Airflow self-adaptive based unmanned aerial vehicle lighting and heat dissipation control method and related device

Abstract

Embodiments of the present application can be applied to the technical field of unmanned aerial vehicles, and specifically provide a lighting and heat dissipation control method for unmanned aerial vehicles based on airflow self-adaptation and related equipment, which comprises the following steps: after collecting flight state parameters in the flight process of the unmanned aerial vehicle and airflow parameters around the lighting assembly, generating an airflow effectiveness index, and combining the current thermal state parameters of the lighting assembly to determine the heat dissipation restriction type of the lighting assembly under the current flight state; selecting a corresponding heat dissipation adjustment mode through the heat dissipation restriction type to adjust the working state or spatial configuration parameters of the heat dissipation related components of the lighting assembly. By cooperatively utilizing the flight state parameters in the flight process of the unmanned aerial vehicle, the airflow parameters around the lighting assembly, and the thermal state parameters of the lighting assembly itself, the safety and continuous working ability of the unmanned aerial vehicle in performing the lighting task under multiple flight conditions are improved, and the problem of insufficient heat dissipation stability of the lighting assembly of the unmanned aerial vehicle under complex flight conditions is overcome.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicles (UAVs), and more specifically, to a UAV lighting and heat dissipation control method and related equipment based on airflow adaptation. Background Technology

[0002] With the widespread application of drone technology in fields such as inspection, security, emergency lighting, and nighttime operations, drones typically need to be equipped with lighting components to meet operational needs in low-light or no-light environments. These lighting components continuously generate heat during operation; insufficient heat dissipation can easily lead to decreased lighting efficiency, shortened lifespan, and even compromise the overall operational safety of the drone.

[0003] In the prior art, the heat generated by the lighting component is conducted to the external environment through a metal heat sink, heat sink or thermal conduction structure, or a cooling fan is installed inside or near the lighting component to enhance airflow, or the operating temperature of the lighting component is monitored by a temperature detection element, and the operating power of the lighting component is limited or the start and stop of the heat dissipation device is triggered when the temperature reaches a preset threshold.

[0004] Although basic heat dissipation requirements of lighting components can be met under static or minimally changing conditions by setting up heat dissipation structures or controlling heat dissipation based on temperature thresholds, during drone flight, the airflow distribution around the lighting components exhibits significant dynamism and unevenness due to continuous changes in flight speed, flight attitude, and external environmental conditions. Existing heat dissipation control methods based on fixed heat dissipation structures or single temperature feedback are unable to reflect changes in airflow conditions in a timely manner, which can easily lead to fluctuations in heat dissipation efficiency and, consequently, localized insufficient heat dissipation in certain flight conditions. Summary of the Invention

[0005] The embodiments of this application provide a method and related equipment for controlling the heat dissipation of UAV lighting based on airflow adaptation, which can overcome the problem of insufficient heat dissipation stability of UAV lighting components under complex flight conditions.

[0006] Other features and advantages of this application will become apparent from the following detailed description, or may be learned in part from practice of this application.

[0007] According to one aspect of the embodiments of this application, an airflow-adaptive UAV lighting heat dissipation control method is provided, applied to a UAV equipped with a lighting component. The control method includes: collecting flight state parameters and airflow parameters around the lighting component during the flight of the UAV; comprehensively evaluating the airflow conditions around the lighting component based on the flight state parameters and the airflow parameters to generate an airflow effectiveness index; obtaining the current thermal state parameters of the lighting component, and determining the heat dissipation limitation type of the lighting component under the current flight state based on the airflow effectiveness index and the thermal state parameters; selecting a corresponding heat dissipation adjustment mode according to the heat dissipation limitation type, and adjusting the working state or spatial configuration parameters of the heat dissipation-related components of the lighting component according to the heat dissipation adjustment mode.

[0008] In some embodiments of this application, based on the foregoing scheme, the step of collecting flight state parameters of the UAV during flight and airflow parameters around the lighting component includes: acquiring flight state parameters of the UAV's current flight attitude, flight speed, and flight altitude through the UAV's flight control system; acquiring speed change information of local airflow around the lighting component; synchronizing the flight state parameters with the speed change information to obtain synchronized data; and performing directional correction and attitude compensation on the speed change information based on the synchronized data and the installation orientation relationship of the lighting component on the UAV body to generate airflow parameters.

[0009] In some embodiments of this application, based on the foregoing scheme, the step of comprehensively evaluating the airflow conditions around the lighting component based on the flight state parameters and the airflow parameters to generate an airflow effectiveness index includes: determining the airflow direction and airflow intensity range corresponding to the current flight state according to the flight state parameters; mapping the airflow parameters to an effective airflow component corresponding to the heat dissipation surface of the lighting component according to the airflow direction; and performing stability correction on the effective airflow component by the change amplitude of the airflow parameters within a preset time window to generate an airflow effectiveness index.

