Aircraft landing stage static pressure source position error correction method for simulator

Abstract

The invention belongs to the technical field of aircraft control simulation, relates to an aircraft landing stage static pressure source position error correction method for a simulator, and aims to solve the problem that the existing static pressure source position error correction technology lacks targeted calibration on a landing stage ground effect. The method comprises the steps of obtaining real flight data and simulated flight data in a landing stage, calculating a difference value of flight parameters, and obtaining a residual expected value; fitting to obtain an error parameter, calculating a pressure coefficient caused by a static pressure source position error, and determining the position error; superposing the position error to the flight parameter of the simulated flight data, returning to recalculate the difference value until the residual expected value is smaller than the threshold value, and finishing correction; the error parameters comprise a pressure coefficient difference value under the zero attack angle, the slope of the pressure coefficient difference value changing along with the attack angle and an influence factor of the ground effect on the position error. Measured values of the static pressure sensor are corrected in real time, and static pressure source position errors caused by the ground effect in the landing stage are effectively eliminated.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft control simulation, and in particular relates to a method, system, electronic equipment and computer-readable storage medium for correcting static pressure source position errors during the landing phase of an aircraft used in a simulator. Background Art

[0002] In the field of aviation, static pressure sensors are core components for obtaining atmospheric static pressure. Their measurement accuracy is directly related to the accuracy of key flight parameters such as aircraft airspeed, altitude, and Mach number, which in turn affects flight safety and controllability. However, due to the influence of the fuselage shape, aerodynamic layout, and flight state, airflow disturbances around the fuselage can cause the air pressure value measured by the static pressure sensor to deviate from the true atmospheric static pressure, i.e., static pressure source position error. This error is particularly significant during complex maneuvers such as aircraft takeoff and landing, flap and slat opening and closing, and spoiler operation, and may cause deviations in flight parameter calculations and even lead to serious safety hazards.

[0003] Existing research on correcting static pressure source position errors focuses on the impact of aircraft configuration (such as flaps, spoilers, and landing gear status) on static pressure source errors. These efforts attempt to develop universal correction methods applicable to all flight phases by establishing theoretical models or integrating limited flight test data. While these methods aim to cover all flight phases, they rely on theoretical modeling or limited flight test data, lack a systematic process for comparing simulator and real-world flight data, and often overlook significant differences in airflow characteristics across different phases. This makes it difficult to fully reflect the error characteristics under complex flight conditions, particularly the unique aerodynamic environment of landing, which hinders the optimization of correction algorithms.

[0004] Alternatively, free flight and takeoff maneuvers can be calibrated to reduce errors through methods such as aerodynamic compensation and atmospheric data inertial reference unit (ADRIU) calibration. However, this method generally lacks targeted calibration for the ground effect during landing. Since the aircraft flies close to the ground during landing, the aerodynamic interaction between the ground and the fuselage creates unique airflow interference. The ADRIU is not optimized for this phase, resulting in airspeed position errors that may still be within 4 knots at touchdown, posing a safety risk and failing to fully meet actual flight safety requirements.

[0005] Therefore, it is urgent to carry out special research on the static pressure source position error during the landing phase to improve the accuracy of flight parameter calculation in complex scenarios and fill the gaps in existing technologies. Summary of the Invention

[0006] To address the aforementioned problems in the prior art, namely, the lack of targeted calibration of the ground effect during the landing phase in the existing static pressure source position error correction technology, making it difficult to accurately reflect the error characteristics under the unique aerodynamic environment during the landing phase, the present invention, in its first aspect, provides a method for correcting the static pressure source position error during the landing phase of an aircraft simulator, the method comprising: S1. Collect real flight data and restore it through simulation to obtain simulated data; S2. Back-driving the simulator based on the simulation data to complete aircraft trim and initialization, collect complete simulation data, and then obtain simulated flight data of the landing phase; S3. Calculate the difference between the flight parameters of the actual flight data and the simulated flight data during the landing phase, and then obtain the expected value of the residual; S4. Fitting is performed based on the residual expected value to obtain the error parameter; The error parameters include the pressure coefficient difference at zero angle of attack, the slope of the pressure coefficient difference as the angle of attack changes, and the influence factor of the ground effect on the position error; S5. Calculating a pressure coefficient caused by a static pressure source position error based on the error parameter, and further calculating a position error of a flight parameter caused by the static pressure source position error; S6. Superimpose the position error on the flight parameters of the simulated flight data, and return to S3 until the expected value of the residual is less than a predetermined threshold. Calculate the pressure coefficient caused by the static pressure source position error in the current iteration, and complete the correction.

