Airplane weight and balance calculation system and method

Abstract

The application discloses an aircraft weight and gravity center calculation system and method, which comprises a hardware part and a software part. The hardware part is composed of multiple wireless weighing devices integrated with weighing sensors, signal conditioning modules and data transmitters, wireless receivers and portable industrial control terminals. The software part is deployed on the industrial control terminal, adopts a layered architecture, and comprises a multi-model parameter adaptive module, a dynamic moment compensation module and a gravity center calculation module. The system realizes the decoupling of model parameters and calculation logic through a model configuration table in JSON format, supports adaptive moment compensation in a few-piece / multi-piece state, and has the functions of structured storage of weighing data and standardized export. The application solves the problems of low calculation efficiency, easy errors and poor multi-model adaptability of the existing aircraft weighing manual calculation, significantly improves the calculation efficiency, reduces human errors, realizes multi-model adaptive management and standardized data management, and is suitable for rapid determination of weight and gravity center in the process of aircraft maintenance and manufacturing.

Description

Technical Field

[0001] This invention relates to the field of aviation maintenance technology, and in particular to an aircraft weight and center of gravity calculation system and method. Background Technology

[0002] Aircraft weight and center of gravity are core technical indicators in the entire life cycle management of aircraft, and their changes directly affect the aircraft's flight performance, maneuverability, takeoff and landing safety, and fuel economy. During aircraft manufacturing, repair, modification, and routine maintenance, it is necessary to frequently measure and verify the aircraft's weight and center of gravity. Currently, the methods for processing weight and center of gravity data in aircraft repair shops and maintenance units remain relatively outdated. According to research, approximately 80% of the work currently relies on manual calculations, while 20% uses Excel spreadsheets for semi-automatic calculations. Specifically, operators need to manually record the weight data of each weighing point, then calculate the center of gravity position item by item using calculators or Excel formulas based on aircraft parameters and measuring point coordinates, and finally fill in the relevant technical forms. This traditional method has the following technical drawbacks: Low processing efficiency: The weighing data processing flow for a single aircraft typically includes multiple steps such as data recording, manual calculation, cross-checking, and form filling, taking a total of about 60 minutes, which is difficult to meet the needs of batch and high-frequency maintenance operations. High risk of human error: Manual entry of weighing data, manual substitution of formulas, and manual editing of spreadsheets can easily introduce recording errors, formula errors, or calculation deviations, and there is a lack of effective real-time verification mechanisms. Poor compatibility with multiple models: Different weighing scales have different weighing point layouts, coordinate references, correction coefficients, and other parameters. Under the current method, each time the model is changed, the parameters need to be manually searched and the calculation formulas adjusted again, which is cumbersome, error-prone, and lacks an adaptive parameter management mechanism. Lack of a standardized data management system: Weighing records are mostly stored in paper or scattered electronic documents, making it difficult to quickly query, compare and analyze historical data and trace quality, which is not conducive to monitoring aircraft weight change trends and supporting maintenance decisions. On-site operations are constrained by cables: Traditional weighing equipment mostly uses wired connections between sensors and terminals. In maintenance workshops or outdoor environments, cable laying is difficult, easily damaged, and inconvenient to move, reducing operational flexibility. In addition, although some existing digital weighing systems have achieved electronic data acquisition, their software is usually strongly coupled with specific aircraft models. Expanding to new aircraft models requires redevelopment or code modification, resulting in high maintenance costs. At the same time, for aircraft in an "incomplete state" (lacking or additionally installed certain components) due to maintenance procedures, there is a lack of a universal dynamic torque compensation mechanism, leading to large deviations in center of gravity calculation. Summary of the Invention

[0003] The main objective of this invention is to provide an aircraft weight center of gravity calculation system and method, which aims to solve existing technical problems.

