57 results about "Flight altitude" patented technology

This application discloses an aerial photography flight path planning method, which includes: acquiring a planar polygonal region; generating a first photography point; selecting a second photography point from the first photography point and setting constraints; if no set of second photography points satisfying the conditions exists, decreasing the focal length in the preset camera parameters and / or increasing the preset drone flight altitude, and then re-executing the step of calculating the rectangular coverage area to select the second photography point; if a set of second photography points satisfying the conditions exists, recording the current camera parameters and drone flight altitude, then increasing the focal length and / or decreasing the flight altitude, and re-executing the step of calculating the rectangular coverage area to select the second photography point; using the set of second photography points that last satisfied the constraints as the final planning result; planning the flight path and generating an aerial photography flight path file. This application can be used to solve the technical problems of low coverage efficiency and poor image clarity in existing aerial photography methods.

The application discloses a kind of ship compliance monitoring methods based on unmanned aerial vehicle and AIS data fusion.The method controls satellite positioning module, IMU and vision sensor of unmanned aerial vehicle to collect data;Satellite positioning antenna is compensated using IMU real-time attitude lever arm effect, and the corrected unmanned aerial vehicle coordinates are obtained;Based on vision SFM algorithm and unmanned aerial vehicle positioning displacement baseline, the relative position vector of ship is solved, and the absolute coordinate of ship is obtained by space projection;Through linear interpolation, the time and space alignment of measured data and AIS data is realized;Finally, coordinate deviation is calculated, and dynamic threshold based on flight height, sea state and other environmental parameters is combined to determine the compliance of ship.The application realizes independent high-precision solution and full-dimensional verification of ship position, heading and speed, effectively solves the problems of AIS data fraud identification difficulty, large environmental interference and other problems, and greatly improves the accuracy and intelligent level of maritime non-site law enforcement.

The application relates to a flight path height determination method and device of a UAV, electronic equipment and a medium, the method comprising: acquiring a scene type where the UAV is located, a UAV model and a signal strength coefficient; according to the UAV model, acquiring a wind force grade coefficient and a fuselage size parameter corresponding to the UAV model; if the scene type is a first scene, according to the fuselage size parameter corresponding to the UAV model, the wind force grade coefficient and the signal strength coefficient, determining the flight path height of the UAV; if the scene type is a second scene, acquiring a UAV speed, and according to the UAV speed, the fuselage size parameter, the wind force grade coefficient and the signal strength coefficient, determining the flight path height of the UAV. Through the method, the scene type where the UAV is located, the UAV model, the navigation signal strength and the flying UAV speed are comprehensively considered, the accuracy of the flight path height calculation is improved, and the flight adaptability and task execution capability of the UAV in a complex environment are enhanced.

This invention relates to a method and apparatus for accurate identification of persons in distress in multiple scenarios, belonging to the field of water rescue technology. The method includes determining a search area and an optimal flight altitude based on the distress information of the persons in distress, UAV flight data, and mission requirements. This allows the UAV to acquire the most suitable video image data from its current perspective when it reaches the optimal flight altitude within the search area, improving search efficiency. Furthermore, it allows for detail restoration and degradation recovery of the current video images, resulting in clearer video images and improved video data quality. Finally, it allows for multi-scale feature extraction from the clear video images to obtain the identification results of the persons in distress, thus extracting comprehensive information about the persons in distress from the video data.

The invention discloses a method and a system for generating and executing an anti-interference flight strategy of a C2 link of an unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicle communication. The method comprises the following steps: acquiring urban building material parameters and unmanned aerial vehicle flight parameters; based on the parameters, combining a free space path loss model, a Rice fading model and a blade peak diffraction model to construct an urban environment channel model; injecting same-frequency Wi-Fi interference and building reflection interference signals to calculate a signal to interference plus noise ratio; based on the signal to interference plus noise ratio, calculating the bit error rate and evaluating the anti-interference performance, and generating an anti-interference optimization scheme including frequency band switching and flight height adjustment; and controlling the unmanned aerial vehicle to execute the strategy. Aiming at the problems of Wi-Fi co-frequency interference, building shielding, glass curtain wall multipath reflection and the like in a complex urban environment, frequency band self-adaptive switching and flight height optimization are realized through multi-model joint simulation and dynamic strategy generation, the bit error rate is reduced, the anti-interference capability is improved, and the method has the advantages of being simple in structure and convenient to operate. And the communication reliability and the flight safety of the unmanned aerial vehicle in a complex urban environment are effectively guaranteed.

