A general rocket flight test telemetry data rapid analysis and interpretation system and method

Abstract

A general rocket flight test telemetry data rapid analysis and interpretation system and method, comprising: an original file analysis module, according to the measurement data parameter file, the rocket flight test telemetry data original file is parsed to obtain measurement data, and then sent to the time zero correction module; the time zero correction module, the time axis is set for the measurement data, the time axis zero point is corrected, the measurement data is aligned, and then sent to the data noise reduction processing module; the data noise reduction processing module, the noise data in the measurement data is identified, the noise data is reduced, and then sent to the calculation interpretation and output module; the calculation interpretation and output module, the data type contained in the measurement data is interpreted, corresponding processing is carried out, and the result is output. The present application can improve the work efficiency of data interpretation and comparison required in rocket flight test.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of rocket test system, and particularly relates to a universal rocket flight test telemetry data rapid analysis and interpretation system and method. BACKGROUND

[0002] The judgment of the working state of the rocket in the flight test process depends on the measurement data in the flight process of the rocket body. These measurement data (such as battery voltage, ignition instruction and ignition signal, rudder working instruction and feedback signal, angular velocity, acceleration, temperature, etc.) are recorded by the on-board sensor and transmitted to the on-board telemetry device, and then transmitted to the ground telemetry station by the telemetry device. The original file of the flight test telemetry data transmitted to the ground telemetry station needs to be extracted by the special telemetry data decomposition software, and stored as a TXT data file. Test personnel use drawing tools such as Origin to draw TXT data files, and mostly manually interpret key data by cursor comparison. Due to the large amount of measurement data and the variety of data, relying on manual data interpretation, comparison and review not only increases the workload of the test personnel and reduces the efficiency, but also easily causes human interpretation omission and deviation, and the interpretation accuracy is difficult to control. The rocket needs data interpretation in the ground stage of the bench test, vibration and impact test, and rocket head comprehensive test. The current method wastes a lot of manpower and time cost. SUMMARY

[0003] The present application provides a universal rocket flight test telemetry data rapid analysis and interpretation system and method, which solves the technical problems of manual data interpretation and comparison, large workload and low efficiency in previous rocket flight tests.

[0004] The present application provides a universal rocket flight test telemetry data rapid analysis and interpretation system, which comprises:

[0005] An original file analysis module analyzes the rocket flight test telemetry data original file according to the measurement data parameter file to obtain the measurement data, and then sends the measurement data to a time zero point correction module;

[0006] The time zero point correction module sets a time axis for the measurement data, corrects the zero point of the time axis, aligns the measurement data, and then sends the measurement data to a data noise reduction processing module;

[0007] The data noise reduction processing module identifies the noise data in the measurement data, reduces the noise data, and then sends the measurement data to a calculation interpretation and output module;

[0008] The calculation interpretation and output module interprets the data types contained in the measurement data, performs corresponding processing, and outputs the results.

[0009] Further, the content of the measurement data parameter file comprises: a channel table of a rocket flight test telemetry data original file, measurement data parameters, and a digital signal communication protocol.

[0010] The channel table of the rocket flight test telemetry data original file is used to indicate distribution information of each measurement data channel in the flight test telemetry data original file.

[0011] The measurement data parameter type comprises a measurement data name, a signal type, a sensor linear calibration characteristic equation slope, a sensor linear calibration characteristic equation intercept, a drawing pattern requirement, and a calculation mode, and each measurement data parameter corresponds to each measurement data channel in the channel table of the rocket flight test telemetry data original file.

[0012] The digital signal communication protocol file comprises a data name, a data length, a data type, and a scale, and flight test telemetry data original files are parsed and converted into measurement data according to the digital signal communication protocol.

[0013] Further, the original file parsing module parses the rocket flight test telemetry data original file according to the measurement data parameter file to obtain measurement data, and further comprises:

[0014] First, a plurality of measurement data initialization matrices are established, each initialization matrix corresponding to a measurement data parameter type; the rocket flight test telemetry data original file is divided into data blocks; a frame header of the data block is extracted to establish a frame header index, a measurement data index matrix is generated according to the distribution information of each measurement data channel; corresponding measurement data is extracted from the data block based on the measurement data index matrix, the measurement data is filled into the initialization matrix according to the measurement data index to obtain a measurement data matrix; and the measurement data is converted into actual physical quantities according to the sensor linear calibration characteristic equation slope and the sensor linear calibration characteristic equation intercept.

