Flight simulator data packet processing system

Abstract

The invention provides a flight simulator data packet processing system. The flight simulator data packet processing system comprises a data management module, a curve drawing module, a flight parameter data processing module and a compatibility checking module, the data management module is used for storing and querying test flight data of the flight simulator and performing classified management on original flight data; the curve drawing module is used for carrying out visual curve drawing on the data on the basis of the data in the data management module; the flight parameter data processing module is used for carrying out outlier identification, elimination and correction processing on the data acquired from the data management module; the compatibility checking module is used for carrying out error analysis and error correction on the data packet processed by the flight parameter data processing module, so that important test indexes are in an allowable error range, and all flight motion parameters are compatible with one another; according to the flight simulator data packet processing system, a selectable data processing method can be realized, the data packet can be processed and visually displayed, so that the development work efficiency related to the data packet is improved, the time and human input in the aspect of data processing is less, a graphical operation interface is provided, and a user can more simply know and use the system.

Description

Technical Field

[0001] The invention relates to a method for processing a data packet, in particular to a system for processing a flight simulator data packet. Background Art

[0002] The flight simulator data package is a collection of various data required for designing, manufacturing and testing flight simulators provided to flight simulator manufacturers after approval by the civil aviation administration or other aviation administration agencies. It should include the design and performance data required for a flight simulator of a specific aircraft model, and is the basis for developing flight simulators. As it has a direct impact on the simulation degree of flight simulators, it has now become an essential test system for high-level flight simulation equipment.

[0003] After the development of the flight simulator is completed, the flight simulator should be objectively tested according to the objective identification standards. In theory, the test should include multiple test flight subjects, including the test of the aircraft performance, handling quality, motion system and other parts of the flight simulator, and the final test results should be formed into an identification test guide document. The system can be applied to the research and development, testing, maintenance and identification of flight simulators.

[0004] Shanghai Aircraft Customer Service Co., Ltd., a subsidiary of Commercial Aircraft Corporation of China, and the Civil Aviation Science and Technology Research Institute of China, jointly conducted a comprehensive study on the development and review technology of the D-level data package of the flight simulator in the special scientific research project of the Ministry of Industry and Information Technology of China for civil aircraft, combining the development of the ARJ21 aircraft flight simulator and the C919 large aircraft project. By studying relevant standards and regulations at home and abroad, combined with the development of flight simulators, the basic framework of the civil aircraft simulator data package was established, the data that should be included in the civil aircraft simulator data package was clarified, the data in the data package was reasonably classified, and the various data collection and processing methods were clarified, forming the flight simulator data package specification, and taking the ARJ21-700 aircraft as the research object, the ARJ21-700 flight simulator data package (hereinafter referred to as the ARJ21 data package) was developed, and the flight simulator data package specification was verified.

[0005] The ARJ21 data package is a flight simulation equipment data package developed by my country in accordance with CCAR-60 and related international and domestic standards that can support the development, identification and operation of flight simulators. The ARJ21 data package development and simulator verification have gone through the key stages of data demand determination, ARJ21 data package architecture design, flight test requirements formulation, engineering data package development, flight test verification data package development, verification plan determination, simulator design and manufacturing, configuration upgrade, and transitional C / D-level certification. Among them, the verification data package includes verification reference data, matching certification information, verification data roadmap and other explanatory information, all of which are flight test data. It is the first complete flight simulator verification data package in China.

[0006] During the development of the ARJ21 data package, the flight simulator data package data decomposition method and data configuration control method were established in accordance with international standards, a data package version control mechanism was formulated, and rich experience has been accumulated in the flight simulator data package configuration management.

[0007] Although the existing flight simulator data packages can meet the needs of relevant national industry standards, the operation still requires professionals, which leads to problems such as difficult data processing and high threshold for use. Since the original collected data files contain a lot of information and content, they cannot be used directly, resulting in a lot of time and manpower required to analyze and process these data in the actual application process. According to the above situation, most domestic data packages have the problems of high threshold for use and difficult data processing. At the same time, it is difficult to integrate the data comprehensively and intuitively, which is not conducive to the development of subsequent research and experiments. Summary of the invention

[0008] The present invention provides a flight simulator data packet processing system, which solves the above problems. The technical solution is as follows:

[0009] A flight simulator data packet processing system comprises a data management module, a curve drawing module, a flight parameter data processing module and a compatibility check module; the data management module is used for storing and querying the test flight data of the flight simulator, and for classifying and managing the original flight data; the curve drawing module processes the data intuitively based on the data in the data management module; the flight parameter data processing module identifies, removes and corrects the wild values ​​of the data obtained from the data management module; the compatibility check module is used for analyzing and correcting the data packets processed by the flight parameter data processing module, so that important test indicators are within the allowable error range and all flight motion parameters are compatible with each other.

