Unmanned aerial vehicle architecture system

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle architecture system which comprises a center bearing plate assembly, a vehicle arm module, a limiting transmitting assembly, a control module, an environment sensing module and a display module. The center bearing plate is of a sandwich type structure, the machine arms are installed in a dip angle mode through clamps, the limiting launching assembly is provided with an elastic mechanism, the control module analyzes the operation state based on sensor data and adjusts power output and posture strategies, and the environment sensing module monitors air pressure and vibration to adjust the power mode. Loads can be effectively dispersed, stress concentration is reduced, the rigidity and stability of the unmanned aerial vehicle in a high-vibration task are improved, the service life is prolonged, and the flight safety is guaranteed through intelligent regulation and control.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) architecture technology, and more specifically, to a UAV architecture system. Background Technology

[0002] With the continuous development of drone technology, the limitations of traditional single-function drone architecture are gradually becoming apparent. In modern industry, competitive events, and complex mission scenarios, higher demands are being placed on the stability, lightweight design, and modularity of drone systems.

[0003] Currently, most existing drones focus on providing basic flight functions, lacking comprehensive consideration of structural strength and weight balance, modular design, and efficient maintenance. Meanwhile, user demands for drone performance are increasing, such as optimized center of gravity, rapid disassembly, and collaborative operation with other devices, requirements that current technologies have not fully met. Furthermore, with the widespread adoption of carbon fiber composites, high-strength aluminum alloys, and intelligent control systems, drone functionality is no longer limited to a single flight platform but is gradually evolving towards multi-functional integration. However, existing drone architectures still have shortcomings in center plate design, arm connections, and barrel positioning, making it difficult to achieve efficient collaboration and flexible expansion between components. This limitation often necessitates additional structural adjustments or auxiliary equipment when deploying drones in high-mobility or high-vibration environments, increasing the complexity of operation and maintenance.

[0004] Therefore, there is an urgent need to invent a drone architecture system designed to address the performance fluctuations caused by inadequate structural design during long-term operation, which are not adequately considered in existing technologies. Particularly in high-maneuverability missions, localized stress concentrations can affect overall rigidity and service life, thereby posing challenges to flight stability. Summary of the Invention

[0005] In view of this, the present invention proposes an unmanned aerial vehicle (UAV) architecture system, aiming to solve the performance fluctuation problem caused by unreasonable structural design during high-maneuverability operation of UAVs in existing technologies. Especially in long-term high-vibration mission scenarios, local stress concentration may affect the overall rigidity and service life, thereby posing a challenge to flight stability.

[0006] This invention proposes an unmanned aerial vehicle (UAV) architecture system, comprising: The central load-bearing plate assembly consists of two layers of carbon fiber panels connected by several 7075 aerospace aluminum columns to form a sandwich structure. The carbon fiber panels are fixed to the aluminum columns by bolts, and the aluminum columns are distributed in a grid pattern to distribute the load. The robotic arm module is connected to the central support plate assembly via a special fixture. The fixture is made of high-strength aluminum alloy and has positioning holes. The robotic arm is installed at a 3° tilt angle by engaging with the fixture through two holes machined at an angle of 177°. The limiting launch assembly is equipped with an elastic limiting mechanism, which includes a sliding groove centering unit and a spring support unit. The sliding groove centering unit is formed by printing and fixedly connected to the central bearing plate assembly. The spring support unit forms a stable channel by cooperating with the sliding groove centering unit through an industrial-grade spring. The control module is connected to the central support plate assembly, the arm module, the limit launch assembly, and the external terminal equipment, respectively. It is used to analyze the UAV's operating status based on the data collected by the sensors, and adjust the power output parameters and attitude control strategies according to the operating status. The environmental perception module is equipped with a barometric pressure sensor and an accelerometer to monitor changes in the environment in which the UAV is located in real time and adjust the power output mode based on these changes. The display module, which is connected to the control module, is used to present the drone's operating status and key data.

[0007] Furthermore, when the control module analyzes the drone's operational status based on data collected by sensors, it includes: The control module acquires the stress distribution at different locations of the central bearing plate assembly and determines high-stress areas based on stress distributions exceeding a preset stress threshold. The control module determines the first stress characteristic based on the ratio of the strain rate in the high-stress region to a preset strain rate threshold. The control module determines the second stress characteristic based on the difference between the overall average stress of the central bearing plate assembly and the preset average stress threshold. The control module determines the UAV's operating status characteristics based on the sum of the first stress characteristics and the second stress characteristics.

