152 results about "Flight direction" patented technology

The invention provides a multi-source information fusion unmanned aerial vehicle marine target tracking method and system, and relates to the technical field of data processing, and the method comprises the steps: obtaining image data, and extracting the features of a target region; unmanned aerial vehicle attitude data, radar position detection data and AIS identification data are obtained, attitude disturbance correction is executed, and time axis alignment is performed on the data; calculating the visual feature matching offset of the adjacent frames, and comparing the visual feature matching offset with the radar azimuth change trend; constructing a candidate target spatial position set, and executing distance convergence screening and spatial overlapping constraint processing of a geometric projection range on the candidate target spatial position set; motion direction continuity comparison is executed, and target position data is generated; generating a track control instruction for controlling the flight direction and speed of the unmanned aerial vehicle according to the target position data, and adjusting the subsequent flight path of the unmanned aerial vehicle according to the track control instruction; according to the invention, autonomy and accuracy of unmanned aerial vehicle marine target tracking are improved.

The invention is suitable for the technical field of image processing, and provides a visual obstacle avoidance method and device for an unmanned aerial vehicle, and the method comprises the steps: collecting a plurality of real-time depth images based on a preset sampling frequency, and determining whether a dynamic obstacle exists or not according to the real-time depth images; when the existence of the dynamic obstacle is determined, constructing a current obstacle avoidance space sphere according to the depth value in the real-time depth image, the speed of the unmanned aerial vehicle and the actual estimated length of the obstacle; when the flight direction of the unmanned aerial vehicle intersects with the current obstacle avoidance space sphere, calculating an obstacle avoidance bypassing route based on the surface edge of the current obstacle avoidance space sphere; and controlling the unmanned aerial vehicle to perform obstacle avoidance flight based on the obstacle avoidance bypassing route. Compared with a traditional obstacle avoidance method, the method can more intelligently plan the detour route of the unmanned aerial vehicle, and guarantees the stability and safety of the flight process.

The invention relates to the technical field of aircrafts, in particular to a master-slave multi-rotor unmanned aerial vehicle which comprises a control system and a storage battery. The device further comprises a structure assembly. The structural assembly comprises a tetrahedral shell, coaxial reverse dual motors, two main rotors, three branch pipes, three driving mechanisms and three slave rotors. The control system controls operation of the whole, and the storage battery supplies power to the whole. The large-size main rotor is used for replacing a traditional multi-rotor to provide main lifting force, the efficiency can be improved, the energy utilization level can be improved, and meanwhile the loading capacity is higher compared with the multi-rotor; a combined triangle is used as a main structural form, so that the structural stability and reliability under various stress conditions are ensured, and the use is more stable under a complex scene; the flight direction, attitude and stability are controlled by three small-size slave rotors; therefore, the problems that an existing multi-rotor unmanned aerial vehicle is low in energy utilization efficiency and poor in loading capacity are solved.

The invention relates to a community low altitude-oriented aircraft path planning and traffic capacity evaluation system. The system comprises an airspace facility modeling module, a facility relation judgment module, a hierarchical airspace segmentation module, a noise-speed-safe distance constraint calculation module, a dynamic obstacle marking module, a multi-target path planning module and a bottleneck identification and traffic capacity evaluation module. The method comprises the following steps: modeling airspace facilities, and judging a facility relationship based on spatial geometric attributes and function use requirements of the facilities; performing hierarchical grid division on the low altitude of the community, calculating a safety distance along the movement direction and a safety distance perpendicular to the flight direction, and performing obstacle marking on grids around the building based on the safety distances and the flight direction; and performing path search based on an improved A * algorithm, identifying a bottleneck region, extracting parameters, and calculating the maximum allowable speed of the bottleneck region and the total traffic capacity of the bottleneck region. The system can relieve environmental troubles such as safety compliance dispute and noise pollution caused by operation of the low-altitude aircraft.