[0010] The data management module is divided into six submodules: data loading, data storage, data query and browsing, data output, data package version management, balancing points and data summary. The data loading and data storage can quickly import the test flight data of the flight simulator, and classify and manage the original flight data according to the test flight subjects and time information; the data query and browsing are used to query all test pedigrees under the subject, and quickly import the corresponding test flight data, supporting data query, access, browsing and output; the data output allows the data in the data package to be segmented and classified into the database by subject through the database operation function, forming the original test flight data of the subject in the flight data package; the data package version management is used to provide version identification information; the balancing points and data summary are used to selectively perform input and output constraints and state definitions before starting balancing according to different mission requirements and flight stages.

[0011] The curve drawing module has the function of displaying the curve value and time point where the mouse is placed, as well as the parameter name and source information, and can draw multiple curves on the same drawing board.

[0012] The flight parameter data processing module removes and corrects outliers on the data according to a seven-point second-order forward differential algorithm, and then performs filtering on the data.

[0013] The seven-point second-order forward differential algorithm is to obtain the calculation data set The first 6 data are obtained by using the Lagrange interpolation formula:

[0014]

[0015] In the above formula: i = 7, 8…, N, N represents the smoothed calculated value of the outlier point; y i is the original data, To calculate the data, the first 6 data points are calculated by formula (1), and then the data points of the following points are calculated in chronological order. Comparing calculated data With the original data y i The difference The difference between the wild value and the smoothed calculated value can be obtained.

[0016] The data is subjected to outlier elimination and correction, and the interpolation formula is used:

[0017]

[0018] Where l = k, k + 1, ..., k + m (m = 3), j and k represent natural numbers, and y l Represents interpolation.

[0019] The compatibility check module includes drawing a curve of the main response of the aircraft to see whether it meets the standard tolerance requirements; constructing an observation equation group to check the compatibility between various measurement parameters, and building an error model of the measurement parameters, identifying the steady-state deviation, proportional factor and white noise of the measurement parameters through the least squares method or the maximum likelihood method, and then reconstructing the measurement data using the identification results, and finally using it for the aerodynamic derivative identification of the aircraft.

[0020] The method of identifying the steady-state deviation, proportional factor and white noise of the measurement parameters by the least square method or the maximum likelihood method includes the following calculation steps:

[0021] Derivative the components of the aircraft velocity V along the three coordinate axes of the body coordinate system:

[0022]

[0023] μ, υ, w are the speeds of the aircraft V along the three coordinate axes of the body coordinate system, corresponding to is the component of the velocity change rate along the ground coordinate; g represents the gravitational acceleration;

[0024] q, p, and r represent the angular velocity of the aircraft along the three coordinate axes of the body coordinate system;

[0025] θ, φ, ф are the Euler angles of the aircraft along the three coordinate axes of the body coordinate system;

[0026] n x 、n y 、n z Represents the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system;

[0027] Then the speed, angle of attack, and sideslip angle are calculated in turn for use in the observation equation:

[0028]

[0029] The actual noise is in the body coordinate component. The noise is the deviation of the linear acceleration measurement value caused by the measurement sensor or the system error of the airborne equipment:

[0030]

[0031] n x 、n y 、n z Respectively represent the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; n xe 、n ye 、n ze Respectively represent the test measurement data of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Respectively represent the system deviation values ​​of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Respectively represent the error correction of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system;

[0032] The relationship formula between the true value, deviation value and proportional factor of the pitch angle, roll angle and sideslip angle in the Euler angle is:

[0033]

[0034] represents the experimental measurement data of Euler angle; φ , θ , b represents the scale factor of the Euler angle; φ , b θ , Represents the system deviation value of Euler angle; η φ , η θ , η θ represents the error correction of Euler angles;

[0035] The observation equation mainly deals with the main state quantities of the aircraft (speed V e , angle of attack α e , sideslip angle β e ) and Euler angles Height e Observation is performed to observe the compatibility of the obtained flight parameter data (after data processing) to ensure that the data is valid and available. The observation equation is as follows:

