the difference between the forward and return rudder surface deflection when the same command signal is used. Figure 4 .

[0003] In order to obtain the above parameters, there are two methods generally used by testers:

[0004] One is the "zero-position force method", which is to fix the output end (or rudder) of the control mechanism at zero position, apply loads in positive and negative directions to the hand-grip point of the control mechanism (the load is slightly larger than the friction force of the control mechanism), and measure the range of motion of the control mechanism to obtain the empty stroke of the rod force and the empty stroke of the transmission.

[0005] Another method is the "continuous control method", that is, within the full range of travel, control the steering wheel (steering stick or pedal) or use simulation instructions to control the movement of the rudder surface for one cycle, collect the control force, control displacement, command signal and rudder surface deflection data through the acquisition equipment, and then draw the rod force-rod displacement relationship curve, the control displacement-rudder surface deflection relationship curve, and the command signal-rudder surface deflection relationship curve. Pick up the rod force idle travel, transmission idle travel, friction force and system hysteresis loop from the curve graph.

[0006] Regardless of the test method, during the test, the data collected by the test personnel through the measuring equipment is a set of discrete data points that change over time. When reading data such as rod force idle travel, transmission idle travel, friction force and hysteresis loop, the existing method is to draw a curve graph and manually read these parameter values ​​from the curve graph. When reading these parameter values, the data is discrete data points, and the process data and return data cannot be completely aligned in the vertical direction or horizontal direction of the coordinate axis, and there is a certain error in manual reading. In addition, due to the huge amount of test data, manual data reading is time-consuming and labor-intensive, and the efficiency is extremely low. Summary of the invention

[0007] The purpose of the present invention is to provide a method for automatically and quickly reading data values ​​such as rod force idle travel, transmission idle travel, friction force and hysteresis loop. The method can greatly improve the data reading efficiency, overcome the disadvantage that the process data and the return data cannot be completely aligned, and improve the accuracy of data reading.

[0008] Technical solution: A flight control system test data processing and analysis method, firstly, obtains the flight control system test data; the acquisition process is: operate the aircraft control stick, control wheel or pedal for one cycle, and collects the time history data of control force, control displacement, control surface deflection (or control mechanism output displacement) and other parameters during the control process through measuring equipment;

[0009] Assign the array consisting of the control displacement and the control force or the array consisting of the control displacement and the control surface deflection to (X, Y), and perform smoothing on the amplitude-valued test data (X, Y); calculate the maximum and minimum values ​​of X and Y;

[0010] Determine the number of rows and columns of the image matrix T according to the accuracy requirements and the size range of the test data;

[0011] The smoothed test data is rounded according to the accuracy requirements, and the rounded data is interpolated and filled along the time series according to the accuracy distance;

[0012] According to the size of the value, the interpolated data is mapped to the image matrix T, and the corresponding elements of T are assigned 1; other unmapped elements in the matrix T are assigned 0.

[0013] By searching the matrix T, assigning the value of 1 to the elements between the elements with the value of 1 in each row, and calculating the sum Z of the values ​​of the elements in each row of the matrix T;

[0014] According to the definitions of rod force idle travel, transmission idle travel, friction force, hysteresis loop and other parameters, the corresponding Z value can be read to obtain the corresponding numerical value.

[0015] The data processing flow includes the following steps:

[0016] Step 1: Obtain the test measurement data (X, Y), smooth the test data (X, Y) to obtain (X t ,Y t ).

[0017] Step 2: Calculate X min , X max , Y min , Y max .

[0018] Step 3: According to the measurement and calculation accuracy requirements, determine the row accuracy α and column accuracy β of the X and Y image matrices.

[0019] Step 4: Calculate the number of rows and columns of the image matrix T of X and Y, and define the initial value of T as a two-dimensional zero matrix.

[0020] Number of rows:

[0021] Number of columns:

[0022] Step 5: Determine (X t ,Y t ) corresponds to the element T in T i,j , and assign the element a value of 1.

[0023]

[0024] Step 6: Fill (X) along time by interpolation calculation t , Y t ) and (X t+1 , Y t+1 ), the number of interpolation points n is:

[0025] (n must be no less than 1, otherwise n = 0)

[0026] Interpolation point (X t ′ ,Y t ′ ):

[0027] X′ t =X t +kα, k≤n

[0028]

[0029] Step 7: Determine the interpolation point (X t ′ ,Y t ′ ) in T i,j The corresponding element T i+k,j+l , and assign the element a value of 1. Where l:

[0030]

[0031] Step 8: Find the matrix T i,j The elements with value 1 in each row and the 0-valued elements between these elements are assigned value 1.

[0032] Step 9: Calculate the matrix T i,j The sum of the values ​​of each row Z i. and the sum of the elements in each column Z ·j :

[0033]

[0034] Step 10: Calculate the rod force idle travel, transmission idle travel, friction or hysteresis loop.