[0015] Further, the time zero point correction module sets a time axis for the measurement data, corrects a time axis zero point of the measurement data, and aligns the measurement data, and specifically comprises:

[0016] Time zero point signal data in the measurement data is selected to form a matrix UT0, and the matrix size of the matrix UT0 is 1×m;

[0017] Frame count data in the measurement data is selected to form a matrix FRAME, and the matrix size of the matrix FRAME is 1×n;

[0018] The matrix FRAME is interpolated to expand the matrix size of the matrix FRAME to 1×m, and the matrix is named as a matrix T; the matrix T is divided by a frame count sampling frequency to obtain a matrix T', and the matrix T' is a time axis matrix without zero point correction.

[0019] The time zero signal data is a step signal, the position index of the rising edge thereof is t0, and the value of the matrix T' at the t0 index is z, and z is subtracted from each element of T' as the time axis of all measurement data.

[0020] Further, a data denoising processing module identifies noise data in the measurement data and performs denoising processing on the noise data, specifically including:

[0021] A difference matrix of the matrix FRAME is calculated, and an absolute value of the difference matrix is calculated to obtain a matrix MA,

[0022] Data values in the matrix MA that are less than or equal to a threshold value d are changed to 1, and data in the matrix MA that is greater than the threshold value d is changed to infinity.

[0023] The measurement data matrix is multiplied by the matrix MA to assign noise data in the measurement data matrix to infinity, and the measurement data matrix is filtered to remove the infinite data to complete data denoising processing.

[0024] Further, a calculation interpretation and output module performs corresponding processing and outputs results according to the data types contained in the measurement data, specifically including:

[0025] If pulse signals in the measurement data need to be output, rising edge time nodes and pulse width times of the pulse signals are calculated, and corresponding graphs are drawn;

[0026] If the average value of the measurement data needs to be output, the average value of the measurement data is calculated, and the average value of the measurement data is displayed and output or output in a file;

[0027] If a continuous pattern of the measurement data needs to be output, the matrix T is used as the X-axis, and the measurement data is used as the Y-axis to output the pattern.

[0028] The application also proposes a general rocket flight test telemetry data rapid analysis interpretation method, including:

[0029] A rocket flight test telemetry data original file is parsed according to a measurement data parameter file to obtain measurement data;

[0030] A time axis is set for the measurement data, the time axis zero point is corrected, and the measurement data is aligned;

[0031] Noise data in the measurement data is identified, and denoising processing is performed on the noise data;

[0032] Data types contained in the measurement data are interpreted for corresponding processing and output results.

[0033] Further, the content of the measurement data parameter file comprises: a channel table of a rocket flight test telemetry data original file, measurement data parameters, and a digital signal communication protocol.

[0034] The channel table of the rocket flight test telemetry data original file is used to indicate distribution information of each measurement data channel in the flight test telemetry data original file.

[0035] The measurement data parameter type comprises a measurement data name, a signal type, a sensor linear calibration characteristic equation slope, a sensor linear calibration characteristic equation intercept, a drawing pattern requirement, and a calculation mode, and each measurement data parameter corresponds to each measurement data channel in the channel table of the rocket flight test telemetry data original file.

[0036] The digital signal communication protocol file comprises a data name, a data length, a data type, and a scale, and the flight test telemetry data original file is parsed and converted into measurement data according to the digital signal communication protocol.

[0037] Further, the parsing of the rocket flight test telemetry data original file according to the measurement data parameter file to obtain measurement data further comprises:

[0038] First, a plurality of measurement data initialization matrices are established, each initialization matrix corresponding to a measurement data parameter type; the rocket flight test telemetry data original file is divided into data blocks; a frame header of the data block is extracted to establish a frame header index, a measurement data index matrix is generated according to the distribution information of each measurement data channel; corresponding measurement data is extracted from the data block based on the measurement data index matrix, the measurement data is filled into the initialization matrix according to the measurement data index to obtain a measurement data matrix; and the measurement data is converted into actual physical quantities according to the sensor linear calibration characteristic equation slope and the sensor linear calibration characteristic equation intercept.