[0036]

[0037] in:

[0038] λ V is the scale factor of velocity V, b V is the system deviation of velocity V, η V is the error correction of velocity V;

[0039] λ a is the scale factor of the angle of attack α, b a is the systematic deviation of the angle of attack α, η a is the error correction for the angle of attack α;

[0040] λ β is the scale factor of the sideslip angle β, b β is the system deviation of the sideslip angle β, η β is the error correction of the sideslip angle β;

[0041] λ θ , is the scale factor of the Euler angles; b θ , is the systematic deviation of the Euler angles; η θ , is the error correction of the Euler angles;

[0042] λ H is the scale factor for height, b H is the systematic deviation of height; η H is the error correction for the height.

[0043] Furthermore, for the nonlinear state equations containing process noise, the aircraft motion equations used for compatibility verification are:

[0044]

[0045] By taking the derivative of the Euler angle of the kinematic equation, we can get the measure of the torque along the body axis of the aircraft attitude change:

[0046]

[0047] The lambda * is the scale factor: b * is the system deviation: the lower e represents the test measurement data;

[0048] Through the kinematic equations of the three components of the body velocity expressed in formula (8) and the kinematic equations of the three components of the body angular velocity expressed in formula (9), the measurement parameter error model and the simplified compatibility test equation are constructed, the flight parameter data are tested for compatibility, the steady-state deviation (b) and the proportional factor (λ) are identified, and the data are reconstructed so that the steady-state deviation and the proportional factor deviation of the data are eliminated, the data compatibility is achieved, and the dynamic equations of the aircraft can be satisfied.

[0049] The flight simulator data packet processing system can implement optional data processing methods, process data packets and visualize them, thereby improving the efficiency of development work related to data packets, reducing time and manpower investment in data processing, and having a graphical operation interface, allowing users to more easily understand and use the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 It is a schematic diagram of the processing system of the flight simulator data packet.

[0051] Figure 2 It is a workflow diagram of the processing system of the flight simulator data packet;

[0052] Figure 3 This is a screenshot of the software with the outlier data identification, elimination and correction functions. DETAILED DESCRIPTION

[0053] All data in the flight simulator data package is obtained by capturing the serial data electrical signal on the aviation bus. The original flight data file contains a lot of content. When doing objective testing of the simulator and flight simulation model verification, it is necessary to identify and intercept the effective part, and perform outlier elimination, correction, high-frequency noise filtering, curve smoothing and other processing. Figure 1 and Figure 2 As shown, the flight simulator data packet processing system includes: a data management module, a curve drawing module, a flight parameter data processing module, and a compatibility check module. The data processing is realized through the above modules.

[0054] The flight parameter data package processing software is developed based on MatLab software. Through the customized UI operation interface, calling MatLab drawing, numerical simulation, filtering, matching and other algorithms, the flight parameter data is processed to form the flight simulation model verification data package, QTG test verification data package and system matching certification data package.

[0055] The data management module can be divided into submodules such as data loading, data storage, data query and browsing, data output, data package version management, balancing points and data summary. The data loading and data storage can quickly import (load) the test flight data of the flight simulator, and classify and manage the original flight data according to the test flight subject, time and other information. The data query and browsing can query all the test pedigrees under the subject by entering the subject name (click the corresponding subject name with the mouse), and quickly import the corresponding test flight data, support data query, access, browsing and output functions; and have parameter search, list selection, parameter source display and other functional database operation functions. Data output is to allow the data in the data package to be segmented and stored by subject classification through the database operation function, forming the original test flight data of the subject in the flight data package. The data package version management is to provide version identification information to uniquely identify a version of the data package. The balancing points and data summary are based on the flight state to be balanced, and the state variables and their derivatives are constrained to obtain the balance point under a given flight state, and the nonlinear model is balanced. Depending on the mission requirements and flight phases, input and output constraints and state definitions must be selectively performed before starting balancing.

[0056] The curve drawing module uses the Qt drawing function to process the data intuitively based on the data in the data management module. The module can realize quick preview in the form of curves, which is convenient for developers or users to observe the changes in data more intuitively and analyze them. It has functions such as overall preview, local refinement, multi-window synchronization, manual sorting, data comparison, etc., and has a stepless zoom function. Each curve can be moved and zoomed. It has the curve value and time point display where the mouse stops, parameter name, source and other information display, and multiple curves are drawn on the same drawing board, which is convenient for comparative analysis.