[0004] To achieve the above objectives, the present invention provides an aircraft weight and center of gravity calculation system, comprising: Multiple wireless weighing devices, each integrating a weighing sensor, a signal conditioning module and a data transmitter, are used to sense the weight signal of the corresponding measuring point when lifting the aircraft, and then convert it into a digital signal and transmit it wirelessly. A wireless receiver, connected to a portable industrial control terminal device, is used to receive digital signals sent by the plurality of wireless weighing devices; Portable industrial control terminal equipment, equipped with weight and center of gravity calculation software; Deployed in the portable industrial control terminal device, including: The multi-model parameter adaptive module is used to decouple model parameters from calculation logic. It integrates and stores parameters of multiple models in JSON format through a model configuration table, and adaptively calls the corresponding model parameters when the user selects a model category. The dynamic torque compensation module is used to introduce an adaptive compensation factor to dynamically compensate for the torque of missing or multiple parts when the aircraft is in an incomplete state. The center of gravity calculation module is used to automatically calculate the weight and center of gravity of the aircraft based on the digital signal, the parameters of the selected aircraft model, and the compensation results.

[0005] Furthermore, the wireless weighing device is a movable columnar structure with a spherical dome at the top and a hydraulic jack at the bottom. The weighing sensor, signal conditioning module, and data transmitter are integrated inside the columnar structure. The aircraft is weighed in a horizontal position by adjusting the height of the hydraulic jack.

[0006] Furthermore, the hardware component uses Giant520 weighing modules to construct a multi-channel sensor data processing system, employing a single-module parallel multi-channel sensor and multi-module Modbus networking architecture; the software accurately parses the weighing data and calibration parameters output by the Giant520 module through the Modbus protocol.

[0007] Furthermore, the wireless weighing device and the wireless receiver use a 433MHz wireless communication interface for data transmission. This wireless communication interface is connected to the Giant520 weighing module based on an RS485 bus, forming a wireless weighing communication link that is resistant to electromagnetic interference.

[0008] Furthermore, the software component adopts a layered architecture, comprising an application layer, a business logic layer, and a data layer from top to bottom, with communication between layers via interfaces; wherein, The application layer includes a graphical user interface module, which provides functions such as device selection, data entry, result display, historical query, and file export. The business logic layer includes the multi-model parameter adaptive module, the dynamic torque compensation module, and the center of gravity calculation module; The data layer includes a data management module, which is used to realize the structured storage and standardized export of weighing data.

[0009] Furthermore, the dynamic torque compensation module adopts the equivalent weight-torque substitution principle and achieves torque compensation in the case of fewer or more parts through the following formula: ; in, For torque values ​​of fewer or more parts, Weight for fewer or more items.

[0010] Furthermore, the center of gravity calculation module adopts the center of gravity calculation formula in the wing coordinate system, substitutes the correction coefficients specific to the aircraft model, and outputs the center of gravity position as a percentage of the wing's mean aerodynamic chord; the correction coefficients include weight distribution correction coefficients, lateral moment compensation coefficients, and comprehensive error correction values.

[0011] A method for calculating the center of gravity of an aircraft based on the above system includes the following steps: Configure and store model parameters for multiple machine types, decoupling the model parameters from the computing logic; The weight data of multiple measuring points on the aircraft is collected by multiple wireless weighing devices and transmitted wirelessly to a portable industrial control terminal. Responding to the user's selected device type, the corresponding device parameters are automatically retrieved. Determine whether the aircraft is in an incomplete state with missing or extra parts. If so, introduce an adaptive compensation factor to dynamically compensate for the torque. Based on the collected weight data, the called aircraft model parameters, and the compensated torque, the total weight and center of gravity of the aircraft are automatically calculated. The calculated weight and center of gravity results are stored in a structured manner and / or exported in a standardized manner.

[0012] Furthermore, when collecting weight data, the Giant520 weighing module parses multi-channel sensor data based on the Modbus protocol and performs three levels of verification: built-in AD filtering and anti-shake to filter out noise, static detection and zero-point tracking to eliminate vibration and drift, and software range and consistency verification to eliminate abnormal data.

[0013] Furthermore, the multi-model parameter adaptive calling specifically involves: storing the parameters of each model in JSON format to form a model configuration table; when the user selects a model category, the software reads the parameters of the corresponding model from the configuration table and directly inputs them into the centroid algorithm for calculation.

[0014] The beneficial effects of this invention are reflected in: This invention significantly reduces processing time by automatically collecting weighing data, automatically calling machine parameters via software, and automatically calculating weight and center of gravity and exporting results.

[0015] This invention uses digital signal acquisition to replace manual reading, and the center of gravity calculation is automatically performed by a fixed algorithm module, avoiding errors from manual recording, formula substitution, and Excel formula editing. The software further incorporates the decimal high-precision arithmetic library to ensure floating-point operation accuracy. Simultaneously, the data acquisition end uses a three-level verification mechanism to eliminate abnormal data, guaranteeing the accuracy and repeatability of the calculation results.