[0010] In some embodiments of this application, based on the foregoing scheme, the step of obtaining the current thermal state parameters of the lighting component and determining the heat dissipation limitation type of the lighting component under the current flight state based on the airflow effectiveness index and the thermal state parameters includes: obtaining thermal state parameters characterizing the current operating temperature and temperature rise rate of the lighting component; performing correlation analysis between the thermal state parameters and the airflow effectiveness index; determining the airflow insufficiency type when the airflow effectiveness index is in a first preset range and the thermal state parameters exceed the corresponding temperature threshold; determining the unfavorable airflow direction type when the airflow effectiveness index is in a second preset range and the temperature rise rate of the thermal state parameters exceeds a preset change threshold; and using the airflow insufficiency type or the unfavorable airflow direction type as the heat dissipation limitation type corresponding to the lighting component under the current flight state.

[0011] In some embodiments of this application, based on the foregoing scheme, the step of selecting a corresponding heat dissipation adjustment mode according to the heat dissipation limitation type, and adjusting the working state or spatial configuration parameters of the heat dissipation-related components of the lighting component according to the heat dissipation adjustment mode, includes: selecting a heat dissipation adjustment mode matching the heat dissipation limitation type from a preset library of multiple heat dissipation adjustment modes according to the heat dissipation limitation type; when the heat dissipation limitation type is insufficient airflow, selecting an airflow enhancement mode from the heat dissipation adjustment mode library to adjust the working state of the heat dissipation-related components of the lighting component; when the heat dissipation limitation type is unfavorable airflow direction, selecting an airflow redirection mode from the heat dissipation adjustment mode library to adjust the spatial configuration parameters of the heat dissipation-related components of the lighting component.

[0012] In some embodiments of this application, based on the foregoing scheme, in the airflow enhancement mode, an auxiliary cooling fan disposed inside the lighting assembly is activated and the speed of the auxiliary cooling fan is adjusted according to the thermal state parameters.

[0013] In some embodiments of this application, based on the foregoing scheme, in the airflow redirection mode, the target adjustment angle of the adjustable guide plate set on the housing of the lighting component is calculated according to the angle between the airflow direction and the axial direction of the heat dissipation channel, and the adjustable guide plate is controlled to rotate to the target adjustment angle.

[0014] According to another aspect of the embodiments of this application, a heat dissipation control system for a drone lighting component based on airflow adaptation is provided, for application to a drone equipped with a lighting component, comprising: a data acquisition module for acquiring flight state parameters and airflow parameters around the lighting component during the flight of the drone; a data evaluation module for comprehensively evaluating the airflow conditions around the lighting component based on the flight state parameters and the airflow parameters, and generating an airflow effectiveness index; a constraint analysis module for obtaining the current thermal state parameters of the lighting component, and determining the heat dissipation constraint type of the lighting component under the current flight state based on the airflow effectiveness index and the thermal state parameters; and a heat dissipation adjustment module for selecting a corresponding heat dissipation adjustment mode according to the heat dissipation constraint type, and adjusting the working state or spatial configuration parameters of the heat dissipation-related components of the lighting component according to the heat dissipation adjustment mode.

[0015] According to another aspect of the embodiments of this application, an electronic device is provided, including a memory and a processor, wherein the memory stores a computer program that can run on the processor, and the processor executes the computer program to implement the airflow-adaptive UAV lighting and heat dissipation control method described above.

[0016] According to another aspect of the embodiments of this application, a computer-readable storage medium is provided having a computer program stored thereon, which, when run by a processor, causes the processor to perform the airflow-adaptive UAV lighting and heat dissipation control method as described in any one of the above embodiments.

[0017] Compared with existing technologies, this application has the following advantages: By synergistically utilizing the flight state parameters of the UAV during flight, the airflow parameters around the lighting component, and the thermal state parameters of the lighting component itself, it can not only reflect the actual impact of flight state changes on airflow conditions, but also accurately characterize the effectiveness of airflow conditions on the heat dissipation capacity of the lighting component, thereby avoiding the problem of insufficient adaptability caused by controlling based solely on a single temperature or fixed heat dissipation strategy; at the same time, by introducing airflow effectiveness indicators and a determination mechanism for heat dissipation limitation types, the heat dissipation adjustment mode can correspond to the actual heat dissipation bottleneck under the current flight state, which is beneficial to improve the pertinence and stability of heat dissipation adjustment of the lighting component without significantly increasing structural complexity and energy consumption, reducing the risk of performance degradation or reliability decline of the lighting component due to local overheating, improving the safety and continuous working capability of the UAV in performing lighting tasks under multiple flight conditions, and overcoming the problem of insufficient heat dissipation stability of UAV lighting components under complex flight conditions. Attached Figure Description

[0018] Figure 1This is a flowchart illustrating the UAV lighting and heat dissipation control method based on airflow adaptation provided in an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure of a drone equipped with a lighting component in an embodiment of the present invention; Figure 3 This is a schematic block diagram of the structure of the airflow-adaptive heat dissipation control system for UAV lighting components provided in an embodiment of the present invention; Figure 4 This is a schematic block diagram of the structure of the electronic device provided in the embodiment of the present invention.