[0008] Furthermore, when the control module adjusts the power output parameters and attitude control strategy based on the characteristics of the UAV's operating status, it includes: If the operating state characteristics are greater than or equal to the preset operating state characteristic threshold, the control module will reduce the power output and adjust the attitude control strategy to a stable mode. If the operating state characteristics are less than the preset operating state characteristic threshold, the control module will maintain the current power output and attitude control strategy unchanged.

[0009] Furthermore, when the environmental perception module adjusts the power output mode based on environmental changes, it includes: The environmental perception module determines the first environmental feature based on the ratio of the change in air pressure to a preset threshold value. The environmental perception module determines the second environmental feature based on the difference between the vibration frequency detected by the accelerometer and the preset vibration frequency threshold. The environmental perception module determines the power adjustment parameters based on the sum of the first environmental feature and the second environmental feature; The environmental perception module adjusts the power output mode based on the power adjustment parameters.

[0010] Furthermore, when the control module adjusts the UAV's operating state in response to operating state characteristics and power adjustment parameters, it includes: If the operating status characteristics and power adjustment parameters are both greater than the preset threshold, the control module will reduce the power output and activate the auxiliary stabilization device for active correction. If the operating status characteristics are less than the preset threshold and the power adjustment parameter is greater than the preset threshold, the control module will only reduce the power output. If both the operating status characteristics and the power adjustment parameters are less than the preset threshold, the control module will maintain the current operating status.

[0011] Furthermore, when the control module adjusts the UAV's operating status based on operating status characteristics and power adjustment parameters, it includes: The control module determines the first operating factor based on the ratio of the operating state characteristics to the preset operating state characteristic threshold; The control module determines the second operating factor based on the ratio of the power adjustment parameter to the preset power adjustment parameter threshold. The control module determines the comprehensive operating parameters of the UAV based on the sum of the first operating factor and the second operating factor; The control module adjusts the power output and attitude control strategy based on the comprehensive operating parameters.

[0012] Furthermore, when the control module adjusts the power output and attitude control strategy based on comprehensive operating parameters, it includes: If the overall operating parameters are greater than or equal to the preset overall operating parameter threshold, the control module will reduce the power output and adjust the attitude control strategy to a stable mode. If the overall operating parameters are less than the preset overall operating parameter threshold, the control module will maintain the current power output and attitude control strategy unchanged.

[0013] Furthermore, when the overall operating parameters of the UAV do not meet the preset standards, the control module determines whether to activate the auxiliary stabilization device based on preset operating state characteristic thresholds and current operating state characteristics, including: If the preset operating state characteristic threshold is less than or equal to the current operating state characteristic, the control module will activate the auxiliary stabilization device. If the preset operating state characteristic threshold is greater than the current operating state characteristic, the control module will not activate the auxiliary stabilization device.

[0014] Furthermore, it also includes: The fault warning module, which is connected to the control module, is used to monitor the operating status of the UAV and determine whether there are potential risks based on the operating status characteristics and power adjustment parameters. If a potential risk exists, the fault warning module generates a warning message and sends it to an external terminal device via the communication module.

[0015] Compared with existing technologies, the advantages of this invention are as follows: By employing a sandwich-style central support plate structure formed by upper and lower carbon fiber panels and 7075 aerospace aluminum pillars, the overall structure possesses the advantages of lightweight and high strength, effectively distributing loads and improving load-bearing capacity and vibration resistance, thereby reducing the weight of the fuselage while ensuring flight stability and endurance. The arm module is connected to the central support plate assembly through high-strength aluminum alloy clamps and utilizes a 177° double-hole fit to achieve a 3° tilt angle installation, which not only ensures the precise positioning and stability of the arm but also optimizes the force direction, thereby improving power output efficiency and reducing the risk of loosening and vibration during flight. The limiting launch assembly adopts an elastic limiting mechanism that combines a sliding centering unit and a spring support unit, providing a stable channel and achieving high-precision limiting, effectively ensuring the reliability and repeatability of the launch action and improving the safety of system operation. The control module connects to all components and external terminal devices. Based on data collected by sensors, it analyzes the UAV's operational status and, combined with monitoring results from the barometric pressure sensor and accelerometer in the environmental perception module, dynamically adjusts power output parameters and attitude control strategies. This allows the UAV to adapt to changes in the external environment in real time, achieving stable flight and efficient energy management. The display module, connected to the control module, intuitively presents the UAV's operational status and key data, facilitating real-time monitoring and timely adjustments by the operator. Therefore, this architecture system demonstrates significant advantages in structural robustness, flight intelligence, safety and reliability, and ease of operation. Attached Figure Description