This application discloses a method, apparatus, equipment, and storage medium for urban engineering surveying based on unmanned aerial vehicles (UAVs), relating to the field of UAV surveying technology. It aims to solve the problems of blind spots and large measurement errors in traditional UAV surveying. The method includes: real-time scanning of the terrain contour of the surveying area using a terrain sensing device mounted on the UAV to obtain terrain height data; constructing a three-dimensional flight profile based on the terrain height data, and determining the UAV's flight altitude in real-time according to the three-dimensional flight profile and the ground safety distance range, generating a flight path adapted to the terrain; adjusting the attitude of the surveying pod according to the flight path and the direction of the surveying target using a rotatable pod drive device, so that the main sensors inside the surveying pod are vertically aligned with the surface of the surveying target; receiving ground reference station data through a dynamic reference correction module, and correcting the positioning data during the surveying process in real-time using ground control points as a reference, and outputting the surveying results.

This invention discloses a UAV-GPR noise suppression and imaging method and apparatus based on Hankel trajectory matrix decomposition, belonging to the field of ground-penetrating radar technology. The method first preprocesses the radar echo data and constructs a Hankel-block-Hankel trajectory matrix, achieving noise suppression through singular value decomposition and adaptive truncation and reconstruction based on a quasi-local curvature metric. Then, the derivative threshold reference point method is used to accurately extract the arrival time of surface reflections from the noise-suppressed data, thereby estimating and correcting flight altitude variations. Next, singular value decomposition based on a distance threshold is applied to suppress surface reflections in the altitude-corrected data. Finally, a time-delay summation imaging method based on refraction point approximation in a two-layer medium model is derived, and the filtered data is focused and imaged using the average flight altitude. This invention achieves accurate detection and location of underground targets.

This application discloses a method, system, drone, and medium for preventing multi-rotor drones from crashing. The method includes: real-time monitoring of the motors of all rotor components on the drone to identify the faulty motor; controlling the arm corresponding to the faulty motor to perform swing control, controlling the arm corresponding to the adjacent motor of the faulty motor to perform a first rotation control, and performing a first speed increase control on all non-faulty motors; based on a drive device, controlling the diagonal motor of the faulty motor to perform a second rotation control, and performing a second speed increase control on the diagonal motor; obtaining the current flight altitude, and executing emergency landing control based on the current flight altitude. This application can accurately identify and locate the faulty motor, and through the control of the arms and rotor components, enables the drone to maintain stability in the air and land stably on the ground, effectively preventing drone crashes and ensuring the safety and stability of drone landing.

This invention discloses a method and system for assessing human-machine interaction risks in low-altitude manned aircraft, relating to the field of interaction assessment. The risk assessment method includes the following steps: Step 1: Real-time acquisition of the user's weight, height, and center of gravity position body posture data through sensors installed on the low-altitude manned aircraft; Step 2: Real-time acquisition of environmental state data of the current flight environment, including wind speed, wind direction, airflow turbulence intensity, temperature, humidity, and flight altitude; Step 3: Based on different flight modes of the aircraft, preset corresponding acceleration setting coefficients for takeoff acceleration, cruise acceleration, turning acceleration, and emergency braking acceleration; This can simulate the center of gravity shift response under different acceleration modes, calculate the user's center of gravity shift coefficient under different preset action modes, quantify the stability risk of the user's body balance in real time, and achieve accurate classification and judgment of risk status.

The application provides a target projectile and an aircraft. The target projectile comprises a head part in a conical shape, a projectile body comprising at least one engine body section, a first engine body section close to the head part being connected to the head part, a tail part arranged at an end of the engine body section away from the head part and comprising at least two tail wings distributed around an axis of the engine body section, and a rudder part arranged at an end of the first engine body section close to the head part and comprising at least two rudder wings distributed around an axis of the first engine body section, wherein in a first plane perpendicular to the axis of the engine body section, the orthographic projection of the at least two rudder wings is staggered with the orthographic projection of the at least two tail wings. The application realizes controllable supersonic flight of the target projectile in a large airspace and a wide speed range, with a flight height of 0.1-20 km and a flight speed of 0.3-2.4 Ma.

