Flight simulation equipment engine balancing method, system, equipment and storage medium

Abstract

The present invention belongs to the field of flight control and data processing technology, and specifically relates to a method, system and equipment for balancing the engine of a flight simulation device, aiming to solve the problem of slow engine trimming speed. The present invention can comprehensively consider the influence of various environmental factors on engine trimming by establishing a steady-state database. During the trimming process, the operating point is screened according to the current environmental parameters, and the target throttle lever angle is determined in combination with the target thrust. This calculation method based on the actual environment and precise mapping relationship can significantly improve the accuracy and speed of trimming, so that the engine can reach a trimmed state more accurately under various environmental conditions. Achieving faster, more accurate and reliable engine trimming helps to improve the efficiency during flight training. Back-driving the engine after determining the target throttle lever angle helps to reduce the problem of unstable engine operation caused by improper balancing, thereby improving the stability and reliability of the entire flight simulation system.

Description

Technical Field

[0001] The present invention belongs to the technical field of flight control and data processing, and in particular relates to a balancing method, system and equipment for an engine of a flight simulation device. Background Art

[0002] Trimming a flight simulator involves achieving a state of force balance. Currently, the trimming method for flight simulators involves calculating the actual force values ​​based on parameters such as the flight simulator's engine thrust. This calculation combines the force difference with the target force values ​​to determine whether the trim solution is complete. If the trim solution is deemed incomplete, another force solution is performed based on parameters such as engine thrust until the trim solution is determined to be complete. Finally, the target data obtained upon completion of the trim solution is used to drive the flight control and powertrain systems of the flight simulator.

[0003] To obtain engine thrust, engine trimming is required. Engine trimming aims to achieve the target thrust. During engine trimming, the thrust response at different throttle lever positions is calculated in real time, and the input throttle lever position is iteratively adjusted until the target thrust is achieved.

[0004] However, due to the inertia delay characteristics of the engine (typical response time is 3-5 seconds), a single engine trim requires multiple iterations, and each iteration is inefficient and converges slowly. It takes a long time for the engine to output the corresponding target thrust to complete the trim. Summary of the Invention

[0005] In order to solve the above-mentioned problems in the prior art, namely, the problems of low iteration efficiency and slow convergence speed of engine trim, the present invention provides a method for trimming an engine of a flight simulation device, comprising:

[0006] Establishing a steady-state database for a flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle, and a plurality of preset environmental parameters at different operating points;

[0007] According to the current environmental parameters of the flight simulation device, all operating condition points that meet the current environmental parameters are screened out in the steady-state database;

[0008] screening a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device;

[0009] The target throttle lever angle required for the flight simulation device to reach a trim state is determined based on the thrust and throttle lever angle corresponding to the plurality of target operating points, and the engine is backdriven based on the target throttle lever angle to complete the engine trim.

[0010] In an optional embodiment, the above-mentioned flight simulation device engine trim method further includes:

[0011] performing simulation verification on the target throttle lever angle to obtain a verification value of the simulation verification, and determining that the verification value is less than or equal to a preset threshold, then backdriving the engine based on the target throttle lever angle;

[0012] If it is determined that the verification value is greater than a preset threshold, the target throttle lever angle is corrected, and the engine is backdriven based on the corrected target throttle lever angle.

[0013] In an optional embodiment, the step of performing simulation verification on the target throttle stick angle to obtain a simulation verification value includes:

[0014] Inputting the target throttle lever angle and the current environmental parameters into a preset engine dynamic model to obtain an actual thrust corresponding to the target throttle lever angle;

[0015] A difference ratio between the actual thrust and the target thrust is determined as a verification value for simulation verification.

[0016] In an optional embodiment, correcting the target throttle stick angle includes:

[0017] generating an angle compensation coefficient according to the target throttle lever angle and the target thrust;

[0018] The target throttle lever angle is compensated based on the angle compensation coefficient to obtain a corrected target throttle lever angle.

[0019] In an optional embodiment, establishing a steady-state database of the flight simulation device includes:

[0020] The region within the flight envelope corresponding to the flight simulation device is discretized into a plurality of operating points, the thrust of the engine, the throttle lever angle, and a plurality of preset environmental parameters at each of the operating points are collected, and a multidimensional mapping relationship is established between the thrust of the engine, the throttle lever angle, and the plurality of preset environmental parameters corresponding to each of the operating points.