[0016] This invention decouples aircraft model parameters from computational logic, integrating multiple aircraft model parameters through a JSON-formatted aircraft model configuration table. Users only need to select the aircraft model category in the interface, and the system can adaptively call the corresponding coordinate reference, correction coefficients, and other parameters, directly inputting them into the centroid algorithm without modifying the core code or redeveloping the software. For expansion to new aircraft models, only one record needs to be added to the configuration table, greatly reducing the system's maintenance and upgrade costs. This invention addresses the common "incomplete state" of aircraft during maintenance. It introduces an adaptive compensation factor based on the principle of "equivalent weight-torque substitution," automatically compensating for the weight and torque of missing or redundant parts during center of gravity calculation. This mechanism ensures that the calculation results accurately reflect the aircraft's center of gravity in its complete or actual operational state, avoiding calculation errors caused by process retention and improving the system's applicability in complex maintenance environments. This invention uses JSON format to structure and store all historical weighing records, supporting record querying, filtering, deletion, backup, and recovery. It also provides standardized Excel export functionality, facilitating integration with existing maintenance management systems or the generation of technical reports. This standardized data management provides reliable data support for trend analysis of aircraft weight and center of gravity changes, quality traceability, and maintenance decision-making. The hardware of this invention employs a wireless communication design, possessing strong anti-electromagnetic interference and penetration capabilities, making it suitable for complex electromagnetic environments such as those involving frequency converters and avionics equipment in aircraft repair shops. The wireless transmission distance can reach over 100 meters, eliminating the constraints of cables. The weighing device is designed as a movable columnar structure, used in conjunction with a hydraulic jack, making it portable and quick to deploy, significantly improving operational flexibility in field and workshop environments. This invention's software adopts a layered architecture and modular design (application layer, business logic layer, and data layer). Each module has a clear responsibility and is loosely coupled, facilitating subsequent functional expansion (such as adding new models or report templates). Developed using Python and PySide6, it has cross-platform capabilities and can be deployed on multiple operating systems such as Windows, Linux, and macOS, adapting to the IT environments of different maintenance units. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the software structure of the aircraft weight and center of gravity calculation system of the present invention; Figure 3 This is a schematic diagram of the aircraft weight and center of gravity calculation process of the present invention; Figure 4 This is a schematic diagram of the design process for calculating the weight and center of gravity of the aircraft according to the present invention. Figure 5 This is a schematic diagram of the hardware connection structure for calculating the aircraft weight and center of gravity of the present invention.

[0018] Explanation of reference numerals in the attached figures: 1. Wireless weighing device; 2. Wireless receiver; 3. Portable industrial control terminal equipment. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] This embodiment provides an aircraft weight and center of gravity calculation system, which consists of hardware and software components working together.

[0021] Please see Figure 1 and Figure 4 The hardware consists of three wireless weighing devices 1, one wireless data receiver 2, and one portable industrial control terminal device 3 (such as a ruggedized laptop or industrial tablet). Each wireless weighing device integrates a load cell, signal conditioning circuit, power supply, and data transmitter. The overall design is a movable cylindrical structure with a spherical top and a hydraulic jack at the bottom. The wireless data receiver connects to the portable industrial control terminal device via a USB interface.

[0022] Please see Figure 2The software is deployed on portable industrial control terminal equipment, developed using Python 3.9, based on the PySide6 graphical user interface framework, and runs on the Windows 10 operating system. The software adopts a layered architecture, divided from top to bottom into the application layer (graphical user interface module), the business logic layer (multi-model parameter adaptive module, dynamic torque compensation module, center of gravity calculation module), and the data layer (data management module).

[0023] Before weighing the aircraft, the operator places three wireless weighing devices at three preset weighing points on the aircraft (e.g., the corresponding positions of the left main wheel, right main wheel, and nose or tail wheel). A hydraulic jack is inserted into the bottom of each weighing device, with the spherical jack at the top contacting the aircraft's predetermined weighing point. The operator simultaneously adjusts the height of the three hydraulic jacks until the aircraft is level (this can be determined using a bubble level or the aircraft's own level indicator).