[0039] Further, the time axis of the measurement data is set, the measurement data time axis zero point is corrected, and the measurement data is aligned, specifically comprising:

[0040] Time zero signal data groups in the measurement data are selected to form a matrix UT0, and the matrix size of the matrix UT0 is 1×m;

[0041] Frame count data in the measurement data are selected to form a matrix FRAME, and the matrix size of the matrix FRAME is 1×n;

[0042] The matrix FRAME is interpolated, the matrix size of the matrix FRAME is expanded to 1×m, and the matrix is named as a matrix T; the matrix T is divided by the frame count sampling frequency to obtain a matrix T', and the matrix T' is a time axis matrix without zero point correction;

[0043] The time zero signal data is a step signal, the position index of the rising edge of which is t0, and the value of the matrix T' at the t0 index is z, and z is subtracted from each element of T' as the time axis of all measurement data;

[0044] The noise data in the measurement data is identified, and the noise data is subjected to noise reduction processing, specifically including:

[0045] The difference matrix of the matrix FRAME is calculated, and the absolute value of the difference matrix is obtained to obtain the matrix MA,

[0046] The data values in the matrix MA that are less than or equal to the threshold value d are changed to 1, and the data in the matrix MA that is greater than the threshold value d is changed to infinity.

[0047] The measurement data matrix is multiplied by the matrix MA to assign the noise data in the measurement data matrix to infinity, and the measurement data matrix is subjected to filtering processing to remove the infinite data to complete the data noise reduction processing.

[0048] The data type contained in the measurement data is processed and the results are outputted, specifically including:

[0049] If the pulse signal in the measurement data needs to be outputted, the rising edge time node and the pulse width time of the pulse signal are calculated, and the corresponding graph is drawn;

[0050] If the average value of the measurement data needs to be outputted, the average value of the measurement data is calculated, and then the average value of the measurement data is displayed and outputted or outputted in a file;

[0051] If the continuous pattern of the measurement data needs to be outputted, the matrix T is used as the X axis, and the measurement data is used as the Y axis to output the pattern.

[0052] Compared with the prior art, the present application has the following advantages:

[0053] 1) Convenient operation, saving time cost: the platform realizes encapsulation of the channel table, the coefficient table, the communication protocol, the data nominal value and the analysis calculation demand and other system parameters into a configuration file; the operator only needs to input the path of the flight test telemetry data original file, and the data can be automatically analyzed, the control instruction, the ignition signal, the voltage and the sensor data and other indicators can be analyzed, and the required pattern can be drawn according to the configuration file setting, and the data interpretation time can be reduced to less than 10 minutes.

[0054] 2) Save space cost: the platform can directly use flight test telemetry data original file, without data decomposition storage as multiple TXT files, the memory space occupied by the stored data is reduced to 1 / 10 or less, and the data redundancy is greatly reduced; the platform uses a matrix adaptive block reading algorithm for file reading, reduces the program space complexity, and solves the problem of memory overflow in platform operation.

[0055] 3) General platform, strong expansibility: only need to change the system parameters in the configuration file, it can be directly applied to various types of carriers; the platform modularizes and encapsulates file reading, channel analysis, filtering and noise reduction, time sequence index calculation and pattern drawing algorithm function modules, which is convenient for quickly integrating and building various data processing platforms to meet different test requirements. DETAILED DESCRIPTION

[0056] To explain the technical content, algorithm characteristics, purposes and effects of the present application in detail, the present application provides a general rocket flight test telemetry data rapid analysis and interpretation system and method. The system comprises the following:

[0057] I. Rocket full system parameter configuration module.

[0058] The types of measurement data, sampling frequency and channel position of different types of rockets are different. The universality of the present application is reflected in that for different types of rockets, only the full system parameter configuration needs to be modified, and the original test data of the type can be analyzed and interpreted. The parameters of the present application are configured as 3 TXT files, which are independent of the analysis platform, and are convenient for test personnel to write and modify at any time.

[0059] TXT file 1 is a flight test telemetry data channel table, which indicates the distribution and order of each measurement data channel in a frame of original data. The measurement data is picked, that is, according to the arrangement position of the data in the channel table, the measurement data is picked from the flight test telemetry data original file. 1 launch rocket corresponds to 1 fixed channel table, in order to facilitate the platform to automatically read this file, the file name is fixed as 《channel table.txt》, which cannot be changed.