[0021] In an optional embodiment, determining the target throttle lever angle required for the flight simulation device to reach a trim state based on the thrust and throttle lever angles corresponding to the plurality of target operating points includes:

[0022] Selecting two operating points closest to the target thrust from among the plurality of target operating points;

[0023] According to the thrust and throttle lever angle corresponding to the two operating points, the reverse interpolation method is used to solve and obtain the target throttle lever angle.

[0024] In an optional embodiment, the environmental parameters include at least: flight altitude, ambient temperature and airspeed.

[0025] Another aspect of the present invention provides a flight simulation device engine trim system, comprising:

[0026] A database module is used to establish a steady-state database for the flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle and multiple preset environmental parameters at different operating points;

[0027] A first screening module is configured to screen out all operating condition points that meet the current environmental parameters of the flight simulation device in the steady-state database;

[0028] a second screening module, configured to screen a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device;

[0029] The trim module is used to determine the target throttle lever angle required for the flight simulation device to reach a trim state based on the thrust and throttle lever angle corresponding to the multiple target operating points, and to backdrive the engine based on the target throttle lever angle to complete the engine trim.

[0030] A third aspect of the present invention provides an electronic device, comprising:

[0031] at least one processor;

[0032] and a memory communicatively coupled to at least one of said processors;

[0033] 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 balancing method for the engine of the flight simulation device.

[0034] According to a fourth aspect of the present invention, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are used to be executed by the computer to implement the above-mentioned flight simulation device engine balancing method.

[0035] Beneficial effects of the present invention:

[0036] (1) The flight simulator engine trimming method, system, and device provided by the present invention can comprehensively consider the impact of various environmental factors on engine trimming by establishing a steady-state database that stores multi-dimensional mapping relationships between engine thrust, throttle lever angle, and multiple preset environmental parameters at different operating points. During the trimming process, the operating point is selected based on the current environmental parameters, and the target throttle lever angle is determined in combination with the target thrust. This calculation method based on the actual environment and precise mapping relationships can significantly improve the accuracy and speed of trimming, allowing the engine to achieve a more accurate trim state under various environmental conditions. Achieving faster, more accurate, and more reliable engine trimming helps improve the efficiency of flight training.

[0037] (2) The present invention backdrives the engine after determining the target throttle lever angle, which helps reduce engine operating instability caused by improper balancing and improves the stability and reliability of the entire flight simulation system. This provides pilots with a more realistic flight simulation experience, helps them better familiarize themselves with engine trim operations in different environments, and improves their ability to respond in actual flights. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] 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:

[0039] Figure 1 It is a flow chart of a method for balancing an engine of a flight simulation device provided in an embodiment of the present application.

[0040] 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

[0041] 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.

[0042] 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.

[0043] In order to more clearly explain the balancing method of the flight simulation device engine provided by this application, the following Figure 1 Each step in the embodiment of the present invention is described in detail.

[0044] The first embodiment of the present application provides a method for balancing an engine of a flight simulation device, including:

[0045] S101: Establishing a steady-state database for a flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle, and a plurality of preset environmental parameters at different operating points.

[0046] In this step, by establishing a steady-state database, a multidimensional mapping relationship between the engine's thrust and throttle lever angle at different operating points and multiple preset environmental parameters can be stored. This provides a data foundation for subsequent balancing operations. By pre-collecting and organizing a large amount of relevant data under different operating conditions, a comprehensive mapping relationship is established, ensuring that corresponding reference data is available for query and analysis under various environmental conditions and engine operating states. Based on this large amount of relevant data under different operating conditions, the balancing process can be ensured to have accurate and rich data support, improving the accuracy and reliability of balancing and reducing balancing errors caused by missing or incomplete data.

[0047] The environmental parameters of the embodiment of the present application include at least: flight altitude, ambient temperature and airspeed.

[0048] Specifically, a steady-state database of the flight simulation equipment is established, including:

[0049] The region within the flight envelope corresponding to the flight simulation device is discretized into a plurality of operating points, the thrust of the engine, the throttle lever angle, and a plurality of preset environmental parameters at each of the operating points are collected, and a multidimensional mapping relationship is established between the thrust of the engine, the throttle lever angle, and the plurality of preset environmental parameters corresponding to each of the operating points.