[0024] Each wireless weighing device contains a load cell (resistive strain gauge sensor) that converts the weight of the aircraft it bears into a millivolt-level analog electrical signal. This signal is sent to a signal conditioning circuit, amplified, filtered, and then converted into a digital weight value by a 24-bit analog-to-digital converter. This digital value is then transmitted periodically via a data transmitter (433MHz wireless module) with a broadcast period set to 100ms to ensure real-time performance.

[0025] The wireless data receiver receives data frames from three weighing devices. Each frame contains the device address (e.g., Addr1, Addr2, Addr3), the weight value, battery level, and a checksum. The receiver then transmits the parsed data to the software system of the portable industrial control terminal device via a USB virtual serial port. The transmission protocol uses the Modbus RTU simplified format, with a baud rate of 115200 bps, 8 data bits, 1 stop bit, and no parity check.

[0026] The core hardware of this embodiment uses three Giant520 weighing modules, each connected in parallel to three 350Ω load cells (corresponding to three-point support at the same weighing point, improving stability). The three modules form a Modbus network via an RS485 bus, with each module assigned an independent slave address (0x01, 0x02, 0x03). Each module has a built-in 24-bit Σ-Δ ADC with a sampling frequency of 10Hz, and digital filtering and anti-jitter functions are enabled to filter out aircraft engine vibration or mechanical noise transmitted from the ground.

[0027] At the data parsing level, the software reads the original AD value and internal calibration coefficients (range coefficient, zero point coefficient) from the holding register of each Giant520 module via the Modbus protocol, and converts the AD value into a standard weight value (unit: kilogram) according to the following engineering conversion formula: W=(A Draw ZERO coef )×(Range / AD max )×SCALE; Among them, A Draw For the original AD reading, ZERO coef This is the zero-point coefficient. Range is the sensor's measurement range (e.g., 5000 kg), AD max The full-scale AD value is (2^24-1), and SCALE is the correction factor (determined by metrological calibration).

[0028] To ensure data reliability, this embodiment implements a three-level verification mechanism: Level 1 (Hardware Level): Utilizing the Giant520 module's built-in 24-bit ADC, low-pass digital filtering, and anti-jitter functions, high-frequency noise and contact jitter are suppressed at the source.

[0029] Level 2 (Signal Level): The software collects 10 consecutive data packets and calculates the static detection index. If the weight change of 50 consecutive sampling points (within 5 seconds) does not exceed ±0.5kg, it is determined to be a static working condition. The zero-point tracking algorithm is activated. When the weight value deviates from the initial zero point for a long period of time by more than ±2kg, the zero-point offset is automatically corrected to eliminate the influence of tooling deformation or temperature drift.

[0030] Level 3 (Software Level): Perform consistency verification on the three sensor values ​​of each module. If the range of the three values ​​exceeds the preset threshold (e.g., 5% of the maximum value), the weighing posture is determined to be abnormal and the operator is prompted to readjust the jack. At the same time, perform timing verification to detect data packet loss or timestamp jumps and remove abnormal frames.

[0031] This embodiment utilizes a hybrid interface of 433MHz low-frequency wireless communication and RS485 wired communication in an aircraft repair workshop (containing strong electromagnetic interference sources such as frequency converter power supply vehicles and avionics equipment). Specifically, the wireless links from the three sets of wireless weighing devices to the wireless receivers use the 433MHz frequency band, with a transmit power set to 10dBm. The communication distance can reach 1km in open conditions, and it can still operate stably within a 50-meter range after penetrating metal skin and tooling inside the workshop. The wireless receivers are connected to portable industrial control terminals via an RS485 bus (using twisted-pair shielded cable), with a differential signal transmission distance of up to 1200 meters, ensuring reliability for deployment across aircraft positions in a large hangar. Compared with conventional WiFi or Bluetooth, this combined communication method has a measured packet loss rate of less than 0.1% and a reconnection time of less than 1 second, meeting high reliability requirements.