[0007] In some preferred embodiments, the collected real flight data is preprocessed and used as input data to input into a simulator to perform flight simulation and collect simulation data; the preprocessing includes denoising and aligning timestamps, and the simulation data includes control data, environmental data, and system output data.

[0008] In some preferred embodiments, the flight parameters include Mach number, altitude and speed.

[0009] In some preferred embodiments, based on the expected value of the residual, the error parameter is obtained by fitting the error model, and the method is as follows: S41. Based on the simulation process, obtain the aircraft pressure coefficient; S42. During the landing phase, the pressure coefficient of the aircraft at zero angle of attack is obtained by combining the aircraft pressure coefficient and related parameters with angle of attack manipulation; S43, obtaining the pressure coefficient at different attack angles, and then obtaining the slope of the pressure coefficient as the attack angle changes; S44. Obtain the ground effect influence factor based on the engineering approximation method.

[0010] In some preferred embodiments, the pressure coefficient caused by the static pressure source position error is calculated based on the error parameter, and the method is: Calculate the pressure coefficient caused by the static pressure source position error based on the error parameter : ; in, represents the body attack angle; represents the pressure coefficient difference at zero angle of attack; It represents the slope of the pressure coefficient changing with the angle of attack; It represents the coefficient that takes the influence of ground effect into account.

[0011] In some preferred embodiments, the position error is superimposed on the flight parameters of the simulated flight data by: The Mach number position error, the altitude position error, and the speed position error are respectively superimposed on the flight parameters of the simulated flight data to obtain the indicated parameters to determine the parameter correction: ; ; ; The indicated parameters include indicated airspeed , indicating pressure altitude , indicated Mach number ; If the current expected value of the residual is not less than the predetermined threshold, the indication parameter is used as the flight parameter of the simulated flight data of the landing phase in the next iteration, and the process returns to step S3 to recalculate the difference.

[0012] Beneficial effects of the present invention: The present invention introduces a ground effect correction coefficient to perform real-time correction on the static pressure sensor measurement value, effectively eliminating the static pressure source position error caused by the ground effect during the landing phase. Ultimately, the resulting airspeed error on the simulator is corrected, significantly reducing the airspeed position error during the landing phase. This avoids risks such as landing attitude misjudgment and touchdown speed anomalies caused by parameter calculation deviations, thereby improving the reliability of flight parameters. Establish a dedicated error analysis model and calibration mechanism based on the aerodynamic characteristics of ground effect, improve the static pressure source error correction technology system, and fill the gap in landing phase error correction technology; By combining the systematic comparison of simulator and real flight data, a standardized error collection and verification process is established to make the correction method more in line with actual flight conditions, provide data support for engineering applications, improve the simulation accuracy of simulator flight parameters, and enhance the realism of the flight simulator. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Other features, objects and advantages of the present application will become more apparent upon reading the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 This is a flow chart of a method for correcting static pressure source position errors during the landing phase of an aircraft simulator according to an embodiment of the present invention; Figure 2 It is a structural diagram of a computer system of a server for implementing the method, system, and device embodiments of the present application. DETAILED DESCRIPTION

[0014] The present application will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are intended only to illustrate the relevant invention and are not intended to limit the invention. It should also be noted that, for ease of description, only portions relevant to the relevant invention are shown in the accompanying drawings.

[0015] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0016] The present invention provides a method for correcting the static pressure source position error during the landing phase of an aircraft for a simulator. To address the problems that existing static pressure source position error correction technologies lack targeted calibration for the ground effect during the landing phase and are unable to accurately reflect the error characteristics under the unique aerodynamic environment of the landing phase, the method introduces a ground effect correction coefficient to perform real-time correction on the static pressure sensor measurement value, effectively eliminating the static pressure source position error caused by the ground effect during the landing phase, and ultimately correcting the airspeed error caused thereby on the simulator.