[0050] It's important to note that the flight envelope refers to the range of an aircraft's flight, defined by various flight parameters (such as altitude, speed, and overload). It describes the area within which an aircraft can safely fly. Beyond this area, the aircraft may face various risks, such as stall and structural damage.

[0051] The area within the flight envelope of the flight simulator is discretized into N (N ≥ 10,000) operating points, which means that the originally continuous area within the flight envelope is divided into separate, discontinuous points. The engine parameter data is collected in real time through the shared memory of the flight simulator, where the parameter data at least includes the throttle angle and thrust. The engine parameter data and environmental parameters (ambient temperature, ambient pressure, flight altitude and airspeed) of each operating point are recorded to form a multi-dimensional mapping relationship , where F is the engine thrust, X is the throttle lever angle, H is the flight altitude, T is the ambient temperature, and A is the airspeed.

[0052] It can be understood that each discrete operating point represents a specific operating condition of the flight simulator under various flight environments. By analyzing and studying these discrete operating points, we can understand the performance, stability, maneuverability, and other characteristics of the flight simulator under different flight environments.

[0053] Furthermore, a multidimensional relational database (such as MySQL Cluster) is used to partition and store all data at different operating points according to the flight envelope. The data at each operating point includes multidimensional parameters (engine thrust, throttle lever angle, flight altitude, ambient temperature, and airspeed). The flight altitude covers an altitude range of 0 to 15,000 meters, an ambient temperature range of -60°C to +60°C, and a throttle lever angle range of 0% to 100%, storing over 10,000 steady-state data points.

[0054] By storing all data at different operating points in a multidimensional relational database, data storage becomes more logical and organized. Different flight phases and operating points correspond to different partitions, facilitating targeted data management and maintenance while also reducing data redundancy and improving storage space utilization.

[0055] More importantly, multidimensional relational databases support efficient query operations, allowing for rapid location and retrieval of required data based on various query conditions, such as environmental parameters. Properly designed database indexes can further improve query efficiency and meet the demand for real-time data access during flight simulation.

[0056] Alternatively, principal component analysis can be used to reduce the dimensionality of all data at different operating points, achieving standardization of multidimensional data. The covariance matrix is ​​calculated, the principal components are extracted, and then projected into a two-dimensional feature space. The goal is to convert high-dimensional data into low-dimensional data while preserving as much important information as possible. This simplifies the data structure, reduces computational effort, and eliminates correlations between features, further improving storage space utilization.

[0057] S102: According to the current environmental parameters of the flight simulation device, all operating points that meet the current environmental parameters are screened out from the steady-state database.

[0058] In this step, based on the current environmental parameters of the flight simulator, all operating points that meet these parameters are identified from the steady-state database. This focuses attention on operating points that match the current actual environment. This eliminates interference from other operating points unrelated to the current environment, making subsequent analysis and calculations more accurate and efficient. This step improves the efficiency of selecting target operating points, reduces unnecessary calculations, and improves the consistency of balancing results with the actual environment, avoiding trim inaccuracies caused by environmental differences.

[0059] S103: Filtering a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device.

[0060] In this step, among the operating points that meet the current environmental parameters, multiple target operating points are selected based on the target thrust required for balancing.

[0061] The target thrust is used to further filter the operating points in step S102, obtaining operating points directly related to achieving the trim target. By using the target thrust as a screening criterion, specific operating conditions that are likely to achieve a trim state under the current circumstances can be identified, providing a more precise basis for determining the final target throttle lever angle. This makes the trim process more targeted, enabling more accurate identification of operating points that approach or meet the trim requirements, laying the foundation for precise trimming.

[0062] It should be noted that when the flight simulation equipment is trimmed, the thrust that the engine needs to achieve is calculated as the target thrust.

[0063] S104: Determine a target throttle lever angle required for the flight simulation device to reach a trim state based on the thrusts and throttle lever angles corresponding to the plurality of target operating points, and backdrive the engine based on the target throttle lever angle to complete engine trim.