The invention discloses an airship type unmanned aerial vehicle inspection system and inspection method, and belongs to the field of inspection unmanned aerial vehicles. The system comprises a laser radar, an image acquisition device, an airship capsule filled with helium, a standby safety airbag, a communication module and a ground control center, in the method, the ground control center sets an inspection path and issues the inspection path, and the unmanned aerial vehicle flies according to a preset path. During fault detection, the high-definition camera collects images to recognize line cracks and broken strands, the thermal infrared imager monitors the joint temperature, the gas sensor detects abnormal gas, and multi-source data fusion assists in defect positioning. The routing inspection takes a starting point-terminal point connecting line of a power transmission line as a reference, identifies main obstacles and surrounding nodes to perform global planning, performs key routing inspection on a risk area in combination with historical data, and initializes and guides a flight direction through a Q value to reduce invalid exploration. The four-rotor unmanned aerial vehicle solves the problems of short flight time and poor stability of a four-rotor unmanned aerial vehicle, improves the inspection stability and cruising ability, and improves the inspection efficiency of a power transmission line and the reliability of a power system.

The invention discloses a distribution network unmanned aerial vehicle ground simulation flight method and device based on AI vision and a medium, and the method comprises the steps: collecting a first real-time image in a flight direction in real time in a height calibration stage before an unmanned aerial vehicle flies to a next target tower pole; dynamically adjusting the height of the unmanned aerial vehicle according to the image width ratio of the distribution wire in the first real-time image until the target tower safety height is reached; after the unmanned aerial vehicle flies over the target tower pole according to the target safety height, a second real-time image in the flight direction is collected in real time through the visual sensor; and according to the image width ratio of the power distribution wire in each second real-time image and the real-time positioning information of the unmanned aerial vehicle, controlling the unmanned aerial vehicle to perform flight height change with the height fluctuation of the power distribution wire in the flight direction by taking the target tower pole as a starting point, and according to the technical scheme of the embodiment of the invention, autonomous height adjustment of the unmanned aerial vehicle is realized through visual intelligent analysis; the equipment cost and the operation complexity are greatly reduced, and the inspection efficiency and quality of the unmanned aerial vehicle are remarkably improved.

The embodiment of the invention provides a rocket vertical recovery method and system and a rocket, and the method comprises the steps: after a first-stage rocket is separated, the thrust of a central engine of the first-stage rocket is adjusted to a preset proportion of rated thrust so as to provide positive overload for a propellant in a storage tank; the propellant can be gathered to an outlet in the bottom of the storage tank through positive overload; the flying direction of the first-stage rocket deviates from the current flying direction by performing bidirectional swinging on the central engine, and the posture of downward diving of the first-stage rocket towards the earth direction is kept; tangential force in two different directions tangent to the current flight direction of the first-stage rocket can be generated at the same time by swinging the center engine in two directions, the posture of the first-stage rocket is adjusted to the upward flight posture from the downward diving posture, and speed reduction is conducted till the first-stage rocket lands on the earth. The thrust of the center engine of the first-stage rocket is adjusted to be small, and attitude control and propellant management of first-stage rocket recovery are achieved.

The invention relates to a control method, a control system and a traction system of a traction unmanned aerial vehicle. The traction unmanned aerial vehicle comprises a plurality of vertical rotors and two tension rotors. The rotation axis direction of each tension rotor wing is the first direction. The traction drone is configured to be connected to the unpowered aircraft through a traction rope. The control method comprises the following steps: acquiring a preset flight direction of the unpowered aircraft; the traction unmanned aerial vehicle is controlled to move to the front upper portion of the unpowered aircraft in the preset flight direction; and controlling the traction unmanned aerial vehicle to pull the unpowered aircraft to rise to a preset height through the traction rope. Wherein the step of controlling the traction unmanned aerial vehicle to pull the unpowered aircraft to rise to the preset height through the traction rope comprises the substeps that when the unpowered aircraft climbs, the angle between the first direction and the direction of the traction rope is controlled to be smaller than or equal to 20 degrees.

The invention discloses an unmanned aerial vehicle autonomous route planning method and system capable of adapting to environmental changes. The method comprises the steps of obtaining a dynamic three-dimensional situation map of a flight area of an unmanned aerial vehicle based on multi-source data of the flight area of the unmanned aerial vehicle; acquiring a current no-fly zone and weather forecast information of the flight area of the unmanned aerial vehicle, and analyzing and acquiring a flight risk distribution condition of the flight area of the unmanned aerial vehicle based on the dynamic three-dimensional situation map; considering the flight risk distribution condition of the unmanned aerial vehicle flight area, the unmanned aerial vehicle flight task and the unmanned aerial vehicle self-state information to generate an unmanned aerial vehicle reference route; and automatically adjusting the flight speed, the flight height and the flight course of the unmanned aerial vehicle according to a preset flight parameter adjustment model based on the acquired multi-source data and the state information of the unmanned aerial vehicle in the process of flying along the reference route. According to the invention, the reliability and safety of flight task execution of the unmanned aerial vehicle in a complex dynamic environment can be improved.