[0035] Rod force empty travel:

[0036] Δx f =α·Z ·j (when , Y is the operating force)

[0037] Transmission idle travel:

[0038] Δx δ =α·Z ·j (when When Y is the deflection of the rudder surface)

[0039] Hysteresis loop:

[0040] Δx max =β·max{Z i·}

[0041] Friction:

[0042]

[0043] Beneficial technical effects: The present invention provides a method for automatically and quickly reading data values ​​such as rod force idle stroke, transmission idle stroke, friction force and hysteresis loop. When processing data such as rod force idle stroke, transmission idle stroke, friction force and hysteresis loop, the method overcomes the disadvantage of low manual reading efficiency and eliminates errors caused by subjective factors when manually processing data, thereby improving work efficiency and the accuracy of test results. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 Define the schematic diagram for the rod force empty travel;

[0045] Figure 2 Define a schematic diagram for the transmission idle stroke;

[0046] Figure 3 Define a schematic diagram for friction;

[0047] Figure 4 Define a schematic diagram for the hysteresis loop;

[0048] Figure 5 is a flow chart;

[0049] Figure 6 is the matrix T after the test data is mapped;

[0050] Figure 7 is the interpolated matrix T;

[0051] Figure 8 is the filled matrix T. DETAILED DESCRIPTION

[0052] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. In order to facilitate the elaboration of the technical solution of the present invention, the specific data here are simplified. The simplified data is only for a better understanding of the present invention by showing examples of the present invention. The present invention is not limited to the specific objects of data processing.

[0053] Figure 5 The overall implementation flow chart of the present invention is presented, which is suitable for analyzing the flight control system rod force idle travel, transmission idle travel, friction and hysteresis data. This embodiment adopts this process, and the data analysis includes the following steps:

[0054] Step 1: Obtain the test measurement data (X, Y), smooth the test data (X, Y) to obtain (X t ,Y t ). Assume that the test data is smoothed to obtain the following table data:

[0055] time 1 2 3 4 5 6 7 8 9 10 11 12 X 0.0 0.6 1.1 1.5 2.0 2.6 2.4 2.1 1.3 0.9 0.4 -0.1 Y 0.5 -5.0 -10.0 -14.0 -19.0 -25.0 -25.0 -22.0 -14.0 -10.0 -5.3 0.0 time 13 14 15 16 17 18 19 20 21 22 23 24 X -0.6 -1.1 -1.3 -1.9 -2.6 -2.4 -2.0 -1.6 -1.1 -0.6 0.0 - Y 4.9 9.9 12.0 18.0 24.5 24.5 21.0 17.0 12.0 6.5 0.0 -

[0056] Step 2: Calculate X min , X max , Y min , Y max They are -2.6, 2.6, -25 and 24.5 respectively.

[0057] Step 3: According to the measurement and calculation accuracy requirements, determine the row accuracy α and column accuracy β of the image matrix of X and Y. Assume that the accuracy α of X is 0.1 and the accuracy β of Y is 1.

[0058] Step 4: Calculate the number of rows and columns of the image matrix T of X and Y, and define the initial value of T as a two-dimensional zero matrix.

[0059] Number of rows:

[0060] Number of columns:

[0061] Step 5: Determine (X t ,Y t ) corresponds to the element T in T i,j , and assign the element a value of 1.

[0062]

[0063] After step 5, T i,j Matrix Figure 6 .

[0064] Step 6: Fill (X) along time by interpolation calculation t , Y t ) and (X t+1 , Y t+1 ), the number of interpolation points n is:

[0065] (n must be no less than 1, otherwise n = 0)

[0066] Interpolation point (X′ t ,Y′ t ):

[0067] X′ t =X t +kα, k≤n

[0068]

[0069] Step 7: Determine the interpolation point (X′ t ,Y′ t ) in T i,j The corresponding element T i+k,j+l , and assign the element a value of 1. Where l:

[0070]

[0071] The T of the test data after interpolation i,j Matrix Figure 7 .

[0072] Step 8: Find the matrix T i,j The elements with value 1 in each row are assigned value 1, and the 0-value elements between these elements are assigned value 1. i,j Matrix Figure 8 .

[0073] Step 9: Calculate the matrix T i,j The sum of the values ​​of each row Z i· The sum of the elements in each column Z j :

[0074]

[0075] Step 10: Calculate the rod force idle travel, transmission idle travel, friction or hysteresis loop.

[0076] Rod force empty travel:

[0077] Δx f=α·Z· j (when , Y is the operating force)

[0078] It can be calculated that Δx f =0.3

[0079] Transmission idle travel:

[0080] Δx δ =α·Z ·j (when When Y is the deflection of the rudder surface)

[0081] It can be calculated that Δx δ =0.3

[0082] Hysteresis loop:

[0083] Δx max =β·max{Z i·}

[0084] It can be calculated that Δx max =3

[0085] Friction:

[0086]

[0087] Calculation shows that f = 1.5

[0088] The present invention proposes a method for automatically and quickly reading data values ​​such as rod force idle stroke, transmission idle stroke, friction force and hysteresis loop; this method can greatly improve the efficiency of data reading, overcome the disadvantage that process data and return data cannot be completely aligned, and improve the accuracy of data reading. Of course, the implementation of the above-mentioned program steps can be hardware, software or a combination of the two. When implemented in hardware, it can be an electronic circuit, a dedicated integrated circuit, a plug-in, a function card, etc. When implemented in software, it can be compiled into a program or a code segment; the data processing and analysis method is loaded into the computer's memory in the form of a computer program, and the computer includes a processor and the memory. When the computer program is executed by the processor, the process of the data processing and analysis method is implemented. The data processing and analysis method is loaded into a computer-readable storage medium in the form of a computer program. When the computer program is executed by the processor, the process of the method is implemented.