The embodiment of the application relates to the technical field of flight control, and discloses a wide-range aircraft attitude control method, device and equipment, which comprises the following steps: constructing a dynamic model of a wide-range aircraft based on a nonlinear model state quantity and a control input; obtaining a linear variable parameter model of the wide-range aircraft based on the dynamic model of the wide-range aircraft by adopting a linear variable parameter vector, the linear variable parameter vector comprising a Mach number, a flight height, an angle of attack and a sideslip angle; constructing a self-disturbance rejection controller of a roll channel, a pitch channel and a yaw channel based on the linear variable parameter model of the wide-range aircraft for flight attitude control; and performing attitude control on a target wide-range aircraft according to the self-disturbance rejection controller of the roll channel, the pitch channel and the yaw channel. The self-disturbance rejection controller is used for responding to local uncertainty in a mode, so that high-precision stable control of the wide-range aircraft is realized.

This invention discloses a rapid registration method for visible light and infrared images from a UAV, belonging to the fields of image processing and UAV remote sensing technology. The method includes: acquiring camera intrinsic parameters, calculating the intrinsic parameter ratio, and obtaining a fixed offset value through benchmark calibration in a high-altitude scene; simultaneously acquiring visible light and infrared images of the same scene, and obtaining the flight altitude and the physical baseline distance between the two cameras; scaling the infrared image according to the camera intrinsic parameters to determine the registration window size; constructing a physical offset model to establish the total offset value of the registration window center relative to the visible light image center; determining the registration window center by applying the total offset value to the visible light image center in the visible light image coordinate system, and calculating the coordinates of the four corner points according to the registration window size to achieve accurate registration. This method features high computational efficiency, fast registration speed, and no need for a large training dataset, thus meeting the rapid registration requirements of visible light and infrared images from UAVs.

This invention discloses a method and system for simulating aircraft communication performance in complex environments. The method includes: determining a field environment map model for aircraft flight; constructing a complete aircraft model with antennas installed; selecting a base station model based on the field environment map model and building antennas on the base station model to obtain a complex environment scenario; simulating the aircraft flight process based on the complete aircraft model in the complex environment scenario, and analyzing the impact of different flight altitudes on communication performance. This invention simulates aircraft communication performance by analyzing and comparing the impact of different flight environments and flight states on aircraft communication performance. In practical engineering applications, it can effectively improve aircraft communication performance and avoid unclear communication and data parsing errors.

This invention relates to the field of watershed topographic monitoring technology, providing a method and system for intelligent watershed monitoring based on UAV oblique photography. The method includes the following steps: Based on a watershed digital elevation model, the flight altitude is dynamically adjusted according to topographic undulations to acquire oblique photographic images; potential feature points are initially screened on each image, and the quality index of each potential feature point is determined based on neighborhood conditions and elevation information; the final retained feature points are determined based on a quadtree algorithm, topographic conditions, and the quality index; the texture information of the surrounding images of the final retained feature points is encoded, and this encoded information is used for comparison and matching in different images; feature point matching is performed, and the matching confidence of each feature point is determined. When the matching confidence is lower than a confidence threshold, dynamic accuracy compensation is performed based on structure tensor and texture gradient to determine the 3D model. This invention can promptly detect and correct errors that occur during the matching process, improving the accuracy and quality of the 3D model.

This invention discloses a multi-target detection method and system based on digital twins for the low-altitude domain. The method proposes the DT-YOLO end-to-end detection framework, addressing the challenges of small target detection from a UAV perspective, poor adaptability to complex environments, and high training data acquisition costs. Through the collaborative design of four core modules—a lightweight backbone network, a high-resolution feature pyramid, multi-scale adaptive enhancement, and hybrid balanced loss—it achieves high-precision, lightweight, and weather-adaptive multi-target detection. The system employs a graphical user interface for intuitive human-computer interaction. This invention combines deep learning methods with digital twin technology to perform real-time identification, localization, and detection of various targets, including vehicles and pedestrians, in UAV aerial images, and possesses robust detection capabilities under various weather conditions, flight altitudes, and viewing angles.