[0019] Explanation of reference numerals in the attached figures: 10. Airflow-adaptive UAV lighting component heat dissipation control system; 11. Data acquisition module; 12. Data evaluation module; 13. Constraint analysis module; 14. Heat dissipation adjustment module; 20. Electronic equipment; 21. Memory; 22. Processor; 30. UAV; 40. Auxiliary cooling fan; 50. Adjustable air guide plate; 60. Heat dissipation channel. Detailed Implementation

[0020] Exemplary embodiments will now be described in a more comprehensive manner with reference to the accompanying drawings. However, the exemplary embodiments can be implemented in various forms and should not be construed as limited to these examples; rather, these embodiments are provided so that this application will be more comprehensive and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art.

[0021] Furthermore, the features, structures, or characteristics described in this application can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to provide a full understanding of the embodiments of this application. However, those skilled in the art will recognize that when implementing the technical solutions of this application, not all the detailed features in the embodiments may be used, one or more specific details may be omitted, or other methods, elements, devices, steps, etc., may be employed.

[0022] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0023] The flowcharts shown in the accompanying drawings are merely illustrative and do not necessarily include all content and operations / steps, nor do they necessarily have to be performed in the described order. For example, some operations / steps can be broken down, while others can be combined or partially combined; therefore, the actual execution order may change depending on the specific circumstances.

[0024] It should be noted that "multiple" in this article refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A alone, A and B simultaneously, or B alone. The character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0025] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0026] Example 1: like Figure 1 and Figure 2 As shown, this embodiment provides a UAV lighting heat dissipation control method based on airflow adaptation, applied to a UAV 30 equipped with lighting components. It can accurately acquire and characterize the airflow state around the lighting components under different flight attitudes and speeds, providing a quantifiable data basis for heat dissipation control. The control method includes the following steps: Step S100: Collect flight status parameters and airflow parameters around the lighting components during the flight of the UAV 30.

[0027] By synchronously collecting flight status parameters and airflow change information in the vicinity of the lighting component during the flight of the UAV 30, a basic data set is constructed to describe the external airflow environment of the lighting component under the current flight state. The flight status parameters and the airflow parameters are recorded in time series form and correspond to the current flight timestamp of the UAV 30.

[0028] For example, when the UAV 30 performs hovering, constant speed cruise or variable speed flight missions, flight status parameters and airflow parameters under different flight conditions are collected simultaneously, so that the collected data can truly reflect the changes in the airflow environment in which the lighting components are used in actual use.

[0029] In another example, step S100 can be further implemented as follows: The flight control system of the UAV 30 acquires flight status parameters that characterize the current flight attitude, flight speed, and flight altitude of the UAV 30.

[0030] Real-time flight data for flight control is directly read from the flight control system of the UAV 30. The flight attitude includes pitch angle, roll angle and yaw angle. The flight speed is the instantaneous speed value of the UAV 30 in space. The flight altitude is the real-time altitude value of the UAV 30 relative to the takeoff reference plane. All of the above flight status parameters are output with a uniform sampling period and are accompanied by corresponding time stamps.

[0031] For example, pitch angle, roll angle and yaw angle are obtained through the inertial measurement unit built into the flight control system, flight speed is obtained through the speed calculation module of the flight control system, and flight altitude is obtained through the altitude calculation module. The sampling period is set to 50 milliseconds to ensure the accuracy of the response of flight state parameters to changes in flight attitude.

[0032] At least one airflow sensing unit is set in the vicinity of the lighting component to obtain information on the speed change of the local airflow around the lighting component; during the flight of the UAV 30, the flight status parameters are synchronized with the speed change information obtained by the airflow sensing unit to obtain synchronized data.

[0033] The airflow sensing unit is fixedly installed at a preset position near the inlet of the heat dissipation channel 60 of the lighting component or on the surface of the housing. The airflow sensing unit outputs measurement values ​​related to local airflow speed changes. The data output by the airflow sensing unit is time-aligned with the flight status parameters through a unified time reference to eliminate time deviations caused by sampling delays or different data refresh frequencies.

[0034] For example, an airflow sensing unit based on the thermal film velocity measurement principle is used to obtain local airflow velocity change information, and the sampling time of the airflow sensing unit is aligned with the timestamp of the flight status parameters output by the flight control system through the time synchronization module inside the UAV 30, with the time synchronization error controlled within 5 milliseconds.

[0035] Based on the synchronized data and the installation orientation of the lighting components on the UAV 30 body, the velocity change information is corrected for direction and compensated for attitude to generate airflow parameters that characterize the actual flow state around the lighting components.

[0036] Based on the installation orientation of the lighting component relative to the UAV's 30-body coordinate system, the velocity change information acquired by the airflow sensing unit is transformed from the sensor coordinate system to a reference coordinate system consistent with the heat dissipation direction of the lighting component. Combined with flight attitude parameters, attitude compensation is performed on the airflow direction so that the corrected airflow parameters can accurately reflect the actual airflow direction and intensity received by the lighting component under the current flight attitude.