[0060] TXT file 2 is each measurement data parameter, according to the actual interpretation of the needs of writing, test personnel can write the path and file name of this file from the platform main program, so the file name is self-defined. Format is each measurement data parameter occupies a line, the contents of this line are arranged in order: measurement data name (consistent with the measurement data name in the file "channel table.txt"), signal type (analog / digital), sensor linear calibration characteristic equation slope, sensor linear calibration characteristic equation intercept, whether to draw a plot (plot / NA, plot is the drawing method to indicate that the plot is drawn, NA indicates not to draw), calculation method (pulse / ave, pulse is the pulse method used to indicate the identification of pulse signal rising edge and pulse width, ave is the average method used to indicate the calculation of data average). Each line of parameters is separated by spaces.

[0061] TXT file 3 is a digital signal communication protocol, which extracts a certain digital data from the flight test telemetry data original file. This data needs to be further decomposed into multiple measurement data according to its communication protocol. The digital signal communication protocol TXT file is written by the test personnel from the platform main program, so the file name is self-defined. Format: data name, data length, data type (unsigned integer / integer), scale. Each data parameter occupies a line and is separated by spaces.

[0062] II. Flight test telemetry data original file reading and analysis module.

[0063] The function of the flight test telemetry data original file reading and analyzing module is to read the original file, decompose and extract the original file into various measurement data matrices according to the rocket flight test parameter file, and store the matrices in the analyzing and interpreting platform for subsequent use. The matrix self-adaptive block reading method is used to solve the problem of memory overflow when reading large files into the platform. The platform is programmed based on the Matlab program language. The original file is directly read into the matrix, which will cause the Out of Memory error prompt. The reason is that the data volume of the original file is large, and the required memory allocation exceeds the standard. The key steps of the algorithm are as follows: 1) create multiple measurement data initialization matrices, the name of each measurement data matrix is read from TXT file 2, the matrix size is 1×N, N = flight time (input from the main program of the platform / min) × sampling frequency × the number of channels occupied by the measurement data (read from TXT file 1 “Channel Table.txt”); 2) read the computer memory and set the data block size according to the memory; 3) extract the frame header index of the data block, combine the wave channel distribution position of each measurement data in TXT file 1 “Channel Table.txt”, and generate a measurement data index matrix; 4) based on each measurement data index matrix, each item of measurement data can be picked out from the data block, and sequentially filled into the measurement data matrix initialized in step 1); 5) repeat steps 3) and 4) until the last character of the file is read to automatically stop, and each measurement data decomposed from the data block is sequentially filled into the initial matrix, thereby completing the measurement data picking; 5) convert the measurement data into actual physical quantities according to the slope and intercept of the sensor linear calibration characteristic equation in TXT file 2.

[0064] III. Time zero correction module.

[0065] The measurement data has been obtained through the flight test telemetry data original file reading and analyzing module described above. Now the time axis needs to be set for the measurement data, and the steps are as follows: 1) select the “T0 signal” data matrix UT0 in the measurement data, and the matrix size is 1×m; 2) select the “frame count” data matrix FRAME in the measurement data, and the matrix size is 1×n; 3) perform linear interpolation on the FRAME matrix to expand its size to 1×m, and name the new matrix as T. Divide the frame count sampling frequency (frame count sampling frequency is obtained from the flight test parameter file) of the matrix T point, and the T’ is obtained, which is the time axis matrix without zero correction; 4) the “T0 signal” measurement data records the time point of the rocket separation from the ground, and defines the time point as the system zero point. The data is a step signal, and the position index of the rising edge is t0; 5) find the value of the time axis matrix T’ at the t0 index, which is z. Subtract z from each element of T’, and the formula is T’ = T’-z, which completes the zero correction and obtains the time axis of all measurement data.