[0016] Figure 1 A functional block diagram of an unmanned aerial vehicle (UAV) architecture system provided in an embodiment of the present invention; Figure 2 This is a flowchart illustrating an unmanned aerial vehicle (UAV) architecture system provided in an embodiment of the present invention. Detailed Implementation

[0017] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey its scope to those skilled in the art. It should be noted that, unless otherwise specified, embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0018] like Figures 1-2 As shown in some embodiments of this application, this embodiment provides an unmanned aerial vehicle (UAV) architecture system, including: a central support plate assembly, an arm module, a limit launch assembly, a control module, an environmental perception module, a display module, and a fault early warning module.

[0019] Specifically, the central support plate assembly uses two layers of carbon fiber panels connected by several 7075 aerospace aluminum pillars to form a sandwich structure. The carbon fiber panels are fixed to the aluminum pillars with bolts, and the aluminum pillars are distributed in a grid pattern to distribute the load. The arm module is connected to the central support plate assembly via a special clamp made of high-strength aluminum alloy. The clamp has positioning holes, and the arm is installed at a 3° tilt angle by engaging with the clamp through a double hole machined at a 177° angle. The limiting launch assembly is equipped with an elastic limiting mechanism, which includes a slide centering unit and a spring support unit. The slide centering unit is formed by printing parts. The drone is fixedly connected to the central support plate assembly. The spring support unit forms a stable channel through the cooperation of industrial-grade springs and the sliding centering unit. The control module is connected to the central support plate assembly, the arm module, the limit launch assembly, and the external terminal equipment. It is used to analyze the drone's operating status based on the data collected by the sensors and adjust the power output parameters and attitude control strategy according to the operating status. The environmental perception module is equipped with a barometric pressure sensor and an accelerometer to monitor changes in the drone's environment in real time and adjust the power output mode according to the environmental changes. The display module is connected to the control module to display the drone's operating status and key data.

[0020] Specifically, the fault warning module is connected to the control module to monitor the UAV's operating status and determine whether there are potential risks based on the operating status characteristics and power adjustment parameters. If a potential risk exists, the fault warning module generates a warning message and sends it to an external terminal device through the communication module.

[0021] Understandably, the central support plate assembly employs a sandwich structure formed by connecting two layers of carbon fiber panels with 7075 aerospace-grade aluminum pillars. Combined with a grid-like distribution of aluminum pillars, this structure achieves high-strength support while ensuring lightweight design, effectively dispersing loads and impacts generated during flight, thus providing a robust and stable core support frame for the entire aircraft. The arm module is securely connected to the central support plate assembly via high-strength aluminum alloy clamps, and utilizes 177° double-hole machining to achieve a 3° tilt angle installation. This design allows the arm to maintain precise positioning while optimizing the propeller airflow direction, improving power efficiency and flight stability. Secondly, the limiting launch assembly, through the elastic limiting mechanism formed by the cooperation of the slide centering unit and the spring support unit, achieves stable limiting and precise reset of the UAV during module assembly and operation. Its fundamental principle lies in utilizing the elastic recovery characteristics of industrial-grade springs and the guiding characteristics of the slide to construct a stable limiting channel, thereby ensuring the repeatability and reliability of the actions. Furthermore, the control module, as the core processing unit of the system, is interconnected with the support plate, arms, limit components, and external terminals. It performs real-time analysis of the UAV's operational status based on sensor data and dynamically adjusts power output in conjunction with attitude control algorithms. The environmental perception module acquires external environmental parameters through barometric pressure sensors and accelerometers, enabling feedback adjustment of flight attitude and power mode in response to environmental changes. Its working principle is to convert environmental disturbance information into control inputs, thereby driving the control module to correct flight strategies and ensure flight stability and adaptability. Finally, the fault warning module is linked to the control module. Its principle is to establish a logic for identifying potential risks by continuously monitoring and comparing the UAV's operational status characteristics and power adjustment parameters. When abnormal trends or state deviations are detected, a warning message is immediately generated and fed back to the external terminal via the communication module. This achieves a closed-loop risk management mechanism from perception and analysis to feedback, thereby significantly improving the operational safety and controllability of the UAV in complex environments.