[0057] The flight parameter data processing module performs a series of processing operations on the data obtained from the data management module, such as data interception, fitting, outlier identification, elimination and correction, etc., to process the data packet. First, outliers are eliminated and corrected according to the seven-point second-order forward difference algorithm, and then the data is filtered. In the actual operation process, the user can manually select a data processing method to process the data packet according to the curve drawing situation of the above-mentioned curve drawing module, and return the processed data packet to the data management module and the curve drawing module, which will be managed and stored by the data management module, and the curve drawing module will draw images to facilitate further observation and processing, and the compatibility check module will perform error analysis.

[0058] In the flight parameter data processing module, the outlier identification and correction adopts a seven-point second-order forward difference algorithm to obtain the calculation data set The first 6 data of are obtained by using the Lagrange interpolation formula. The specific algorithm formula is as follows:

[0059]

[0060] (i=7,8…,N) N represents the smoothed calculated value of the outlier point, which is a natural number.

[0061] In the above formula: y i The original data of the time selected for the original flight parameter data, To calculate the data, the first 6 data points are calculated by formula (1), and then the data points of the following points are calculated in chronological order. Comparing calculated data With the original data y i The difference The difference between the calculated wild value and the smoothed calculated value is obtained, which represents the difference between the wild value and the smoothed calculated value.

[0062] The outlier points identified above are eliminated, and the Lagrange interpolation formula is used to calculate the correction value. The interpolation formula is as follows:

[0063]

[0064] Where l = k, k + 1, ..., k + m (m = 3), j and k represent natural numbers, and y l Represents interpolation.

[0065] Finally, the seven-point second-order algorithm is used to smooth the data as a whole. The processing effect is as follows Figure 3 shown.

[0066] The compatibility check module is used to ensure that the important test indicators are within the allowable error range and that all flight motion parameters are compatible with each other through error analysis and error correction of the data packets processed by the flight parameter data processing module. Curves such as angle of attack and pitch angle can be drawn for the main responses of the aircraft to see whether the standard tolerance requirements are met; an observation equation group can also be constructed to check the compatibility between the various measurement parameters, and an error model of the measurement parameters can be constructed. The steady-state deviation (b), proportional factor (λ) and white noise (n) of the measurement parameters of formula (3) can be obtained by least squares method or maximum likelihood method identification, and then the measurement data can be reconstructed using the identification results, and finally can be used for the aerodynamic derivative identification of the aircraft.

[0067] The forward direction of the aircraft is called the longitudinal axis, the vertical direction is the vertical axis, and the direction in which the wings are spread is the horizontal axis. Among them, the components of the aircraft speed V along the three coordinate axes of the body coordinate system are derived:

[0068]

[0069] μ, υ, w are the speeds of the aircraft V along the three coordinate axes of the body coordinate system, corresponding to is the component of the velocity change rate along the ground coordinate; g represents the gravitational acceleration.

[0070] q, p, and r represent the angular velocity of the aircraft along the three coordinate axes of the body coordinate system;

[0071] θ, φ, ф are the Euler angles of the aircraft along the three coordinate axes of the body coordinate system;

[0072] n x 、n y 、n z Represents the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system;

[0073] Then the speed, angle of attack, and sideslip angle are calculated in turn for use in the observation equation:

[0074]

[0075] The actual noise is in the body coordinate component. The noise is the deviation of the linear acceleration measurement value caused by the measurement sensor or the system error of the airborne equipment:

[0076]

[0077] n x 、n y 、n z Respectively represent the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; n xe 、n ye 、n zeRespectively represent the test measurement data of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Respectively represent the system deviation values ​​of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; They respectively represent the error correction of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system.

[0078] The relationship formula between the true value, deviation value and proportional factor of the pitch angle, roll angle and sideslip angle in the Euler angle is:

[0079]

[0080] represents the experimental measurement data of Euler angle; φ , θ , b represents the scale factor of the Euler angle; φ , b θ , Represents the system deviation value of Euler angle; η φ , η θ , η θ Represents the error correction of the Euler angles.