[0017] A method for correcting static pressure source position errors during the landing phase of an aircraft simulator according to the present invention comprises: S1. Collect real flight data and restore it through simulation to obtain simulated data; S2. Back-driving the simulator based on the simulation data to complete aircraft trim and initialization, collect complete simulation data, and then obtain simulated flight data of the landing phase; S3. Calculate the difference between the flight parameters of the actual flight data and the simulated flight data during the landing phase, and then obtain the expected value of the residual; S4. Fitting is performed based on the residual expected value to obtain the error parameter; The error parameters include the pressure coefficient difference at zero angle of attack, the slope of the pressure coefficient difference as the angle of attack changes, and the influence factor of the ground effect on the position error; S5. Calculating a pressure coefficient caused by a static pressure source position error based on the error parameter, and further calculating a position error of a flight parameter caused by the static pressure source position error; S6. Superimpose the position error on the flight parameters of the simulated flight data, and return to S3 until the expected value of the residual is less than a predetermined threshold. Calculate the pressure coefficient caused by the static pressure source position error in the current iteration, and complete the correction.

[0018] In order to more clearly explain the static pressure source position error correction method for the aircraft landing phase of the simulator of the present invention, the following is combined with Figure 1 Each step in the embodiment of the present invention is described in detail.

[0019] The first embodiment of the present invention provides a method for correcting static pressure source position errors during the landing phase of an aircraft simulator, comprising steps S1 to S6. Each step is described in detail as follows: S1. Collect real flight data and restore it through simulation to obtain simulated data; The collected real flight data (such as QAR data) is preprocessed and used as input data to input into the simulator for flight simulation. The complete simulation data is collected and time segments are intercepted to obtain flight data during the landing phase. The preprocessing includes denoising and aligning timestamps. The simulation data includes control data, environmental data, and system output data.

[0020] Preferably, in this embodiment, denoising is performed based on a three-stage cascaded adaptive denoising architecture for multi-source heterogeneous noise (such as IMU high-frequency vibration noise, GPS jump noise, control surface signal quantization noise, etc.) present in real flight data. The method is as follows: 1) Build a sensor noise prior model: For the angular rate signal obtained by the inertial measurement unit (IMU) , whose noise contains zero-mean Gaussian white noise and non-stationary vibration terms, and is modeled as: ; in, is the noise standard deviation, obtained from the sensor manual or static calibration; is the non-stationary vibration noise term based on the current flight pressure altitude h(t) and the current Mach number M(t), specifically ; is the aerodynamic thermal-structural coupling coefficient, calibrated by historical data, is the normalized random disturbance term, simulating the vibration phase uncertainty; For GPS location signals The jump noise of is eliminated by robust estimation, and the displacement change at adjacent moments is defined as: ; like If it is established, it is marked as an abnormal point and removed or repaired by interpolation (such as spline interpolation). is the dynamic threshold; in, is the current flight speed, is the empirical coefficient, is the sampling period.

[0021] Obtain the angular rate signal after preliminary denoising and the GPS position signal after preliminary denoising as input for subsequent wavelet decomposition and threshold processing .

[0022] 2) Adaptive wavelet threshold denoising: Select Daubechies wavelet basis and scaling functions Perform J-layer decomposition on each sensor signal: ; Definition j The energy of the layer wavelet detail coefficient is ; The estimated local signal-to-noise ratio is: ; Actual thresholds for each layer Adjusted by exponential decay and combined with the flight phase gain factor: ; in, is the low-frequency approximation coefficient, For the j Layer high-frequency detail coefficient, E0 can be replaced by the original signal energy; basic threshold ; From the prior model or residual estimate, N is the signal length; is the attenuation coefficient (0.1 to 0.3 is used in this embodiment), For reference signal-to-noise ratio, the historical average value is taken; is the flight phase gain factor, and its value varies in different flight phases; The detail coefficients are processed using a standard soft threshold function: ; The processed coefficients and approximate coefficients Inverse transform to get the intermediate denoised signal: ; 3) Residual noise suppression through wavelet-Kalman cascade filtering: The signal after wavelet denoising , construct a state space model for Kalman filtering, and use angular velocity For example, define the state vector , the equation of state: ; Observation equation: ; in, is the observed value at time t, is the angular acceleration, the covariance matrix Q and variance R are dynamically adjusted according to the flight phase (such as climb, cruise, maneuver), and R is estimated by the residual variance after wavelet denoising; F is the state transfer matrix, is the process noise, assuming it is zero-mean Gaussian white noise, H is the observation matrix, is the observation noise, which is assumed to be zero-mean Gaussian white noise; Perform the standard Kalman filter prediction-update steps to obtain the optimal state estimate , the final denoised signal is the first element of the state vector: .