This invention provides a method and system for projecting anomaly data from aerial magnetic surveys obtained by drone terrain-following flight onto the ground. [Solution] The method includes the steps of: acquiring aeronautical magnetic data at a fixed flight altitude during terrain-following flight; acquiring spectral information of the fixed flight altitude Dirichlet problem solution under initial boundary value conditions for ground magnetic anomalies; establishing a least-squares iterative optimization solution of the inverse Fourier transform of the aeronautical magnetic data and spectral information; and obtaining ground projection data based on the least-squares iterative optimization solution. The present invention is an efficient and practical application method technology that can obtain aeronautical magnetic anomaly resolution equivalent to that of ground collection while taking advantage of the rapid data collection efficiency of drone aeronautical magnetic surveys. This method technology has a significant effect in improving the application effect of low-altitude drone aeronautical magnetic surveys and expanding the flight altitude space of drone aeronautical magnetic surveys.

This invention provides a visual positioning method for UAV cruise based on an optoelectronic payload. The method includes: using the optoelectronic payload to perform downward-looking imaging of the ground to acquire an original image; correcting the original image according to the attitude of the optoelectronic payload and the flight altitude to acquire a corrected image; and performing feature extraction and matching on a reference image and the corrected image respectively to achieve visual positioning during the UAV cruise phase. Specifically, correcting the original image according to the attitude of the optoelectronic payload and the flight altitude includes: performing orthorectification on the original image according to the attitude of the optoelectronic payload to acquire an orthorectified image; and performing scale correction on the orthorectified image according to the flight altitude and the spatial resolution of the reference image to acquire a corrected image. This invention solves the technical problems of complex structure and high cost associated with using dedicated imaging devices for visual positioning during the UAV cruise phase in existing technologies.

The application discloses an angle adjusting method and device for shooting a hot spot of a photovoltaic power station by using a UAV, and belongs to the technical field of image acquisition and analysis, and comprises the following steps: S1, acquiring basic data; S2, calculating an optimal flight height according to an infrared camera focal length, a flight angle, an installation angle of a photovoltaic cell panel, an illumination intensity, a solar elevation angle, a wind speed and an environmental temperature change; S3, adjusting a pitch angle of the infrared camera according to the optimal flight height, the solar elevation angle, the illumination intensity, the wind speed, the environmental temperature change, the infrared camera focal length and a straight-line distance of a starting point; and S4, calculating a shortest flight path according to the optimal flight height, a UAV flight speed, a shooting task time, an image resolution, the flight angle, the solar elevation angle, an environmental temperature value before the UAV flight, the illumination intensity, the wind speed and the environmental temperature change. The application can improve the precision of hot spot detection.

The application belongs to the technical field of aviation power system, and discloses a kind of hot drive duct fan's aircraft propulsion system and its operating method, wherein the system includes variable power and control unit, heat exchange combustion unit, closed cycle power unit and thrust fan;Heat exchange combustion unit provides heat energy to closed cycle power unit by fuel combustion, and closed cycle power unit converts heat energy into mechanical energy to drive thrust fan movement;Wherein, closed cycle power unit includes closed cycle gas circuit, gas circulates in closed cycle pipeline, heat exchange combustion unit provides heat energy for gas in closed cycle gas circuit, drives SCO2 turbine to rotate, and drives thrust fan to operate.The application provides thrust for fan while providing cooling heat sink for hot drive type closed cycle power unit, with the advantage of large cold quantity;At the same time, it can adapt to wider range of environmental pressure changes, and the output power has the advantage of small attenuation with the change of aircraft flight height.

1. The name of the design product: integrated mechanical oxygen supply anti-G regulator. 2. The use of the design product: the design belongs to the appearance design of the integrated mechanical oxygen supply anti-G regulator, which integrates the oxygen supply regulator and the anti-G regulator, and provides oxygen supply and overload protection for the user in different flight altitudes and flight conditions. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view.