[0081] The observation equation mainly deals with the main state quantities of the aircraft (speed V e , angle of attack α e , sideslip angle β e ) and Euler angles Height e Observation is performed to observe the compatibility of the obtained flight parameter data (after data processing) to ensure that the data is valid and available. The observation equation is as follows:

[0082]

[0083] λ V is the scale factor of velocity V, b V is the system deviation of velocity V, η V is the error correction of velocity V; a is the scale factor of the angle of attack α, b a is the systematic deviation of the angle of attack α, η a is the error correction of the angle of attack α; λ β is the scale factor of the sideslip angle β, b β is the system deviation of the sideslip angle β, η β is the error correction of the sideslip angle β;

[0084] λ θ , is the scale factor of the Euler angles; b θ , is the systematic deviation of the Euler angles; η θ , is the error correction of the Euler angles;

[0085] λ H is the scale factor for height, b H is the systematic deviation of height; η H is the error correction for the height;

[0086] In general, the * is the scale factor: b * is the system deviation: the lower part e represents the test measurement data. η with subscript _* These are error corrections.

[0087] Wherein: the values ​​with subscript e are measured values, and the values ​​without subscript e are true values.

[0088] For a nonlinear state equation group containing process noise, it is very difficult to perform state estimation and parameter identification. The simplified approach is to ignore the process noise and refer to formula (3) to perform linearization of the nonlinear state equation group for state estimation. By taking the velocity derivative of the kinematic equation, the force measurement of the aircraft along the body axis is obtained. The aircraft motion equation group used for compatibility testing in this paper is:

[0089]

[0090] By taking the derivative of the Euler angle of the kinematic equation, we can get the measure of the torque along the body axis of the aircraft attitude change:

[0091]

[0092] The lambda * is the scale factor: b * is the system deviation: the lower part e represents the test measurement data.

[0093] Through the kinematic equations of the three components of the body velocity expressed in formula (8) and the kinematic equations of the three components of the body angular velocity expressed in formula (9), the measurement parameter error model and the simplified compatibility test equation are constructed, the flight parameter data are tested for compatibility, the steady-state deviation (b) and the proportional factor (λ) are identified, and the data are reconstructed so that the steady-state deviation and the proportional factor deviation of the data are eliminated, the data compatibility is achieved, and the dynamic equations of the aircraft can be satisfied.

[0094] The present invention can realize optional data processing, process and visualize data packets, thereby improving the efficiency of development work related to data packets, reducing the time and manpower investment in data processing, and having a graphical operation interface, allowing users to understand and use the system more easily.

Claims

1. A flight simulator data packet processing system, characterized in that: It includes a data management module, a curve drawing module, a flight parameter data processing module, and a compatibility check module; the data management module is used for storing and querying the test flight data of the flight simulator, and classifying and managing the original flight data; the curve drawing module processes the data intuitively based on the data in the data management module; the flight parameter data processing module identifies, eliminates and corrects the wild values ​​of the data obtained from the data management module; the compatibility check module is used for analyzing and correcting the data packets processed by the flight parameter data processing module, so that the important test indicators are within the allowable error range and all the flight motion parameters are compatible with each other.

2. The flight simulator data packet processing system according to claim 1, characterized in that: The data management module is divided into six submodules: data loading, data storage, data query and browsing, data output, data package version management, balancing points and data summary. The data loading and data storage can quickly import the test flight data of the flight simulator, and classify and manage the original flight data according to the test flight subjects and time information; the data query and browsing are used to query all test pedigrees under the subject, and quickly import the corresponding test flight data, supporting data query, access, browsing and output; the data output allows the data in the data package to be segmented and classified into the database by subject through the database operation function, forming the original test flight data of the subject in the flight data package; the data package version management is used to provide version identification information; the balancing points and data summary are used to selectively perform input and output constraints and state definitions before starting balancing according to different mission requirements and flight stages.

3. The flight simulator data packet processing system according to claim 1, characterized in that: The curve drawing module has the function of displaying the curve value and time point where the mouse is placed, as well as the parameter name and source information, and can draw multiple curves on the same drawing board.

4. The flight simulator data packet processing system according to claim 1, characterized in that: The flight parameter data processing module removes and corrects outliers on the data according to a seven-point second-order forward differential algorithm, and then performs filtering on the data.