[0066] Four, data noise reduction processing module. Due to environmental noise and acquisition frame loss and other factors, the collected data has a large number of noise points, which seriously affects the subsequent calculation. Analysis of the measurement data shows that each measurement data will have noise points at the same time point, so identifying the noise point index of a measurement data can be identified. The key steps are as follows: 1) calculate the difference matrix of the "frame count" data matrix FRAME in the measurement data and take the absolute value of the difference matrix to obtain the matrix MA; 2) set the allowable error d, change the data value in the MA matrix ≤d to 1, and change the data in the MA matrix >d to NAN (NAN in matlab program language means infinity), MA becomes a noise point index; 3) multiply each measurement data matrix point by MA matrix, which can assign the noise point to NAN, and then perform linear interpolation, which completes the data noise reduction processing. If further noise reduction is required, the median filter algorithm can be used to process each data in turn. The median filter algorithm is configured in this module, and whether to use it can be selected according to the needs of the test personnel.

[0067] Five, calculation interpretation and output module.

[0068] According to the calculation method in TXT file 2 (each measurement data parameter file), the measurement data is calculated. If the calculation method is "pulse", the rising edge time node and pulse width time of the measurement data pulse signal are calculated; if the calculation method is "ave", the average value of the measurement data is calculated. The calculated data is displayed on the platform working interface and stored as an excel file according to the test personnel report preparation report format.

[0069] According to whether the drawing is drawn in TXT file 2 (each measurement data parameter file), the drawing is output. If the drawing is plot, the T matrix calculated in the time zero correction module is used as the X axis, and the measurement data matrix is used as the Y axis, and the drawing is output; if the drawing is NA, no drawing is output.

[0070] The application also provides a general rocket flight test telemetry data rapid analysis method, comprising:

[0071] According to the measurement data parameter file, the rocket flight test telemetry data raw file is parsed to obtain the measurement data.

[0072] A time axis is set for the measurement data, the time axis zero point is corrected, and the measurement data is aligned.

[0073] The noise data in the measurement data is identified and the noise data is processed.

[0074] The data type contained in the measurement data is interpreted and the results are output.

[0075] The content of the measurement data parameter file includes: a channel table of a rocket flight test telemetry data original file, measurement data parameters, and a digital signal communication protocol.

[0076] The channel table of the rocket flight test telemetry data original file is used to indicate distribution information of each measurement data channel in the flight test telemetry data original file.

[0077] The measurement data parameter type includes a measurement data name, a signal type, a sensor linear calibration characteristic equation slope, a sensor linear calibration characteristic equation intercept, a drawing pattern requirement, and a calculation mode, and each measurement data parameter corresponds to each measurement data channel in the channel table of the rocket flight test telemetry data original file.

[0078] The digital signal communication protocol file includes a data name, a data length, a data type, and a scale, and the flight test telemetry data original file is parsed and converted into measurement data according to the digital signal communication protocol.

[0079] The rocket flight test telemetry data original file is parsed according to the measurement data parameter file to obtain measurement data, and further includes:

[0080] First, a plurality of measurement data initialization matrices are established, each initialization matrix corresponding to a measurement data parameter type; the rocket flight test telemetry data original file is divided into data blocks; a frame header of the data block is extracted to establish a frame header index, a measurement data index matrix is generated according to the distribution information of each measurement data channel; corresponding measurement data is extracted from the data block based on the measurement data index matrix, the measurement data is filled into the initialization matrix according to the measurement data index to obtain a measurement data matrix; and the measurement data is converted into actual physical quantities according to the sensor linear calibration characteristic equation slope and the sensor linear calibration characteristic equation intercept.

[0081] A time axis is set for the measurement data, a measurement data time axis zero point is corrected, and the measurement data is aligned, specifically including:

[0082] Time zero signal data groups in the measurement data are selected to form a matrix UT0, and the matrix size of the matrix UT0 is 1×m.

[0083] Frame count data in the measurement data is selected to form a matrix FRAME, and the matrix size of the matrix FRAME is 1×n.

[0084] Interpolation is performed on the matrix FRAME, the matrix size of the matrix FRAME is expanded to 1×m, and the matrix is named as a matrix T; the matrix T is divided by the frame count sampling frequency to obtain a matrix T', and the matrix T' is a time axis matrix without zero point correction.

[0085] The time zero signal data (i.e. "T0 signal" measurement data) is a step signal, the position index of the rising edge of which is t0, and the value of the lookup matrix T' at the t0 index is z, and z is subtracted from each element of T' as the time axis of all measurement data.