The invention provides an unmanned aerial vehicle autonomous inspection method and system based on distribution line electromagnetic characteristic driving, an electromagnetic sensor array is carried on an unmanned aerial vehicle, three electromagnetic sensors are adopted to form a triangular arrangement, the two electromagnetic sensors are arranged along the flight direction of the unmanned aerial vehicle, and the connecting line points to the direction of the head of the unmanned aerial vehicle. The relative attitude of the unmanned aerial vehicle and the distribution line is judged; the third electromagnetic sensor is arranged on the other side of the triangle formed by the third electromagnetic sensor and the connecting line and is used for estimating the transverse distance between the unmanned aerial vehicle and the distribution line; the flight height of the unmanned aerial vehicle is obtained by an airborne barometer, and the flight height of the unmanned aerial vehicle is set according to the height of the distribution line in the area. The unmanned aerial vehicle has the advantages that the electromagnetic sensor array is used for collecting electromagnetic signals of the distribution line, the relative position relation between the unmanned aerial vehicle and the distribution line is estimated according to the electromagnetic field distribution condition, autonomous navigation flight of the unmanned aerial vehicle is achieved, GNSS dependence is reduced, and effective routing inspection is conducted in GNSS signal attenuation or interruption zones.

The invention belongs to the technical field of multi-modal vehicle obstacle avoidance, and relates to a multi-modal vehicle 4D dynamic obstacle avoidance method, which comprises the following steps: taking an air-ground amphibious vehicle, namely a multi-modal vehicle as a center, constructing a plurality of concentrically increasing sphere safety domains which respectively correspond to a collision avoidance area, an early warning area and a trajectory prediction area, the space-time position and the movement track of a dynamic obstacle are monitored and predicted in real time, a three-dimensional space is divided into eight quadrants according to the flight direction based on the current course of a multi-mode vehicle, different sensing priorities and obstacle avoidance strategies are given to the front quadrant, the side quadrant and the rear quadrant, and particularly, the front quadrant, the side quadrant and the rear quadrant have different sensing priorities and obstacle avoidance strategies. Dynamically adjusting the risk level and the obstacle avoidance response according to the relative speed and the movement trend of the obstacle, and carrying out hierarchical and regional risk perception and management on the dynamic obstacle in different space directions and distance ranges; the method is scientific and reliable in principle, and is suitable for a multi-body cooperative obstacle avoidance scene in an urban low-altitude traffic environment.

This invention proposes a method for fusing multiple interferometric SAR observation data, which can simultaneously perform InSAR data fusion and geolocation, and finally complete the fusion of DEM data in the orthorectified domain. Specifically, this invention combines conventional image registration methods with joint calibration methods, employing a weighted averaging method to fuse multiple InSAR observation data in the orthorectified DEM domain. It can fuse multiple interferometric SAR observation data from different flights, different flight directions, and different perspectives, thereby reducing random errors in the DEM and improving the accuracy of interferometric SAR elevation inversion.

The present application relates to the technical field of low-altitude aircraft, in particular to a pre-turning flight ball car control method and a pre-turning flight ball car, wherein the pre-turning flight ball car control method comprises the following steps: S1, obtaining a pre-turning direction and a current direction; S2, calculating a pre-turning angle and a pre-turning adjustment direction based on the pre-turning direction and the current direction; S3, controlling the pre-turning device to drive the flight driving device or the combination of the flight driving device and the cabin to turn relative to the landing gear to face the pre-turning direction according to the pre-turning angle and the pre-turning direction. In this way, the problems of the existing golf cart, such as limitation, and the traditional aircraft, such as increased flight distance and poor passenger experience caused by adjusting the flight direction after take-off, are solved.