[0032] This embodiment completely decouples aircraft model parameters from calculation logic. A folder named ` / config / aircraft_models / ` is created in the software installation directory, containing parameter files for each aircraft model in JSON format. The filenames are the aircraft model codes (e.g., "C_130.json", "B737.json"). The content structure of each JSON file is shown in the example below: json { "model_name":"C-130 transport aircraft", "coordinate_base":{ "X_B":0.0, "Y_B":0.0,"rotation_angle_deg":4.0 }, "Correction factor":{ "weight_distribution_factor":0.997564, "lateral_moment_factor":0.069756, "comprehensive_error_correction":0.111944, "lateral_correction_Y_T":0.0 }, "mean_aerodynamic_chord":3.451, "sensor_points":[ {"name":"left_main","X_i":2.5,"Y_i":1.8}, {"name":"right_main","X_i":2.5,"Y_i":-1.8}, {"name":"nose","X_i":-5.2,"Y_i":0.0} ] }

[0033] After the user selects an aircraft model from the dropdown menu in the graphical user interface, the software calls the `load_aircraft_model(model_code)` function to dynamically read the corresponding JSON file and cache the parameters. When the user imports weighing data or manually enters the weight of each measuring point, the center of gravity calculation module directly obtains the coordinates and correction coefficients from the cache without modifying any core algorithm code. If a new aircraft model needs to be added, simply create a new JSON file according to the template, place it in the configuration folder, and the software will automatically scan and update the dropdown list upon startup, enabling hot-swappable aircraft model expansion.

[0034] The software in this embodiment performs the following calculation process: Please refer to... Figure 3 ; Step 1: Obtain raw data. Read the weight values ​​G1, G2, and G3 (unit: kg) of the three wireless weighing devices via serial port, corresponding to the left main wheel, right main wheel, and front wheel (or rear wheel) respectively. Users can also manually enter the weighing data in the input boxes on the interface as an alternative input method.

[0035] Step 2: Weight Accumulation and Verification - Calculate the total aircraft weight G total =G1+G2+G3. The software compares the total weight with the maximum takeoff weight preset in the aircraft configuration file. If it exceeds the reasonable range, a warning will be issued.

[0036] Step 3: Calculation of the center of gravity in the fuselage coordinate system. Calculate the preliminary coordinates (X) of the center of gravity according to formulas (1) and (2). T ,Y T ): X T = (G1·X1+G2·X2+G3·X3) / (G1+G2+G3); Y T = (G1·Y1+G2·Y2+G3·Y3) / (G1+G2+G3); Where (X) i ,Y i ) represents the fuselage coordinates (in meters) of the corresponding sensor point read from the aircraft configuration file.

[0037] Step 4: If there are missing or extra parts, perform dynamic torque compensation. When the aircraft is in an "incomplete state" (e.g., without seats, avionics, or additional test fixtures), the operator checks "Enable Missing / Extra Part Compensation" on the interface and enters the weight (g) of the missing / extra part respectively. k and its centroid coordinates z k (Or select from the preset component library). The software then uses formula (11) for compensation: ; Compensated X T,comp Replace the original XT Participate in subsequent calculations. For multiple cases, g k Take a positive value and the torque value ∑g k z k It also takes a positive value; for cases where parts are missing, the software logic treats them as weight and torque that need to be "replaced" and adds them in the calculation so that the final center of gravity reflects the value in the complete state.

[0038] Step 5: Transform to wing coordinate system and output percentage center of gravity. Obtain the reference transformation parameter X from the aircraft configuration. B ,Y B And the rotation angle (e.g., 4° for a certain model), according to formula (5) (X T ,Y T Convert to coordinates in the wing coordinate system (X) T0 ,Y T0 ): X T0 =(X T X B )cos4°+(Y B Y T sin4°; Then, the mean aerodynamic chord length CA (read from the configuration, such as 3.451 meters) is converted to a percentage: X T0 =XT0 / CA×100%; The final center of gravity position is displayed and stored in the form of "XX%MAC".

[0039] Step 6: Simplified Calculation of Aircraft Model Correction Factors To improve on-site calculation efficiency, this embodiment pre-sets simplified formulas for specific aircraft models. For example, for a certain type of transport aircraft, substituting the specific values ​​yields formula (6) and the final formula (10): X T0 =0.997564X T 0.069756Y T 0.111944; X T0 = (0.997564X T 0.161331) / (3.451) × 100%; The software can automatically identify the model and select between the full conversion formula or the simplified formula to ensure that the calculation accuracy is consistent with the manual.