5. The flight simulator data packet processing system according to claim 4, characterized in that: The seven-point second-order forward differential algorithm is to obtain the calculation data set The first 6 data are obtained by using the Lagrange interpolation formula: In the above formula: i = 7, 8…, N, N represents the smoothed calculated value of the outlier point; y i is the original data, To calculate the data, the first 6 data points are calculated by formula (1), and then the data points of the following points are calculated in chronological order. Comparing calculated data With the original data y i The difference The difference between the outlier value and the smoothed calculated value can be obtained.

6. The flight simulator data packet processing system according to claim 5, characterized in that: The data is subjected to outlier elimination and correction, and the interpolation formula is used: Where l = k, k + 1, ..., k + m (m = 3), j and k represent natural numbers, and y l Represents interpolation.

7. The flight simulator data packet processing system according to claim 1, characterized in that: The compatibility check module includes drawing a curve of the main response of the aircraft to see whether it meets the standard tolerance requirements; constructing an observation equation group to check the compatibility between various measurement parameters, and building an error model of the measurement parameters, identifying the steady-state deviation, proportional factor and white noise of the measurement parameters through the least squares method or the maximum likelihood method, and then reconstructing the measurement data using the identification results, and finally using it for the aerodynamic derivative identification of the aircraft.

8. The flight simulator data packet processing system according to claim 7, characterized in that: The method of identifying the steady-state deviation, proportional factor and white noise of the measurement parameters by the least square method or the maximum likelihood method includes the following calculation steps: Derivative the components of the aircraft velocity V along the three coordinate axes of the body coordinate system: μ, υ, w are the speeds of the aircraft V along the three coordinate axes of the body coordinate system, corresponding to is the component of the velocity change rate along the ground coordinate; g represents the gravitational acceleration; q, p, and r represent the angular velocity of the aircraft along the three coordinate axes of the body coordinate system; θ, φ, ф are the Euler angles of the aircraft along the three coordinate axes of the body coordinate system; n x 、n y 、n z Represents the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Then the speed, angle of attack, and sideslip angle are calculated in turn for use in the observation equation: The actual noise is in the body coordinate component. The noise is the deviation of the linear acceleration measurement value caused by the measurement sensor or the system error of the airborne equipment: n x 、n y 、n z Respectively represent the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; n xe 、n ye 、n ze Respectively represent the test measurement data of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Respectively represent the system deviation values ​​of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; Respectively represent the error correction of the linear acceleration of the aircraft along the three coordinate axes of the body coordinate system; The relationship formula between the true value, deviation value and proportional factor of the pitch angle, roll angle and sideslip angle in the Euler angle is: represents the experimental measurement data of Euler angle; φ , θ , b represents the scale factor of the Euler angle; φ 、b θ , Indicates the system deviation value of Euler angle; η φ , η θ , η θ represents the error correction of Euler angles; The observation equation mainly deals with the main state quantities of the aircraft (speed V e , angle of attack α e , sideslip angle β e ) and Euler angles Height e Observation is performed to observe the compatibility of the obtained flight parameter data (after data processing) to ensure that the data is valid and available. The observation equation is as follows: in: λ V is the scale factor of velocity V, b V is the system deviation of velocity V, η V is the error correction of velocity V; a is the scale factor of the angle of attack α, b a is the systematic deviation of the angle of attack α, η a is the error correction of the angle of attack α; λ β is the scale factor of the sideslip angle β, b β is the system deviation of the sideslip angle β, η β is the error correction of the sideslip angle β; λ θ , is the scale factor of the Euler angles; b θ , is the systematic deviation of the Euler angles; η θ , is the error correction of the Euler angles; λ H is the scale factor for height, b H is the systematic deviation of height; η H is the error correction for the height.

9. The flight simulator data packet processing system according to claim 8, characterized in that: For the nonlinear state equations containing process noise, the aircraft motion equations used for consistency testing are: By taking the derivative of the Euler angle of the kinematic equation, we can get the measure of the torque along the body axis of the aircraft attitude change: The lambda * is the scale factor: b * is the system deviation: the lower e represents the test measurement data; Through the kinematic equations of the three components of the body velocity expressed in formula (8) and the kinematic equations of the three components of the body angular velocity expressed in formula (9), the measurement parameter error model and the simplified compatibility test equation are constructed, the flight parameter data are tested for compatibility, the steady-state deviation (b) and the proportional factor (λ) are identified, and the data are reconstructed so that the steady-state deviation and the proportional factor deviation of the data are eliminated, the data compatibility is achieved, and the dynamic equations of the aircraft can be satisfied.

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