In the aerospace industry, the Laval nozzle is primarily used. This nozzle has the problem of not being able to adapt to changes in ambient pressure. Therefore, it loses efficiency as the vehicle ascends. Aerospike nozzles solve this problem, but are more difficult to cool, so they are not a viable alternative to the Laval nozzle. By means of a fixed arrangement of several Laval nozzles, consisting of nozzles (16) directed parallel to the object's flight direction and several nozzles (17) directed at an angle to this jet, the nozzle assembly creates an effect similar to an aerospike. Therefore, at decreasing pressure, such a nozzle assembly exhibits greater efficiency than conventional Laval nozzles. Since the assembly consists entirely of Laval nozzles, it is no more difficult to manufacture and cool than these. Furthermore, the thrust vector exerted by the nozzle assembly, and thus the direction of motion of the object being accelerated, can be controlled by throttling certain secondary nozzles (e.g., 17.2). The resulting fixed connection between the nozzles and combustion chambers allows for higher operating pressure within the combustion chambers, allowing for more efficient fuel use. Since the fixed connection allows for better thrust transfer, the thrust vector can be changed more radically and quickly.

The invention discloses an instrument landing navigation method which comprises the following steps: firstly, constructing an ILS instrument landing system comprising a course beacon LOC and a glide beacon station GS, and accurately calculating a DDM modulation degree difference by adopting a normalization method; then, the system receives an intermediate-frequency 70MHz signal transmitted by the VOR navigation station, and noise and interference components in the signal are effectively removed through digitization and low-pass filtering processing; then, amplitude modulation and frequency modulation demodulation are carried out on the filtered signal, and a key 30Hz navigation signal is successfully extracted; by using the DDM and the 30Hz signal, the system performs zero-cross detection and accurately calculates the phase difference; and finally, according to the calculated phase difference, the system determines the VOR azimuth angle deviation degree of the aircraft relative to the VOR navigation station, and the flight direction of the aircraft is calibrated according to the VOR azimuth angle deviation degree, so that the navigation accuracy and the flight safety are effectively improved.

The invention relates to the technical field of aircrafts, and discloses an aircraft tilting mechanism which comprises a wing fuselage mechanism, and a nacelle mechanism is controlled to tilt through the wing fuselage mechanism, so that the flight direction of an aircraft is controlled; the tilting mechanism is arranged in the wing fuselage mechanism, the other end of the tilting mechanism extends out of the wing fuselage mechanism to be connected with the nacelle mechanism, the tilting mechanism is used for controlling the nacelle mechanism to tilt, and when the nacelle mechanism tilts, the flight state of the aircraft is changed; the transmission mechanism is in transmission connection with the tilting mechanism, and meanwhile, power of the transmission mechanism in the axial direction of the wing fuselage mechanism is converted into power in the radial direction of the wing fuselage mechanism, so that tilting of the wing fuselage mechanism is controlled. The invention has the advantages of light weight, compact structure, low cost, high reliability, large torque and the like, and solves the problems that the control signal needs multiple conversion, the control is complicated, and the structural weight is heavy.

The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising:an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4);a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4);a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.

The disclosure relates to an annular component for an aircraft gas turbine, having a front flange structure in the direction of flight, a rear flange structure in the axial direction and an annulus structure arranged between the flange structures in the axial direction, wherein the annulus structure has a variable cross-sectional form and / or a variable material arrangement in the circumferential direction and / or perpendicularly to the circumferential direction and at least one of the flange structures has at least two annular portions in the circumferential direction, which are each arranged at a different angle relative to the annulus structure. The disclosure furthermore relates to an aircraft gas turbine having an annular component and a method for producing the annular component.

The application discloses a kind of unmanned plane continuous speed space gesture control system and method based on somatosensory glove, including gesture data acquisition module, data transmission module and flight control execution module;Gesture data acquisition module includes palm data acquisition module and palm data solution module.The application utilizes current attitude quaternion to calculate thumb orientation to control flight direction, finger bending angle is converted into flight speed size, uses thumb direction as flight direction, finger bending degree is converted into flight speed, realizes the continuous speed direction space and size space unmanned plane glove control, reduces the computing resource overhead, while overcome the limitation of traditional unmanned plane remote controller, improve control efficiency, with intuitive and convenient operation, response is fast, control is accurate and the like, applicable to the flexible control scene of unmanned plane, enhance the immersion and friendliness of interaction, improve user experience and flight safety.