The present application relates to a control method of an aerial vehicle. The aerial vehicle may comprise a propulsion structure for providing flight power and a spraying apparatus for spraying a material. The control method may comprise determining current target information of the aerial vehicle during a process of the aerial vehicle performing a spraying task, wherein the current target information indicates wind field strength of a downward pressure wind field generated by the propulsion structure; determining, based on the current target information, a desired relative flight altitude of the aerial vehicle corresponding to the current target information relative to the material being sprayed below the aerial vehicle; and controlling the aerial vehicle to fly toward the desired relative flight altitude.

This invention discloses a dual-fuel blending system based on flight altitude and attitude. A remote control command sending unit sends a set target blending ratio (SAF) command to the main control unit. An adaptive command generation unit based on altitude and attitude collects flight altitude data and aircraft pitch angle and attitude data in real time and sends the aircraft data to the main control unit. The main control unit includes a receiving end, an RP-3 aviation kerosene supply unit, and an SAF fuel supply unit. The receiving end receives either the set target blending ratio command or a target blending ratio command generated based on aircraft altitude and attitude data. It drives the RP-3 aviation kerosene supply unit and the SAF fuel supply unit according to the target blending ratio command, achieving phased dynamic blending of SAF and RP-3 aviation kerosene. This invention can achieve a continuously adjustable SAF blending ratio of 0-50%, with a control error ≤ ±2% and a response time ≤ 20ms. It is suitable for dynamic fuel blending scenarios in civil aviation aircraft, general aviation aircraft, and other aircraft, balancing emission reduction benefits and fuel economy.

The application belongs to the technical field of unmanned aerial vehicles, and discloses a hovering test method and system for selected designated aircraft of formation aircraft and application. The method comprises the following steps: the aircraft enters a GPS fixed solution state; a ground station automatically numbers the position and placement distance of the aircraft; the ground station takes the height of the original point aircraft as a reference height and issues a hovering instruction; the aircraft receives the hovering instruction, takes the current position longitude and latitude and the height issued by the ground station as a target position, and performs hovering flight without time limit by default; after completing the hovering test, an operation operator clicks landing, and flight test is completed. Through optimization of the hovering test scheme of the formation aircraft, the aircraft can perform flight test after the ground station issues the flight height, and the test duration when the aircraft flies to a low battery level by default, which improves the flexibility of aircraft verification, and a one-key landing is matched to perfectly replace the hovering test of the dance step waypoint position flight.

This invention relates to the field of cargo management technology, and particularly to a method and system for cargo inspection and supervision based on unmanned aerial vehicles (UAVs). The method includes: scanning cargo to construct a basic cargo storage model; constructing a virtual inspection route and controlling the UAV to move along the virtual route; constructing a path control random function and controlling the UAV's flight altitude according to the path control random function to scan the cargo and obtain real-time scan data; generating a simulated path and generating simulated scan data based on the simulated path, and comparing the results to generate cargo inspection results. During the inspection process, this invention uses a UAV to randomly scan cargo along a random path, thereby obtaining scan data corresponding to each cargo model. Based on the scan data, it determines whether there are any anomalies, greatly reducing labor intensity, enabling cargo supervision over large areas, and ensuring cargo safety.

The application discloses a SOFC system health state estimation method for aviation dynamic harsh environment, a one-dimensional dynamic mechanism model coupled with flight altitude, temperature and pressure change is constructed, and a multi-scale gradual failure model driven by a Gaussian function is introduced to truly simulate macro and micro degradation processes under aviation working conditions; a labeled data set is generated based on the model, an LSTM is trained to predict voltage degradation trend; further, SHAP explainability analysis is fused to screen key features, optimize the model, and quantize the contribution of environmental parameters to health indicators; through space-ground health degradation comparison, it is revealed that high-altitude environment significantly aggravates performance degradation. The method reduces RMSE by 26.2% and MAE by 33.5%, has high precision and strong explainability, and is suitable for real-time health management and predictive maintenance of aviation SOFC systems.