[0022] Specifically, when the control module analyzes the UAV's operating status based on data collected by sensors, the process includes: the control module acquiring the stress distribution at different locations on the central support plate assembly, and determining a high-stress region based on the stress distribution exceeding a preset stress threshold; the control module determining a first stress characteristic based on the ratio of the strain rate within the high-stress region to a preset strain rate threshold; the control module determining a second stress characteristic based on the difference between the overall average stress of the central support plate assembly and a preset average stress threshold; and the control module determining the UAV's operating status characteristic based on the sum of the first and second stress characteristics.

[0023] Specifically, when the control module adjusts the power output parameters and attitude control strategy based on the operating status characteristics of the UAV, it includes: if the operating status characteristics are greater than or equal to the preset operating status characteristic threshold, the control module reduces the power output and adjusts the attitude control strategy to a stable mode; if the operating status characteristics are less than the preset operating status characteristic threshold, the control module maintains the current power output and attitude control strategy unchanged.

[0024] Specifically, when the control module adjusts the UAV's operating state in response to operating state characteristics and power adjustment parameters, it includes: if both the operating state characteristics and power adjustment parameters are greater than a preset threshold, the control module reduces the power output and activates the auxiliary stabilization device for active correction; if the operating state characteristics are less than the preset threshold and the power adjustment parameters are greater than the preset threshold, the control module only reduces the power output; if both the operating state characteristics and power adjustment parameters are less than the preset threshold, the control module maintains the current operating state.

[0025] Specifically, when the control module adjusts the UAV's operating state based on operating state characteristics and power adjustment parameters, the following steps are taken: the control module determines a first operating factor based on the ratio of the operating state characteristics to a preset operating state characteristic threshold; the control module determines a second operating factor based on the ratio of the power adjustment parameters to a preset power adjustment parameter threshold; the control module determines the UAV's comprehensive operating parameters based on the sum of the first and second operating factors; and the control module adjusts the power output and attitude control strategies based on the comprehensive operating parameters.

[0026] Specifically, when the control module adjusts the power output and attitude control strategy based on the comprehensive operating parameters, it includes: if the comprehensive operating parameters are greater than or equal to the preset comprehensive operating parameter threshold, the control module reduces the power output and adjusts the attitude control strategy to a stable mode; if the comprehensive operating parameters are less than the preset comprehensive operating parameter threshold, the control module maintains the current power output and attitude control strategy unchanged.

[0027] Specifically, when the overall operating parameters of the UAV do not meet the preset standards, the control module determines whether to activate the auxiliary stabilization device based on the preset operating state characteristic threshold and the current operating state characteristics. This includes: if the preset operating state characteristic threshold is less than or equal to the current operating state characteristics, the control module activates the auxiliary stabilization device; if the preset operating state characteristic threshold is greater than the current operating state characteristics, the control module does not activate the auxiliary stabilization device.

[0028] Understandably, the control module collects stress distribution data at different locations on the UAV's central bearing plate assembly using sensors, and uses this data to identify high-stress areas. When the local stress exceeds a preset threshold, that area is considered a high-stress area. The first stress characteristic is then determined by the ratio of the strain rate within the high-stress area to the threshold. Simultaneously, the second stress characteristic is obtained by combining the difference between the overall average stress and the average stress threshold. The sum of these two characteristics serves as the UAV's operational status feature. This process essentially involves multi-level stress data fusion, transforming complex stress information into a unified quantitative indicator of operational status.

[0029] Secondly, the control module adjusts the UAV's power output and attitude control based on operational status characteristics. When the operational status characteristics exceed a threshold, it indicates that the UAV is in a high-load or unstable state, and the system will reduce power and switch to a stable control mode; if the status characteristics do not exceed the threshold, the existing power and attitude strategies remain unchanged. This reflects the adaptive control principle based on state determination, ensuring flight stability and safety.