[0037] For example, the attitude compensation calculation is performed on the pitch angle, roll angle and yaw angle based on the Euler angle attitude calculation algorithm. The original velocity change information is mapped into an airflow component along the 60 axis of the heat dissipation channel of the lighting component, and the airflow component is output as an airflow parameter to describe the actual airflow state around the lighting component.

[0038] Step S200: Based on flight status parameters and airflow parameters, comprehensively evaluate the airflow conditions around the lighting components and generate an airflow effectiveness index.

[0039] The collected flight state parameters and airflow parameters are input into the data processing module. By calculating the relationship between the current flight attitude, flight speed and the airflow angle of the lighting component, the local airflow components on the heat dissipation surface of the lighting component are decomposed and quantified to obtain the effective contribution value of the airflow intensity at each local location. Then, the effective airflow contribution values ​​of each local location are summarized according to their weights to form an overall airflow effectiveness index, which is used to characterize the degree of effect of airflow on the heat dissipation of the lighting component under the current flight state.

[0040] If the heat dissipation surface area of ​​the lighting component is 50 square centimeters, when the pitch angle is 10° and the roll angle is 5°, the airflow component along the 60° direction of the heat dissipation channel is calculated by projection method. The effective airflow components of ten equally divided regions on the heat dissipation surface are weighted and summed to obtain the airflow effectiveness index. The value range can be from 0 to 100. The higher the value, the greater the contribution of the airflow to heat dissipation.

[0041] In another example, step S200 can be further implemented as follows: During the flight of the UAV 30, the direction and intensity range of airflow corresponding to the current flight state are determined based on the flight state parameters.

[0042] By using the flight velocity vector and flight attitude angle, combined with the installation orientation of the lighting components relative to the UAV 30 body, the direction of the airflow projection on the heat dissipation surface is calculated, and the airflow intensity is divided into three intensity ranges: high, medium, and low, according to different speed ranges and altitude ranges of the UAV 30.

[0043] When the UAV 30 flies at a speed of 5 to 10 meters per second and at an altitude of 50 to 100 meters, the calculated component of the airflow direction along the axis of the heat dissipation channel 60 is 8 meters per second, which can be classified as a high-intensity range; when the flight speed is less than 5 meters per second or the altitude is less than 50 meters, the component along the axis is 3 meters per second, which can be classified as a medium-intensity range.

[0044] The airflow parameters are mapped to the effective airflow components corresponding to the heat dissipation surface of the lighting component according to the direction of airflow.

[0045] The original airflow parameters are directionally projected, and the measured velocity vector is decomposed into components along the heat dissipation channel 60 of the lighting component and in the vertical direction. The vertical component, which does not contribute much to heat dissipation, is removed, and only the effective airflow component along the heat dissipation direction is retained to form quantified local heat dissipation airflow data.

[0046] For example, at a measurement point where the airflow velocity is 6 meters per second and the direction is at an angle of 30° to the axis of the heat dissipation channel 60, the effective airflow component along the axial direction is approximately 5.2 meters per second obtained by cosine projection, which is used as the effective airflow input at that point.

[0047] The stability of the effective airflow component is corrected by measuring the variation of airflow parameters within a preset time window, thereby generating an airflow effectiveness index that characterizes the contribution of airflow to the heat dissipation of the lighting components under the current flight condition.

[0048] The mapped effective airflow components are subjected to sliding window mean filtering and fluctuation correction to remove the interference of instantaneous airflow pulsation on heat dissipation assessment. At the same time, the trend of airflow contribution is weighted according to historical data so that the final generated airflow effectiveness index can stably reflect the airflow heat dissipation capacity under the current flight state.

[0049] For example, within a time window of 1 second, the effective airflow component along the heat dissipation channel 60 of each sampling point is averaged and weighted in combination with the mean of the previous 3 seconds to obtain a smoothed airflow effectiveness index of 78, which can be directly used to determine the type of heat dissipation limitation.

[0050] Step S300: Obtain the current thermal state parameters of the lighting component, and determine the heat dissipation limitation type of the lighting component under the current flight state based on the airflow effectiveness index and the thermal state parameters.

[0051] The current operating temperature and temperature rise rate of the lighting component are obtained by the temperature sensor and temperature rise rate calculation module inside the lighting component. The thermal state parameters are correlated with the airflow effectiveness index to determine whether the lighting component has heat dissipation limitations under the current flight conditions.

[0052] For example, the surface temperature sensor of the lighting component outputs 65 degrees Celsius, the temperature rise rate is 2 degrees Celsius per second, and the airflow effectiveness index is 50. Based on the preset association rules, it is determined that heat dissipation is limited.

[0053] In another example, step S300 can be further implemented as follows: During the flight of the UAV 30, thermal state parameters characterizing the current operating temperature and temperature rise rate of the lighting components are acquired, and the thermal state parameters are correlated with airflow effectiveness indicators.

[0054] Thermal state parameters are read and paired with airflow effectiveness indicators at corresponding times for analysis. The heat dissipation status is judged using a set threshold range. Temperature and temperature rise rate are compared with airflow effectiveness indicators in a matrix for accurate classification of heat dissipation limitation types.

