88 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 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 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 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 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 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.

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.

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.

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.

The invention discloses a low-altitude flight collision detection method based on conical ray detection. Acquiring environmental space data and position and attitude information of the unmanned aerial vehicle in a three-dimensional space; the flight direction of the unmanned aerial vehicle is obtained according to attitude information processing of the unmanned aerial vehicle in the three-dimensional space, the position of the unmanned aerial vehicle serves as a conical vertex, the flight direction serves as a central axis, and a conical detection area is constructed in combination with the field angle of the unmanned aerial vehicle and a preset detection distance; discretizing the conical detection area to generate a plurality of sub-rays covering the conical detection area; detecting a spatial relationship between each sub-ray and a spatial obstacle according to the environmental spatial data to obtain spatial relationship information of each sub-ray; and adjusting the attitude information of the unmanned aerial vehicle according to the spatial relationship information of each sub-ray. A conical ray detection model is introduced, and compared with traditional single-straight-line ray detection, missing detection and false detection are reduced.

The invention discloses an aircraft and a heat dissipation method thereof, and belongs to the technical field of aircrafts. When the flight direction and / or attitude of the aircraft changes, the heat dissipation surface of the radiator always faces the wind, so that the heat dissipation efficiency of the radiator is improved. The aircraft comprises a fuselage, a power cabin, a first driving assembly, a radiator, a second driving assembly, a detection assembly and a controller. The first driving assembly drives the power cabin to rotate relative to the fuselage, and the second driving assembly drives the radiator to incline relative to the power cabin. The detection assembly is used for measuring the rotation angle of the flight direction of the aircraft and / or the inclination angle of the fuselage. And the controller controls the first driving assembly to move based on the rotation angle and / or controls the second driving assembly to move based on the inclination angle, so that the radiating surface of the radiator is kept in a windward state and is kept vertical to the flight direction of the aircraft when the flight direction and / or attitude of the aircraft are / is changed.

The vector unmanned aerial vehicle of the gyroscope structure comprises a vehicle body and a vehicle frame, and the vehicle frame comprises an inner ring and an outer ring; the fuselage is connected with the inner ring through two collinear first revolute pairs, the axis of the fuselage is a first axis, and the inner ring can rotate around the first axis relative to the fuselage; the inner ring and the outer ring are connected through two collinearly arranged second revolute pairs, the axis of the inner ring and the outer ring is a second axis, and the outer ring can rotate around the second axis relative to the inner ring and can rotate around the first axis relative to the fuselage along with the inner ring; the first axis is vertically intersected with the second axis; the outer ring is connected with a plurality of rotor wing brackets, and each rotor wing bracket is fixedly provided with a rotor wing; the inclination angle of the outer ring relative to the fuselage is changed by controlling the rotating speed of each rotor, and then the flight direction of the unmanned aerial vehicle is changed. The fuselage of the unmanned aerial vehicle can be kept stable all the time, and meanwhile, compared with a traditional vector unmanned aerial vehicle, the control algorithm is simpler.

To realize the tracking of a gliding stage in a missile which repeats jetting intermittently.SOLUTION: When a monitoring satellite 307 having a plurality of monitoring devices detects a significant high-temperature object, the monitoring satellite 307 transmits flying object information to a satellite integrated command center 810 via a satellite information transmission system 403 having a plurality of communication satellites 308. The flying object information includes detected time information, a monitoring satellite ID, a monitoring device ID, and monitoring data. The satellite integrated command center 810 transmits the flying object information to a countermeasure system 405 including a countermeasure asset 801 and a countermeasure ground center 802. The trajectory prediction device 803 derives the position information and the traveling direction of the monitoring satellite having the ID at the detection time in the flying object information, and the line-of-sight direction of the monitoring device having the ID. Then, the trajectory prediction device 803 extracts the high-temperature object luminance from the monitoring data and derives a line-of-sight vector directed to the high-temperature object.SELECTED DRAWING: Figure 9

The invention relates to an interception drone (1) having a drone base body (2) and a plurality of drive devices (3) arranged on the periphery of the drone base body (2). The drive device (3) is arranged and oriented on the drone base body (2) in such a way that the interception drone (1) can be driven and controlled by the drive device (3) in a flight direction (5) along a flight path. The intercepting unmanned aerial vehicle (1) is provided with a capturing net. The capture net is arranged in or on the drone base body (2) in a front drone section (6) of the drone base body (2) in the flight direction (5). The capturing net is fixed to the unmanned aerial vehicle base body (2) by means of a thin and long soft capturing net fixing device. The capturing net is provided with a driving device, and by means of the driving device, the capturing net can be accelerated away from the unmanned aerial vehicle base body (2) in the flight direction (5).