The application relates to the field of aircraft technology, and discloses an aircraft and a thrust device thereof. The thrust device is applied to the tail of the aircraft and comprises a motor module and a propeller. The tail of the aircraft comprises a first surface and a second surface connected with each other. The motor module is vertically installed on the first surface, the first surface is perpendicular to the flight direction of the aircraft, the second surface is extended to be connected with the surface of the aircraft body, the propeller is connected with the motor module, and the propeller rotates to push the aircraft to move forward. The thrust device is directly arranged on the outside of the aircraft, and an additional heat dissipation channel is not needed in the inside of the aircraft, so that the cost of related components is saved.

The application discloses an airborne radar system, which is characterized in that: the airborne radar system comprises cabin equipment for realizing main electrical functions of a radar, more than one belly radar window for realizing communication between inside and outside of an aircraft cabin, an antenna holder for realizing fixed connection of an external antenna and an aircraft body, and an antenna fixedly installed on the antenna holder, and the cabin equipment and the antenna are connected through a radio frequency cable. The application discloses a remote sensing detection method of the airborne radar system, which is characterized in that: the remote sensing detection method mainly has two working states of a transmitting process and a receiving process. The application can be applied to microwave radars, radiation detection, laser surveying and mapping, optical aerial photography and other types of task requirements needing external antennas or components; and in a single flight direction, different types of equipment can be carried to realize optical, microwave and other multifunctional tasks.

There is provided a drone comprising, a main body which is elongated and having a longitudinal axis, the main body being rotatable attached at one end of the elongated body to a propeller body with a shaft so that the main body and the propeller body are arranged to rotate in relation to each other, so that the propeller provides thrust in the direction of the shaft, where the main body rotates around its longitudinal axis, the drone comprising driving means mechanically connected to the shaft, the driving means driving rotation of the bodies in relation to each other, the drone comprising a control device arranged to control the speed of rotation of the driving means to control the thrust and further arranged to control the flight direction of the drone, where the drone is configured to rotate the propeller body at a first rotation speed that is greater than a second rotation speed of the main body in relation to an external frame of reference, the second rotation speed being referred to as roll speed, where the drone is configured such that the longitudinal axis of the main body has, during flight, an angle of attack greater than zero to the flight direction of the drone, said longitudinal axis rotating around the flight direction of the drone, the flight direction being in relation to the external frame of reference, where the rotation around the flight direction occurs with the same angular speed as the main body rolls around the longitudinal axis (roll speed), where the control device is arranged to determine the orientation of the longitudinal axis of the main body in relation to the external frame of reference with a frequency that is higher than the roll speed and adjust the thrust during a subsection of a complete revolution of the main body in relation to the external frame of reference in order to adjust the angle of attack, thereby adjusting the flight direction of the drone.

The invention relates to an unmanned aerial vehicle communication technology, in particular to a communication method and device based on an unmanned aerial vehicle cluster and a storage medium, and the method comprises the steps: in a coding stage, important information is converted into a binary information stream, and the binary information stream is segmented and then jointly coded to the flight direction and relative speed of an unmanned aerial vehicle. Wherein the direction is subjected to multi-bit mapping by dividing a horizontal motion plane into sector pairs, and the speed represents single-bit information through a fast and slow difference by taking a reference machine as a reference. Coding action is executed through the unmanned aerial vehicle, and information is transmitted in a physical space in a visual signal mode. And finally, in a decoding stage, the ground station accurately identifies a motion track through visual sensing and static position detection, and performs reverse solution according to a mapping rule to restore original information, so that robust communication independent of electromagnetic waves is realized. The problems that emergency communication in current complex electromagnetic environments such as battlefields and disaster rescue is high in hardware dependence, and system reliability and maneuverability are affected are solved.

This invention relates to the field of unmanned aerial vehicle (UAV) equipment technology, and discloses a method, apparatus, equipment, and medium for inspecting wind turbines based on UAVs. First, with the UAV reaching its initial cruise position and its battery level within a preset range, an image of the top of the wind turbine is acquired. Then, based on the top image of the wind turbine, the UAV is controlled to fly to the center point of the wind turbine blades and acquire an image of the swept surface. Next, the actual error distance of the swept surface is determined based on the swept surface image. If the actual error distance of the swept surface meets the preset conditions for the swept surface, the reference flight direction of the wind turbine components is determined. Then, based on the component safety distance, the component inspection image overlap rate, and the number of component inspection shots, a sequence of single-step movement distances for each component and the total movement distance of the component are determined. Finally, images are acquired based on the component reference flight direction, the sequence of single-step movement distances, and the total movement distance to obtain a set of component inspection images.