[0064] In this step, a suitable target throttle lever angle is determined by comprehensively considering information from multiple target operating points. The engine is then back-driven to adjust its operating state to a trimmed state that meets the requirements of the flight simulator. When determining the target throttle lever angle, the target throttle lever angle required to achieve a trimmed state for the flight simulator is calculated based on the thrust and throttle lever angles corresponding to the multiple target operating points. Back-driving the engine based on this angle completes engine trim, enabling the flight simulator's engine to operate at the set target thrust under the current conditions. This ensures stable operation of the simulator and improves the realism and accuracy of the flight simulation.

[0065] Specifically, determining a target throttle lever angle required for the flight simulation device to reach a trim state based on the thrusts and throttle lever angles corresponding to the plurality of target operating points includes:

[0066] From the multiple target operating points, the two closest to the target thrust are selected. Based on the thrust and throttle lever angles corresponding to each of these two operating points, a reverse interpolation method is used to determine the target throttle lever angle. This reverse interpolation method directly approaches the target, avoiding the latency of existing engine dynamic models. This reduces the engine trimming time from 10-15 seconds to 1-2 seconds.

[0067] Specifically, among the multiple selected target operating points, find the two operating points closest to the target thrust. This can be done by calculating the absolute difference between the thrust at each operating point and the target thrust, selecting the two operating points with the smallest difference, and determining the corresponding throttle lever angles X1 and X2, and the corresponding thrusts F1 and F2, respectively.

[0068] Use the linear interpolation formula to calculate the target throttle stick angle X' corresponding to the target thrust Ftarget. The linear interpolation formula is: X'=X1+(X2-X1)·(Ftarget-F1) / (F2-F1), F1 <Ftarget<F2。

[0069] Furthermore, the calculated target throttle stick angle needs to be checked for plausibility, for example, to ensure it is within the valid range of throttle stick angles (e.g., between 0 and the maximum throttle angle). If it is not within the valid range, a more complex interpolation function needs to be used, the range of the selected operating points needs to be expanded, or other factors need to be considered to correct the target throttle stick angle.

[0070] Based on the above-mentioned flight simulator engine trim method embodiment, the target throttle lever angle can also be simulated and verified to obtain a simulation verification value. Before actually operating the engine, the rationality and feasibility of the target throttle lever angle can be verified in a simulated environment.

[0071] Specifically, the target throttle stick angle is simulated and verified to obtain a verification value of the simulation verification, including:

[0072] The target throttle lever angle and the current environmental parameters are input into a preset engine dynamic model to obtain an actual thrust corresponding to the target throttle lever angle; and a difference ratio between the actual thrust and the target thrust is determined as a verification value for simulation verification.

[0073] By inputting the target throttle lever angle and current environmental parameters into the simulation model, a single-step simulation is performed to achieve steady-state engine thrust (simulation time 10ms). The forward-verified thrust, Fcalc, corresponding to the target throttle lever angle, is then calculated. The simulation verification value, V, is calculated based on the actual thrust Fcalc, where V = (Fcalc - Ftarget) / Ftarget. This verification value is compared with a preset threshold to provide a basis for subsequent decision-making.

[0074] A determination is made based on a comparison result between the verification value and a preset threshold value as to whether to backdrive the engine based on the target throttle lever angle. If the verification value is determined to be less than or equal to the preset threshold value, the engine is backdriven based on the target throttle lever angle. If the verification value is determined to be greater than the preset threshold value, the target throttle lever angle is corrected, and the engine is backdriven based on the corrected target throttle lever angle.

[0075] If the verification value is less than or equal to the preset threshold, that is, if V ≤ 0.5%, it means that the target throttle stick angle performs well in the simulation and can meet certain performance requirements or error ranges. In this case, the engine can be directly backdriven based on this angle, that is, the actual operation of the engine can be controlled according to this angle to achieve the expected operating state.

[0076] By comparing the verified value with a preset threshold, untested engine operations are avoided, mitigating risk. An inappropriate target throttle lever angle can lead to poor engine performance, damage, or even safety issues. Simulation verification can proactively identify and prevent these adverse consequences, improving engine control accuracy and reliability. Backdrive is only performed when the verified value meets requirements, ensuring that the throttle lever angle input to the engine is verified and feasible, contributing to stable and efficient engine operation.

[0077] If the verification value is greater than the preset threshold, that is, if V>0.5%, it means that the target throttle stick angle fails to meet the expected performance requirements in the simulation or the error range is too large, and correction is required.