[0030] Furthermore, the control module combines operational status characteristics with power adjustment parameters for joint judgment. When both exceed the threshold, it indicates that the UAV is simultaneously experiencing high stress and excessive power load. In this case, not only is the power output reduced, but the auxiliary stabilization device is also activated for active correction. If only the power adjustment parameter exceeds the threshold, power reduction is implemented. If neither exceeds the threshold, the current operational status is maintained. The technical principle behind this lies in the two-factor judgment logic, which achieves more accurate operational risk identification and graded response through the joint constraints of stress and power parameters.

[0031] Furthermore, the control module further transforms the operating status characteristics and power adjustment parameters into operating factors, sums the two to obtain comprehensive operating parameters, and then compares them with preset comprehensive thresholds to form a higher-level basis for judging operating status. Essentially, this process constructs a unified comprehensive operating evaluation index through normalized ratio calculations and parameter fusion to achieve flexible and detailed dynamic control.

[0032] Finally, when the overall operating parameters fail to meet the preset standards, the control module will further determine whether to activate the auxiliary stabilization device. Specifically, if the current operating state characteristics exceed a preset threshold, indicating a significant structural or attitude risk, the stabilization device will be immediately triggered; if they are below the threshold, no additional intervention is required. The principle behind this mechanism is a redundant protection strategy triggered by a risk threshold, ensuring that the UAV still possesses self-stabilization capabilities under extreme operating conditions.

[0033] Specifically, when the environmental perception module adjusts the power output mode based on environmental changes, it includes: the environmental perception module determining a first environmental feature based on the ratio of the air pressure change to a preset change threshold; the environmental perception module determining a second environmental feature based on the difference between the vibration frequency detected by the accelerometer and a preset vibration frequency threshold; the environmental perception module determining a power adjustment parameter based on the sum of the first and second environmental features; and the environmental perception module adjusting the power output mode based on the power adjustment parameter.

[0034] Understandably, the environmental perception module monitors the UAV's environment in real time using barometric pressure sensors and accelerometers, transforming complex environmental changes into quantifiable characteristic indicators. Specifically, the ratio of barometric pressure change to a preset threshold is extracted as the first environmental characteristic, reflecting the UAV's dynamic state in terms of vertical altitude or barometric pressure disturbances; while the difference between the vibration frequency detected by the accelerometer and a preset threshold is extracted as the second environmental characteristic, reflecting the degree of vibration caused by airflow or attitude instability during flight. This process embodies the principle of characterization and standardization of multidimensional environmental signals.

[0035] Secondly, the environmental perception module sums the first and second environmental features to obtain the power adjustment parameters. This step essentially maps environmental disturbances from different sources into a single control factor, thereby simplifying the expression of the impact of complex environmental conditions on flight control and enabling subsequent control modules to make rapid judgments and execute based on a single parameter.

[0036] Finally, the environmental perception module adjusts the UAV's power output mode based on the power adjustment parameter. When the power adjustment parameter is large, the system determines that the current environmental fluctuations are significant, and the UAV needs to improve flight stability by reducing or optimizing the power output mode; when the power adjustment parameter is small, the existing power mode is maintained to ensure a balance between energy efficiency and stability. The technical principle of this part is adaptive power control based on environmental disturbance parameter feedback, which enables the UAV to maintain flight balance and reliability under different air pressure and vibration environments.

[0037] To enable those skilled in the art to fully understand and implement this invention, the specific implementation principle of this invention will be further explained below in conjunction with a specific application scenario.

[0038] The UAV architecture system includes a central support plate assembly, an arm module, a limit-positioning launch assembly, a control module, an environmental perception module, a display module, a communication module, and a fault warning module. These modules work together through mechanical and electrical connections to accomplish the UAV's highly maneuverable operational tasks.

[0039] The central support plate assembly is the core component of the entire UAV architecture system. It employs a sandwich structure consisting of two layers of carbon fiber panels connected by several 7075 aerospace-grade aluminum pillars. The carbon fiber panels are 2 mm thick and sandblasted to enhance friction and improve the reliability of bolted connections. The 7075 aluminum pillars are 5 mm in diameter and 40 mm long, with M3 threaded holes at both ends for secure connection to the carbon fiber panels. The pillars are arranged in an "X" shape along the boom, with a 50 mm spacing between adjacent pillars. This arrangement effectively distributes the load and reduces localized stress concentration. The pillars are secured to the carbon fiber panels using M3 stainless steel bolts, with a tightening torque of 5 Nm to ensure connection strength.