[0040] The data management module in this embodiment implements a lightweight database based on a JSON file system. After each weighing, the software automatically generates a record containing the following fields: record ID (UUID), timestamp (ISO format), machine model code, operator, weight at each measuring point, total weight, center of gravity percentage (MAC%), whether compensation is enabled, list of compensation components, and original data checksum. This record is appended to the file / data / weighing_records.json, with each record being an element of a JSON array.

[0041] Users can filter by date range, machine type, or operator through the "Historical Query" panel in the graphical user interface. Query results are displayed in a table format, supporting multi-select deletion and backup export. The backup function copies all current records to the backup_YYYYMMDD_HHMMSS.json file in the specified directory to prevent data loss.

[0042] The standardized export function uses the openpyxl library to generate Excel reports. The report template includes: basic aircraft information, weighing conditions (temperature, humidity, aircraft level), raw data for each measuring point, weight and center of gravity calculation results, details of missing / excess parts compensation, and operator signature field. The exported Excel file can be directly used for maintenance record archiving or delivered to the customer.

[0043] After the software in this embodiment starts, it displays the main window (QMainWindow), which includes the following areas: Top toolbar: Model selection dropdown menu, weighing data source selection (serial / manual), compensation switch, and component selection button. Central area: Three-channel weighing data display panel (real-time digital and analog dials), total weight display, center of gravity percentage progress bar, and coordinate graph. Right panel: History record list and export operation button. Bottom status bar: Communication status, verification status, and error messages.

[0044] The typical operating procedure is as follows: The user selects the aircraft model (e.g., "C-130"), and the software automatically loads the corresponding configuration. Clicking the "Start Acquisition" button opens the serial port, displays three weight values ​​in real time, and dynamically calculates the center of gravity percentage. After confirming the aircraft is level and the values ​​are stable, clicking the "Lock and Save" button brings up a dialog box asking the user to confirm whether to enable missing / excess component compensation. If compensation is enabled, the missing or added component is selected from the component library list (each component has its weight and center of gravity coordinates pre-stored), or the value is manually entered. The software recalculates the center of gravity after compensation and displays a before-and-after comparison. The user adds notes (e.g., maintenance worker ID number) and clicks "Save Record" to write the data to a JSON file. Selecting "Export Current Record" generates an Excel report and saves it to the specified folder.

[0045] Taking the weighing operation of a certain type of transport aircraft at a maintenance factory as an example: Due to engine replacement, the aircraft's fairing was temporarily not installed (weight 45kg, center of gravity coordinates X=1.2m, Y=0m). Using the system in this embodiment, the operator placed three sets of wireless weighing devices under the landing gear, adjusted the jacks to level the aircraft, selected the aircraft model on the portable industrial control terminal, clicked "collect," and within 5 seconds read the three weights as 3250kg, 3245kg, and 1100kg respectively. The software automatically calculated the total weight as 7595kg, with a center of gravity of 22.3% MAC. Subsequently, the user checked "Missing Parts" on the compensation interface, selected "Fairing" from the parts library, and after automatic compensation by the software, the center of gravity was updated to 23.1% MAC (complete state). The entire process took approximately 2 minutes, while the traditional manual method would take 60 minutes. Comparison with the standard center of gravity data provided by the manufacturer showed a calculation error of less than 0.1% MAC, meeting airworthiness requirements.

[0046] It is understood that the systems, devices, and storage media provided in the embodiments of the present invention correspond to the methods provided in the embodiments of the present invention, and the explanations, examples, and beneficial effects of the relevant content can be referred to the corresponding parts of the above methods.

[0047] In the above embodiments, implementation can be achieved entirely or partially through software, hardware, firmware, or any combination thereof. When implemented using software, it can be implemented entirely or partially as a computer program product. The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, all or part of the processes or functions described in the embodiments of this application are generated. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired (e.g., coaxial cable, fiber optic, digital subscriber line (DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) means. The computer-readable storage medium can be any available medium that a computer can access or a data storage device such as a server or data center that integrates one or more available media. The available medium can be a magnetic medium (e.g., floppy disk, hard disk, magnetic tape), an optical medium (e.g., DVD), or a semiconductor medium (e.g., solid state disk (SSD)).

[0048] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are 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 elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0049] The various embodiments in this specification are described in a related manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions of the method embodiments.