[0078] Specifically, the target throttle stick angle is corrected, including:

[0079] An angle compensation coefficient is generated according to the target throttle lever angle and the target thrust; and the target throttle lever angle is compensated based on the angle compensation coefficient to obtain a corrected target throttle lever angle.

[0080] The angle compensation coefficient S is generated by the following formula:

[0081] ;

[0082] in, is the throttle stick angle before correction, i.e. the target throttle stick angle; Target thrust, is the relationship function between thrust and throttle lever, It is the derivative of the function of the relationship between thrust and throttle lever, that is, thrust sensitivity.

[0083] The target throttle stick angle is compensated using the following formula:

[0084] ;

[0085] in, is the corrected throttle stick angle. It should be noted that each adjustment , the maximum number of iterations is 2 to avoid overshoot and ensure that the total time is < 200ms.

[0086] By correcting the target throttle lever angle, it is made closer to the actual required angle. The engine is then back-driven based on the corrected angle. This ensures that the engine can operate under a more appropriate throttle lever angle control to achieve better performance and working conditions. Even if there is a deviation in the initially calculated target throttle lever angle, it can be corrected to make it more in line with actual needs, ensuring that the engine can operate as close to the ideal state as possible under various conditions. This improves the performance and stability of the engine. This embodiment can correct the angle based on the results of simulation verification, effectively handle different operating conditions and possible errors, and improve the reliability and adaptability of the entire engine control system.

[0087] 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.

[0088] The second embodiment of the present application provides a flight simulation device engine trim system, comprising:

[0089] A database module is used to establish a steady-state database for the flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle and multiple preset environmental parameters at different operating points;

[0090] A first screening module is configured to screen out all operating condition points that meet the current environmental parameters of the flight simulation device in the steady-state database;

[0091] a second screening module, configured to screen a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device;

[0092] The trim module is used to determine the target throttle lever angle required for the flight simulation device to reach a trim state based on the thrust and throttle lever angle corresponding to the multiple target operating points, and to backdrive the engine based on the target throttle lever angle to complete the engine trim.

[0093] In an optional embodiment, the balancing system of the engine of the flight simulation device further includes:

[0094] a verification module, configured to perform simulation verification on the target throttle lever angle to obtain a verification value of the simulation verification, and if it is determined that the verification value is less than or equal to a preset threshold, backdrive the engine based on the target throttle lever angle;

[0095] The correction module is configured to correct the target throttle lever angle if it determines that the verification value is greater than a preset threshold, and backdrive the engine based on the corrected target throttle lever angle.

[0096] In an optional embodiment, the verification module includes:

[0097] The verification unit is configured to input the target throttle lever angle and the current environmental parameters into a preset engine dynamic model to obtain an actual thrust corresponding to the target throttle lever angle; and determine a difference ratio between the actual thrust and the target thrust as a verification value for simulation verification.

[0098] In an optional embodiment, the correction module includes:

[0099] The correction unit is configured to generate an angle compensation coefficient according to the target throttle lever angle and the target thrust; and compensate the target throttle lever angle based on the angle compensation coefficient to obtain a corrected target throttle lever angle.

[0100] In an optional embodiment, the database module includes:

[0101] The database unit is used to discretize the area within the flight envelope corresponding to the flight simulation device into multiple operating points, collect the engine thrust, throttle lever angle and multiple preset environmental parameters at each operating point, and establish a multi-dimensional mapping relationship between the engine thrust, throttle lever angle and multiple preset environmental parameters corresponding to each operating point.

[0102] In an optional embodiment, the balancing module includes:

[0103] The balancing unit is used to select two operating points closest to the target thrust from the multiple target operating points; and to obtain the target throttle lever angle by using a reverse interpolation method based on the thrust and throttle lever angle corresponding to the two operating points.

[0104] In an optional embodiment, the environmental parameters include at least: flight altitude, ambient temperature and airspeed.

[0105] 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.

[0106] It should be noted that the engine trim system for the flight simulation device provided in the above embodiment is merely illustrated by the division of the above functional modules. In actual applications, the above 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 embodiment 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 on the present invention.

[0107] An electronic device according to a third embodiment of the present invention includes:

[0108] at least one processor;

[0109] and a memory communicatively coupled to at least one of said processors;

[0110] 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 balancing method for the engine of the flight simulation device.