[0089] The above specific implementation methods or cases are only used to explain the technical solutions of the present invention, and are not intended to limit the present application. Any parts not described in detail are deemed to be conventional technical means or common knowledge in the field. A person of ordinary skill in the art should understand that based on the design concept of the present application, the technical solutions described in the aforementioned implementation methods should be adaptively modified, or some or all of the technical features therein should be replaced by equivalents. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A flight control system test data processing and analysis method, characterized in that: The analytical method comprises the following steps: Step S1, obtaining flight control system test data, including at least time history data of control force, control displacement, and control surface deflection parameters during the control process; Step S2, assigning an array consisting of control displacement and control force or an array consisting of control displacement and control surface deflection to (X, Y), and calculating the maximum and minimum values ​​of X and Y; Step S3, determining the number of rows and columns of the image matrix T according to the accuracy requirement and the size range of the test data; Step S4, rounding the smoothed test data according to the accuracy requirements, and interpolating and filling the rounded data along the time series according to the accuracy distance; Step S5, according to the size of the value, map the interpolated and filled data to the image matrix T, assign the corresponding elements of T to 1; and assign other unmapped elements in the matrix T to 0; Step S6, by searching the matrix T, assigning the value of 1 to the elements in each row between the elements with a value of 1, and calculating the sum Z of the values ​​of the elements in each row of the matrix T; Step S7, read the corresponding Z value according to the definitions of the rod force idle stroke, transmission idle stroke, friction force and hysteresis loop parameters of the system to obtain the corresponding numerical value.

2. A flight control system test data processing and analysis method as claimed in claim 1, characterized in that: In step S2, after obtaining the test measurement data (X, Y), the test data (X, Y) is smoothed to obtain (X t ,Y t ); calculate X min , X max , Y min , Y max .

3. A flight control system test data processing and analysis method as claimed in claim 2, characterized in that: According to the measurement and calculation accuracy requirements, the row accuracy α and column accuracy β of the X and Y image matrices are determined.

4. A flight control system test data processing and analysis method as claimed in claim 3, characterized in that: Calculate the number of rows and columns of the image matrix T of X and Y, and define the initial value of T as a two-dimensional zero matrix; Number of rows: Number of columns:

5. A flight control system test data processing and analysis method as claimed in claim 4, characterized in that: The process of interpolation filling is: determine (X t ,Y t ) corresponds to the element T in T i,j , and assign the element a value of 1; Along time, by interpolation, fill (X t , Y t ) and (X t+1 , Y t+1 ), the number of interpolation points n is: Where n must be no less than 1, otherwise n = 0; Interpolation point (X′ t ,Y′ t ): X′ t =X t +kα,k≤n; Determine the interpolation point (X′ t ,Y′ t ) in T i,j The corresponding element T i+k,j+l , and assign the element a value of 1; where l: In the above formula, α and β are the row precision and column precision of the image matrix respectively; Find the matrix T i,j The elements with value 1 in each row and the 0-valued elements between these elements are assigned value 1.

6. A flight control system test data processing and analysis method as claimed in claim 5, characterized in that: Calculate the matrix T i,j The sum of the values ​​of each row Z i· and the sum of the elements in each column Z j :

7. A flight control system test data processing and analysis method as claimed in claim 6, characterized in that: Calculate rod force idle travel, transmission idle travel, friction or hysteresis loop; Rod force empty travel: Δx f =α·Z ·j , among which, when When , Y is the operating force; Transmission idle travel: Δx δ =α·Z ·j Among them, when When , Y is the deflection of the rudder surface; Hysteresis loop: Δx max =β·max{Z i. } Friction:

8. The flight control system test data processing and analysis method according to claim 1, characterized in that: The parameter acquisition process in step S1 is: operate the aircraft joystick, steering wheel or pedals for one cycle, and collect the time history data of the control force, control displacement and control surface deflection parameters during the operation process through the measuring equipment.

9. A flight control system test data processing and analysis method according to any one of claims 1 to 8, characterized in that: The data processing and analysis method is loaded into the memory of a computer in the form of a computer program. The computer includes a processor and the memory. When the computer program is executed by the processor, the process of the data processing and analysis method is implemented.

10. A flight control system test data processing and analysis method according to claim 9, characterized in that: The data processing and analysis method is loaded into a computer-readable storage medium in the form of a computer program, and when the computer program is executed by a processor, the process of the method is implemented.

Images