[0023] Preferably, the final denoised signal, that is, the first element of the state vector, is a single variable. Alternatively, a corresponding state component may be selected as the output according to specific requirements.

[0024] Dynamic thresholds are used to avoid misjudging normal movement as noise during high-speed flight. A signal-to-noise ratio feedback mechanism is introduced to avoid signal distortion or insufficient denoising caused by traditional hard / soft thresholds. A wavelet-Kalman cascade structure is adopted to balance high-frequency noise suppression and dynamic response fidelity. Non-stationary noise is modeled in combination with flight state parameters (altitude, speed), which improves the physical interpretability of denoising, reduces false system responses caused by noise, and improves the simulation consistency of control data, environmental data, and system output data, supporting high-confidence flight simulation.

[0025] In this embodiment, the above-mentioned standard Kalman filter prediction-update step is a conventional update recursive process based on the prior art and will not be further explained.

[0026] S2. Back-drive the simulator based on the simulation data to complete aircraft trim and initialization, collect complete simulation data, and then obtain simulated flight data of the landing phase.

[0027] Preferably, the control data and environmental data obtained by operating the simulator during the landing phase are combined with data monitoring software to obtain the output data of the aircraft system during this process and the flight parameters; then the environmental parameters of the simulator (such as air pressure, temperature, and wind speed) are set, and the simulator is driven back by the control data to complete the aircraft balancing and initialization, obtain complete simulated flight data, and extract flight parameters such as the Mach number, altitude, and speed during the simulated flight during the landing phase.

[0028] S3. Calculate the difference in flight parameters between the actual flight data and the simulated flight data during the landing phase, and then obtain an expected residual value; the flight parameters include Mach number, altitude, and speed.

[0029] Preferably, the flight parameters such as Mach number, altitude and speed during the simulated flight of the landing phase are compared with the corresponding relevant data in the real flight data to obtain the difference between the two; then, the residual expected value of the simulator data and the real data is obtained by continuously taking the continuous difference.

[0030] S4. Perform fitting based on the residual expected value to obtain error parameters; the error parameters include the pressure coefficient difference at zero angle of attack, the slope of the pressure coefficient difference changing with the angle of attack, and the influence factor of the ground effect on the position error.

[0031] Preferably, based on the expected value of the residual, the error model is fitted to obtain the error parameter, and the method is: S41. Based on the simulation process, obtain the aircraft pressure coefficient: ; in, is the static pressure on the wing surface; is the static pressure of the incoming flow from far ahead; is the air density; is the far front incoming flow speed (airspeed); S42. During the landing phase, the pressure coefficient of the aircraft at zero angle of attack is obtained by combining the aircraft pressure coefficient and related parameters with angle of attack manipulation; S43, obtaining the pressure coefficient at different attack angles, and then obtaining the slope of the pressure coefficient as the attack angle changes; The change of the aircraft pressure coefficient with the angle of attack is a nearly linear process. When flying at low speed (Mach number M < 0.3) and with a small angle of attack (not close to stall), an approximation can be made. By obtaining the pressure coefficient at different angles of attack, the slope of the pressure coefficient with angle of attack can be obtained. S44. The ground effect influence factor is obtained based on the engineering approximation method. The ground effect influence factor is the ratio of the position error to the ground effect intensity. Using the engineering approximation method, it can be expressed as: ; in, is the position error; is the aircraft altitude; is the aerodynamic chord length.

[0032] In this embodiment, the error model is a preset engineering threshold. When a parameter meets the threshold of 10 to the negative power of 3, the parameter is used as the error parameter. The newly calculated pressure coefficient parameter is continuously iterated to obtain the pressure coefficient difference when the threshold range is reached, and the difference is returned for the initial simulator trim. In this embodiment, the pressure coefficient at zero angle of attack is shown in Table 1 below, the slope of the pressure coefficient changing with angle of attack is shown in Table 2 below, and the ground effect influence factor is shown in Table 3.

[0033] Table 1 Pressure coefficient difference at zero angle of attack ( )

[0034] Note: Only used during landing phase Table 2 Slope of pressure coefficient difference with angle of attack ( )

[0035] Table 3 Factors affecting position error due to ground effect

[0036] S5. Calculate a pressure coefficient caused by the static pressure source position error (the difference between the free atmosphere static pressure and the ground effect static pressure at the static pressure sensor) based on the error parameter, and then calculate a position error of the flight parameter caused by the static pressure source position error.