[0050] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft weight and center of gravity calculation system, characterized in that, include: Multiple wireless weighing devices, each integrating a weighing sensor, a signal conditioning module and a data transmitter, are used to sense the weight signal of the corresponding measuring point when lifting the aircraft, and then convert it into a digital signal and transmit it wirelessly. A wireless receiver, connected to a portable industrial control terminal device, is used to receive digital signals sent by the plurality of wireless weighing devices; Portable industrial control terminal equipment, equipped with weight and center of gravity calculation software; Deployed in the portable industrial control terminal device, including: The multi-model parameter adaptive module is used to decouple model parameters from calculation logic. It integrates and stores parameters of multiple models in JSON format through a model configuration table, and adaptively calls the corresponding model parameters when the user selects a model category. The dynamic torque compensation module is used to introduce an adaptive compensation factor to dynamically compensate for the torque of missing or multiple parts when the aircraft is in an incomplete state. The center of gravity calculation module is used to automatically calculate the weight and center of gravity of the aircraft based on the digital signal, the parameters of the selected aircraft model, and the compensation results.

2. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The wireless weighing device is a movable columnar structure with a spherical dome at the top and a hydraulic jack at the bottom. The weighing sensor, signal conditioning module, and data transmitter are integrated inside the columnar structure. The aircraft is weighed in a horizontal position by adjusting the height of the hydraulic jack.

3. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The hardware part uses Giant520 weighing modules to build a multi-channel sensor data processing system, and adopts a single-module parallel multi-channel sensor and multi-module Modbus networking architecture. The software accurately parses the weighing data and calibration parameters output by the Giant520 module via the Modbus protocol.

4. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The wireless weighing device and the wireless receiver use a 433MHz wireless communication interface for data transmission. This wireless communication interface is connected to the Giant520 weighing module based on an RS485 bus, forming a wireless weighing communication link that is resistant to electromagnetic interference.

5. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The software component adopts a layered architecture, comprising, from top to bottom, an application layer, a business logic layer, and a data layer, with communication between layers via interfaces; wherein... The application layer includes a graphical user interface module, which provides functions such as device selection, data entry, result display, historical query, and file export. The business logic layer includes the multi-model parameter adaptive module, the dynamic torque compensation module, and the center of gravity calculation module; The data layer includes a data management module, which is used to realize the structured storage and standardized export of weighing data.

6. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The dynamic torque compensation module adopts the equivalent weight-torque substitution principle and achieves torque compensation in the case of fewer or more parts through the following formula: ； in, For torque values ​​of fewer or more parts, Weight for fewer or more items.

7. The aircraft weight and center of gravity calculation system according to claim 1, characterized in that, The center of gravity calculation module uses the center of gravity calculation formula in the wing coordinate system, substitutes the correction coefficients specific to the aircraft model, and outputs the center of gravity position as a percentage of the wing's mean aerodynamic chord. The correction coefficients include weight distribution correction coefficients, lateral moment compensation coefficients, and comprehensive error correction values.

8. A method for calculating the center of gravity of an aircraft based on the system described in any one of claims 1 to 7, characterized in that, Includes the following steps: Configure and store model parameters for multiple machine types, decoupling the model parameters from the computing logic; The weight data of multiple measuring points on the aircraft is collected by multiple wireless weighing devices and transmitted wirelessly to a portable industrial control terminal. Responding to the user's selected device type, the system adaptively retrieves the corresponding device parameters; Determine whether the aircraft is in an incomplete state with missing or extra parts. If so, introduce an adaptive compensation factor to dynamically compensate for the torque. Based on the collected weight data, the called aircraft model parameters, and the compensated torque, the total weight and center of gravity of the aircraft are automatically calculated. The calculated weight and center of gravity results are stored in a structured manner and / or exported in a standardized manner.

9. The method for calculating the center of gravity of an aircraft according to claim 8, characterized in that, When collecting weight data, the Giant520 weighing module parses multi-channel sensor data based on the Modbus protocol and performs three levels of verification: built-in AD filtering and anti-shake to filter out noise, static detection and zero-point tracking to eliminate vibration and drift, and software range and consistency verification to eliminate abnormal data.

10. The method for calculating the center of gravity of an aircraft according to claim 8, characterized in that, The multi-model parameter adaptive calling method specifically involves storing the parameters of each model in JSON format to form a model configuration table. When the user selects a model category, the software reads the parameters of the corresponding model from the configuration table and directly inputs them into the centroid algorithm for calculation.

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