Methods, systems and apparatus, including computer programs encoded on computer storage media for an unmanned aerial vehicle aerial survey. One of the methods includes receiving information specifying a location to be inspected by an unmanned aerial vehicle (UAV), the inspection including the UAV capturing images of the location. Information describing a boundary of the location to be inspected is obtained. Inspections to be assigned to the location are determined, with the inspection legs being parallel and separated by a particular width. A flight pattern is determined based on a minimum turning radius of the UAV, with the flight pattern specifying an order each inspection leg is to be navigated along, and a direction of the navigation.

This invention relates to the field of aerospace Earth observation and remote sensing imaging technology, and discloses a target-driven dual-camera heterogeneous payload dynamic cooperative aiming method and device. The device includes a base, a wide-area search unit, a high-precision staring unit, a field-of-view deflector, and a cooperative controller. The wide-area search unit and the high-precision staring unit are distributed forward and backward along the flight direction. The cooperative controller identifies potential targets and calculates their geographical locations. It calculates the delay time based on the physical distance and real-time velocity. The cooperative controller calculates the track-crossing swing angle based on the target's position and attitude and sends commands. The field-of-view deflector drives the high-precision staring unit to deflect to the track-crossing swing angle within the delay time. The cooperative controller triggers imaging at the end of the delay time. This invention achieves pointing adjustment and exposure synchronization through heterogeneous payload spatiotemporal coordination and a delay time window, realizing wide-area detection and high-resolution fine imaging of potential targets during a single flight.

The application discloses a kind of based on AI vision's network unmanned plane ground effect flight method, equipment and medium, the method includes: in the height calibration stage before unmanned plane flies to next target tower pole, first real-time image in flight direction is collected in real time;According to the image width proportion of distribution wire in first real-time image, dynamically adjust the height of unmanned plane, until reach target tower safety height;After unmanned plane flies over target tower pole according to target safety height, second real-time image in flight direction is collected in real time by vision sensor;According to the image width proportion of distribution wire in each second real-time image and the real-time positioning information of unmanned plane, control unmanned plane to target tower as starting point, follow the height fluctuation of distribution wire in flight direction and carry out flight height change, the technical scheme of the embodiment of the application realizes unmanned plane autonomous height adjustment by visual intelligent analysis, greatly reduces equipment cost and operation complexity, significantly improves the efficiency and quality of unmanned plane inspection.

This invention provides a method for flying a surface effect wing aircraft that can fly over the sea due to thrust and surface effect. [Configuration] A method for flying a surface effect airfoil aircraft comprising: an aircraft body 1; a propulsion device 5 that generates thrust to propel the aircraft body 1 in the direction of flight; multiple pairs of surface effect wings L1, L2, R1, R2 provided on the left and right sides of the aircraft body 1, whose elevation angle can be independently adjusted, and which generate a surface effect during flight to lift the aircraft body 1; and wall-like members 6L, 6R that connect the tips of each surface effect wing L1, L2, R1, R2 and extend downward from the tips of each surface effect wing L1, L2, R1, R2, wherein the surface effect is adjusted by adjusting the elevation angle of each surface effect wing L1, L2, R1, R2, and the aircraft continues to fly by the surface effect.

A camera 16 onboard an airborne or spaceborne platform 12, moving in a flight direction 14 around the earth at a flight velocity Vgsat, is pivotable about a roll axis 18 in line with the flight direct

The application provides a multi-source information fusion unmanned aerial vehicle offshore target tracking method and system, relates to the technical field of data processing, and the method comprises the following steps: acquiring image data and extracting the features of a target area; acquiring unmanned aerial vehicle attitude data, radar position detection data and AIS identification data, performing attitude disturbance correction, and aligning the data on the time axis; calculating the visual feature matching offset of adjacent frames, comparing the offset with the radar azimuth change trend; constructing a candidate target space position set, performing distance convergence screening and spatial overlap constraint processing of the geometric projection range of the candidate target space position set; performing motion direction continuity comparison to generate target position data; 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; and the application improves the autonomy and accuracy of unmanned aerial vehicle offshore target tracking.