[0040] The arm module is connected to the central support plate assembly via a specialized fixture made of high-strength aluminum alloy and CNC machined. The fixture has two 3mm diameter positioning holes for mating with the double holes on the arm. The double holes on the arm are machined at a 177-degree angle, resulting in a 3-degree tilt angle between the arm and the horizontal plane after installation. This design optimizes the aerodynamic performance of the UAV during flight and reduces vibration transmission. The arm is secured to the fixture with M3 stainless steel bolts, with a tightening torque set at 8 Nm. The bottom of the fixture has two M3 threaded holes for connecting to the aluminum pillars on the central support plate assembly.

[0041] The limiting launch assembly is located at the front of the central support plate assembly and includes a slide centering unit and a spring support unit. The slide centering unit is 3D printed using nylon PA12 to ensure its wear resistance and strength. Four M3 threaded holes are provided on both sides of the slide centering unit for fixed connection to the central support plate assembly via M3 stainless steel bolts 33. The spring support unit includes an industrial-grade spring and a support base. The industrial-grade spring is 0.5 mm thick, and its two ends are fixed to the support base via M3 bolts 36. Two M3 threaded holes are provided at the bottom of the support base for connection to the slide centering unit. For example, the slide centering unit has two parallel slides 37 inside, each 10 mm wide and 5 mm deep, used to guide the movement of the spring support unit.

[0042] The control module connects to the central support plate assembly, the arm module, the limit launch assembly, and external terminal equipment. Its core processor uses an ARM Cortex-M4 chip with a clock frequency of 168 MHz. The control module connects to a barometric pressure sensor (model BMP280) and an accelerometer (model MPU6050) via an I2C bus. When analyzing the UAV's operational status based on sensor data, the control module first acquires stress distribution data at different locations on the central support plate assembly. This stress distribution data is collected using eight strain gauges (14) attached to the carbon fiber panel surface, evenly distributed across the four corners and the center area. The control module compares the acquired stress distribution data with a preset stress threshold. If the stress distribution in a certain area exceeds the preset threshold, it is identified as a high-stress area. The control module further determines a first stress characteristic based on the ratio of the strain rate within the high-stress area to a preset strain rate threshold, and a second stress characteristic based on the difference between the overall average stress of the central support plate assembly and a preset average stress threshold. The control module determines the sum of the first stress characteristic and the second stress characteristic as the operating status characteristic of the UAV.

[0043] The environmental perception module, equipped with a barometric pressure sensor and an accelerometer, monitors changes in the UAV's environment in real time. The barometric pressure sensor has a measurement range of 300 to 1100 hPa and an accuracy of 0.01 hPa. The accelerometer has a measurement range of ±16g and an accuracy of 0.001g. The environmental perception module determines a first environmental characteristic based on the ratio of the change in barometric pressure to a preset threshold value, and determines a second environmental characteristic based on the difference between the vibration frequency detected by the accelerometer and a preset vibration frequency threshold value. The sum of the first and second environmental characteristics is used as the power adjustment parameter, and the power output mode is adjusted accordingly.

[0044] The display module is connected to the control module and uses a 2.8-inch TFT LCD screen with a resolution of 320x240 pixels. The display module communicates with the control module via an SPI bus to present the drone's operating status and key data. The display module's interface is divided into three areas: the left area displays the drone's real-time attitude data, including pitch, roll, and yaw angles; the middle area displays the drone's power output and battery level; and the right area displays air pressure and vibration data collected by the environmental perception module.

[0045] The communication module connects to the control module and uses a CC2541 Bluetooth chip, supporting the Bluetooth 4.0 protocol. The communication module communicates with the control module via a UART interface, transmitting UAV operational status data and critical data to external terminal devices. The communication module packets and packages the data before sending it to a relay device, which then forwards the data to the external terminal devices via a 4G network. The communication module's antenna 71 connects to the CC2541 Bluetooth chip via an SMA interface; antenna 71 has a gain of 2dBi.

[0046] The fault warning module is connected to the control module and uses an STM32F103 microcontroller with a main frequency of 72 MHz. The fault warning module communicates with the control module via a CAN bus to monitor the UAV's operational status and determine the presence of potential risks based on operational status characteristics and power adjustment parameters. If a potential risk is found, the fault warning module generates a warning message and sends it to an external terminal device via the communication module. The warning message includes the risk level, the time of occurrence, and the specific location; the risk level is divided into three categories: low, medium, and high.