[0055] For example, the airflow effectiveness index is divided into three ranges: 0-30, 31-70, and 71-100. The temperature threshold is set to 70 degrees Celsius, and the temperature rise rate threshold is set to 3 degrees Celsius per second. When the airflow effectiveness index is 25 and the temperature is 72 degrees Celsius, it is judged as insufficient airflow. When the airflow effectiveness index is 55 and the temperature rise rate is 3.5 degrees Celsius per second, it is judged as unfavorable airflow direction.

[0056] When the airflow effectiveness index is in the first preset range and the thermal state parameter exceeds the corresponding temperature threshold, it is determined to be an insufficient airflow type.

[0057] Cases where the airflow effectiveness index is below the lower limit of the preset range and the temperature is above the threshold are classified as insufficient airflow type, and this type is recorded as the type of limited heat dissipation of the lighting components under the current flight state.

[0058] For example, if the airflow effectiveness index is 20 and the temperature is 75 degrees Celsius, it is determined to be an insufficient airflow type, and the corresponding heat dissipation adjustment strategy will be triggered.

[0059] When the airflow effectiveness index is in the second preset range and the temperature rise rate of the thermal state parameter exceeds the preset change threshold, it is determined to be an unfavorable airflow direction.

[0060] The situation where the airflow effectiveness index is in the middle range and the temperature rise rate exceeds the preset threshold is classified as unfavorable airflow direction, and this type is recorded as the lighting component heat dissipation limitation type under the current flight state.

[0061] For example, when the airflow effectiveness index is 60 and the temperature rise rate is 3.5 degrees Celsius per second, it is determined to be an unfavorable airflow direction, thus triggering the corresponding heat dissipation adjustment strategy.

[0062] The type of insufficient airflow or unfavorable airflow direction is used as the heat dissipation limitation type for the lighting components under the current flight conditions.

[0063] For example, if the UAV 30 is cruising at low speed and the airflow is weak, it is judged as the type with insufficient airflow. If it is flying at high speed and the local airflow direction is unfavorable, it is judged as the type with unfavorable airflow direction.

[0064] Step S400: Select the corresponding heat dissipation adjustment mode according to the heat dissipation limitation type, and adjust the working status or spatial configuration parameters of the heat dissipation-related components of the lighting component according to the heat dissipation adjustment mode.

[0065] Based on the type of heat dissipation limitation, a corresponding mode is matched from a pre-set heat dissipation adjustment mode library, and the mode parameters are applied to the auxiliary cooling fan 40, adjustable air deflector 50, and other heat dissipation-related components of the lighting assembly to optimize heat dissipation. By controlling and adjusting the working state or spatial position of the heat dissipation components in real time, the lighting assembly maintains a stable temperature under various flight conditions.

[0066] For example, when the heat dissipation limitation type is insufficient airflow, the airflow enhancement mode is selected from the heat dissipation adjustment mode library, and the auxiliary cooling fan 40 inside the lighting component is started and adjusted to the target speed, thereby improving the heat dissipation efficiency.

[0067] In another example, step S400 can be further implemented as follows: Select the appropriate heat dissipation adjustment mode from a library of preset heat dissipation adjustment modes based on the type of heat dissipation limitation.

[0068] Using the heat dissipation limitation type as an index, the corresponding mode parameters in the mode library are queried, including the start / stop status of the auxiliary cooling fan 40, the speed control curve and rotation speed, and the opening / closing status of the adjustable valve of the heat dissipation channel 60. The selected mode parameters are then sent to each heat dissipation-related component for execution.

[0069] For example, the insufficient airflow type corresponds to the airflow enhancement mode, with a target fan speed of 3000 to 5000 revolutions per minute; the unfavorable airflow direction type corresponds to the airflow redirection mode, which can be rotated to a target angle to change the local airflow direction.

[0070] When the heat dissipation limitation type is insufficient airflow, select the airflow enhancement mode in the heat dissipation adjustment mode library to adjust the working status of the heat dissipation-related components of the lighting assembly.

[0071] The auxiliary cooling fan 40 inside the lighting assembly is started, and the fan speed is dynamically adjusted according to the thermal state parameters. The fan speed increases with the temperature according to the preset PID control curve to achieve rapid heat dissipation.

[0072] For example, when the temperature of the lighting components reaches 70 degrees Celsius, the auxiliary cooling fan 40 gradually increases from 3000 rpm to 4500 rpm to enhance heat dissipation efficiency.

[0073] When the heat dissipation limitation type is unfavorable airflow direction, select the airflow redirection mode in the heat dissipation adjustment mode library to adjust the spatial configuration parameters of the heat dissipation-related components of the lighting assembly.

[0074] The target adjustment angle of the adjustable guide plate 50 is calculated based on the angle between the airflow direction and the axis of the heat dissipation channel 60. The guide plate is rotated to the target angle to change the direction of the airflow entering the heat dissipation channel 60, optimize the local airflow field distribution, and make the airflow flow along the heat dissipation channel 60 to improve the heat dissipation efficiency.