A synthetic aperture radar (SAR) for a flight vehicle may include an elongate phased array antenna oriented with a long axis in an elevation direction. The elevation direction is normal to a direction of flight of the flight vehicle. A transmitter is coupled to the elongate phased array antenna, and a receiver is coupled to the elongate phased array antenna. A controller is coupled to the transmitter and receiver and is configured to generate temporally alternating sets of receive beams for respective swaths to be used to form a SAR image across a surface below the flight vehicle. The same center frequency is used to create consistent SARs for all swaths, allowing for coherent combination between subsequent passes over the same swath.

A method of providing navigational assistance includes: obtaining position information of an aerial vehicle relative to a defined path; calculating an intercept angle for the aerial vehicle to direct the aerial vehicle to a preferred track angle; generating a 3-D perspective projection synthetic view window depicts differences in three dimensions between a point on a defined path and the aerial vehicle at a latitude, longitude, altitude, and a given viewing angle. The 3-D perspective projection synthetic view window includes: a graphical depiction of the defined path through a subsequent waypoint, and a 3-D tactical navigational symbol that includes a preferred intercept angle symbol that is positioned relative to the graphical depiction of the defined path based on the preferred track angle and the intercept angle. The method further includes displaying the 3-D perspective projection synthetic view window on a display device for use in navigating the aerial vehicle.

This invention belongs to the field of unmanned aerial vehicle (UAV) control technology, specifically relating to a method and apparatus for UAV altitude hold control. The method includes the following steps: acquiring electrooculogram (EOG) signals; determining the signal source and detecting blink events based on the EOG signals to obtain an updated desired flight altitude change; acquiring electroencephalogram (EEG) signals; decoding the EEG signals to obtain a determined desired flight direction; determining the desired flight altitude based on the desired flight altitude change and the desired flight direction; inputting the desired flight altitude to a model predictive controller to solve for the optimal control input to generate a desired thrust value; and mapping the thrust value to the speed control signals of each control motor through a power conversion module. This invention converts EEG signals into a desired flight direction and EOG signals into a dynamically adjustable desired flight altitude change, comprehensively determining the desired flight altitude, thus achieving excellent precision and stability in UAV altitude hold control.

A tactically deployable rotorcraft for targeted delivery of effects and / or sensors includes a body housing an energy subsystem, a control and communications subsystem, and a modular payload compartment for holding an effect or sensor payload, the body having a generally cylindrical outline and a plurality of arm-rotor niches therein. Arm-rotor assemblies are pivotably mounted to the body, each including an articulating arm and a rotor at a distal end, and each being pivotable between (1) a closed position in a corresponding arm-rotor niche within the outline of the body, and (2) an open position extending from the body with the rotor facing in a flight direction. The rotors are powered by the energy subsystem and controlled by the control and communications subsystem to provide powered flight to a target location for delivery of the effect or sensor payload.

The invention discloses an electromagnetic radiation source positioning method based on circumferential flight direction finding of an unmanned aerial vehicle under a short base line. The method is suitable for a positioning scene of a mobile observation platform for a single static electromagnetic radiation source. The method comprises the following specific steps that firstly, the flight path of the unmanned aerial vehicle-mounted observation platform is made to be a circle, continuous azimuth angle measurement values are obtained, then fitting of direction change continuity of the unmanned aerial vehicle-mounted observation platform is added, real-time observation values and a prediction model are combined through dynamic correction and state updating, and the optimal angle value at the current moment is obtained through estimation; finding two symmetric points which are symmetric about a connecting line of the radiation source and the circle center on the flight path of the circle, and estimating the distance of the electromagnetic radiation source by using the sine theorem; and finally obtaining a position estimation value of the electromagnetic radiation source. At present, in mobile direction-finding positioning, in order to solve the problems of jitter, maneuvering and limited cruising ability of an airborne flight platform, direction change continuity fitting is realized through a filtering algorithm, the problem of limited cruising ability is solved through short-baseline direction finding, and the positioning cost can be reduced.