[0086] Noise data in the measurement data is identified, and the noise data is denoised, specifically including:

[0087] The difference matrix of the matrix FRAME is calculated, and the absolute value of the difference matrix is calculated to obtain the matrix MA.

[0088] Data values in the matrix MA that are less than or equal to a threshold value d are changed to 1, and data in the matrix MA that is greater than the threshold value d is changed to infinity.

[0089] The measurement data matrix is multiplied by the matrix MA to assign noise data in the measurement data matrix to infinity, and the measurement data matrix is filtered to remove the infinite data to complete the data denoising.

[0090] According to the data type contained in the measurement data, corresponding processing is performed and the results are output, specifically including:

[0091] If the pulse signal in the measurement data needs to be output, the rising edge time node and the pulse width time of the pulse signal are calculated, and the corresponding graph is drawn.

[0092] If the average value of the measurement data needs to be output, after the average value of the measurement data is calculated, the average value of the measurement data is displayed and output or output in a file.

[0093] If the continuous pattern of the measurement data needs to be output, the matrix T is used as the X-axis and the measurement data is used as the Y-axis to output the pattern.

Claims

1. A general-purpose rapid analysis and interpretation system for rocket flight test telemetry data, characterized in that, include: The raw file parsing module parses the raw file of the rocket flight test telemetry data from the measurement data parameter file to obtain the measurement data, and then sends it to the time zero point correction module; The analysis process includes: first, establishing multiple measurement data initialization matrices, each corresponding to a measurement data parameter type; dividing the original file of rocket flight test telemetry data into data blocks; extracting the frame headers of the data blocks to establish frame header indexes, and generating a measurement data index matrix based on the distribution information of each measurement data channel; extracting corresponding measurement data from the data blocks based on the measurement data index matrix, and filling the measurement data into the initialization matrix according to the measurement data index to obtain the measurement data matrix; and converting the measurement data into actual physical quantities based on the slope of the sensor linear calibration characteristic equation and the intercept of the sensor linear calibration characteristic equation. The time zero-point correction module sets a time axis for the measurement data, corrects the zero point of the time axis, aligns the measurement data, and then sends it to the data noise reduction processing module. The data denoising module identifies noise data in the measurement data and performs denoising processing on the noise data. Specifically, this includes: selecting frame count data from the measurement data to form a matrix FRAME; calculating the difference matrix of the matrix FRAME; obtaining a matrix MA by taking the absolute value of this difference matrix; changing data values ​​in matrix MA that are less than or equal to a threshold d to 1; changing data values ​​in matrix MA that are greater than the threshold d to infinity; multiplying the measurement data matrix by matrix MA to assign infinity to the noise data in the measurement data matrix; and then filtering the measurement data matrix to remove the infinitely large data to complete the data denoising processing; after completing the data denoising processing, sending the data to the calculation, interpretation, and output module. The calculation, interpretation, and output module interprets the data type contained in the measurement data, processes it accordingly, and outputs the results.

2. The system according to claim 1, characterized in that, The contents of the measurement data parameter file include: the original file of rocket flight test telemetry data channel table, measurement data parameters, and digital signal communication protocol; The channel table in the original file of rocket flight test telemetry data is used to indicate the distribution information of each measurement data channel in the original file of flight test telemetry data; The measurement data parameter types include measurement data name, signal type, slope of sensor linear calibration characteristic equation, intercept of sensor linear calibration characteristic equation, plotting requirements, and calculation method. Each measurement data parameter corresponds to each measurement data channel in the channel table of the original file of the rocket flight test telemetry data. The digital signal communication protocol file includes data name, data length, data type, and scale. The original flight test telemetry data file is parsed and converted into measurement data according to the digital signal communication protocol.

3. The system according to claim 1, characterized in that, The time zero-point correction module sets a time axis for the measurement data, corrects the zero point of the measurement data time axis, and aligns the measurement data. Specifically, it includes: The zero-time signal data selected from the measurement data are used to form a matrix UT0, and the matrix size of UT0 is 1×m; The frame count data selected from the measurement data are used to form a matrix FRAME, and the matrix size of the matrix FRAME is 1×n; Interpolate the FRAME matrix to expand its size to 1×m, and name this matrix T; divide the frame count sampling frequency by the points of matrix T to obtain matrix T', which is the time axis matrix without zero-point correction; The zero-point time signal data is a step signal. The position index of its rising edge is identified as t0. The value of the matrix T' at the index t0 is z. Subtract z from each element of T' to obtain the time axis of all measurement data.