[0075] For example, when the airflow direction is at an angle of 30° to the axis of the heat dissipation channel 60, the adjustable guide plate 50 is rotated to the target angle of 35° to adjust the local airflow direction and reduce the deviation between the airflow and the axis of the heat dissipation channel 60 to 5°, thereby enhancing the heat dissipation contribution.

[0076] In the airflow enhancement mode, the auxiliary cooling fan 40 installed inside the lighting component is activated and its speed is adjusted according to the thermal state parameters to increase the airflow capture area.

[0077] The fan speed is continuously adjusted according to the real-time changes in thermal parameters. The PID adjustment can be calculated using temperature sensor data to ensure that the heat dissipation efficiency is at its optimal level at every point in time.

[0078] For example, when the lighting component temperature is 72 degrees Celsius, the fan speed increases from 3,500 revolutions per minute to 4,800 revolutions per minute, rapidly reducing the component temperature.

[0079] When in the airflow redirection mode, the target adjustment angle of the adjustable guide plate 50 set on the housing of the lighting component is calculated based on the angle between the airflow direction and the axis of the heat dissipation channel 60, and the adjustable guide plate 50 is controlled to rotate to the target adjustment angle to change the direction of airflow into the heat dissipation channel 60 in order to optimize the local airflow field distribution.

[0080] By reading data from the airflow direction sensor and combining it with the geometric parameters of the heat dissipation channel 60, the rotation angle of the guide plate is calculated. The servo motor is then controlled to the target angle, so that the local airflow flows along the optimal channel direction, increasing the residence time of the airflow along the heat dissipation surface and improving the heat dissipation contribution.

[0081] For example, when the measured airflow direction deviates from the axis of the heat dissipation channel by 25°, the guide plate is rotated to the target angle of 28°. After adjustment, the local airflow deviation is reduced to 3°, which effectively improves the heat flow distribution and enhances the overall heat dissipation efficiency.

[0082] In this embodiment, by collecting flight state parameters of the UAV 30 during flight and airflow parameters around the lighting component, combined with the flight attitude, speed, and altitude of the UAV 30, an accurate characterization of the actual airflow state around the lighting component is achieved. By deploying airflow sensing units in the vicinity of the lighting component to acquire local airflow velocity change information, and synchronizing the collected airflow data with the flight state parameters, directional correction and attitude compensation are performed based on the installation orientation of the lighting component on the UAV 30 body, thereby obtaining airflow parameters for evaluating heat dissipation conditions. Based on this, by mapping the airflow parameters to effective airflow components corresponding to the heat dissipation surface of the lighting component according to the airflow direction, and combining the stability correction of the effective airflow component's variation amplitude within a preset time window, an airflow effectiveness index characterizing the contribution of airflow to the heat dissipation of the lighting component under the current flight state is generated. Simultaneously, the thermal state parameters of the lighting component's current operating temperature and temperature rise rate are acquired, and the thermal state parameters are correlated with the airflow effectiveness index to determine the type of heat dissipation limitation of the lighting component under the current flight state, including insufficient airflow and unfavorable airflow direction. Based on this, a heat dissipation adjustment mode matching the type of heat dissipation limitation is selected from the preset heat dissipation adjustment mode library. For the insufficient airflow type, the airflow enhancement mode is adopted, which improves heat dissipation efficiency by starting the auxiliary cooling fan 40 and adjusting its speed. For the unfavorable airflow direction type, the airflow redirection mode is adopted, which calculates the target adjustment angle of the adjustable guide plate 50 and rotates it to the target angle to change the direction of airflow entering the heat dissipation channel 60, optimizes the local airflow field distribution, and thus enhances the heat dissipation contribution.

[0083] Through the aforementioned continuous control methods of flight state parameter acquisition, airflow parameter characterization, airflow effectiveness assessment, thermal state parameter correlation analysis, and dynamic adjustment of heat dissipation mode, adaptive control of the heat dissipation of the UAV lighting components under different flight states and airflow conditions is achieved. This ensures the temperature stability of the lighting components under various flight conditions, while improving the heat dissipation response speed and overall thermal management efficiency. It provides a reliable guarantee for the UAV 30 to provide high-power lighting for a long time in complex flight environments and overcomes the problem of insufficient heat dissipation stability of the UAV lighting components under complex flight conditions.

[0084] Example 2: like Figure 3 As shown, this embodiment provides a heat dissipation control system 10 for UAV lighting components based on airflow adaptation, which is applied to a UAV 30 equipped with lighting components. The system mainly includes the following modules: The data acquisition module 11 is used to collect flight status parameters and airflow parameters around the lighting components during the flight of the UAV 30.

[0085] The data evaluation module 12 is used to comprehensively evaluate the airflow conditions around the lighting components based on flight status parameters and airflow parameters, and generate airflow effectiveness indicators.

[0086] The restricted analysis module 13 is used to obtain the current thermal state parameters of the lighting component and determine the heat dissipation restriction type of the lighting component under the current flight state based on the airflow effectiveness index and thermal state parameters.