[0037] Preferably, in this embodiment, the pressure coefficient caused by the static pressure source position error is calculated based on the error parameter , the method is: ; in, represents the body attack angle; represents the pressure coefficient difference at zero angle of attack; It represents the slope of the pressure coefficient changing with the angle of attack; It represents the coefficient that takes the influence of ground effect into account.

[0038] Preferably, the position error of the flight parameters caused by the static pressure source position error is calculated by: The pressure coefficient caused by the static pressure source position error is converted into Mach number to obtain the Mach number position error: ; According to the Mach number position error, the height position error is determined as: ; According to the height position error, the speed position error (airspeed error) is determined as: ; The position error includes a Mach number position error , height position error , speed and position error ; in, is the pressure coefficient caused by the static pressure source position error, Indicates the indicated pressure altitude; represents the pressure ratio, represents the density ratio, represents the Mach number of the simulated flight data, represents the calibrated airspeed, Indicates the pressure altitude of the simulated flight data.

[0039] S6. Superimpose the position error on the flight parameters of the simulated flight data, and return to S3 until the expected value of the residual is less than a predetermined threshold. Calculate the pressure coefficient caused by the static pressure source position error in the current iteration, and complete the correction.

[0040] Preferably, the position error is superimposed on the flight parameters of the simulated flight data by: The Mach number position error, the altitude position error, and the speed position error are respectively superimposed on the flight parameters of the simulated flight data to obtain the indicated parameters to determine the parameter correction: ; ; ; The indicated parameters include indicated airspeed , indicating pressure altitude , indicated Mach number ; If the current expected value of the residual is not less than the predetermined threshold, the indication parameter is used as the flight parameter of the simulated flight data of the landing phase in the next iteration, and the process returns to step S3 to recalculate the difference.

[0041] The pressure coefficient difference is iteratively calculated, and the pressure coefficient difference calculation is superimposed on the final value to obtain the flight parameters of the simulated flight data, and the parameter correction is performed. The above method can be used to calculate the pressure coefficient difference between the simulator and the real aircraft at zero angle of attack during the landing phase, the slope of the pressure coefficient difference as the angle of attack changes, and the numerical value of the influence factor of the ground effect on the position error. The airspeed difference can be finally obtained through the above formula, which can improve the realism of the pilot's landing phase flight training using the simulator.

[0042] Further preferably, in this embodiment, the predetermined threshold is , that is, the difference is finally obtained in the dimensions of each variable Within.

[0043] Further preferably, in this embodiment, the processing evaluation parameters are established by the core evaluation factors related to the ground effect during the landing phase of the aircraft. , the aerodynamic coupling degree (lift coefficient increment ), pitch moment (head-down moment gradient ), drag characteristics (induced drag reduction rate ), energy attenuation (sink rate suppression parameter ), control sensitivity (rudder effect attenuation ratio The ratio between the gap between the core parameters such as ) and the real data and the reasonable tolerance is included in the evaluation system, and the evaluation parameters are obtained after weighted average. The closer the evaluation parameter is to 0, the more the simulated data has achieved the same effect as the real data. When >1, it indicates that the training effect has deviated from the required one.

[0044] Table 4 Factors affecting position error due to ground effect

[0045] Preferably, as shown in Table 4, each core parameter is given a weight of 20%. By calculating the evaluation parameters related to the ground effect, it can be seen that the static pressure source position error correction system effectively improves the training effect of the flight landing phase, with an improvement ratio of 19.67%.

[0046] Although the various steps in the above embodiment are described in the above-mentioned order, those skilled in the art will understand that in order to achieve the effect of this embodiment, different steps do not have to be executed in such an order. They can be executed simultaneously (in parallel) or in a reverse order. These simple changes are within the scope of protection of the present invention.

[0047] A second embodiment of the present invention provides a static pressure source position error correction system for a simulator during the landing phase of an aircraft, the system comprising a simulator and a central processing unit; The simulator is configured to restore real flight data through simulation to obtain simulation data; and backdrive the simulator based on the simulation data to complete aircraft trim and initialization; The central processing device includes a data acquisition module, a residual calculation module, a parameter calculation module and an error correction module; The data acquisition module is configured to acquire real flight data; acquire complete simulated data after the aircraft is trimmed, and then obtain simulated flight data during the landing phase; The residual calculation module is configured to calculate the difference between the flight parameters of the real flight data and the simulated flight data during the landing phase, thereby obtaining an expected residual value; The parameter calculation module is configured to perform fitting based on the residual expected value to obtain an error parameter, calculate the pressure coefficient caused by the static pressure source position error based on the error parameter, and further calculate the position error of the flight parameter caused by the static pressure source position error; The error correction module is configured to superimpose the position error onto the flight parameters of the simulated flight data, return to the residual calculation module, and calculate the pressure coefficient caused by the static pressure source position error in the current iteration until the expected residual value is less than a predetermined threshold, thereby completing the correction.