4. The system according to claim 3, characterized in that, The calculation, interpretation, and output module processes the measurement data according to its data type and outputs the results, specifically including: If it is necessary to output the pulse signal in the measurement data, calculate the rise time node and pulse width of the pulse signal, and plot the corresponding graph. If the average value of the measurement data needs to be output, then after calculating the average value of the measurement data, display the average value of the measurement data or output it to a file; If a continuous graph of the measurement data needs to be output, the graph is output with the matrix T as the X-axis and the measurement data as the Y-axis.

5. A general-purpose method for rapid analysis and interpretation of rocket flight test telemetry data, characterized in that, include: The process involves parsing the original telemetry data file from the rocket flight test to obtain measurement data. Specifically, this includes: first, establishing multiple measurement data initialization matrices, each corresponding to a measurement data parameter type; dividing the original telemetry data file into data blocks; extracting the frame headers of the data blocks to create frame header indexes; generating a measurement data index matrix based on the distribution information of each measurement data channel; extracting corresponding measurement data from the data blocks based on the measurement data index matrix; filling the initialization matrix with the measurement data according to the measurement data index to obtain the measurement data matrix; and converting the measurement data into actual physical quantities based on the slope of the sensor linear calibration characteristic equation and the intercept of the sensor linear calibration characteristic equation. A time axis is set for the measurement data, the zero point of the time axis is corrected, and the measurement data is aligned. The noise data in the measurement data is identified, and noise reduction processing is performed on the noise data. Specifically, this includes: selecting frame count data from the measurement data to form a matrix FRAME; obtaining the difference matrix of the matrix FRAME; taking the absolute value of this difference matrix to obtain a matrix MA; changing the data values ​​in matrix MA that are less than or equal to a threshold d to 1; changing the data values ​​in matrix MA that are greater than the threshold d to infinity; multiplying the measurement data matrix by matrix MA to assign infinity to the noise data in the measurement data matrix; and then filtering the measurement data matrix to remove the infinitely large data to complete the data noise reduction processing. The data type contained in the measurement data is identified, processed accordingly, and the results are output.

6. The method according to claim 5, characterized in that, The contents of the measurement data parameter file include: the original file of rocket flight test telemetry data channel table, measurement data parameters, and digital signal communication protocol; The channel table in the original file of rocket flight test telemetry data is used to indicate the distribution information of each measurement data channel in the original file of flight test telemetry data; The measurement data parameter types include measurement data name, signal type, slope of sensor linear calibration characteristic equation, intercept of sensor linear calibration characteristic equation, plotting requirements, and calculation method. Each measurement data parameter corresponds to each measurement data channel in the channel table of the original file of the rocket flight test telemetry data. The digital signal communication protocol file includes data name, data length, data type, and scale. The original flight test telemetry data file is parsed and converted into measurement data according to the digital signal communication protocol.

7. The method according to claim 5, characterized in that, The process of setting a time axis for the measurement data, correcting the zero point of the measurement data time axis, and aligning the measurement data specifically includes: The zero-time signal data selected from the measurement data are used to form a matrix UT0, and the matrix size of UT0 is 1×m; The frame count data selected from the measurement data are used to form a matrix FRAME, and the matrix size of the matrix FRAME is 1×n; Interpolate the FRAME matrix to expand its size to 1×m, and name this matrix T; divide the frame count sampling frequency by the points of matrix T to obtain matrix T', which is the time axis matrix without zero-point correction; The zero-point time signal data is a step signal. The position index of its rising edge is identified as t0. The value of the matrix T' at the index t0 is z. Subtract z from each element of T' to obtain the time axis of all measurement data. The process of processing the measurement data according to its data type and outputting the results specifically includes: If it is necessary to output the pulse signal in the measurement data, calculate the rise time node and pulse width of the pulse signal, and plot the corresponding graph. If the average value of the measurement data needs to be output, then after calculating the average value of the measurement data, display the average value of the measurement data or output it to a file; If a continuous graph of the measurement data needs to be output, the graph is output with the matrix T as the X-axis and the measurement data as the Y-axis.