[0087] The heat dissipation adjustment module 14 is used to select the corresponding heat dissipation adjustment mode according to the heat dissipation limitation type, and adjust the working status or spatial configuration parameters of the heat dissipation-related components of the lighting component according to the heat dissipation adjustment mode.

[0088] In this embodiment, the data acquisition module 11 acquires flight state parameters of the UAV 30 during flight, including the UAV 30's flight attitude, flight speed, and flight altitude. Simultaneously, an airflow sensing unit located near the lighting component acquires local airflow velocity change information around the lighting component. The acquired data is synchronized in time, corrected in direction, and compensated for in attitude, generating airflow parameters characterizing the actual airflow conditions around the lighting component. The data evaluation module 12 comprehensively evaluates the airflow conditions around the lighting component based on the flight state parameters and airflow parameters, determining the airflow direction and intensity range. The airflow parameters are mapped to effective airflow components corresponding to the lighting component's heat dissipation surface, and stability is corrected using the variation amplitude within a preset time window, generating an airflow effectiveness index characterizing the contribution of the airflow to the lighting component's heat dissipation under the current flight state. The restricted analysis module 13 obtains the current operating temperature and temperature rise rate of the lighting component, and performs correlation analysis based on the airflow effectiveness index and thermal state parameters. When the airflow effectiveness index is in the first preset range and the thermal state parameters exceed the temperature threshold, it is determined to be an insufficient airflow type. When the airflow effectiveness index is in the second preset range and the temperature rise rate exceeds the preset change threshold, it is determined to be an unfavorable airflow direction type, thereby obtaining the heat dissipation restriction type of the lighting component under the current flight state. The heat dissipation adjustment module 14 selects a matching mode from the preset heat dissipation adjustment mode library according to the heat dissipation restriction type. When it is an insufficient airflow type, the auxiliary cooling fan 40 is started and the fan speed is adjusted. When it is an unfavorable airflow direction type, the target adjustment angle of the adjustable guide vane 50 is calculated and rotated to that angle to optimize the local airflow field distribution, thereby realizing the adaptive adjustment of the working state and spatial configuration parameters of the heat dissipation-related components of the lighting component.

[0089] It should be noted that although several modules or units of the system for executing actions have been mentioned in the detailed description above, this division is not mandatory. In fact, according to the embodiments of this application, the features and functions of two or more modules or units described above can be embodied in one module or unit. Conversely, the features and functions of one module or unit described above can be further divided and embodied by multiple modules or units.

[0090] Example 3: like Figure 4 As shown, this embodiment provides an electronic device 20, including a memory 21 and a processor 22. The memory 21 stores a computer program that can run on the processor 22. When the processor 22 executes the computer program, it implements the airflow-adaptive UAV lighting and heat dissipation control method of Embodiment 1.

[0091] In this embodiment, the computer program stored in the memory 21 runs on the processor 22, causing the processor 22 to sequentially execute operations such as collecting flight state parameters and airflow parameters around the lighting component during the flight of the UAV 30, comprehensively evaluating the airflow conditions around the lighting component based on the flight state parameters and airflow parameters to generate an airflow effectiveness index, acquiring the thermal state parameters of the lighting component and determining the type of heat dissipation limitation, and selecting a heat dissipation adjustment mode and adjusting the working state or spatial configuration parameters of heat dissipation-related components according to the type of heat dissipation limitation. This enables the electronic device 20 to achieve adaptive control of the heat dissipation of the UAV lighting component and optimize the airflow environment by dynamically adjusting the fan speed and the angle of the deflector, thereby ensuring the heat dissipation performance of the lighting component under different flight states.

[0092] Example 4: This embodiment provides a computer-readable storage medium storing a computer program thereon, which, when run by a processor, causes the processor to execute the airflow-adaptive UAV lighting and heat dissipation control method as described in Embodiment 1.

[0093] In this embodiment, a computer program on a computer-readable storage medium, when running on the processor, causes the processor to sequentially execute the airflow-adaptive UAV lighting heat dissipation control method of Embodiment 1. This method includes collecting flight state parameters and airflow parameters around the lighting components, generating airflow effectiveness indicators, determining the type of heat dissipation limitation, selecting the corresponding heat dissipation adjustment mode, and adjusting the working state or spatial configuration parameters of heat dissipation-related components. This enables adaptive heat dissipation control of the UAV lighting components under different flight states and airflow conditions. Furthermore, by adjusting the speed of the auxiliary cooling fan and controlling the angle of the adjustable guide vane, the local airflow field is optimized, thereby effectively managing the temperature rise of the lighting components.

[0094] From the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein can be implemented by software or by combining software with necessary hardware. Therefore, the technical solutions according to the embodiments of this application can be embodied in the form of a software product, which can be stored on a non-volatile storage medium (such as a CD). The method, which is contained in or on a ROM, USB flash drive, external hard drive, etc., includes several instructions to cause an electronic device (which may be a personal computer, server, touch terminal, or network device, etc.) to execute the method according to the embodiments of this application.

[0095] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the embodiments disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein.