The application discloses a lightweight method for reducing calculation amount in high-speed aircraft background schlieren imaging, and belongs to the field of high-speed aircraft air disturbance flow field visualization. The method comprises the following steps: inputting a background image without an aircraft and a background schlieren image with the aircraft; compressing a two-dimensional image to a one-dimensional signal through background difference projection to determine a target frame; predicting the flight direction aircraft vertex coordinates and the heading angle in the normalized target frame by using a trained lightweight neural network; linearly mapping the predicted aircraft vertex coordinates and the heading angle to the original image space to obtain the original aircraft vertex coordinates and the heading angle; and determining a to-be-calculated region through linear segmentation based on the original aircraft vertex coordinates and the heading angle. The method dynamically locks the physical disturbance sensitive domain through the core ideas of lightweight flight target positioning, vertex-heading geometric model and frame linear segmentation, greatly reduces the calculation load and the algorithm power demand on the premise of guaranteeing the integrity of the shock wave pattern.

An unmanned aerial vehicle with mechanical components that transmit torque to the rotor, has foldable wings; on the wings there are in the direction of flight, symmetrically installed on the left and right wings, the boom, the front and rear ends of which are installed with the rotor whose direction can be deflected; torque is transmitted to the rotor by using a flexible shaft or a universal joint, and the rotor deflection and wing folding are achieved by using a worm gear or a motor with a self-locking holding torque, which realizes vertical take-off and landing and attitude control, eliminates the need for aerodynamic components for flight stabilization and attitude control, reduces the aerodynamic resistance of flight, and is conducive to improving flight speed and payload.

A method is provided for operating a synthetic aperture radar (SAR) to acquire image data of a mapping strip comprising one or more sub-mapping strips, wherein the SAR is carried on a platform moving along the flight direction and a radiated beam is directed to the mapping strip. The method includes: for each cluster, electronically manipulating the beam in the azimuth direction along the sub-mapping strip; and mechanically manipulating the beam in the opposite direction to the flight direction during each cluster. This method allows for improved mapping strip resolution.

The application discloses a kind of unmanned aerial vehicle obstacle avoidance trajectory planning methods with tangent line smooth constraint, to solve the problem that trajectory smoothness, obstacle avoidance safety and real-time performance are difficult to consider in complex three-dimensional environment.The method is first to three-dimensional discrete modeling to flight space, constructs local visible area and generates target-oriented trajectory;When detecting potential collision risk, construct navigation plane perpendicular to flight direction at first collision point, project obstacle to two-dimensional plane, extract boundary contour and tangent point, form candidate tangent direction.Adaptive sampling is carried out along the tangent direction combined with kinematic constraint, and continuous feasible candidate waypoints are generated.Subsequently, an evaluation function is constructed by combining angle deviation and safety distance, and the optimal waypoint is selected for iterative updating until the target is reached.Compared with the prior art, the application can generate smooth and continuous unmanned aerial vehicle trajectory in dense obstacle environment, realize smooth, safe and real-time three-dimensional obstacle avoidance flight.

A communication method and apparatus, which belong to the technical field of communications. In the method, n first beams among m*n generated first beams are located in an i-th first coverage range among m first coverage ranges, wherein n and m are positive integers, and i is a positive integer less than or equal to m; the m first coverage ranges are arranged along a first direction within a field-of-view range of a non-terrestrial communication apparatus, wherein the first direction is perpendicular to a flight direction of the non-terrestrial communication apparatus; and coverage ranges of the n first beams among the m*n first beams are arranged along a second direction within the i-th first coverage range, wherein the second direction is the flight direction of the non-terrestrial communication apparatus. In the solution, taking into consideration the characteristic of satellite coverage for ground users, extensive beam coverage can be performed along the flight direction of a satellite, thereby effectively improving the beam coverage effect.