The application belongs to the technical field of aviation power system, and discloses a distributed propulsion system and method for low-altitude aircraft based on supercritical CO2, wherein the system comprises a high-speed start / generator, a SCO2 power device, a system controller, a power distributor, a lithium battery and an electric propulsion unit; the SCO2 power device drives the high-speed start / generator to operate and generate electricity, the generated electricity is provided to the lithium battery and the electric propulsion unit through the power distributor, the system controller collects signals of the high-speed start / generator and the lithium battery, and the system controller controls the high-speed start / generator, the SCO2 power device, the power distributor and the lithium battery; the SCO2 power device is a structure for converting heat energy of external heat carriers into kinetic energy. The application can be used for manned aircraft and unmanned aerial vehicles adopting rotor take-off and thrust cruise, the system state is not affected by flight height and environmental air pressure, and the output power has the advantage of small attenuation with the change of the flight height of the aircraft.

The application relates to a thrust control system under a FLCH mode, comprising: an upper branch, comprising: a height difference calculation module configured to calculate a height difference between a target height and a current height of an aircraft; a latch module configured to latch a value of the height difference according to a manual operation reaction time delay and an industry requirement; a vertical speed calculator configured to calculate a corresponding expected vertical speed according to the latched height difference output by the latch module; and a thrust calculator configured to calculate a corresponding thrust according to the expected vertical speed; a lower branch, comprising: a selector configured to select an integral rate according to an integral rate judgment condition; an integrator configured to integrate by time according to the selected integral rate to output a compensation thrust; and an adder configured to add the thrust from the upper branch and the compensation thrust from the lower branch to output a thrust command.

The invention relates to a system for recording and analysing flight data of an aircraft (A) flying at low altitude below 3000 meters, the aircraft (A) comprising integrated sensors (A1), the system comprising: - an on-board housing (1) in the aircraft (A), containing independent sensors (11) that are separate from the integrated sensors (A1) and operate autonomously without any connection to the integrated sensors (A1) of the aircraft (A), the on-board housing (1) comprising a connectivity module (14) for transmitting the flight data from the independent sensors (11) to the ground, the connectivity module (14) supporting various communication technologies, in particular 3G and 4G, thus ensuring continuous and reliable transmission, and - an analysis module (2) that remains on the ground, is equipped with reception means (23) and receives the flight data transmitted by the connectivity module (14) of the on-board housing (1), the analysis module (2) comprising analysis means (21) for analysing the received flight data, characterized in that it furthermore comprises: - an automatic network switch (141) for automatically switching between the available networks, giving preference to the most stable and fastest connections, in order to ensure uninterrupted transmission of the data, even in the event of signal loss or weak connection, and - a temporary buffer memory (13) for ensuring continuity of the recordings by managing any connection losses, the temporary buffer memory (13) storing the flight data during periods when the connection is interrupted and, once the connection has been restored, the data stored in the temporary buffer memory (13) are automatically transmitted, ensuring that all flight information is correctly recorded and sent, even during a loss of connection.

The method includes: controlling unmanned aerial vehicle to be aligned with ground orbit in destination site and continue to fly at predetermined flight altitude, in response to the unmanned aerial vehicle flying to first preset airspace near the destination site; controlling the unmanned aerial vehicle to be separated from first cabin carried by the unmanned aerial vehicle and place the separated first cabin at first position of lifting platform of shuttle vehicle driving along the ground orbit and controlling the unmanned aerial vehicle to be combined with second cabin carried at second position of the lifting platform, in response to the unmanned aerial vehicle flying to position directly above the first position and being in relatively static state with the shuttle vehicle; and controlling the unmanned aerial vehicle to fly to next destination site, in response to completion of the combination of the unmanned aerial vehicle and the second cabin.

This invention proposes a vehicle-mounted drone intelligent point-and-fly control system, method, storage medium, and computer program product. The system includes: a map and interaction module, a geographic data service module, and a task planning and decision-making module. This invention enables deep integration of drones and vehicles, utilizing the vehicle's large screen and computing power to achieve intelligent point-and-fly flight; adaptively planning flight altitude based on cloud-based geographic data and task type; parallel processing of interactive commands such as zooming, gimbal control, and destination changes during flight, achieving a smooth "what you see is what you get" operation; and combining video clicks with cloud-based POI data to present building information in an augmented reality manner, achieving an intelligent "what you see is what you know" experience.