[0096] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.

Claims

1. A method for controlling the heat dissipation of lighting in a drone based on airflow adaptation, applied to a drone equipped with lighting components, characterized in that, The control method includes: The flight control system of the UAV acquires the current flight attitude, flight speed and flight altitude of the UAV; it acquires the speed change information of the local airflow around the lighting component, and synchronizes the flight status parameters with the speed change information to obtain synchronized data; based on the synchronized data and the installation orientation of the lighting component on the UAV body, it performs directional correction and attitude compensation on the speed change information to generate airflow parameters. Based on the flight state parameters, determine the airflow direction and airflow intensity range corresponding to the current flight state; map the airflow parameters to an effective airflow component corresponding to the heat dissipation surface of the lighting component according to the airflow direction; and perform stability correction on the effective airflow component by the change amplitude of the airflow parameters within a preset time window to generate an airflow effectiveness index. The thermal state parameters characterizing the current operating temperature and temperature rise rate of the lighting component are obtained, and the thermal state parameters are correlated with the airflow effectiveness index. When the airflow effectiveness index is in a first preset range and the thermal state parameter exceeds the corresponding temperature threshold, it is determined to be an insufficient airflow type. When the airflow effectiveness index is in a second preset range and the temperature rise rate of the thermal state parameter exceeds a preset change threshold, it is determined to be an unfavorable airflow direction type. The insufficient airflow type or the unfavorable airflow direction type is taken as the heat dissipation limitation type of the lighting component under the current flight state. According to the heat dissipation limitation type, a heat dissipation adjustment mode matching the heat dissipation limitation type is selected from a preset library of multiple heat dissipation adjustment modes; when the heat dissipation limitation type is insufficient airflow, the airflow enhancement mode in the heat dissipation adjustment mode library is selected, the auxiliary cooling fan set inside the lighting component is started, and the speed of the auxiliary cooling fan is adjusted according to the thermal state parameters; when the heat dissipation limitation type is unfavorable airflow direction, the airflow redirection mode in the heat dissipation adjustment mode library is selected, the target adjustment angle of the adjustable guide plate set on the housing of the lighting component is calculated according to the angle between the airflow direction and the axial direction of the heat dissipation channel, and the adjustable guide plate is controlled to rotate to the target adjustment angle.

2. A heat dissipation control system for a drone lighting component based on airflow adaptation, used in drones equipped with lighting components, characterized in that, include: The data acquisition module is used to acquire flight status parameters such as the current flight attitude, flight speed, and flight altitude of the UAV through the UAV's flight control system; acquire speed change information of the local airflow around the lighting component; synchronize the flight status parameters with the speed change information to obtain synchronized data; and perform directional correction and attitude compensation on the speed change information based on the synchronized data and the installation orientation of the lighting component on the UAV body to generate airflow parameters. The data evaluation module is used to determine the airflow direction and airflow intensity range corresponding to the current flight state based on the flight state parameters; map the airflow parameters to an effective airflow component corresponding to the heat dissipation surface of the lighting component according to the airflow direction; and perform stability correction on the effective airflow component by measuring the change amplitude of the airflow parameters within a preset time window to generate an airflow effectiveness index. The constrained analysis module is used to acquire thermal state parameters characterizing the current operating temperature and temperature rise rate of the lighting component, and to perform correlation analysis between the thermal state parameters and the airflow effectiveness index. When the airflow effectiveness index is in a first preset range and the thermal state parameters exceed the corresponding temperature threshold, it is determined to be an insufficient airflow type. When the airflow effectiveness index is in a second preset range and the temperature rise rate of the thermal state parameters exceeds a preset change threshold, it is determined to be an unfavorable airflow direction type. The insufficient airflow type or the unfavorable airflow direction type is used as the heat dissipation constrained type corresponding to the lighting component under the current flight state. The heat dissipation adjustment module is used to select a heat dissipation adjustment mode that matches the heat dissipation limitation type from a preset library of multiple heat dissipation adjustment modes according to the heat dissipation limitation type; when the heat dissipation limitation type is insufficient airflow, the airflow enhancement mode in the heat dissipation adjustment mode library is selected, the auxiliary cooling fan installed inside the lighting component is started, and the speed of the auxiliary cooling fan is adjusted according to the thermal state parameters; when the heat dissipation limitation type is unfavorable airflow direction, the airflow redirection mode in the heat dissipation adjustment mode library is selected, the target adjustment angle of the adjustable guide plate installed on the housing of the lighting component is calculated according to the angle between the airflow direction and the axial direction of the heat dissipation channel, and the adjustable guide plate is controlled to rotate to the target adjustment angle.

3. An electronic device, characterized in that, It includes a memory and a processor, the memory storing a computer program that can run on the processor, and the processor executing the computer program to implement the airflow-adaptive UAV lighting and heat dissipation control method of claim 1.

4. A computer-readable storage medium, characterized in that, It stores a computer program that, when run by a processor, causes the processor to execute the airflow-adaptive UAV lighting and heat dissipation control method as described in claim 1.

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