[0111] A fourth embodiment of the present invention provides a computer-readable storage medium, wherein the computer-readable storage medium stores computer instructions, and the computer instructions are configured to be executed by the computer to implement the aforementioned flight simulation device engine trim method.

[0112] 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 storage device and processing device described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0113] 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.

[0114] 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.

[0115] 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.

[0116] 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.

[0117] 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.

[0118] 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).

[0119] 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.

[0120] The terms "first", "second", etc. are used to distinguish similar objects, rather than to describe or indicate a particular order or sequence.

[0121] 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.

[0122] 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 will be 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 balancing an engine of a flight simulation device, characterized in that: include: Establishing a steady-state database for a flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle, and a plurality of preset environmental parameters at different operating points; According to the current environmental parameters of the flight simulation device, all operating condition points that meet the current environmental parameters are screened out in the steady-state database; screening a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device; The target throttle lever angle required for the flight simulation device to reach a trim state is determined based on the thrust and throttle lever angle corresponding to the plurality of target operating points, and the engine is backdriven based on the target throttle lever angle to complete the engine trim.

2. The flight simulation device engine trim method according to claim 1, wherein: Also includes: performing simulation verification on the target throttle lever angle to obtain a verification value of the simulation verification, and determining that the verification value is less than or equal to a preset threshold, then backdriving the engine based on the target throttle lever angle; If it is determined that the verification value is greater than a preset threshold, the target throttle lever angle is corrected, and the engine is backdriven based on the corrected target throttle lever angle.

3. The flight simulation device engine trim method according to claim 2, wherein: The performing simulation verification on the target throttle lever angle to obtain a verification value of the simulation verification includes: Inputting the target throttle lever angle and the current environmental parameters into a preset engine dynamic model to obtain an actual thrust corresponding to the target throttle lever angle; The difference ratio between the actual thrust and the target thrust is determined as a verification value of the simulation verification; the difference ratio=(actual thrust−target thrust) / target thrust.

4. The flight simulation device engine trim method according to claim 2, wherein: Correcting the target throttle stick angle includes: generating an angle compensation coefficient according to the target throttle lever angle and the target thrust; The target throttle lever angle is compensated based on the angle compensation coefficient to obtain a corrected target throttle lever angle.

5. The flight simulation device engine trim method according to claim 1, characterized in that: The step of establishing a steady-state database for the flight simulation device includes: The region within the flight envelope corresponding to the flight simulation device is discretized into a plurality of operating points, the thrust of the engine, the throttle lever angle, and a plurality of preset environmental parameters at each of the operating points are collected, and a multidimensional mapping relationship is established between the thrust of the engine, the throttle lever angle, and the plurality of preset environmental parameters corresponding to each of the operating points.

6. The flight simulation device engine trim method according to claim 1, characterized in that: Determining the target throttle lever angle required for the flight simulation device to reach a trim state based on the thrusts and throttle lever angles corresponding to the plurality of target operating points includes: Selecting two operating points closest to the target thrust from among the plurality of target operating points; According to the thrust and throttle lever angle corresponding to the two operating points, the reverse interpolation method is used to solve and obtain the target throttle lever angle.

7. The flight simulation device engine trim method according to claim 1, characterized in that: The environmental parameters include at least: flight altitude, ambient temperature and airspeed.

8. A flight simulation equipment engine trim system, characterized in that: include: A database module is used to establish a steady-state database for the flight simulation device; wherein the steady-state database stores a multi-dimensional mapping relationship between the engine thrust, throttle lever angle and multiple preset environmental parameters at different operating points; A first screening module is configured to screen out all operating condition points that meet the current environmental parameters of the flight simulation device in the steady-state database; a second screening module, configured to screen a plurality of target operating points from all operating points that meet the current environmental parameters according to the target thrust required for trimming the flight simulation device; The trim module is used to determine the target throttle lever angle required for the flight simulation device to reach a trim state based on the thrust and throttle lever angle corresponding to the multiple target operating points, and to backdrive the engine based on the target throttle lever angle to complete the engine trim.

9. An electronic device, characterized in that: include: at least one processor; and a memory communicatively coupled to at least one of said processors; 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 balancing method of the flight simulation device engine according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to be executed by the computer to implement the balancing method for the engine of the flight simulation device according to any one of claims 1 to 7.

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