[0048] It should be noted that the above-mentioned embodiment provides a static pressure source position error correction system for the landing phase of an aircraft simulator, and is merely illustrated by the division of the above-mentioned functional modules. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the modules or steps in the embodiments of the present invention can be further decomposed or combined. For example, the modules in the above-mentioned embodiments can be combined into one module or further divided into multiple sub-modules to complete all or part of the functions described above. The names of the modules and steps involved in the embodiments of the present invention are merely for the purpose of distinguishing the modules or steps and are not to be considered as improper limitations of the present invention.

[0049] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working process and related instructions of the system described above can refer to the corresponding process in the aforementioned method embodiment and will not be repeated here.

[0050] An electronic device according to a third embodiment of the present invention includes: at least one processor; and a memory communicatively connected to at least one of the processors; wherein, The memory stores instructions that can be executed by the processor, and the instructions are used to be executed by the processor to implement the above-mentioned static pressure source position error correction method for the aircraft landing phase of the simulator.

[0051] A fourth embodiment of the present invention provides a computer-readable storage medium storing computer instructions, wherein the computer instructions are used to be executed by a computer to implement the above-mentioned method for correcting the static pressure source position error of an aircraft landing phase for a simulator.

[0052] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working processes and related instructions of the electronic device and computer-readable storage medium described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0053] Those skilled in the art should be able to appreciate that the modules and method steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of the two, and the programs corresponding to the software modules and method steps can be placed in random access memory (RAM), internal memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disks, removable disks, CD-ROMs, or any other form of storage medium known in the art. In order to clearly illustrate the interchangeability of electronic hardware and software, the above description has generally described the components and steps of each example according to their functions. Whether these functions are performed in electronic hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art may use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0054] Reference below Figure 2 , which shows a structural diagram of a computer system of a server for implementing the method, system, and device embodiments of the present application. Figure 2 The server shown is merely an example and should not limit the functions and scope of use of the embodiments of the present application.

[0055] like Figure 2 As shown, the computer system includes a central processing unit (CPU) 201, which can perform various appropriate actions and processes according to the program stored in the read-only memory (ROM) 202 or the program loaded from the storage part 208 to the random access memory (RAM) 203. Various programs and data required for system operation are also stored in the RAM 203. The CPU 201, ROM 202 and RAM 203 are connected to each other via a bus 204. An input / output (I / O) interface 205 is also connected to the bus 204.

[0056] The following components are connected to the I / O interface 205: an input section 206 including a keyboard, a mouse, and the like; an output section 207 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 208 including a hard disk and the like; and a communication section 209 including a network interface card such as a LAN (Local Area Network) card or a modem. The communication section 209 performs communication processing via a network such as the Internet. A drive 210 is also connected to the I / O interface 205 as needed. A removable medium 211, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 210 as needed, so that a computer program read therefrom can be installed into the storage section 208 as needed.

[0057] In particular, according to an embodiment of the present disclosure, the process described above with reference to the flowchart can be implemented as a computer software program. For example, an embodiment of the present disclosure includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 209, and / or installed from the removable medium 211. When the computer program is executed by the central processing unit (CPU) 201, the above-mentioned functions defined in the method of the present application are executed. It should be noted that the computer-readable medium mentioned above in the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, an electrical connection having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transfer a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code embodied on a computer-readable medium may be transmitted using any suitable medium, including, but not limited to, wireless, wire, optical cable, RF, etc., or any suitable combination thereof.

[0058] Computer program code for performing the operations of the present application may be written in one or more programming languages, or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, C++, and conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user's computer, partially on the user's computer, as a stand-alone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving a remote computer, the remote computer may be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer (e.g., through the Internet using an Internet service provider).

[0059] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order than that marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0060] The terms "first", "second", etc. are used to distinguish similar objects, rather than to describe or indicate a particular order or sequence.