[0047] When the control module adjusts the UAV's operating state in response to operating state characteristics and power adjustment parameters, it first determines a first operating factor based on the ratio of the operating state characteristics to a preset operating state characteristic threshold, and then determines a second operating factor based on the ratio of the power adjustment parameters to a preset power adjustment parameter threshold. The control module determines the sum of the first and second operating factors as the UAV's comprehensive operating parameters, and adjusts the power output and attitude control strategy based on these comprehensive operating parameters. If the comprehensive operating parameters are greater than or equal to a preset comprehensive operating parameter threshold, the control module reduces the power output and adjusts the attitude control strategy to a stable mode. If the comprehensive operating parameters are less than the preset comprehensive operating parameter threshold, the control module maintains the current power output and attitude control strategy unchanged.

[0048] When the overall operating parameters of the UAV do not meet preset standards, the control module determines whether to activate the auxiliary stabilization device based on preset operating state characteristic thresholds and the current operating state characteristics. If the preset operating state characteristic thresholds are less than or equal to the current operating state characteristics, the control module activates the auxiliary stabilization device. The auxiliary stabilization device consists of four miniature electric actuators, each with a maximum thrust of 5 kg and a stroke of 20 mm. The actuators are connected to the control module via PWM signals, and the control module adjusts the extension and retraction of the actuators according to the overall operating parameters to achieve active correction. If the preset operating state characteristic thresholds are greater than the current operating state characteristics, the control module does not activate the auxiliary stabilization device.

[0049] All the modules are powered by a lithium battery pack with a nominal voltage of 22.2 volts and a capacity of 10,000 mAh. The lithium battery pack connects to the power management module via an XT60 connector. The power management module uses an MP2615 chip and supports a maximum charging current of 6 amps. The power management module provides stable 5V and 3.3V power to each module through a DC-DC conversion circuit.

[0050] In the above embodiments, the sandwich-style central support plate structure formed by the upper and lower carbon fiber panels and 7075 aerospace aluminum pillars provides the advantages of lightweight and high strength. This effectively distributes the load and improves load-bearing capacity and vibration resistance, thus reducing the weight of the fuselage while ensuring flight stability and endurance. The arm module is connected to the central support plate assembly via high-strength aluminum alloy clamps and utilizes a 177° double-hole fit to achieve a 3° tilt angle installation. This not only ensures the precise positioning and stability of the arm but also optimizes the force direction, thereby improving power output efficiency and reducing the risk of loosening and vibration during flight. The limiting launch assembly employs an elastic limiting mechanism that combines a sliding centering unit and a spring support unit. This provides a stable channel and achieves high-precision limiting, effectively ensuring the reliability and repeatability of the launch action and improving the safety of system operation. The control module connects to all components and external terminal devices. Based on data collected by sensors, it analyzes the UAV's operational status and, combined with monitoring results from the barometric pressure sensor and accelerometer in the environmental perception module, dynamically adjusts power output parameters and attitude control strategies. This allows the UAV to adapt to changes in the external environment in real time, achieving stable flight and efficient energy management. The display module, connected to the control module, intuitively presents the UAV's operational status and key data, facilitating real-time monitoring and timely adjustments by the operator. Therefore, this architecture system demonstrates significant advantages in structural robustness, flight intelligence, safety and reliability, and ease of operation.

[0051] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program goods. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program goods embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0052] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program goods according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0053] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0054] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0055] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. An unmanned aerial vehicle (UAV) architecture system, characterized in that, include: The central load-bearing plate assembly consists of two layers of carbon fiber panels connected by several 7075 aerospace aluminum columns to form a sandwich structure. The carbon fiber panels are fixed to the aluminum columns by bolts, and the aluminum columns are distributed in a grid pattern to distribute the load. The robotic arm module is connected to the central support plate assembly via a special fixture. The fixture is made of high-strength aluminum alloy and has positioning holes. The robotic arm is installed at a 3° tilt angle by engaging with the fixture through two holes machined at an angle of 177°. The limiting launch assembly is equipped with an elastic limiting mechanism, which includes a sliding groove centering unit and a spring support unit. The sliding groove centering unit is formed by printing and fixedly connected to the central bearing plate assembly. The spring support unit forms a stable channel by cooperating with the sliding groove centering unit through an industrial-grade spring. The control module is connected to the central support plate assembly, the arm module, the limit launch assembly, and the external terminal equipment, respectively. It is used to analyze the UAV's operating status based on the data collected by the sensors, and adjust the power output parameters and attitude control strategies according to the operating status. The environmental perception module is equipped with a barometric pressure sensor and an accelerometer to monitor changes in the environment in which the UAV is located in real time and adjust the power output mode based on these changes. The display module, which is connected to the control module, is used to present the drone's operating status and key data.

2. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, When the control module analyzes the drone's operational status based on data collected by sensors, it includes: The control module acquires the stress distribution at different locations of the central bearing plate assembly and determines high-stress areas based on stress distributions exceeding a preset stress threshold. The control module determines the first stress characteristic based on the ratio of the strain rate in the high-stress region to a preset strain rate threshold. The control module determines the second stress characteristic based on the difference between the overall average stress of the central bearing plate assembly and the preset average stress threshold. The control module determines the UAV's operating status characteristics based on the sum of the first stress characteristics and the second stress characteristics.

3. The unmanned aerial vehicle (UAV) architecture system as described in claim 2, characterized in that, When the control module adjusts the power output parameters and attitude control strategy based on the characteristics of the UAV's operating status, it includes: If the operating state characteristics are greater than or equal to the preset operating state characteristic threshold, the control module will reduce the power output and adjust the attitude control strategy to a stable mode. If the operating state characteristics are less than the preset operating state characteristic threshold, the control module will maintain the current power output and attitude control strategy unchanged.

4. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, When the environmental perception module adjusts the power output mode based on environmental changes, it includes: The environmental perception module determines the first environmental feature based on the ratio of the change in air pressure to a preset threshold value. The environmental perception module determines the second environmental feature based on the difference between the vibration frequency detected by the accelerometer and the preset vibration frequency threshold. The environmental perception module determines the power adjustment parameters based on the sum of the first environmental feature and the second environmental feature; The environmental perception module adjusts the power output mode based on the power adjustment parameters.

5. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, When the control module adjusts the UAV's operating state in response to operating state characteristics and power adjustment parameters, it includes: If the operating status characteristics and power adjustment parameters are both greater than the preset threshold, the control module will reduce the power output and activate the auxiliary stabilization device for active correction. If the operating status characteristics are less than the preset threshold and the power adjustment parameter is greater than the preset threshold, the control module will only reduce the power output. If both the operating status characteristics and the power adjustment parameters are less than the preset threshold, the control module will maintain the current operating status.

6. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, When the control module adjusts the UAV's operating status based on operating status characteristics and power adjustment parameters, it includes: The control module determines the first operating factor based on the ratio of the operating state characteristics to the preset operating state characteristic threshold; The control module determines the second operating factor based on the ratio of the power adjustment parameter to the preset power adjustment parameter threshold. The control module determines the comprehensive operating parameters of the UAV based on the sum of the first operating factor and the second operating factor; The control module adjusts the power output and attitude control strategy based on the comprehensive operating parameters.

7. The unmanned aerial vehicle (UAV) architecture system as described in claim 6, characterized in that, When the control module adjusts the power output and attitude control strategy based on comprehensive operating parameters, it includes: If the overall operating parameters are greater than or equal to the preset overall operating parameter threshold, the control module will reduce the power output and adjust the attitude control strategy to a stable mode. If the overall operating parameters are less than the preset overall operating parameter threshold, the control module will maintain the current power output and attitude control strategy unchanged.

8. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, When the overall operating parameters of the UAV do not meet the preset standards, the control module determines whether to activate the auxiliary stabilization device based on the preset operating state characteristic thresholds and the current operating state characteristics, including: If the preset operating state characteristic threshold is less than or equal to the current operating state characteristic, the control module will activate the auxiliary stabilization device. If the preset operating state characteristic threshold is greater than the current operating state characteristic, the control module will not activate the auxiliary stabilization device.

9. The unmanned aerial vehicle (UAV) architecture system as described in claim 1, characterized in that, Also includes: The fault warning module, which is connected to the control module, is used to monitor the operating status of the UAV and determine whether there are potential risks based on the operating status characteristics and power adjustment parameters. If a potential risk exists, the fault warning module generates a warning message and sends it to an external terminal device via the communication module.

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