[0061] The term "comprise" or any other similar term is intended to cover non-exclusive inclusion such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0062] Thus far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is readily understood by those skilled in the art that the scope of protection of the present invention is obviously not limited to these specific embodiments. Without departing from the principles of the present invention, those skilled in the art may make equivalent changes or substitutions to the relevant technical features, and the technical solutions after such changes or substitutions will fall within the scope of protection of the present invention.

Claims

1. A method for correcting static pressure source position error during the landing phase of an aircraft simulator, characterized in that: The method comprises: S1. Collect real flight data and restore it through simulation to obtain simulated data; S2. Back-driving the simulator based on the simulation data to complete aircraft trim and initialization, collect complete simulation data, and then obtain simulated flight data of the landing phase; S3. Calculate the difference between the actual flight data and the simulated flight data during the landing phase, and then obtain the expected value of the residual; S4. Fitting is performed based on the residual expected value to obtain the error parameter; The error parameters include the pressure coefficient difference at zero angle of attack, the slope of the pressure coefficient difference as the angle of attack changes, and the influence factor of the ground effect on the position error; S5. Calculating a pressure coefficient caused by a static pressure source position error based on the error parameter, and further calculating a position error of a flight parameter caused by the static pressure source position error; S6. Superimpose the position error on the flight parameters of the simulated flight data, and return to S3 until the expected value of the residual is less than a predetermined threshold. Calculate the pressure coefficient caused by the static pressure source position error in the current iteration, and complete the correction.

2. The method for correcting static pressure source position error during the landing phase of an aircraft simulator according to claim 1, characterized in that: The collected real flight data is preprocessed and used as input data to input into the simulator to perform flight simulation and collect simulation data; the preprocessing includes denoising and aligning timestamps, and the simulation data includes control data, environmental data, and system output data.

3. The method for correcting static pressure source position error during landing phase of an aircraft simulator according to claim 1, characterized in that: The flight parameters include Mach number, altitude and speed.

4. The method for correcting static pressure source position error during the landing phase of an aircraft simulator according to claim 3, characterized in that: Based on the expected value of the residual, the error model is fitted to obtain the error parameters. The method is: S41. Based on the simulation process, obtain the aircraft pressure coefficient; S42. During the landing phase, the pressure coefficient of the aircraft at zero angle of attack is obtained based on the aircraft pressure coefficient and the angle of attack control; S43, obtaining the pressure coefficient at different attack angles, and then obtaining the slope of the pressure coefficient as the attack angle changes; S44. Obtain the ground effect influence factor based on the engineering approximation method.

5. The method for correcting static pressure source position error during the landing phase of an aircraft simulator according to claim 4, characterized in that: The pressure coefficient caused by the static pressure source position error is calculated based on the error parameter as follows: Calculate the pressure coefficient caused by the static pressure source position error based on the error parameter : ； in, represents the body attack angle; represents the pressure coefficient difference at zero angle of attack; It represents the slope of the pressure coefficient changing with the angle of attack; It represents the coefficient that takes the influence of ground effect into account.

6. The method for correcting static pressure source position error during the landing phase of an aircraft simulator according to claim 5, characterized in that: The method for calculating the position error of flight parameters caused by the position error of static pressure source is: The pressure coefficient caused by the static pressure source position error is converted into Mach number to obtain the Mach number position error: ； According to the Mach number position error, the height position error is determined as: ； According to the height position error, the speed position error is determined as: ； The position error includes a Mach number position error , height position error , speed and position error ; in, is the pressure coefficient caused by the static pressure source position error, Indicates the indicated pressure altitude; represents the pressure ratio, represents the density ratio, represents the Mach number of the simulated flight data, represents the calibrated airspeed, Indicates the pressure altitude of the simulated flight data.

7. The method for correcting static pressure source position error during landing phase of an aircraft simulator according to claim 6, characterized in that: The position error is correspondingly superimposed on the flight parameters of the simulated flight data by: The Mach number position error, the altitude position error, and the speed position error are respectively superimposed on the flight parameters of the simulated flight data to obtain the indicated parameters to determine the parameter correction: ； ； ； The indicated parameters include indicated airspeed , indicating pressure altitude , indicated Mach number ; If the current expected value of the residual is not less than the predetermined threshold, the indication parameter is used as the flight parameter of the simulated flight data of the landing phase in the next iteration, and the process returns to step S3 to recalculate the difference.

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